subject:(Solar Sail)

Stellenbosch University

1. Jordaan, Willem Hendrik. Spinning solar sail : the deployment and control of a spinning solar sail satellite.

Degree: D.Phil, Electrical and Electronic Engineering, 2016, Stellenbosch University

URL: http://hdl.handle.net/10019.1/98477

► ENGLISH ABSTRACT: Solar sailing has become a viable and practical option for current satellite missions. A spinning solar sail has a number advantages above a… (more)

▼ ENGLISH ABSTRACT: Solar sailing has become a viable and practical option for current satellite missions. A spinning solar sail has a number advantages above a 3-axis stabilised sail. A spinning sail is more resistant to disturbance torques and the misalignment of the centre of mass and centre of pressure. The spinning sail generates a constant centrifugal force, which reduces sail billowing and makes it possible to use wire booms. The new tri-spin solar sail and tri-spin Gyro satellite configurations are proposed that combines the advantages of the spinning and 3-axis stabilised sail designs. This study focuses on the deployment control of the sail and the orientation control of the satellite. Different deployment methods of a rotating structure are studied. The active deployment method makes use of a separate module with an actuator on the rotating system to deploy the structure. The passive deployment method, deploys the structure by using centrifugal force generated by continually spinning the deployment mechanism. A pulse deployment controller and model estimation methods for the passive deployment mechanism are proposed to improve the controllability of the passive deployment method. The mathematical models of these methods are investigated in simulation. A deployment demonstrator is built, which is able to perform either an active or a passive deployment. The theoretical simulation results show promising correlations to the practical results from the deployment demonstrator. Further experiments are conducted to investigate methods to increase the damping of a wire boom. The orientation control includes the development of an accurate mathematical model of the satellite. This model contains the rigid dynamics of the satellite and the non-rigid dynamics of the rotating wire booms. The moment of inertia of the satellite is used as a cross-coupling parameter between the rigid satellite dynamics and non-rigid wire dynamics. The dynamics of the wire booms are examined and the main parameters to keep the wire booms stable are identified. Attitude manoeuvres for changing the orbit altitude of a satellite in earth- and sun-centred orbits are implemented within an orbital simulation to reveal the change in orbital elements caused by the solar thrust. An attitude determination and control system (ADCS) is designed for the conceptual satellite. The state determination and attitude controllers are designed to perform the needed manoeuvres for a satellite to change its altitude by using solar pressure. The controller design includes a magnetic B-dot, a deployment rate controller, solar tracking controller, aerodynamic controller and momentum dumping controller. The performance of the ADCS design on a tri-spin solar sail satellite are investigated through an in depth simulation, which includes: the dynamic models created for the rigid satellite, the non-rigid wire booms and deployment methods. The simulations reveal that it is feasible to implement the ADCS system on the novel tri-spin solar sail… Advisors/Committee Members: Steyn, W. H., Stellenbosch University. Faculty of Engineering. Dept. of Electrical and Electronic Engineering..

Subjects/Keywords: Solar sails; UCTD; Spin (Aerodynamics); Solar sail satellite

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APA (6^th Edition):

Jordaan, W. H. (2016). Spinning solar sail : the deployment and control of a spinning solar sail satellite. (Doctoral Dissertation). Stellenbosch University. Retrieved from http://hdl.handle.net/10019.1/98477

Chicago Manual of Style (16^th Edition):

Jordaan, Willem Hendrik. “Spinning solar sail : the deployment and control of a spinning solar sail satellite.” 2016. Doctoral Dissertation, Stellenbosch University. Accessed January 24, 2021. http://hdl.handle.net/10019.1/98477.

MLA Handbook (7^th Edition):

Jordaan, Willem Hendrik. “Spinning solar sail : the deployment and control of a spinning solar sail satellite.” 2016. Web. 24 Jan 2021.

Vancouver:

Jordaan WH. Spinning solar sail : the deployment and control of a spinning solar sail satellite. [Internet] [Doctoral dissertation]. Stellenbosch University; 2016. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/10019.1/98477.

