You searched for subject:(Nanosatellites).
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Cape Peninsula University of Technology
1.
Louw, Etnard.
The design and construction of the front end section of an L-band receiver for nano- satellite application
.
Degree: 2015, Cape Peninsula University of Technology
URL: http://etd.cput.ac.za/handle/20.500.11838/2376 
► Optimum communication can only be achieved with a very sensitive front-end section in the receiver on a satellite because the transmitted signal from the ground…
(more)
▼ Optimum communication can only be achieved with a very sensitive front-end section in the receiver on a satellite because the transmitted signal from the ground station must travel hundreds of kilometres through the earth's atmosphere to a low earth orbit (LEO) satellite. This dissertation presents the design of the front end section of the receiver suitable for use in a nano-satellite. Specifically, various transistor technologies are evaluated by designing five low noise amplifiers to determine the optimum performing amplifier. The bandwidth of the front end section was controlled by designing coupled line microstrip filter.
For consistency, the same design technique was followed in the design of each LNA. Simulations were performed and the results were compared to the actual measured results of the constructed amplifiers to facilitate conclusions to be made.
Design specifications for the LNAs were obtained from the F'SATI Space CubeSat Programme Technical Specification document.
To control the bandwidth of the front end section, various types of band-pass filters were investigated, resulting in a coupled line band-pass filter being simulated and implemented. The simulated results were compared to the measured results of the constructed filter.
In the final stage of this dissertation, comparisons of each amplifier’s performance were made, resulting in the final recommendation for this project.
Subjects/Keywords: Nanosatellites;
Low noise amplifiers
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APA (6th Edition):
Louw, E. (2015). The design and construction of the front end section of an L-band receiver for nano- satellite application
. (Thesis). Cape Peninsula University of Technology. Retrieved from http://etd.cput.ac.za/handle/20.500.11838/2376
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Louw, Etnard. “The design and construction of the front end section of an L-band receiver for nano- satellite application
.” 2015. Thesis, Cape Peninsula University of Technology. Accessed January 28, 2021.
http://etd.cput.ac.za/handle/20.500.11838/2376.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Louw, Etnard. “The design and construction of the front end section of an L-band receiver for nano- satellite application
.” 2015. Web. 28 Jan 2021.
Vancouver:
Louw E. The design and construction of the front end section of an L-band receiver for nano- satellite application
. [Internet] [Thesis]. Cape Peninsula University of Technology; 2015. [cited 2021 Jan 28].
Available from: http://etd.cput.ac.za/handle/20.500.11838/2376.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Louw E. The design and construction of the front end section of an L-band receiver for nano- satellite application
. [Thesis]. Cape Peninsula University of Technology; 2015. Available from: http://etd.cput.ac.za/handle/20.500.11838/2376
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
University of Toronto
2.
Choi, Mirue.
Design and Development of Generic Nanosatellite Bus Ground Control Software Suite.
Degree: 2010, University of Toronto
URL: http://hdl.handle.net/1807/25455
► This thesis describes, in chronological order, the design and implementation of four separate ground control applications for use of the Generic Nanosatellite Bus, a multi-purpose…
(more)
▼ This thesis describes, in chronological order, the design and implementation of four separate ground control applications for use of the Generic Nanosatellite Bus, a multi-purpose satellite platform developed at the UTIAS Space Flight Laboratory. A direct ground control application and time-tagged remote control application are used to provide full control over a Generic Nanosatellite Bus satellite for short and long term operational and testing purposes. Similarly, a direct control application and a scheduling application are implemented for the control of the payload computer on CanX-3 BRIght-star Target Explorer, a stellar-observation satellite based on the Generic Nanosatellite Bus platform. This thesis goes into details on how the display and control interface is implemented and used, what set of actions are taken to create and interpret packets exchanged over a communications link, and what precautions are taken in the face of expected issues.
MAST
Advisors/Committee Members: Zee, Robert E., Aerospace Science and Engineering.
Subjects/Keywords: Nanosatellites; Ground Control; 0538
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APA (6th Edition):
Choi, M. (2010). Design and Development of Generic Nanosatellite Bus Ground Control Software Suite. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/25455
Chicago Manual of Style (16th Edition):
Choi, Mirue. “Design and Development of Generic Nanosatellite Bus Ground Control Software Suite.” 2010. Masters Thesis, University of Toronto. Accessed January 28, 2021.
http://hdl.handle.net/1807/25455.
MLA Handbook (7th Edition):
Choi, Mirue. “Design and Development of Generic Nanosatellite Bus Ground Control Software Suite.” 2010. Web. 28 Jan 2021.
Vancouver:
Choi M. Design and Development of Generic Nanosatellite Bus Ground Control Software Suite. [Internet] [Masters thesis]. University of Toronto; 2010. [cited 2021 Jan 28].
Available from: http://hdl.handle.net/1807/25455.
Council of Science Editors:
Choi M. Design and Development of Generic Nanosatellite Bus Ground Control Software Suite. [Masters Thesis]. University of Toronto; 2010. Available from: http://hdl.handle.net/1807/25455
Cape Peninsula University of Technology
3.
Dixon, Benjamin Deon.
In-situ monitoring using nano-satellites : a systems level approach
.
Degree: 2015, Cape Peninsula University of Technology
URL: http://etd.cput.ac.za/handle/20.500.11838/2194
► Traditional satellite systems employed for use with in-situ monitoring systems are large satellites that have a long development time, high cost and complex sub-systems. The…
(more)
▼ Traditional satellite systems employed for use with in-situ monitoring systems are large
satellites that have a long development time, high cost and complex sub-systems. The end use of relaying data for in-situ monitoring becomes a costly application for the end user. Shifting this application to make use of nano-satellites, such as CubeSats, for data relaying will make the application more attractive to the end user when measurements are required outside existing ground based communications infrastructure. CubeSats are small, simple satellites that yield a short development time and very low cost compared to conventional satellites. Their sub-systems are generally built from off the shelf components. This keeps the designs simple, manufacture cost low with the potential for flying the latest technologies. This research set out to analyse various scenarios related to in-situ monitoring governed by parameters such as the maximum revisit time, satellite orbit altitude, quantity of sensor nodes and data quantity relayed in the system. A systems level approach is used to analyse each designed scenario using a simulation tool called Systems Tool Kit by Agilent Graphics Incorporated. The data acquired for each scenario through simulation was validated using theoretical approximation methods, which included parameters such as coverage potential, total node access time, communication link performance, power resources, memory resources, access time and number of ground stations. The focus was put on these parameters since they are the main constraints when designing a system using nano-satellites. The outcome of the research was to create an analysis reference for designing an in-situ monitoring system using nano-satellites. It outlines the methods used to calculate and simulate each of the constraints governing the system. Each designed scenario showed satisfactory performance within the defined parameters and can be practically implemented
as a reference for designing similar systems.
Advisors/Committee Members: Blanchard, Y (advisor), Van Zyl, R. R (advisor).
Subjects/Keywords: Nanosatellites;
Environmental monitoring – Remote sensing;
CubeSats;
Nanosatellites – Orbits
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APA (6th Edition):
Dixon, B. D. (2015). In-situ monitoring using nano-satellites : a systems level approach
. (Thesis). Cape Peninsula University of Technology. Retrieved from http://etd.cput.ac.za/handle/20.500.11838/2194
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Dixon, Benjamin Deon. “In-situ monitoring using nano-satellites : a systems level approach
.” 2015. Thesis, Cape Peninsula University of Technology. Accessed January 28, 2021.
http://etd.cput.ac.za/handle/20.500.11838/2194.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Dixon, Benjamin Deon. “In-situ monitoring using nano-satellites : a systems level approach
.” 2015. Web. 28 Jan 2021.
Vancouver:
Dixon BD. In-situ monitoring using nano-satellites : a systems level approach
. [Internet] [Thesis]. Cape Peninsula University of Technology; 2015. [cited 2021 Jan 28].
Available from: http://etd.cput.ac.za/handle/20.500.11838/2194.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Dixon BD. In-situ monitoring using nano-satellites : a systems level approach
. [Thesis]. Cape Peninsula University of Technology; 2015. Available from: http://etd.cput.ac.za/handle/20.500.11838/2194
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Stellenbosch University
4.
Jurgen, Ludemann.
Sub-pixel image translation estimation on a nanosatellite platform.
Degree: MEng, Electrical and Electronic Engineering, 2019, Stellenbosch University
URL: http://hdl.handle.net/10019.1/105831
► ENGLISH ABSTRACT: Nanosatellites are limited in their physical size, which limits the physical size of payloads they can carry, thereby limiting the quality of images…
(more)
▼ ENGLISH ABSTRACT: Nanosatellites are limited in their physical size, which limits the physical size
of payloads they can carry, thereby limiting the quality of images taken during
CubeSat Earth Observation missions. Algorithms exist that combine partially
overlapping images to produce better output image quality. These algorithms
may either improve the signal-to-noise ratio via averaging, increase resolution
via super-resolution or merely remove redundant information via mosaicing.
Typically, they only function properly if the geometric transformations between
consecutive images are known with high accuracy. They can either be applied
terrestrially or on-board a satellite. Downloading large raw image data sets for
terrestrial processing is impractical for a CubeSat mission, and therefore an
on-board solution is desirable.
This thesis discusses the accurate determination of the transformation
between consecutive images on-board, laying the foundation for e cient onboard
de-noising, super-resolution and mosaicing. Two common methods
used to determine translation { normalised cross correlation (NCC) and phase
correlation { are investigated. From simulated results, NCC is shown to be
the better candidate for our application. NCC achieves sub-pixel accuracy
by making use of polynomial least squares regression. NCC is well suited for
implementation on a satellite platform where images are captured in quick
succession, resulting in partially overlapping images with little rotation between
frames.
We compare two potential hardware platforms { the MicroZed 7020 and
Jetson TK1 { and then describe how we implemented our proposed solution
onto the former, using a hardware description language. Software simulation
and rmware-implementation results, using simulated data, are compared
and discussed. Subsequently, the MicroZed 7020's implemented design is
characterised, compared and discussed in terms of algorithm and platform
performance.
AFRIKAANSE OPSOMMING: Nanosatelliete is beperk t.o.v hul grootte, gevolglik is die `loonvrag' wat hulle
kan dra ook beperk. Dit het 'n negatiewe uitwerking op die kwaliteit van die beelde, wat tydens waarnemings missies van CubeSats gemaak word. Algoritmes
bestaan wat gedeeltelik oorvleuelende beelde kombineer om vir hoer kwaliteit `uitset' beelde te sorg. Sulke algoritmes kan die sein-tot-ruis verhouding verbeter via `beeld-sommering', die resolusie verhoog deur super-resolusie of oorbodige
informasie via `mosaïekmetodes' verminder. Sodanige algoritmes funksioneer slegs optimaal wanneer die geometriese transformasies tussen agtereenvolgende
beelde tot 'n hoë vlak van akkuraatheid bepaal word. Die soort algoritmes kan aan boord, of op die grond toegepas word. Dit is onprakties is om sulke groot ongeformatteerde datastelle af te laai vir prossessering op die grond tydens die
missie van 'n Nanosatelliet, dus geniet 'n aanboord oplossing voorkeur.
Hierdie tesis bespreek die akkurate bepaling van inter-beeld transformasies aan bord boord van 'n satelliet. Dit l^e…
Advisors/Committee Members: Barnard, Arno, Smit, W., Malan, D. F., Stellenbosch University. Faculty of Engineering. Dept. of Electrical and Electronic Engineering..
Subjects/Keywords: UCTD; Nanosatellites; Image – Translations; Image analysis
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APA (6th Edition):
Jurgen, L. (2019). Sub-pixel image translation estimation on a nanosatellite platform. (Thesis). Stellenbosch University. Retrieved from http://hdl.handle.net/10019.1/105831
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Jurgen, Ludemann. “Sub-pixel image translation estimation on a nanosatellite platform.” 2019. Thesis, Stellenbosch University. Accessed January 28, 2021.
http://hdl.handle.net/10019.1/105831.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Jurgen, Ludemann. “Sub-pixel image translation estimation on a nanosatellite platform.” 2019. Web. 28 Jan 2021.
Vancouver:
Jurgen L. Sub-pixel image translation estimation on a nanosatellite platform. [Internet] [Thesis]. Stellenbosch University; 2019. [cited 2021 Jan 28].
Available from: http://hdl.handle.net/10019.1/105831.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Jurgen L. Sub-pixel image translation estimation on a nanosatellite platform. [Thesis]. Stellenbosch University; 2019. Available from: http://hdl.handle.net/10019.1/105831
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
University of Toronto
5.
Hiemstra, Jesse Mathew.
Mechanical Design and Development of a Modular Drag Sail for the CanX-7 Nanosatellite Mission.
Degree: 2014, University of Toronto
URL: http://hdl.handle.net/1807/68017
► The drag sail developed for the CanX-7 nanosatellite mission is an aerodynamic deorbiting device suited to small spacecraft. The drag sail enables spacecraft within a…
(more)
▼ The drag sail developed for the CanX-7 nanosatellite mission is an aerodynamic deorbiting device suited to small spacecraft. The drag sail enables spacecraft within a range of bus and orbit properties to comply with international regulations that require newly-launched satellites to be removed from low Earth orbit after their end of mission, with the intent of reducing the rate of orbital debris formation. The overall design uses a modular approach that enables integration with two existing spacecraft busses, and also allows for distributed mounting on notional busses yet to be designed. Additive fabrication allows for complex part geometry that enables the drag sail components to be compactly stowed within a small volume. A model of the deployment mechanism dynamics in terms of basic design parameters reproduces a simplified picture of the operation of the real system at room temperature.
M.A.S.
Advisors/Committee Members: Zee, E Robert, Aerospace Science and Engineering.
Subjects/Keywords: Deorbiting; Drag sails; Nanosatellites; Spacecraft; 0538
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APA (6th Edition):
Hiemstra, J. M. (2014). Mechanical Design and Development of a Modular Drag Sail for the CanX-7 Nanosatellite Mission. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/68017
Chicago Manual of Style (16th Edition):
Hiemstra, Jesse Mathew. “Mechanical Design and Development of a Modular Drag Sail for the CanX-7 Nanosatellite Mission.” 2014. Masters Thesis, University of Toronto. Accessed January 28, 2021.
http://hdl.handle.net/1807/68017.
MLA Handbook (7th Edition):
Hiemstra, Jesse Mathew. “Mechanical Design and Development of a Modular Drag Sail for the CanX-7 Nanosatellite Mission.” 2014. Web. 28 Jan 2021.
Vancouver:
Hiemstra JM. Mechanical Design and Development of a Modular Drag Sail for the CanX-7 Nanosatellite Mission. [Internet] [Masters thesis]. University of Toronto; 2014. [cited 2021 Jan 28].
Available from: http://hdl.handle.net/1807/68017.
Council of Science Editors:
Hiemstra JM. Mechanical Design and Development of a Modular Drag Sail for the CanX-7 Nanosatellite Mission. [Masters Thesis]. University of Toronto; 2014. Available from: http://hdl.handle.net/1807/68017
Cape Peninsula University of Technology
6.
Bakam Nguenouho, Odette Sandrine.
Ceramic coaxial resonator filter in a CubeSat system
.
Degree: 2017, Cape Peninsula University of Technology
URL: http://etd.cput.ac.za/handle/20.500.11838/2639
► RF and microwave filters can be implemented using ceramic coaxial resonators. This technology has been widely employed in nanosatellite communications systems recently, owing to its…
(more)
▼ RF and microwave filters can be implemented using ceramic coaxial resonators. This technology has been widely employed in nanosatellite communications systems recently, owing to its large quality factor (Q), permitting them to have low loss and narrow bandwidth. Features such as high selectivity, high power handling, excellent rejection, and low passband insertion loss are just a few of the key performance areas offered by ceramic coaxial resonators. This feature makes them suitable for use in bandpass filters.
Applications with demanding specifications requiring low volume and mass make use of this technology. Fulfilling the required performance goals can be challenging, given the size and weight restriction. Difficulties such as finding the correct length of resonators and the coupling capacitors’ structure to meet the size restriction, limit the type of ceramic coaxial resonators to use.
This thesis presents the design of a bandpass filter using ceramic coaxial resonators, which provides evidence of the concept for F’SATI’s future needs. This design will be used in an imminent space mission and the intention is to mount the bandpass filter in the receiver communications system. An intensive investigation was conducted into the use of filters for nanosatellite communication systems. The Chebyshev LC ladder low pass prototype was used to derive the conventional bandpass filter. Thereafter, the coupled resonator bandpass filter was derived using the conventional bandpass filter topology combined with the admittance inverter. Following this, using the ceramic coaxial resonators datasheet and information provided by the manufacturers, the coupled resonator bandpass filter was converted into a 3D model for further simulations, using CST Microwave Studio®. The ceramic coaxial resonator filter fabricated using Rogers’s material provided satisfactory results at its operating frequency between 2.2 GHz and 2.3 GHz. A radiation level test was performed on the filter to justify the use of the metallic enclosure. The test presented a low level of radiation measured at the filter operating frequency (2.25 GHz). The filter was also subjected to temperature cycling.
Advisors/Committee Members: Van Zyl, Robert (advisor).
Subjects/Keywords: Coaxial cables;
Resonators;
Radio frequency;
Nanosatellites
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APA (6th Edition):
Bakam Nguenouho, O. S. (2017). Ceramic coaxial resonator filter in a CubeSat system
. (Thesis). Cape Peninsula University of Technology. Retrieved from http://etd.cput.ac.za/handle/20.500.11838/2639
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Bakam Nguenouho, Odette Sandrine. “Ceramic coaxial resonator filter in a CubeSat system
.” 2017. Thesis, Cape Peninsula University of Technology. Accessed January 28, 2021.
http://etd.cput.ac.za/handle/20.500.11838/2639.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Bakam Nguenouho, Odette Sandrine. “Ceramic coaxial resonator filter in a CubeSat system
.” 2017. Web. 28 Jan 2021.
Vancouver:
Bakam Nguenouho OS. Ceramic coaxial resonator filter in a CubeSat system
. [Internet] [Thesis]. Cape Peninsula University of Technology; 2017. [cited 2021 Jan 28].
Available from: http://etd.cput.ac.za/handle/20.500.11838/2639.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Bakam Nguenouho OS. Ceramic coaxial resonator filter in a CubeSat system
. [Thesis]. Cape Peninsula University of Technology; 2017. Available from: http://etd.cput.ac.za/handle/20.500.11838/2639
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Cape Peninsula University of Technology
7.
Hillier, Caleb Pedro.
A system on chip based error detection and correction implementation for nanosatellites
.
Degree: 2018, Cape Peninsula University of Technology
URL: http://etd.cput.ac.za/handle/20.500.11838/2841
► This thesis will focus on preventing and overcoming the effects of radiation in RAM on board the ZA cube 2 nanosatellite. The main objective is…
(more)
▼ This thesis will focus on preventing and overcoming the effects of radiation in RAM on board the ZA cube 2 nanosatellite. The main objective is to design, implement and test an effective error detection and correction (EDAC) system for nanosatellite applications using a SoC development board. By conducting an in-depth literature review, all aspects of single-event effects are investigated, from space radiation right up to the implementation of an EDAC system. During this study, Hamming code was identified as a suitable EDAC scheme for the prevention of single-event effects. During the course of this thesis, a detailed radiation study of ZA cube 2’s space environment is conducted. This provides insight into the environment to which the satellite will be exposed to during orbit. It also provides insight which will allow accurate testing should accelerator tests with protons and heavy ions be necessary. In order to understand space radiation, a radiation study using ZA cube 2’s orbital parameters was conducted using OMERE and TRIM software. This study included earth’s radiation belts, galactic cosmic radiation, solar particle events and shielding. The results confirm that there is a need for mitigation techniques that are capable of EDAC. A detailed look at different EDAC schemes, together with a code comparison study was conducted. There are two types of error correction codes, namely error detection codes and error correction codes. For protection against radiation, nanosatellites use error correction codes like Hamming, Hadamard, Repetition, Four Dimensional Parity, Golay, BCH and Reed Solomon codes. Using detection capabilities, correction capabilities, code rate and bit overhead each EDAC scheme is evaluated and compared. This study provides the reader with a good understanding of all common EDAC schemes. The field of nanosatellites is constantly evolving and growing at a very fast speed. This creates a growing demand for more advanced and reliable EDAC systems that are capable of protecting all memory aspects of satellites. Hamming codes are extensively studied and implemented using different approaches, languages and software. After testing three variations of Hamming codes, in both Matlab and VHDL, the final and most effective version was Hamming [16, 11, 4]2. This code guarantees single error correction and double error detection. All developed Hamming codes are suited for FPGA implementation, for which they are tested thoroughly using simulation software and optimised.
Subjects/Keywords: Nanosatellites;
Error-correcting codes (Information theory);
Radiation
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Manager
APA (6th Edition):
Hillier, C. P. (2018). A system on chip based error detection and correction implementation for nanosatellites
. (Thesis). Cape Peninsula University of Technology. Retrieved from http://etd.cput.ac.za/handle/20.500.11838/2841
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Hillier, Caleb Pedro. “A system on chip based error detection and correction implementation for nanosatellites
.” 2018. Thesis, Cape Peninsula University of Technology. Accessed January 28, 2021.
http://etd.cput.ac.za/handle/20.500.11838/2841.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Hillier, Caleb Pedro. “A system on chip based error detection and correction implementation for nanosatellites
.” 2018. Web. 28 Jan 2021.
Vancouver:
Hillier CP. A system on chip based error detection and correction implementation for nanosatellites
. [Internet] [Thesis]. Cape Peninsula University of Technology; 2018. [cited 2021 Jan 28].
Available from: http://etd.cput.ac.za/handle/20.500.11838/2841.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Hillier CP. A system on chip based error detection and correction implementation for nanosatellites
. [Thesis]. Cape Peninsula University of Technology; 2018. Available from: http://etd.cput.ac.za/handle/20.500.11838/2841
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
University of Washington
8.
Song, Michelle.
Optimization and Scheduling Methodologies to Enable Low Earth Orbit Nano-satellite Communication.
Degree: 2018, University of Washington
URL: http://hdl.handle.net/1773/42413
► Communications with low earth orbit (LEO) nano-satellites (nanosats) are challenging due to the short contact time intervals with ground nodes and uncertainty in successful delivery…
(more)
▼ Communications with low earth orbit (LEO) nano-satellites (nanosats) are challenging due to the short contact time intervals with ground nodes and uncertainty in successful delivery of messages due to the varying signal-to-noise ratio (SNR) in the environment. This thesis presents optimization models to enable minimum-delay store-and-forward communications between terrestrial gateways and remote users (e.g., ships) via nanosats. Optimization models are formulated to enable timely delivery of messages between nanosats and remote users. Unit-sized messages destined for remote users must be routed from gateways to nanosats to final remote destinations. The connection between nanosats and remote users may not always be well established. The uncertainty in knowing if a message needs to be sent again or was successfully delivered is modeled using a chance constraint in the optimization model. A network flow program is formulated to optimize the scheduling and routing of messages from a central command and control center (CCC) to gateways to nanosats and ultimately to the remote user. The decisions are chosen to minimize the total message delivery time while considering the nanosat contact time windows with gateways and remote users and the solar charging time windows of the nanosats. Although the scheduling and routing decisions are binary variables, the optimization models are shown to satisfy the integrality property. Therefore the relaxed network model can be solved much faster than a binary integer problem. Results on a realistic problem are presented. Comparisons are made to consider the difference between a basic deterministic model, a model with energy constraints, and a chance-constrained model (with and without energy constraints). Comparisons are also made to simple greedy heuristics to demonstrate the value of optimization.
Advisors/Committee Members: Zabinsky, Zelda B (advisor).