Council of Science Editors:

Jordaan WH. Spinning solar sail : the deployment and control of a spinning solar sail satellite. [Doctoral Dissertation]. Stellenbosch University; 2016. Available from: http://hdl.handle.net/10019.1/98477

Stellenbosch University

2. Hibbert, Luke Thirkell. The deployment of a spinning solar sail.

Degree: MEng, Electrical and Electronic Engineering, 2019, Stellenbosch University

URL: http://hdl.handle.net/10019.1/105819

► ENGLISH ABSTRACT: In recent years, interest in solar sailing has grown greatly, and significant research and resources are being contributed to its development and the… (more)

▼ ENGLISH ABSTRACT: In recent years, interest in solar sailing has grown greatly, and significant research and resources are being contributed to its development and the development of similar and supporting technologies. Sailcraft utilise large deployable membrane structures to exchange momentum with photons in order to generate thrust from Solar Radiation Pressure. Many small solar sailing satellites make use of three-axis stabilisation and semi-rigid booms, however this design places limits on the sizes of sails possible due to the physical properties of these booms and the size of the deployment mechanisms required. Larger sails are desired in order to achieve greater solar thrust. The use of a spinning solar sailcraft with flexible booms makes it possible to deploy significantly larger sails, as the centrifugal force acts to deploy the sail and maintain the deployment thereof, eliminating the limits enforced by available semi-rigid boom technologies. The low cost and small size of CubeSats may be used to further develop spinning solar sail technology. This thesis focuses on the deployment of a spinning solar sail on a CubeSat platform. The dynamic equations which describe the behaviour of a spinning solar sailing satellite with flexible booms during- and post- deployment are developed. These equations, which describe the system, are used to investigate the behavioural trends in the deployment under various deployment strategies. Particular focus is given to the passive deployment of the sail booms. No direct active control is placed on the boom deployment in this case; the deployment rate is instead indirectly controlled through the spin rate of the satellite. This is achieved by the application of rotational damping to the pulley on which the booms are stowed and where from they are deployed. Passive deployment cases are investigated where control is based on strategies including free spin, centrifugal force-based control and constant spin rate control. The dynamics of active deployment, where the deployment rate is directly controlled, are also investigated. An experimental deployment mechanism is designed in order to validate the trends seen in the cases of passive deployment. This experimental deployment mechanism makes use of a geared rotary damper to apply a torque to the pulley from which the booms deploy - this slows the deployment rate with no external inputs. The trends seen in simulation are confirmed where possible. A control algorithm is developed, which is capable of detecting the deployment state of the booms based on the control input supplied to the motor driving the mechanism spin. Based on the deployment state detected, the spin rate of the mechanism can be appropriately adjusted. Based on the practical experience and insights gained from experimentation, the designs of three deployment mechanisms are presented. Two of the mechanisms designed make use of rotary dampers in different configurations in order to achieve passive deployment. The third mechanism is… Advisors/Committee Members: Jordaan, H. W., Steyn, W. H., Stellenbosch University. Faculty of Engineering. Dept. of Electrical and Electronic Engineering..

Subjects/Keywords: The Deployment of a Spinning Solar Sail; UCTD; Solar sails; Solar radiation – Pressure

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APA (6^th Edition):

Hibbert, L. T. (2019). The deployment of a spinning solar sail. (Thesis). Stellenbosch University. Retrieved from http://hdl.handle.net/10019.1/105819

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Hibbert, Luke Thirkell. “The deployment of a spinning solar sail.” 2019. Thesis, Stellenbosch University. Accessed January 24, 2021. http://hdl.handle.net/10019.1/105819.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Hibbert, Luke Thirkell. “The deployment of a spinning solar sail.” 2019. Web. 24 Jan 2021.

Vancouver:

Hibbert LT. The deployment of a spinning solar sail. [Internet] [Thesis]. Stellenbosch University; 2019. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/10019.1/105819.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Hibbert LT. The deployment of a spinning solar sail. [Thesis]. Stellenbosch University; 2019. Available from: http://hdl.handle.net/10019.1/105819

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

North Carolina State University

3. Hays, Scott. A Study of the Advantages of Using a Tether Ballast Mass as Part of the Control System in a Solar Sail Based Solar Storm Warning Mission.