Subjects/Keywords: Nanosatellites; Network; Optimization; Industrial engineering; Industrial engineering
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APA (6th Edition):
Song, M. (2018). Optimization and Scheduling Methodologies to Enable Low Earth Orbit Nano-satellite Communication. (Thesis). University of Washington. Retrieved from http://hdl.handle.net/1773/42413
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Song, Michelle. “Optimization and Scheduling Methodologies to Enable Low Earth Orbit Nano-satellite Communication.” 2018. Thesis, University of Washington. Accessed January 28, 2021.
http://hdl.handle.net/1773/42413.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Song, Michelle. “Optimization and Scheduling Methodologies to Enable Low Earth Orbit Nano-satellite Communication.” 2018. Web. 28 Jan 2021.
Vancouver:
Song M. Optimization and Scheduling Methodologies to Enable Low Earth Orbit Nano-satellite Communication. [Internet] [Thesis]. University of Washington; 2018. [cited 2021 Jan 28].
Available from: http://hdl.handle.net/1773/42413.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Song M. Optimization and Scheduling Methodologies to Enable Low Earth Orbit Nano-satellite Communication. [Thesis]. University of Washington; 2018. Available from: http://hdl.handle.net/1773/42413
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
University of Canterbury
9.
Muruganandan VA.
Hardware Design and Star Selection Algorithm for Arcsecond Pico Star Tracker.
Degree: PhD, Mechanical Engineering, 2018, University of Canterbury
URL: http://dx.doi.org/10.26021/10150
► The star tracker estimates pointing knowledge of a satellite in arcsecond accuracy in three axes without apriori knowledge. But star trackers are larger in size,…
(more)
▼ The star tracker estimates pointing knowledge of a satellite in arcsecond accuracy in three axes without apriori knowledge. But star trackers are larger in size, heavier, power hungry and expensive for nanosatellite missions. The Arcsecond Pico Star Tracker (APST) is designed based on the limitations of nanosatellites and estimated to provide pointing knowledge in arcsecond. The APST is developed using fully COTS components because it’s affordable, and less development time. A theoretical model is developed to estimate the performance of the COTS components (image sensor, lens, and baffle) used in the APST. Using this model, it’s possible to validate if the components meet the requirements of the star tracker. But COTS component decreases the overall performance due to the errors in image sensor noise, lens distortion, and aberration etc. In APST, the lens distortion and inaccurate centroiding are the dominant error sources. The radial lens distortion causes an error in angular distance measurement, which leads misidentifying or identification of stars and high processing time. This leads to functional failure of APST. To overcome this, the relative star selection method is developed which selects the stars based on the angular distance information. Based on the fact that star pair with low angular distance has minimum measurement error, the relative star selection selects the four stars with low measurement error. It’s compared with conventional bright star selection method, whereas stars are selected based on brightness. The relative selection algorithm is tested with 75-star constellation in star simulator and it has delivered 100% success rate and accuracy of 71 arcseconds in boresight. Whereas the conventional bright star selection delivered low success rate of 28% because the star pairs are not selected based on angular distance separation. Hence the relative star selection algorithm is efficient for APST.
Subjects/Keywords: Nanosatellites; Pico Star Tracker; Star Selection Algorithm
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APA (6th Edition):
VA, M. (2018). Hardware Design and Star Selection Algorithm for Arcsecond Pico Star Tracker. (Doctoral Dissertation). University of Canterbury. Retrieved from http://dx.doi.org/10.26021/10150
Chicago Manual of Style (16th Edition):
VA, Muruganandan. “Hardware Design and Star Selection Algorithm for Arcsecond Pico Star Tracker.” 2018. Doctoral Dissertation, University of Canterbury. Accessed January 28, 2021.
http://dx.doi.org/10.26021/10150.
MLA Handbook (7th Edition):
VA, Muruganandan. “Hardware Design and Star Selection Algorithm for Arcsecond Pico Star Tracker.” 2018. Web. 28 Jan 2021.
Vancouver:
VA M. Hardware Design and Star Selection Algorithm for Arcsecond Pico Star Tracker. [Internet] [Doctoral dissertation]. University of Canterbury; 2018. [cited 2021 Jan 28].
Available from: http://dx.doi.org/10.26021/10150.
Council of Science Editors:
VA M. Hardware Design and Star Selection Algorithm for Arcsecond Pico Star Tracker. [Doctoral Dissertation]. University of Canterbury; 2018. Available from: http://dx.doi.org/10.26021/10150
Cape Peninsula University of Technology
10.
Maleka, Motlokwe.
Development of a power distribution module for a nanosatellite
.
Degree: 2013, Cape Peninsula University of Technology
URL: http://etd.cput.ac.za/handle/20.500.11838/1073
► The space environment is characterised by harsh radiation, extreme temperatures and vacuum. Electronics subsystems for satellite applications are designed to be fault tolerant and robust…
(more)
▼ The space environment is characterised by harsh radiation, extreme temperatures and
vacuum. Electronics subsystems for satellite applications are designed to be fault tolerant
and robust enough to survive this environment. A power distribution module (PDM) for a
CubeSat nanosatellite application is developed here, with the aim to distribute power to
CubeSat subsystems reliably. The PDM prototype is carefully designed with reference to an
extensive literature study. The study dwells on the low Earth orbit (LEO) space environment,
critically identifying radiation sources and temperature ranges in the LEO. The study further
investigates traditional analogue techniques of logic circuit design using bipolar junction
transistors (BJTs) which are known for their higher tolerance to radiation sources as
compared to recent integrated circuits (ICs). Careful consideration is given to different ways
of designing a fault tolerant system. The study specifically looks at redundant circuit design
within the limitations of weight and space of a nanosatellite. Possible electrical faults in
power systems are identified, which include over-currents, over-voltages, over-temperatures,
inrush currents and latchup. This study shows that identified faults generally are overcurrents.
A power switch is included in each power distribution channel to trip the current in
case a faulty condition is detected. The PDM is designed to have eight power output
distribution channels to allow a subsystem load to connect to more than one channel,
thereby meeting its power requirements. The PDM power channels are designed identically.
Upon application, current limits are selected by a two-resistor divider circuit and connectors
are used to connect to a required voltage bus at manufacturing time. The system’s
functionality is tested and verified using an Arduino development board interfaced to all I2C
devices as a master node, typically the on-board computer (OBC) in a real satellite mission.
The system’s functionality in a Gamma irradiated laboratory environment is verified to
perform as required. The PDM system is further tested in a temperature cycled chamber
from -31°C to 61°C. The system survived the entire eight hour test duration of two cycles. It
is observed that the system is fault tolerant to radiation sources up to 10 krad and the
temperature limits mentioned. The PDM system is recommended as an additional module to
the CubeSat electrical power subsystem (EPS), thereby improving the reliability of the power
subsystem.
Keywords: CubeSat, power channel, module, radiation, reliability, efficiency, I2C, prototype.
Subjects/Keywords: Electric power distribution;
Nanosatellites;
Dissertations, Academic;
MTech;
Theses, dissertations, etc.
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APA (6th Edition):
Maleka, M. (2013). Development of a power distribution module for a nanosatellite
. (Thesis). Cape Peninsula University of Technology. Retrieved from http://etd.cput.ac.za/handle/20.500.11838/1073
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Maleka, Motlokwe. “Development of a power distribution module for a nanosatellite
.” 2013. Thesis, Cape Peninsula University of Technology. Accessed January 28, 2021.
http://etd.cput.ac.za/handle/20.500.11838/1073.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Maleka, Motlokwe. “Development of a power distribution module for a nanosatellite
.” 2013. Web. 28 Jan 2021.
Vancouver:
Maleka M. Development of a power distribution module for a nanosatellite
. [Internet] [Thesis]. Cape Peninsula University of Technology; 2013. [cited 2021 Jan 28].
Available from: http://etd.cput.ac.za/handle/20.500.11838/1073.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Maleka M. Development of a power distribution module for a nanosatellite
. [Thesis]. Cape Peninsula University of Technology; 2013. Available from: http://etd.cput.ac.za/handle/20.500.11838/1073
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
11.
Aheieva, Kateryna.
Development of a Vacuum Arc Thruster for Nanosatellites : 超小型衛星搭載用真空アーク推進機の開発.
Degree: 博士（工学）, 2017, Kyushu Institute of Technology / 九州工業大学
URL: http://hdl.handle.net/10228/5971
九州工業大学博士学位論文 学位記番号:工博甲第422号 学位授与年月日:平成28年9月23日
1. Introduction|2. Experimental apparatus and test setup|3. Vacuum Arc Thruster|4. Satellite deorbit system based on the Vacuum Arc Thruster|5. Vacuum Arc Thruster on-board satellite Horyu-4|6. Conclusions
平成28年度
Advisors/Committee Members: 豊田, 和弘.Subjects/Keywords: Electric propulsion; Nanosatellites; Plasma; Space debris; deorbiting; Vacuum arc thruster
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APA (6th Edition):
Aheieva, K. (2017). Development of a Vacuum Arc Thruster for Nanosatellites : 超小型衛星搭載用真空アーク推進機の開発. (Thesis). Kyushu Institute of Technology / 九州工業大学. Retrieved from http://hdl.handle.net/10228/5971
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Aheieva, Kateryna. “Development of a Vacuum Arc Thruster for Nanosatellites : 超小型衛星搭載用真空アーク推進機の開発.” 2017. Thesis, Kyushu Institute of Technology / 九州工業大学. Accessed January 28, 2021.
http://hdl.handle.net/10228/5971.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Aheieva, Kateryna. “Development of a Vacuum Arc Thruster for Nanosatellites : 超小型衛星搭載用真空アーク推進機の開発.” 2017. Web. 28 Jan 2021.
Vancouver:
Aheieva K. Development of a Vacuum Arc Thruster for Nanosatellites : 超小型衛星搭載用真空アーク推進機の開発. [Internet] [Thesis]. Kyushu Institute of Technology / 九州工業大学; 2017. [cited 2021 Jan 28].
Available from: http://hdl.handle.net/10228/5971.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Aheieva K. Development of a Vacuum Arc Thruster for Nanosatellites : 超小型衛星搭載用真空アーク推進機の開発. [Thesis]. Kyushu Institute of Technology / 九州工業大学; 2017. Available from: http://hdl.handle.net/10228/5971
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Cape Peninsula University of Technology
12.
Maqina, Sinamandla Mvuyisi.
X-band antenna design for nano-satellite applications
.
Degree: 2018, Cape Peninsula University of Technology
URL: http://etd.cput.ac.za/handle/20.500.11838/2703
► This research report discusses feasible designs of conformal antennas that provide a proof of concept for the French South African Institute of Technology’s future needs.…
(more)
▼ This research report discusses feasible designs of conformal antennas that provide a proof of concept for the French South African Institute of Technology’s future needs. The design is to be used in forthcoming space missions and the intention is to mount the antenna on the surface of a spacecraft. Hence, a low profile is mandatory along with good circular polarisation radiation characteristics. Microstrip patch antennas have been chosen for this purpose simply because they have low profile and conform to most structures, thus fulfilling the requirements stated above. All the designs that are featured in this thesis were modelled and validated using the electromagnetic simulation software FEKO and prototypes were built and tested. The simulations and measured results are supplemented by theory. Sometimes it can be challenging to design and develop an antenna that fulfils the required performance goals given the size and weight restrictions that are specified for nano-satellite technology. Therefore, the first phase of this project finds a good balance between the criteria set for CubeSat platforms and antenna performance. The second phase is validation. Single patch antennas and a sequential rotated patch array were designed, built and tested. The sequential rotated patch array offers considerable improvements in performance when compared to single patch antennas. For instance, the 3 dB axial ratio bandwidth increased to 9.6 % from 2 % when a sequential rotated array was used. The CubeSat normally flies in the inclined regions of the low Earth orbit (LEO). This area has high-energy auroral electron fluxes, in which the high-density electrons build up on ungrounded surfaces of spacecraft and cause discharge arcing. The discharge can affect the satellite operation and, in the worst case, cause permanent damage to the components. A mitigation technique by means of a bleeding path provides a quick route to ground and the space-qualified material that is used will ensure that the antenna is robust enough to survive this.
Subjects/Keywords: Antennas (Electronics);
Nanosatellites;
CubeSat;
Microstrip antennas – Design and construction
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APA ·
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Manager
APA (6th Edition):
Maqina, S. M. (2018). X-band antenna design for nano-satellite applications
. (Thesis). Cape Peninsula University of Technology. Retrieved from http://etd.cput.ac.za/handle/20.500.11838/2703
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Maqina, Sinamandla Mvuyisi. “X-band antenna design for nano-satellite applications
.” 2018. Thesis, Cape Peninsula University of Technology. Accessed January 28, 2021.
http://etd.cput.ac.za/handle/20.500.11838/2703.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Maqina, Sinamandla Mvuyisi. “X-band antenna design for nano-satellite applications
.” 2018. Web. 28 Jan 2021.
Vancouver:
Maqina SM. X-band antenna design for nano-satellite applications
. [Internet] [Thesis]. Cape Peninsula University of Technology; 2018. [cited 2021 Jan 28].
Available from: http://etd.cput.ac.za/handle/20.500.11838/2703.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Maqina SM. X-band antenna design for nano-satellite applications
. [Thesis]. Cape Peninsula University of Technology; 2018. Available from: http://etd.cput.ac.za/handle/20.500.11838/2703
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
University of Manchester
13.
Crisp, Nicholas Husayn.
A Methodology for the Integrated Design of Small
Satellite Constellation Deployment.
Degree: 2016, University of Manchester
URL: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:302321
► A growing interest in distributed systems of small satellites has recently emerged due to their ability to perform a variety of new mission types, increasing…
(more)
▼ A growing interest in distributed systems of small
satellites has recently emerged due to their ability to perform a
variety of new mission types, increasing technical capability, and
reduced time and cost for development. However, the lack of
available and dedicated small launch services currently restricts
the establishment of these systems in orbit. Secondary payload
launch opportunities and alternative deployment strategies can
address the issue of access-to-orbit and support the delivery of
the constellation to the correct orbit configuration following
launch. Of these deployment strategies, the method of indirect
plane separation, which utilises the natural precession of Earth
orbits, is particularly applicable to the deployment of small
satellite constellations due to the potential to significantly
reduce propulsive requirements, albeit at the cost of increased
deployment time.A review of satellite constellation design revealed
that existing methods and tools are not suitable for the analysis
of small satellite constellations and are not equipped to
investigate alternative deployment strategies, despite the
potential benefits of improved access-to-orbit, reduced system
complexity, and reduced cost. To address the identified gaps in the
design process, a methodology in which the analysis of small
satellite constellation deployment is integrated into the system
design framework is presented in this thesis. The corresponding
system design-space is subsequently explored using a numerical
optimisation method, which aids the identification of effective
system designs and promotes the understanding of relationships
between the design variables and output objectives. The primary
objectives of this methodology are to ensure that the different
opportunities for deployment of small satellite constellations are
thoroughly examined during the design process and to support the
development of improved mission and system designs.The presented
methodology is demonstrated using a reduced order framework
comprised of an analysis for the deployment of small satellite
constellations, preliminary vehicle and propulsion system sizing
processes, and system cost estimating relationships. Using this
simplified mission design framework, the design space-exploration
of three small satellite constellation mission case-studies is
performed by application of a multiobjective genetic algorithm.
Objectives of time-to-deploy, system mass, and system cost are used
to direct the optimisation process and search for the most
effective solutions in the system design-space. In order to perform
the analysis of constellation deployment by the process of indirect
plane separation, a simulation method using a semi-analytical
propagation technique and time-varying atmospheric density model
was developed and verified by comparison to the actual deployment
of the FORMOSAT-3/COSMIC mission.The results of the case-studies
presented illustrate the ability of the developed methodology to
support the design process for satellite constellations and enable
the…
Advisors/Committee Members: HOLLINGSWORTH, PETER PM, Hollingsworth, Peter, Smith, Katharine.
Subjects/Keywords: Small satellites; Nanosatellites; Access to orbit; Genetic algorithm; Multiobjective optimisation
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APA ·
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MLA ·
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CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Crisp, N. H. (2016). A Methodology for the Integrated Design of Small
Satellite Constellation Deployment. (Doctoral Dissertation). University of Manchester. Retrieved from http://www.manchester.ac.uk/escholar/uk-ac-man-scw:302321
Chicago Manual of Style (16th Edition):
Crisp, Nicholas Husayn. “A Methodology for the Integrated Design of Small
Satellite Constellation Deployment.” 2016. Doctoral Dissertation, University of Manchester. Accessed January 28, 2021.
http://www.manchester.ac.uk/escholar/uk-ac-man-scw:302321.
MLA Handbook (7th Edition):
Crisp, Nicholas Husayn. “A Methodology for the Integrated Design of Small
Satellite Constellation Deployment.” 2016. Web. 28 Jan 2021.
Vancouver:
Crisp NH. A Methodology for the Integrated Design of Small
Satellite Constellation Deployment. [Internet] [Doctoral dissertation]. University of Manchester; 2016. [cited 2021 Jan 28].
Available from: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:302321.
Council of Science Editors:
Crisp NH. A Methodology for the Integrated Design of Small
Satellite Constellation Deployment. [Doctoral Dissertation]. University of Manchester; 2016. Available from: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:302321
University of Toronto
14.
Elliott, Jennifer.
The Thermal Design and Analysis of the CanX-4/-5 and NEMO-AM Nanosatellites.
Degree: 2014, University of Toronto
URL: http://hdl.handle.net/1807/67848
► The main appeal of small satellites is that they are capable of fulfilling many of the same tasks as larger satellites, with lower development and…
(more)
▼ The main appeal of small satellites is that they are capable of fulfilling many of the same tasks as larger satellites, with lower development and launch costs. However, their smaller size can impose limitations on many of their systems, including their thermal control systems, which are often required to be passive and simple. This work summarizes the design and analysis of the thermal control systems for two small satellite missions, CanX-4/-5 and NEMO-AM. The development of a finite-difference thermal model using a commercial software package is described, followed by an overview of the analysis performed and the thermal control strategies employed in the satellites. The final analysis predictions show that the satellite temperatures for both missions were maintained within their required limits.
M.A.S.
Advisors/Committee Members: Zee, E Robert, Aerospace Science and Engineering.
Subjects/Keywords: nanosatellites; passive thermal control; small satellites; thermal control; 0538
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APA (6th Edition):
Elliott, J. (2014). The Thermal Design and Analysis of the CanX-4/-5 and NEMO-AM Nanosatellites. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/67848
Chicago Manual of Style (16th Edition):
Elliott, Jennifer. “The Thermal Design and Analysis of the CanX-4/-5 and NEMO-AM Nanosatellites.” 2014. Masters Thesis, University of Toronto. Accessed January 28, 2021.
http://hdl.handle.net/1807/67848.
MLA Handbook (7th Edition):
Elliott, Jennifer. “The Thermal Design and Analysis of the CanX-4/-5 and NEMO-AM Nanosatellites.” 2014. Web. 28 Jan 2021.
Vancouver:
Elliott J. The Thermal Design and Analysis of the CanX-4/-5 and NEMO-AM Nanosatellites. [Internet] [Masters thesis]. University of Toronto; 2014. [cited 2021 Jan 28].
Available from: http://hdl.handle.net/1807/67848.
Council of Science Editors:
Elliott J. The Thermal Design and Analysis of the CanX-4/-5 and NEMO-AM Nanosatellites. [Masters Thesis]. University of Toronto; 2014. Available from: http://hdl.handle.net/1807/67848
University of Toronto
15.
Singarayar, Fiona.
Preliminary System Development and Detailed Structural Design and Analysis for the CanX-7 Nanosatellite.
Degree: 2012, University of Toronto
URL: http://hdl.handle.net/1807/33531
► Satellites placed in LEO can remain there for an inde finite period of time. To reduce the density of this orbit so as to avoid…
(more)
▼ Satellites placed in LEO can remain there for an inde finite period of time. To reduce the
density of this orbit so as to avoid potential collisions with other satellites, the IADC has
published a report that suggests any satellite in LEO should de-orbit within 25 years. CanX-
7 is a de-orbiting technology demonstration mission intended to help solve the global space debris problem. The work summarized in this thesis describes the author's contribution to the CanX-7 preliminary system development, as well as to the deployment detection and structural subsystems. Discussed herein are the challenges of carrying forward multiple designs in parallel
and the factors and design trades that aid the decision-making process. This thesis not only presents the description of the final design of the nanosatellite, but also the evolution of the spacecraft from when it was initially envisioned in 2010 to its current state at the time of this writing.
MAST
Advisors/Committee Members: Zee, Robert E., Aerospace Science and Engineering.
Subjects/Keywords: De-orbit technology; Nanosatellites; System development; structural design; 0538
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Manager
APA (6th Edition):
Singarayar, F. (2012). Preliminary System Development and Detailed Structural Design and Analysis for the CanX-7 Nanosatellite. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/33531
Chicago Manual of Style (16th Edition):
Singarayar, Fiona. “Preliminary System Development and Detailed Structural Design and Analysis for the CanX-7 Nanosatellite.” 2012. Masters Thesis, University of Toronto. Accessed January 28, 2021.
http://hdl.handle.net/1807/33531.
MLA Handbook (7th Edition):
Singarayar, Fiona. “Preliminary System Development and Detailed Structural Design and Analysis for the CanX-7 Nanosatellite.” 2012. Web. 28 Jan 2021.
Vancouver:
Singarayar F. Preliminary System Development and Detailed Structural Design and Analysis for the CanX-7 Nanosatellite. [Internet] [Masters thesis]. University of Toronto; 2012. [cited 2021 Jan 28].
Available from: http://hdl.handle.net/1807/33531.
Council of Science Editors:
Singarayar F. Preliminary System Development and Detailed Structural Design and Analysis for the CanX-7 Nanosatellite. [Masters Thesis]. University of Toronto; 2012. Available from: http://hdl.handle.net/1807/33531
Cape Peninsula University of Technology
16.
Biyoghe, Joel S.
Design and implementation of a high data rate QPSK demodulator for nanosatellites
.
Degree: 2017, Cape Peninsula University of Technology
URL: http://etd.cput.ac.za/handle/20.500.11838/2744
► This dissertation presents the development of a quadrature phase shift keying (QPSK) demodulator for nanosatellites that complies with both the limited resources associated with nanosatellites…
(more)
▼ This dissertation presents the development of a quadrature phase shift keying (QPSK) demodulator for nanosatellites that complies with both the limited resources associated with nanosatellites as well as the flexibility and configurability required for a software defined radio (SDR) platform. This research project is a component of a bigger project, which is to develop a high-speed receiver for nanosatellites, and aims to provide a practical solution to the need for communication technologies that support emerging nanosatellite applications, such as Earth observation and communications. The development of the QPSK demodulator follows an all-digital implementation approach. The main reason for selecting this approach is to have a system that is flexible and reconfigurable to comply with the SDR requirements. Another reason for selecting this approach is to comply with the low noise system, low power consumption as well as the small size and weight requirements associated with nanosatellites. The QPSK demodulator is implemented on an IGLOO2 Field Programmable Gate Array (FPGA), due to its robustness to radiation and high-speed capability. Initially, the techniques used to design each subsystem of the QPSK demodulator are selected. Then, algorithms to digitally implement the designed subsystems are produced. Thereafter, the code for the digital QPSK demodulator is written and verified in Matlab first. The simulation of the Matlab-based QPSK demodulator performs satisfactorily. Subsequently, the code to implement the QPSK demodulator on an FPGA (IGLOO2) has been written in Libero, using VHSIC Hardware Description Language (VHDL). The resulting FPGA-based QPSK demodulator has been emulated in Libero (an integration and development environment (IDE) for Microsemi FPGAs) using a test-bench as well as other analysis tools. The test-bench results are visualized using Modelsim.
The results show that the demodulator can support data rates up to 13.25 Mbps if 16 samples-per-symbols are used, and up to 26.5 Mbps if 8 samples-per-symbols are used. It also has a very good bit-error-rate performance, which is simulated to be within a factor of 5 of the theoretical limit of QPSK modulation. Finally, the demodulator consumes less than 15 mW at the maximum operating speed. and has been coded to mitigate the effects of space radiation and noise contriution by the demodulator itself.