Degree: MS, Aerospace Engineering, 2007, North Carolina State University

URL: http://www.lib.ncsu.edu/resolver/1840.16/604

Subjects/Keywords: spacecraft; controls; solar sail; dynamics

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APA (6^th Edition):

Hays, S. (2007). A Study of the Advantages of Using a Tether Ballast Mass as Part of the Control System in a Solar Sail Based Solar Storm Warning Mission. (Thesis). North Carolina State University. Retrieved from http://www.lib.ncsu.edu/resolver/1840.16/604

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Hays, Scott. “A Study of the Advantages of Using a Tether Ballast Mass as Part of the Control System in a Solar Sail Based Solar Storm Warning Mission.” 2007. Thesis, North Carolina State University. Accessed January 24, 2021. http://www.lib.ncsu.edu/resolver/1840.16/604.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Hays, Scott. “A Study of the Advantages of Using a Tether Ballast Mass as Part of the Control System in a Solar Sail Based Solar Storm Warning Mission.” 2007. Web. 24 Jan 2021.

Vancouver:

Hays S. A Study of the Advantages of Using a Tether Ballast Mass as Part of the Control System in a Solar Sail Based Solar Storm Warning Mission. [Internet] [Thesis]. North Carolina State University; 2007. [cited 2021 Jan 24]. Available from: http://www.lib.ncsu.edu/resolver/1840.16/604.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Hays S. A Study of the Advantages of Using a Tether Ballast Mass as Part of the Control System in a Solar Sail Based Solar Storm Warning Mission. [Thesis]. North Carolina State University; 2007. Available from: http://www.lib.ncsu.edu/resolver/1840.16/604

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Purdue University

4. Das, Ashwati. Solar Sail Trajectory Design In The Earth-Moon Circular Restricted Three Body Problem.

Degree: MS, Aeronautics and Astronautics, 2014, Purdue University

URL: http://docs.lib.purdue.edu/open_access_theses/316

► The quest to explore the Moon has helped resolve scientific questions, has spurred leaps in technology development, and has revealed Earth's celestial companion to… (more)

▼ The quest to explore the Moon has helped resolve scientific questions, has spurred leaps in technology development, and has revealed Earth's celestial companion to be a gateway to other destinations. With a renewed focus on returning to the Moon in this decade, alternatives to chemical propulsion systems are becoming attractive methods to efficiently use scarce resources and support extended mission durations. Thus, an investigation is conducted to develop a general framework, that facilitates propellant-free Earth-Moon transfers by exploiting sail dynamics in combination with advantageous transfer options offered in the Earth-Moon circular restricted multi-body dynamical model. Both periodic orbits in the vicinity of the Earth-Moon libration points, and lunar-centric long-term capture orbits are incorporated as target destinations to demonstrate the applicability of the general framework to varied design scanarios, each incorporating a variety of complexities and challenges. The transfers are comprised of three phases - a spiral Earth escape, a transit period, and, finally, the capture into a desirable orbit in the vicinity of the Moon. The Earth-escape phase consists of spiral trajectories constructed using three different sail steering strategies - locally optimal, on/off and velocity tangent. In the case of the Earth-libration point transfers, naturally occurring flow structures (e.g., invariant manifolds) arising from the mutual gravitational interaction of the Earth and Moon are exploited to link an Earth departure spiral with a destination orbit. In contrast, sail steering alone is employed to establish a link between the Earth-escape phase and capture orbits about the Moon due to a lack of applicable natural structures for the required connection. Metrics associated with the transfers including flight-time and the influence of operational constraints, such as occultation events, are investigated to determine the available capabilities for Earth-Moon transfers given current sail technology levels. Although the implemented steering laws suffice to generate baseline paths, infeasible turn rate demands placed on the sail are also investigated to explore the technical hurdles in designing Earth-Moon transfers. The methodologies are suitable for a variety of mission scenarios and sail configurations, rendering the resulting trajectories valuable for a diverse range of applications. Advisors/Committee Members: Kathleen C. Howell, James M. Longuski, David Minton.