Subjects/Keywords: Matlab;
Phase shift keying;
Demodulation (Electronics);
Digital communication;
Nanosatellites
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APA (6th Edition):
Biyoghe, J. S. (2017). Design and implementation of a high data rate QPSK demodulator for nanosatellites
. (Thesis). Cape Peninsula University of Technology. Retrieved from http://etd.cput.ac.za/handle/20.500.11838/2744
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Biyoghe, Joel S. “Design and implementation of a high data rate QPSK demodulator for nanosatellites
.” 2017. Thesis, Cape Peninsula University of Technology. Accessed January 28, 2021.
http://etd.cput.ac.za/handle/20.500.11838/2744.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Biyoghe, Joel S. “Design and implementation of a high data rate QPSK demodulator for nanosatellites
.” 2017. Web. 28 Jan 2021.
Vancouver:
Biyoghe JS. Design and implementation of a high data rate QPSK demodulator for nanosatellites
. [Internet] [Thesis]. Cape Peninsula University of Technology; 2017. [cited 2021 Jan 28].
Available from: http://etd.cput.ac.za/handle/20.500.11838/2744.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Biyoghe JS. Design and implementation of a high data rate QPSK demodulator for nanosatellites
. [Thesis]. Cape Peninsula University of Technology; 2017. Available from: http://etd.cput.ac.za/handle/20.500.11838/2744
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Cape Peninsula University of Technology
17.
Njouakoua Tchonko, Leon.
Reconfigurable photovoltaic modules for robust nanosatellite power systems
.
Degree: 2018, Cape Peninsula University of Technology
URL: http://etd.cput.ac.za/handle/20.500.11838/2620
► Until recently, the focus of most solar technology development for space was towards more efficient, more radiation-resistant and increasingly powerful arrays. During a space mission,…
(more)
▼ Until recently, the focus of most solar technology development for space was towards more efficient, more radiation-resistant and increasingly powerful arrays. During a space mission, solar cells are not only exposed to irradiation by electrons, but also to a range of other particles, like protons. Thus, solar cells on robust
nanosatellites are extremely exposed to an environment, which includes the high-energy electrons and protons of the earth’s radiation belts, which leads towards the degradation process of the individual solar cell. Solar cell radiation shielding design ensures the protection of the solar cells from the particular radiation environment found in space. While the design principles of a solar photovoltaic automatic switching fault tolerant system which can detect and bypass faulty photovoltaic cells will be presented through this research work. The ability of such a system to be reconfigured using implemented switching matrix system makes it efficient under various environments and faulty conditions.
Advisors/Committee Members: Raji, Atanda Kamoru (advisor).
Subjects/Keywords: Nanosatellites;
Photovoltaic power generation;
Solar energy;
Photovoltaic cells
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APA (6th Edition):
Njouakoua Tchonko, L. (2018). Reconfigurable photovoltaic modules for robust nanosatellite power systems
. (Thesis). Cape Peninsula University of Technology. Retrieved from http://etd.cput.ac.za/handle/20.500.11838/2620
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Njouakoua Tchonko, Leon. “Reconfigurable photovoltaic modules for robust nanosatellite power systems
.” 2018. Thesis, Cape Peninsula University of Technology. Accessed January 28, 2021.
http://etd.cput.ac.za/handle/20.500.11838/2620.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Njouakoua Tchonko, Leon. “Reconfigurable photovoltaic modules for robust nanosatellite power systems
.” 2018. Web. 28 Jan 2021.
Vancouver:
Njouakoua Tchonko L. Reconfigurable photovoltaic modules for robust nanosatellite power systems
. [Internet] [Thesis]. Cape Peninsula University of Technology; 2018. [cited 2021 Jan 28].
Available from: http://etd.cput.ac.za/handle/20.500.11838/2620.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Njouakoua Tchonko L. Reconfigurable photovoltaic modules for robust nanosatellite power systems
. [Thesis]. Cape Peninsula University of Technology; 2018. Available from: http://etd.cput.ac.za/handle/20.500.11838/2620
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
York University
18.
Benari, Guy David.
Automated Geolocation Design for Nanosatellite Missions
Missions Based on Coastline Detection for Near Infrared Spectrometers.
Degree: PhD, Earth & Space Science, 2018, York University
URL: http://hdl.handle.net/10315/34379
► Geolocation, defined as the determination of the location on the ground from which a remote sensing observation is made, is a critical task in delivering…
(more)
▼ Geolocation, defined as the determination of the location on the ground from which a remote sensing observation is made, is a critical task in delivering accurate and reliable scientific data from an Earth observation (EO) spaceborne measurement system. Geolocation accuracy is a mission requirement, whose validation in EO missions with low resolution spectrometers is a challenging problem. While various techniques are proposed for large space missions, limited techniques are available for CubeSat-class, resource constrained, low resolution spectrometer payloads. In this dissertation, a novel approach for automated geolocation accuracy assessment using coastline detection was developed and implemented for CubeSat-class nanosatellite missions with low-resolution single-pixel spectrometers in nadir viewing configurations. The algorithm was demonstrated using Argus 1000 near-infrared (NIR) spectrometer data aboard the CanX-2 nanosatellite in order to verify the mission requirements of 1 (1) pointing knowledge uncertainty. The same algorithm was also applied to airborne data using the Ocean Optics FLAME-NIR spectrometer for validation purposes. Radiometric calibration was also performed on both instruments for use in field campaigns.
From the spaceborne data analysis, 270 spectrometer data sets were analyzed, from which 55 coastlines were detected. The mean angular error in the data sets was 0.44 and the standard deviation was 0.57, which was consistent with the CanX-2 mission requirements. The airborne data analysis yielded similar results using the same coastline detection algorithm as the spaceborne data analysis. A total of 7 data sets were acquired over two days at two data collection sites. 36 coastline crossings were detected and a mean angular error of 9.7 was observed, with a standard deviation of 6.8. Compared to the spaceborne data, higher error was observed due to the lower speed and altitude of the UAV compared to the satellite.
Advisors/Committee Members: Lee, Regina S. K. (advisor).
Subjects/Keywords: Remote sensing; Geolocation; Coastline Detection; Nanosatellites; NIR spectrometers; Earth Observation
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APA ·
Chicago ·
MLA ·
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CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Benari, G. D. (2018). Automated Geolocation Design for Nanosatellite Missions
Missions Based on Coastline Detection for Near Infrared Spectrometers. (Doctoral Dissertation). York University. Retrieved from http://hdl.handle.net/10315/34379
Chicago Manual of Style (16th Edition):
Benari, Guy David. “Automated Geolocation Design for Nanosatellite Missions
Missions Based on Coastline Detection for Near Infrared Spectrometers.” 2018. Doctoral Dissertation, York University. Accessed January 28, 2021.
http://hdl.handle.net/10315/34379.
MLA Handbook (7th Edition):
Benari, Guy David. “Automated Geolocation Design for Nanosatellite Missions
Missions Based on Coastline Detection for Near Infrared Spectrometers.” 2018. Web. 28 Jan 2021.
Vancouver:
Benari GD. Automated Geolocation Design for Nanosatellite Missions
Missions Based on Coastline Detection for Near Infrared Spectrometers. [Internet] [Doctoral dissertation]. York University; 2018. [cited 2021 Jan 28].
Available from: http://hdl.handle.net/10315/34379.
Council of Science Editors:
Benari GD. Automated Geolocation Design for Nanosatellite Missions
Missions Based on Coastline Detection for Near Infrared Spectrometers. [Doctoral Dissertation]. York University; 2018. Available from: http://hdl.handle.net/10315/34379
University of Toronto
19.
Wheeler, Clyde Bennet.
Adaptation of Commercial Off-the-shelf Camera Technology for Deployment Imaging and Inspection on Small Satellites.
Degree: 2017, University of Toronto
URL: http://hdl.handle.net/1807/77909
► Commercial off-the-shelf camera technology is frequently adapted for use onboard small satellites to aid in the validation of deployment mechanisms. Commercial off-the-shelf cameras are not…
(more)
▼ Commercial off-the-shelf camera technology is frequently adapted for use onboard small satellites to aid in the validation of deployment mechanisms. Commercial off-the-shelf cameras are not designed with this application nor the constraints of a small satellite in mind, however, and as a result often perform poorly on-orbit. To address this problem on the Miniature Visual Inspection Camera - a commercial off-the-shelf derived deployment imaging and inspection camera under development at the Space Flight Laboratory - a set of requirements were derived. Their verification revealed that this camera was initially incapable of producing neither video nor properly exposed images at the start of this research project. This thesis develops and discusses the measures undertaken to correct these problems in the context of the CanX-7 and NORSAT-2 small satellite missions, on which the Miniature Visual Inspection Camera will fly.
M.A.S.
Advisors/Committee Members: Zee, Robert E, Aerospace Science and Engineering.
Subjects/Keywords: imaging science; microsatellites; nanosatellites; radiometric calibration; radiometry; small satellites; 0538
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APA ·
Chicago ·
MLA ·
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CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Wheeler, C. B. (2017). Adaptation of Commercial Off-the-shelf Camera Technology for Deployment Imaging and Inspection on Small Satellites. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/77909
Chicago Manual of Style (16th Edition):
Wheeler, Clyde Bennet. “Adaptation of Commercial Off-the-shelf Camera Technology for Deployment Imaging and Inspection on Small Satellites.” 2017. Masters Thesis, University of Toronto. Accessed January 28, 2021.
http://hdl.handle.net/1807/77909.
MLA Handbook (7th Edition):
Wheeler, Clyde Bennet. “Adaptation of Commercial Off-the-shelf Camera Technology for Deployment Imaging and Inspection on Small Satellites.” 2017. Web. 28 Jan 2021.
Vancouver:
Wheeler CB. Adaptation of Commercial Off-the-shelf Camera Technology for Deployment Imaging and Inspection on Small Satellites. [Internet] [Masters thesis]. University of Toronto; 2017. [cited 2021 Jan 28].
Available from: http://hdl.handle.net/1807/77909.
Council of Science Editors:
Wheeler CB. Adaptation of Commercial Off-the-shelf Camera Technology for Deployment Imaging and Inspection on Small Satellites. [Masters Thesis]. University of Toronto; 2017. Available from: http://hdl.handle.net/1807/77909
Cape Peninsula University of Technology
20.
Driver, Nicole Andrea.
Assessment and development of de-orbiting technology for nanosatellites
.
Degree: 2019, Cape Peninsula University of Technology
URL: http://etd.cput.ac.za/handle/20.500.11838/3112
► The accumulating space debris has been a developing problem for many years. Technological advances led to the creation of nanosatellites, which allows more affordable access…
(more)
▼ The accumulating space debris has been a developing problem for many years. Technological advances led to the creation of
nanosatellites, which allows more affordable access to space. As a result, the number of satellite launches is rapidly increasing, which, translates into an increase in debris in the low earth orbit (LEO) and geostationary orbit (GEO). To comply with the Inter-Agency Space Debris Coordination Committee (IADC) requirement of a 25-year maximum orbital lifetime,
nanosatellites must have an end of life strategy. Failure to meet these guidelines may not only cause catastrophic collisions but may make future space travel even more challenging. Consequently, orbital lifetime predictions must be completed for
nanosatellites. Considering this, the aim of this thesis is to investigate the orbital lifetime predictions for the nanosatellite ZACube-2, and the effects on the orbital lifetime if ZACube-2 is fitted with deorbiting technology, specifically a drag argumentation device. An in-depth literature review regarding the current state of technology pertaining to nanosatellite de-orbiting was conducted. This was followed by studies regarding orbital dynamics and perturbation forces. Four case studies were simulated in NASA’s Debris assessment software (DAS 2.0) using orbital parameters extracted from the two-line element (TLE) file. General information such as launch date and final mass was provided by F’SATI. The Baseline case study presented the orbital lifetime of ZACube-2, without any drag enhancement device. This was followed by case study 1,2 and 3 which represented ZACube-2 when fitted with three different drag enhancement devices. A comparison study indicated a reduction in all three cases.