Subjects/Keywords: Applied sciences; Occultation; Sail; Solar; Steering; Transfer; Turn; Aerospace Engineering

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APA (6^th Edition):

Das, A. (2014). Solar Sail Trajectory Design In The Earth-Moon Circular Restricted Three Body Problem. (Thesis). Purdue University. Retrieved from http://docs.lib.purdue.edu/open_access_theses/316

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Das, Ashwati. “Solar Sail Trajectory Design In The Earth-Moon Circular Restricted Three Body Problem.” 2014. Thesis, Purdue University. Accessed January 24, 2021. http://docs.lib.purdue.edu/open_access_theses/316.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Das, Ashwati. “Solar Sail Trajectory Design In The Earth-Moon Circular Restricted Three Body Problem.” 2014. Web. 24 Jan 2021.

Vancouver:

Das A. Solar Sail Trajectory Design In The Earth-Moon Circular Restricted Three Body Problem. [Internet] [Thesis]. Purdue University; 2014. [cited 2021 Jan 24]. Available from: http://docs.lib.purdue.edu/open_access_theses/316.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Das A. Solar Sail Trajectory Design In The Earth-Moon Circular Restricted Three Body Problem. [Thesis]. Purdue University; 2014. Available from: http://docs.lib.purdue.edu/open_access_theses/316

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Arizona

5. Bowers, Kade. Radiometric Modeling for Breakthrough Starshot: How Sail Shape and BRDF Impact the Adaptive Optics .

Degree: 2020, University of Arizona

URL: http://hdl.handle.net/10150/642124

► The Breakthrough Starshot program is an ambitious project to achieve interstellar travel by using a massive laser array to propel a nanocraft to 20% the… (more)

Subjects/Keywords: Adaptive Optics; BRDF; Breakthrough Starshot; Directed Energy; Solar Sail; Space Travel

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APA (6^th Edition):

Bowers, K. (2020). Radiometric Modeling for Breakthrough Starshot: How Sail Shape and BRDF Impact the Adaptive Optics . (Masters Thesis). University of Arizona. Retrieved from http://hdl.handle.net/10150/642124

Chicago Manual of Style (16^th Edition):

Bowers, Kade. “Radiometric Modeling for Breakthrough Starshot: How Sail Shape and BRDF Impact the Adaptive Optics .” 2020. Masters Thesis, University of Arizona. Accessed January 24, 2021. http://hdl.handle.net/10150/642124.

MLA Handbook (7^th Edition):

Bowers, Kade. “Radiometric Modeling for Breakthrough Starshot: How Sail Shape and BRDF Impact the Adaptive Optics .” 2020. Web. 24 Jan 2021.

Vancouver:

Bowers K. Radiometric Modeling for Breakthrough Starshot: How Sail Shape and BRDF Impact the Adaptive Optics . [Internet] [Masters thesis]. University of Arizona; 2020. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/10150/642124.

Council of Science Editors:

Bowers K. Radiometric Modeling for Breakthrough Starshot: How Sail Shape and BRDF Impact the Adaptive Optics . [Masters Thesis]. University of Arizona; 2020. Available from: http://hdl.handle.net/10150/642124

University of Colorado

6. Parsay, Khashayar. Invariant Solar Sail Formations in Elliptical Sun-Synchronous Orbits.

Degree: PhD, Aerospace Engineering Sciences, 2016, University of Colorado

URL: https://scholar.colorado.edu/asen_gradetds/155

► Current and past missions that study the Earth's geomagnetic tail require multiple spacecraft to fly in formation about a highly eccentric Keplerian reference orbit… (more)