A new inflatable cube de-orbiting device (ICDD) concept was also presented, and the effects it has on the orbital lifetime predictions are showcased in case study three. Two deployment concepts were considered and evaluated against design requirements. Solidworks software was used to model the most suitable concept as well as perform finite element analysis on the structure. Static analysis was followed by natural frequency analysis in which the natural frequencies of the components and assembled structure were extracted. The Soyuz launch vehicle’s sinusoidal testing requirements were used to evaluate the structures survivability under dynamic loading. Based on the finite element , and harmonic analysis it was concluded that the structures will survive the launch conditions of the Soyuz launch vehicle. Furthermore, individual parameters affecting orbital lifetime predictions are also identified, in the form of a mass and cross-sectional sensitivity study and a ballistic coefficient versus orbital time study.
Advisors/Committee Members: Oliver, Graeme John, Prof (advisor).
Subjects/Keywords: Nanosatellites;
De-orbiting;
Cube satellites;
CubeSats;
ZACube-2;
Drag Augmentation Devices
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APA ·
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MLA ·
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CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Driver, N. A. (2019). Assessment and development of de-orbiting technology for nanosatellites
. (Thesis). Cape Peninsula University of Technology. Retrieved from http://etd.cput.ac.za/handle/20.500.11838/3112
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Driver, Nicole Andrea. “Assessment and development of de-orbiting technology for nanosatellites
.” 2019. Thesis, Cape Peninsula University of Technology. Accessed January 28, 2021.
http://etd.cput.ac.za/handle/20.500.11838/3112.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Driver, Nicole Andrea. “Assessment and development of de-orbiting technology for nanosatellites
.” 2019. Web. 28 Jan 2021.
Vancouver:
Driver NA. Assessment and development of de-orbiting technology for nanosatellites
. [Internet] [Thesis]. Cape Peninsula University of Technology; 2019. [cited 2021 Jan 28].
Available from: http://etd.cput.ac.za/handle/20.500.11838/3112.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Driver NA. Assessment and development of de-orbiting technology for nanosatellites
. [Thesis]. Cape Peninsula University of Technology; 2019. Available from: http://etd.cput.ac.za/handle/20.500.11838/3112
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Cape Peninsula University of Technology
21.
Nkonzo, Zukisa.
Continuous improvement practices within a nanosatellite manufacturing capability
.
Degree: 2019, Cape Peninsula University of Technology
URL: http://etd.cput.ac.za/handle/20.500.11838/2934
► This study investigates the current innovation and development process approaches, with the intention of understanding and elucidating the internal dynamics of continuous quality improvement strategies…
(more)
▼ This study investigates the current innovation and development process approaches, with the intention of understanding and elucidating the internal dynamics of continuous quality improvement strategies within the disruptive technological innovation and development set-up of the French South African Institute of Technology (F'SATI) in the Cape Peninsula University of Technology (CPUT). The research objectives were to look for answers within a innovation and development process approach by investigating the flexibility of the development process, setting up of an improvement targets, monitoring and measuring performance, applicability, and the use of risk-based thinking, lean manufacturing principle applications, and possible means to sustained good working practice for future innovation and development activities. Mixed research methodology was used to obtain meaningful and value-added results. Data was collected through group interviews (n1= 3 groups), a structured questionnaire completed by innovation and development full-time employees (n2 = 10 employees) and thorough review of documented organisational knowledge. Thematic data analysis was used to analyse qualitative data from the interviews, SPSS software was also used to analyse the quantitative data, and Cronbach's Alpha was used to test quantitative dataset reliability. Furthermore, an expert judgment approach was used to validate the results obtained from the research study through presentation of research findings to the innovation and development team. It was evident from the findings that even though continuous improvement approaches and a well-established systems engineering approach was in place, personnel capacity and resource capabilities, adopted organisational policies and procedures, and constant application of internal operational procedures remains a challenge within the F'SATI. The study recommends that the innovation and development centre needs to increase personnel capacity, with respect to required technical and interpersonal skills, more resources that are fit for purpose, to making use of value-adding business relations with external providers through a benchmarking approach, and to be released from dependency on the CPUT procurement system, in order to improve turnaround and delivery times.
Advisors/Committee Members: Moll, C.M., Prof (advisor), Hillmer, G., Prof (advisor).
Subjects/Keywords: Nanosatellites – Design and construction;
Manufacturing processes;
Continuous improvement process;
Lean manufacturing
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Export
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APA (6th Edition):
Nkonzo, Z. (2019). Continuous improvement practices within a nanosatellite manufacturing capability
. (Thesis). Cape Peninsula University of Technology. Retrieved from http://etd.cput.ac.za/handle/20.500.11838/2934
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Nkonzo, Zukisa. “Continuous improvement practices within a nanosatellite manufacturing capability
.” 2019. Thesis, Cape Peninsula University of Technology. Accessed January 28, 2021.
http://etd.cput.ac.za/handle/20.500.11838/2934.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Nkonzo, Zukisa. “Continuous improvement practices within a nanosatellite manufacturing capability
.” 2019. Web. 28 Jan 2021.
Vancouver:
Nkonzo Z. Continuous improvement practices within a nanosatellite manufacturing capability
. [Internet] [Thesis]. Cape Peninsula University of Technology; 2019. [cited 2021 Jan 28].
Available from: http://etd.cput.ac.za/handle/20.500.11838/2934.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Nkonzo Z. Continuous improvement practices within a nanosatellite manufacturing capability
. [Thesis]. Cape Peninsula University of Technology; 2019. Available from: http://etd.cput.ac.za/handle/20.500.11838/2934
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
22.
Crisp, Nicholas Husayn.
A methodology for the integrated design of small satellite constellation deployment.
Degree: PhD, 2016, University of Manchester
URL: https://www.research.manchester.ac.uk/portal/en/theses/a-methodology-for-the-integrated-design-of-small-satellite-constellation-deployment(46968b9a-6151-4e35-905d-e1b9b7f0609a).html
;
http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.701132
► A growing interest in distributed systems of small satellites has recently emerged due to their ability to perform a variety of new mission types, increasing…
(more)
▼ A growing interest in distributed systems of small satellites has recently emerged due to their ability to perform a variety of new mission types, increasing technical capability, and reduced time and cost for development. However, the lack of available and dedicated small launch services currently restricts the establishment of these systems in orbit. Secondary payload launch opportunities and alternative deployment strategies can address the issue of access-to-orbit and support the delivery of the constellation to the correct orbit configuration following launch. Of these deployment strategies, the method of indirect plane separation, which utilises the natural precession of Earth orbits, is particularly applicable to the deployment of small satellite constellations due to the potential to significantly reduce propulsive requirements, albeit at the cost of increased deployment time. A review of satellite constellation design revealed that existing methods and tools are not suitable for the analysis of small satellite constellations and are not equipped to investigate alternative deployment strategies, despite the potential benefits of improved access-to-orbit, reduced system complexity, and reduced cost. To address the identified gaps in the design process, a methodology in which the analysis of small satellite constellation deployment is integrated into the system design framework is presented in this thesis. The corresponding system design-space is subsequently explored using a numerical optimisation method, which aids the identification of effective system designs and promotes the understanding of relationships between the design variables and output objectives. The primary objectives of this methodology are to ensure that the different opportunities for deployment of small satellite constellations are thoroughly examined during the design process and to support the development of improved mission and system designs. The presented methodology is demonstrated using a reduced order framework comprised of an analysis for the deployment of small satellite constellations, preliminary vehicle and propulsion system sizing processes, and system cost estimating relationships. Using this simplified mission design framework, the design space-exploration of three small satellite constellation mission case-studies is performed by application of a multiobjective genetic algorithm. Objectives of time-to-deploy, system mass, and system cost are used to direct the optimisation process and search for the most effective solutions in the system design-space. In order to perform the analysis of constellation deployment by the process of indirect plane separation, a simulation method using a semi-analytical propagation technique and time-varying atmospheric density model was developed and verified by comparison to the actual deployment of the FORMOSAT-3/COSMIC mission. The results of the case-studies presented illustrate the ability of the developed methodology to support the design process for satellite constellations and enable the…
Subjects/Keywords: 629.43; Small satellites; Nanosatellites; Access to orbit; Genetic algorithm; Multiobjective optimisation
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APA (6th Edition):
Crisp, N. H. (2016). A methodology for the integrated design of small satellite constellation deployment. (Doctoral Dissertation). University of Manchester. Retrieved from https://www.research.manchester.ac.uk/portal/en/theses/a-methodology-for-the-integrated-design-of-small-satellite-constellation-deployment(46968b9a-6151-4e35-905d-e1b9b7f0609a).html ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.701132
Chicago Manual of Style (16th Edition):
Crisp, Nicholas Husayn. “A methodology for the integrated design of small satellite constellation deployment.” 2016. Doctoral Dissertation, University of Manchester. Accessed January 28, 2021.
https://www.research.manchester.ac.uk/portal/en/theses/a-methodology-for-the-integrated-design-of-small-satellite-constellation-deployment(46968b9a-6151-4e35-905d-e1b9b7f0609a).html ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.701132.
MLA Handbook (7th Edition):
Crisp, Nicholas Husayn. “A methodology for the integrated design of small satellite constellation deployment.” 2016. Web. 28 Jan 2021.
Vancouver:
Crisp NH. A methodology for the integrated design of small satellite constellation deployment. [Internet] [Doctoral dissertation]. University of Manchester; 2016. [cited 2021 Jan 28].
Available from: https://www.research.manchester.ac.uk/portal/en/theses/a-methodology-for-the-integrated-design-of-small-satellite-constellation-deployment(46968b9a-6151-4e35-905d-e1b9b7f0609a).html ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.701132.
Council of Science Editors:
Crisp NH. A methodology for the integrated design of small satellite constellation deployment. [Doctoral Dissertation]. University of Manchester; 2016. Available from: https://www.research.manchester.ac.uk/portal/en/theses/a-methodology-for-the-integrated-design-of-small-satellite-constellation-deployment(46968b9a-6151-4e35-905d-e1b9b7f0609a).html ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.701132
Cape Peninsula University of Technology
23.
Cupido, Stephen William John.
Augmentation of a nano-satellite electronic power system using a field-programmable-gate-array.
Degree: 2013, Cape Peninsula University of Technology
URL: http://etd.cput.ac.za/handle/20.500.11838/1084
► The CubeSat standard has various engineering challenges due to its small size and surface area. The challenge is to incorporate a large amount of technology…
(more)
▼ The CubeSat standard has various engineering challenges due to its small size and surface area. The challenge is to incorporate a large amount of technology into a form factor no bigger than 10cm3. This research project investigates the space environment, solar cells, secondary sources of power, and Field-Programmable-Gate-Array (FPGA) technology in order to address the size, weight and power challenges presented by the CubeSat standard. As FPGAs have not yet been utilised in this particular sub-system as the main controller, this research investigates whether or not the implementation of an FPGA-based electronic power supply sub-system will optimise its functionality by overcoming these size weight and power challenges.
The SmartFusion FPGA was chosen due to its analogue front end which can reduce the number of peripheral components required by such complex systems. Various maximum power point tracking algorithms were studied and it was determined that the perturb-and-observe maximum power point tracking algorithm best suits the design constraints, as it only requires the measurement of either solar cell voltage or solar cell current, thus further decreasing the component count. The SmartFusion FPGA analogue compute engine allows for increased performance of the perturb-and-observe algorithm implemented on the microcontroller sub-system as it allows for the offloading of many repetitive calculations. A VHDL implementation of the pulse-width-modulator was developed in order to produce the various changes in duty cycle produced by the perturb-and-observe algorithm.
The aim of this research project was achieved through the development and testing of a nano-satellite power system prototype using the SmartFusion FPGA from Microsemi with a decreased number of peripheral circuits. Maximum power point was achieved in 347ms at worst case with a 55% decrease in power consumption from the estimated 330mW as indicated in the power budget. The SmartFusion FPGA consumes only a worst case of 148.93mW. It was found that the unique features of the SmartFusion FPGA do in fact address the size weight and power constraints of the CubeSat standard within this sub-system.
Subjects/Keywords: Nanosatellites;
Electric power systems;
Field programmable gate arrays;
Dissertations, Academic;
MTech;
Theses, dissertations, etc.
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Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Cupido, S. W. J. (2013). Augmentation of a nano-satellite electronic power system using a field-programmable-gate-array.
(Thesis). Cape Peninsula University of Technology. Retrieved from http://etd.cput.ac.za/handle/20.500.11838/1084
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Cupido, Stephen William John. “Augmentation of a nano-satellite electronic power system using a field-programmable-gate-array.
” 2013. Thesis, Cape Peninsula University of Technology. Accessed January 28, 2021.
http://etd.cput.ac.za/handle/20.500.11838/1084.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Cupido, Stephen William John. “Augmentation of a nano-satellite electronic power system using a field-programmable-gate-array.
” 2013. Web. 28 Jan 2021.
Vancouver:
Cupido SWJ. Augmentation of a nano-satellite electronic power system using a field-programmable-gate-array.
[Internet] [Thesis]. Cape Peninsula University of Technology; 2013. [cited 2021 Jan 28].
Available from: http://etd.cput.ac.za/handle/20.500.11838/1084.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Cupido SWJ. Augmentation of a nano-satellite electronic power system using a field-programmable-gate-array.
[Thesis]. Cape Peninsula University of Technology; 2013. Available from: http://etd.cput.ac.za/handle/20.500.11838/1084
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
University of California – Irvine
24.
Timilsina, Navin.
Electrospray Thrusters for Attitude Control of a 1-U CubeSat.
Degree: Mechanical and Aerospace Engineering, 2014, University of California – Irvine
URL: http://www.escholarship.org/uc/item/3506d0z7
► With a rapid increase in the interest in use of nanosatellites in the past decade, finding a precise and low-power-consuming attitude control system for these…
(more)
▼ With a rapid increase in the interest in use of nanosatellites in the past decade, finding a precise and low-power-consuming attitude control system for these satellites has been a real challenge. In this thesis, it is intended to design and test an electrospray thruster system that could perform the attitude control of a 1-unit CubeSat. Firstly, an experimental setup is built to calculate the conductivity of different liquids that could be used as propellants for the CubeSat. Secondly, a Time-Of-Flight experiment is performed to find out the thrust and specific impulse given by these liquids and hence selecting the optimum propellant. On the other hand, a colloidal thruster system for a 1-U CubeSat is designed in Solidworks and fabricated using Lathe and CNC Milling Machine. Afterwards, passive propellant feeding is tested in this thruster system. Finally, the electronic circuit and wireless control system necessary to remotely control the CubeSat is designed and the final testing is performed. Among the propellants studied, Ethyl ammonium nitrate (EAN) was selected as the best propellant for the CubeSat. Theoretical design and fabrication of the thruster system was performed successfully and so was the passive propellant feeding test. The satellite was assembled for the final experiment but unfortunately the microcontroller broke down during the first test and no promising results were found out. However, after proving that one thruster works with passive feeding, it could be said that the ACS testing would have worked if we had performed vacuum compatibility tests for other components beforehand.
Subjects/Keywords: Aerospace engineering; Attitude Control System; Colloidal Thrusters; Conductivity; CubeSat; Nanosatellites; Time Of Flight
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APA (6th Edition):
Timilsina, N. (2014). Electrospray Thrusters for Attitude Control of a 1-U CubeSat. (Thesis). University of California – Irvine. Retrieved from http://www.escholarship.org/uc/item/3506d0z7
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Timilsina, Navin. “Electrospray Thrusters for Attitude Control of a 1-U CubeSat.” 2014. Thesis, University of California – Irvine. Accessed January 28, 2021.
http://www.escholarship.org/uc/item/3506d0z7.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Timilsina, Navin. “Electrospray Thrusters for Attitude Control of a 1-U CubeSat.” 2014. Web. 28 Jan 2021.
Vancouver:
Timilsina N. Electrospray Thrusters for Attitude Control of a 1-U CubeSat. [Internet] [Thesis]. University of California – Irvine; 2014. [cited 2021 Jan 28].
Available from: http://www.escholarship.org/uc/item/3506d0z7.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Timilsina N. Electrospray Thrusters for Attitude Control of a 1-U CubeSat. [Thesis]. University of California – Irvine; 2014. Available from: http://www.escholarship.org/uc/item/3506d0z7
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Stellenbosch University
25.
Botma, Pieter Johannes.
The design and development of an ADCS OBC for a CubeSat.
Degree: MScEng, Electrical and Electronic Engineering, 2011, Stellenbosch University
URL: http://hdl.handle.net/10019.1/18040
► ENGLISH ABSTRACT: The Electronic Systems Laboratory at Stellenbosch University is currently developing a fully 3-axis controlled Attitude Determination and Control Subsystem (ADCS) for CubeSats. This…
(more)
▼ ENGLISH ABSTRACT: The Electronic Systems Laboratory at Stellenbosch University is currently developing a fully 3-axis controlled Attitude Determination and Control Subsystem (ADCS) for CubeSats. This thesis describes the design and development of an Onboard Computer (OBC) suitable for ADCS application. A separate dedicated OBC for ADCS purposes allows the main CubeSat OBC to focus only on command and data handling, communication and payload management.
This thesis describes, in detail the development process of the OBC. Multiple Microcontroller Unit (MCU) architectures were considered before selecting an ARM Cortex-M3 processor due to its performance, power efficiency and functionality. The hardware was designed to be as robust as possible, because radiation tolerant and redundant components could not be included, due to their high cost and the technical constraints of a CubeSat.
The software was developed to improve recovery from lockouts or component failures and to enable the operational modes to be configured in real-time or uploaded from the ground station. Ground tests indicated that the OBC can handle radiation-related problems such as latchups and bit-flips. The peak power consumption is around 500 mW and the orbital average is substantially lower. The proposed OBC is therefore not only sufficient in its intended application as an ADCS OBC, but could also stand in as a backup for the main OBC in case of an emergency.
AFRIKAANSE OPSOMMING: Die Elektroniese Stelsels Laboratorium by die Universiteit van Stellenbosch is tans besig om ’n volkome 3-as gestabiliseerde oriëntasiebepaling en -beheerstelsel (Engels: ADCS) vir ’n CubeSat te ontwikkel. Hierdie tesis beskryf die ontwerp en ontwikkeling van ’n aanboordrekenaar (Engels: OBC) wat gebruik kan word in ’n ADCS. ’n Afsonderlike OBC wat aan die ADCS toegewy is, stel die hoof-OBC in staat om te fokus op beheer- en datahantering, kommunikasie en loonvragbestuur.
Hierdie tesis beskryf breedvoerig die werkswyse waarvolgens die OBC ontwikkel is. Verskeie mikroverwerkers is as moontlike kandidate ondersoek voor daar op ’n ARM Cortex-M3-gebaseerde mikroverwerker besluit is. Hierdie mikroverwerker is gekies vanweë sy spoed, effektiewe kragverbruik en funksionaliteit. Die hardeware is ontwikkel om so robuust moontlik te wees, omdat stralingbestande en oortollige komponente weens kostebeperkings, asook tegniese beperkings van ’n CubeSat, nie ingesluit kon word nie.
Die programmatuur is ontwikkel om van ’n uitsluiting en ’n komponentfout te kan herstel. Verder kan programme wat tydens vlug in werking is, verstel word en vanaf ’n grondstasie gelaai word. Grondtoetse het aangedui dat die OBC stralingverwante probleme, soos ’n vergrendeling (latchup) of bis-omkering (bit-flip), kan hanteer. Die maksimum kragverbruik is ongeveer 500 mW en die gemiddelde wentelbaankragverbruik is beduidend kleiner. Die voorgestelde OBC is dus voldoende as ADCS OBC asook hoof-OBC in geval van nood.
Advisors/Committee Members: Steyn, W. H., Stellenbosch University. Faculty of Engineering. Dept. of Electrical and Electronic Engineering..
Subjects/Keywords: Electronic engineering; Artificial satellites – Control systems; Interactive computer systems; Nanosatellites – Control systems
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APA (6th Edition):
Botma, P. J. (2011). The design and development of an ADCS OBC for a CubeSat. (Masters Thesis). Stellenbosch University. Retrieved from http://hdl.handle.net/10019.1/18040
Chicago Manual of Style (16th Edition):
Botma, Pieter Johannes. “The design and development of an ADCS OBC for a CubeSat.” 2011. Masters Thesis, Stellenbosch University. Accessed January 28, 2021.
http://hdl.handle.net/10019.1/18040.
MLA Handbook (7th Edition):
Botma, Pieter Johannes. “The design and development of an ADCS OBC for a CubeSat.” 2011. Web. 28 Jan 2021.
Vancouver:
Botma PJ. The design and development of an ADCS OBC for a CubeSat. [Internet] [Masters thesis]. Stellenbosch University; 2011. [cited 2021 Jan 28].
Available from: http://hdl.handle.net/10019.1/18040.
Council of Science Editors:
Botma PJ. The design and development of an ADCS OBC for a CubeSat. [Masters Thesis]. Stellenbosch University; 2011. Available from: http://hdl.handle.net/10019.1/18040
Cape Peninsula University of Technology
26.
Shumba, Angela-Tafadzwa.
Channel coding on a nano-satellite platform
.
Degree: 2018, Cape Peninsula University of Technology
URL: http://etd.cput.ac.za/handle/20.500.11838/2768
► The concept of forward error correction (FEC) coding introduced the capability of achieving near Shannon limit digital transmission with bit error rates (BER) approaching 10-9…
(more)
▼ The concept of forward error correction (FEC) coding introduced the capability of achieving near Shannon limit digital transmission with bit error rates (BER) approaching 10-9 for signal to noise power (Eb/No) values as low as 0.7. This brought about the ability to transmit large amounts of data at fast rates on bad/noisy communication channels. In nano-satellites, however, the constraints on power that limit the energy that can be allocated for data transmission result in significantly reduced communication system performance. One of the effects of these constraints is the limitation on the type of channel coding technique that can be implemented in these communication systems. Another limiting factor on nano-satellite communication systems is the limited space available due to the compact nature of these
satellites, where numerous complex systems are tightly packed into a space as small as 10x10x10cm. With the miniaturisation of Integrated-Circuit (IC) technology and the affordability of Field-Programmable-Gate-Arrays (FPGAs) with reduced power consumption, complex circuits can now be implemented within small form factors and at low cost. This thesis describes the design, implementation and cost evaluation of a ½-rate convolutional encoder and the corresponding Viterbi decoder on an FPGA for nano-satellites applications. The code for the FPGA implementation is described in VHDL and implemented on devices
from the Artix7 (Xilinx), Cyclone V (Intel-fpga), and Igloo2 (Microsemi) families. The implemented channel code has a coding gain of ~3dB at a BER of 10-3. It can be noted that the implementation of the encoder is quite straightforward and that the main challenge is in the implementation of the decoder.
Subjects/Keywords: Nanosatellites;
Field programmable gate arrays;
Signal processing – Digital techniques;
Error-correcting codes (Information theory)
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APA ·
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APA (6th Edition):
Shumba, A. (2018). Channel coding on a nano-satellite platform
. (Thesis). Cape Peninsula University of Technology. Retrieved from http://etd.cput.ac.za/handle/20.500.11838/2768
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Shumba, Angela-Tafadzwa. “Channel coding on a nano-satellite platform
.” 2018. Thesis, Cape Peninsula University of Technology. Accessed January 28, 2021.
http://etd.cput.ac.za/handle/20.500.11838/2768.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Shumba, Angela-Tafadzwa. “Channel coding on a nano-satellite platform
.” 2018. Web. 28 Jan 2021.
Vancouver:
Shumba A. Channel coding on a nano-satellite platform
. [Internet] [Thesis]. Cape Peninsula University of Technology; 2018. [cited 2021 Jan 28].
Available from: http://etd.cput.ac.za/handle/20.500.11838/2768.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Shumba A. Channel coding on a nano-satellite platform
. [Thesis]. Cape Peninsula University of Technology; 2018. Available from: http://etd.cput.ac.za/handle/20.500.11838/2768
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
York University
27.
Lohmann, Andrew Joachim.
Star Imager For Nanosatellite Applications.
Degree: MSc -MS, Earth & Space Science, 2018, York University
URL: http://hdl.handle.net/10315/34411
► This research examines the feasibility of Commercial-off-the-shelf Complementary Metal-Oxide-Semiconductor image sensors for use on nanosatellites as a star imager. An emphasis is placed on method…
(more)
▼ This research examines the feasibility of Commercial-off-the-shelf Complementary Metal-Oxide-Semiconductor image sensors for use on
nanosatellites as a star imager. An emphasis is placed on method selection and implementation of the star imager algorithm: Centroiding, Identification and Attitude Determination. The star imager algorithm makes use of the Lost-in-Space condition to provide attitude knowledge for each image. Flat Field, Checker Board and Point Spread Function calibration methods were employed to characterize the star imager. Finally, feasibility testing of the star imager is accomplished through simulations and night sky images.
Advisors/Committee Members: Lee, Regina S. K. (advisor).
Subjects/Keywords: Aerospace engineering; Complementary Metal-Oxide-Semiconductor; Commercial-off-the-shelf; Star Camera; Space Science; Nanosatellites
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APA (6th Edition):
Lohmann, A. J. (2018). Star Imager For Nanosatellite Applications. (Masters Thesis). York University. Retrieved from http://hdl.handle.net/10315/34411
Chicago Manual of Style (16th Edition):
Lohmann, Andrew Joachim. “Star Imager For Nanosatellite Applications.” 2018. Masters Thesis, York University. Accessed January 28, 2021.
http://hdl.handle.net/10315/34411.
MLA Handbook (7th Edition):
Lohmann, Andrew Joachim. “Star Imager For Nanosatellite Applications.” 2018. Web. 28 Jan 2021.
Vancouver:
Lohmann AJ. Star Imager For Nanosatellite Applications. [Internet] [Masters thesis]. York University; 2018. [cited 2021 Jan 28].
Available from: http://hdl.handle.net/10315/34411.
Council of Science Editors:
Lohmann AJ. Star Imager For Nanosatellite Applications. [Masters Thesis]. York University; 2018. Available from: http://hdl.handle.net/10315/34411
York University
28.
Jain, Vidushi.
Abstracting Cubesat Operations: A Path to Real Cubesat Interoperability.
Degree: MSc -MS, Earth & Space Science, 2019, York University
URL: https://yorkspace.library.yorku.ca/xmlui/handle/10315/36806
► Introduction of the CubeSat form factor brought a paradigm shift in the industry. With the size becoming a standard, cost and development time were able…
(more)
▼ Introduction of the CubeSat form factor brought a paradigm shift in the industry. With the size becoming a standard, cost and development time were able to be reduced significantly. However, the industry has not yet fully realized the potential of this new paradigm. Many other simplifications or standardizations can be made, whilst still meeting CubeSat mission requirements.
One area that can be addressed without significant change is CubeSat mission operations. Many operations activities for CubeSat busses are common, or the differences between missions are close enough to benefit from common streamlining.
This thesis proposes abstracted operations sequence for CubeSats. The sequence is demonstrated by applying it to an upcoming CubeSat mission - DESCENT. Simplifications made as a result of this abstraction are demonstrated. The thesis also points to some of the other improvements that could be made longer-term for CubeSat mission designers and operators through further industry standardization.
Advisors/Committee Members: Newland, Franz (advisor).
Subjects/Keywords: Operations research; Space Operations; CubeSats; System Engineering; Space Science; NanoSatellites; DESCENT; System operations; satellite operations
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APA (6th Edition):
Jain, V. (2019). Abstracting Cubesat Operations: A Path to Real Cubesat Interoperability. (Masters Thesis). York University. Retrieved from https://yorkspace.library.yorku.ca/xmlui/handle/10315/36806
Chicago Manual of Style (16th Edition):
Jain, Vidushi. “Abstracting Cubesat Operations: A Path to Real Cubesat Interoperability.” 2019. Masters Thesis, York University. Accessed January 28, 2021.
https://yorkspace.library.yorku.ca/xmlui/handle/10315/36806.
MLA Handbook (7th Edition):
Jain, Vidushi. “Abstracting Cubesat Operations: A Path to Real Cubesat Interoperability.” 2019. Web. 28 Jan 2021.
Vancouver:
Jain V. Abstracting Cubesat Operations: A Path to Real Cubesat Interoperability. [Internet] [Masters thesis]. York University; 2019. [cited 2021 Jan 28].
Available from: https://yorkspace.library.yorku.ca/xmlui/handle/10315/36806.
Council of Science Editors:
Jain V. Abstracting Cubesat Operations: A Path to Real Cubesat Interoperability. [Masters Thesis]. York University; 2019. Available from: https://yorkspace.library.yorku.ca/xmlui/handle/10315/36806
University of Toronto
29.
Leonard, Matthew Leigh.
Software for the Canadian Advanced Nanospace eXperiment-4/5.
Degree: 2012, University of Toronto
URL: http://hdl.handle.net/1807/33285
► The CanX-4 and CanX-5 mission currently under development at The University of Toronto Institute for Aerospace Studies Space Flight Laboratory UTIAS/SFL is a challenging formation…
(more)
▼ The CanX-4 and CanX-5 mission currently under development at The University of Toronto Institute for Aerospace Studies Space Flight Laboratory UTIAS/SFL is a challenging formation flying technology demonstration. Its requirements of sub-metre control accuracy have yet to be realized
with nanosatellites. Many large technical challenges must be addressed in order to ensure the success of the CanX-4/5 mission. This includes the development of software for an intersatellite communication system, integration and optimization of key formation flying algorithms onto the
Payload On-Board Computer as well as the development of a Hardware-In-The-Loop simulator for full on-orbit mission simulations. This thesis will provide background knowledge of the Space Flight Laboratory and its activities, the CanX-4/5 mission, and nally highlight the authors contributions to overcoming each of these technical challenges and ensuring the success of the CanX-4 and CanX-5 mission.
MAST
Advisors/Committee Members: Zee, Robert E., Aerospace Science and Engineering.
Subjects/Keywords: CanX; Embedded Systems; Software; Protocol Stack; Satellite Communications; On-board Computers; Software Optimizations; Nanosatellites; 0544; 0538
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APA (6th Edition):
Leonard, M. L. (2012). Software for the Canadian Advanced Nanospace eXperiment-4/5. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/33285
Chicago Manual of Style (16th Edition):
Leonard, Matthew Leigh. “Software for the Canadian Advanced Nanospace eXperiment-4/5.” 2012. Masters Thesis, University of Toronto. Accessed January 28, 2021.
http://hdl.handle.net/1807/33285.
MLA Handbook (7th Edition):
Leonard, Matthew Leigh. “Software for the Canadian Advanced Nanospace eXperiment-4/5.” 2012. Web. 28 Jan 2021.
Vancouver:
Leonard ML. Software for the Canadian Advanced Nanospace eXperiment-4/5. [Internet] [Masters thesis]. University of Toronto; 2012. [cited 2021 Jan 28].
Available from: http://hdl.handle.net/1807/33285.
Council of Science Editors:
Leonard ML. Software for the Canadian Advanced Nanospace eXperiment-4/5. [Masters Thesis]. University of Toronto; 2012. Available from: http://hdl.handle.net/1807/33285
30.
Evain, Hélène.
Nouvelles configurations de grappes d’actionneurs gyroscopiques pour le contrôle de satellites agiles : New configurations of control moment gyro clusters for the control of agile satellites.
Degree: Docteur es, Automatique, 2017, Toulouse, ISAE
URL: http://www.theses.fr/2017ESAE0044
► Dans cette thèse, le problème du contrôle d’attitude de satellites agiles à l’aide de grappes d’actionneurs gyroscopiques (AGs) est considéré et plus particulièrement son application…
(more)
▼ Dans cette thèse, le problème du contrôle d’attitude de satellites agiles à l’aide de grappes d’actionneurs gyroscopiques (AGs) est considéré et plus particulièrement son application au contrôle de micro/nanosatellites (10-100 kg). Des outils d’analyse topologique sont tout d'abord développés. La comparaison de différentes configurations de grappes justifie le choix d'une géométrie pyramidale à six actionneurs gyroscopiques. Des analyses plus approfondies de cette grappe, avec et sans cas de panne, permettent de déduire des contraintes que la loi de pilotage doit vérifier pour être adaptée à ce système. Pour y répondre, après analyse de la littérature, une nouvelle structure de loi de pilotage ainsi qu’une formulation différente des équations cinématiques sont développées. Cette structure est basée sur l’algorithme du filtre de Kalman étendu. Elle a pour avantages de répondre aux exigences en termes de calcul temps réel au bord des satellites, de flexibilité sur la gestion des contraintes et de facilité d’adaptation en cas de pannes. En outre, une procédure de génération de boucle de commande, englobant la loi de pilotage et un contrôleur robuste du système, est proposée. La généralisation de cette boucle de commande est illustrée sur des bras manipulateurs à base fixe et spatiaux.En parallèle, l’étude du passage des singularités internes intraversables mène à une nouvelle stratégie d’évitement de ces singularités. Des simulations sur des modèles de satellites représentatifs illustrent les résultats. La grappe d’actionneurs et la boucle de commande développées seront testées dans le cadre d’une expérimentation en microgravité.
In this thesis, the attitude control problem for agile satellites with control moment gyro (CMG) clusters is studied. In particular, the problem applies to micro/nanosatellites (10-100kg). First, numerical tools are developed to analyse the compatibility of various cluster configurations with the nanosatellite constraints. The pyramidal six-CMG cluster is then selected. This cluster topology is analysed in depth, with and without actuator failures. Constraints on the development of a steering law adapted to our system are deduced. Among them, the singularity avoidance issue is emphasised. To meet the requirements, an analysis of the literature is carried out. Then, a new steering law structure and a different formulation of the kinematic equations are developed. This structure is based on the extended Kalman filter algorithm. It meets the requirements because it can be calculated in real-time onboard satellites, constraints imposed on the system are handled with flexibility and it is easily adaptable in case of actuator failures. In addition, a procedure to generate the control loop is proposed, containing a robust controller. The generalisation of this control loop is shown on space and fixed-base manipulator arms. Furthermore, the study of the internal elliptic singularities in CMG clusters leads to a new singularity avoidance strategy. Software simulations on highly representative…
Advisors/Committee Members: Alazard, Daniel (thesis director), Rognant, Mathieu (thesis director).
Subjects/Keywords: Actionneur gyroscopique; Allocation; Scao; Singularité; Filtre de Kalman; Nanosatellites; Control Moment Gyro; Allocation; Aocs; Singularity; Kalman filter; Nanosatellite; 629.8
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APA ·
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Export
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APA (6th Edition):
Evain, H. (2017). Nouvelles configurations de grappes d’actionneurs gyroscopiques pour le contrôle de satellites agiles : New configurations of control moment gyro clusters for the control of agile satellites. (Doctoral Dissertation). Toulouse, ISAE. Retrieved from http://www.theses.fr/2017ESAE0044
Chicago Manual of Style (16th Edition):
Evain, Hélène. “Nouvelles configurations de grappes d’actionneurs gyroscopiques pour le contrôle de satellites agiles : New configurations of control moment gyro clusters for the control of agile satellites.” 2017. Doctoral Dissertation, Toulouse, ISAE. Accessed January 28, 2021.
http://www.theses.fr/2017ESAE0044.
MLA Handbook (7th Edition):
Evain, Hélène. “Nouvelles configurations de grappes d’actionneurs gyroscopiques pour le contrôle de satellites agiles : New configurations of control moment gyro clusters for the control of agile satellites.” 2017. Web. 28 Jan 2021.
Vancouver:
Evain H. Nouvelles configurations de grappes d’actionneurs gyroscopiques pour le contrôle de satellites agiles : New configurations of control moment gyro clusters for the control of agile satellites. [Internet] [Doctoral dissertation]. Toulouse, ISAE; 2017. [cited 2021 Jan 28].
Available from: http://www.theses.fr/2017ESAE0044.
Council of Science Editors:
Evain H. Nouvelles configurations de grappes d’actionneurs gyroscopiques pour le contrôle de satellites agiles : New configurations of control moment gyro clusters for the control of agile satellites. [Doctoral Dissertation]. Toulouse, ISAE; 2017. Available from: http://www.theses.fr/2017ESAE0044
◁ [1] [2] ▶
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Open Access Theses and Dissertations