▼ Current and past missions that study the Earth's geomagnetic tail require multiple spacecraft to fly in formation about a highly eccentric Keplerian reference orbit that has its apogee inside a predefined science region of interest. Because the geomagnetic tail is directed along the Sun-Earth line and therefore rotates annually, inertially fixed Keplerian orbits are only aligned with the geomagnetic tail once per year. This limitation reduces the duration of the science phase to less than a few months annually. Solar sails are capable of creating non-Keplerian, Sun-synchronous orbits that rotate with the geomagnetic tail. A solar sail flying in a Sun-synchronous orbit will have a continuous presence in the geomagnetic tail throughout the entire year, which significantly improves the in situ observations of the magnetosphere. To achieve a Sun-synchronous orbit, a solar sail is required to maintain a Sun-pointing attitude, which leads to the artificial precession of the orbit apse line in a Sun-synchronous manner, leaving the orbit apogee inside the science region of interest throughout entire the year. To study the spatial and temporal variations of plasma in the highly dynamic environment of the magnetosphere, multiple spacecraft must fly in a formation. The objective for this dissertation is to investigate the feasibility of solar sail formation flying in the Earth-centered, Sun-synchronous orbit regime. The focus of this effort is to enable formation flying for a group of solar sails that maintain a nominally fixed Sun-pointing attitude during formation flight, solely for the purpose of precessing their orbit apse lines Sun-synchronously. A fixed-attitude solar sail formation is motivated by the difficulties in the simultaneous control of orbit and attitude in flying solar sails. First, the secular rates of the orbital elements resulting from the effects of solar radiation pressure (SRP) are determined using averaging theory for a Sun-pointing attitude sail. These averaged rates are used to analytically derive the necessary conditions for a drift-free solar sail formation in Sun-synchronous orbits, assuming a fixed Sun-pointing orientation for each sail in formation. Next, the problem of formation design is solved using nonlinear programming for optimal two-craft, three-craft, and four-craft solar sail formations, in terms of formation quality and stability. Finally, the problem of formation establishment is addressed using optimal control theory, assuming that the sails are capable of making small changes to their orientations with respect to the Sun. These studies demonstrate the feasibility of solar sail formation flying for exploring the geomagnetic tail and improve upon previous work, which only considered unnatural relative motions that require continuous use of active control to remain in formation. Advisors/Committee Members: Hanspeter Schaub, Daniel Scheeres, Trevor Williams, Dale Lawrence, Webster Cash.

Subjects/Keywords: formation flying; magnetosphere; solar sail; sun-synchronous; Aerospace Engineering; Space Vehicles

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Parsay, K. (2016). Invariant Solar Sail Formations in Elliptical Sun-Synchronous Orbits. (Doctoral Dissertation). University of Colorado. Retrieved from https://scholar.colorado.edu/asen_gradetds/155

Chicago Manual of Style (16^th Edition):

Parsay, Khashayar. “Invariant Solar Sail Formations in Elliptical Sun-Synchronous Orbits.” 2016. Doctoral Dissertation, University of Colorado. Accessed January 24, 2021. https://scholar.colorado.edu/asen_gradetds/155.

MLA Handbook (7^th Edition):

Parsay, Khashayar. “Invariant Solar Sail Formations in Elliptical Sun-Synchronous Orbits.” 2016. Web. 24 Jan 2021.

Vancouver:

Parsay K. Invariant Solar Sail Formations in Elliptical Sun-Synchronous Orbits. [Internet] [Doctoral dissertation]. University of Colorado; 2016. [cited 2021 Jan 24]. Available from: https://scholar.colorado.edu/asen_gradetds/155.

Council of Science Editors:

Parsay K. Invariant Solar Sail Formations in Elliptical Sun-Synchronous Orbits. [Doctoral Dissertation]. University of Colorado; 2016. Available from: https://scholar.colorado.edu/asen_gradetds/155

Delft University of Technology

7. Carzana, Livio (author). Laser-Enhanced Solar Sailing: Modeling and Trajectory Optimization for Interplanetary Missions.

Degree: 2017, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:2c79c372-52d8-4489-93ae-1e2f7c673469

► When sunlight illuminates a body, a tiny pressure is exerted upon its surface due to the photons impacting on it. Such a principle forms the… (more)

▼ When sunlight illuminates a body, a tiny pressure is exerted upon its surface due to the photons impacting on it. Such a principle forms the basis of solar sailing, in which the solar radiation pressure is used to accelerate highly reflective lightweight structures called solar sails. Similarly, a laser-enhanced solar sail is a solar sail in which also an external laser beam pointed towards the sail is exploited to generate thrust. In this way an additional laser radiation pressure is exerted onto the sail, hence conferring higher propulsive and steering capabilities, and leading to an increased maneuverability of the sailcraft. The main purpose of this thesis project is to provide a model of the laser-enhanced solar sail dynamics and to establish the advantages of laser-enhanced solar sailing as compared to "traditional" solar sailing. The analysis has been pursued focusing on interplanetary missions and considering ideal sails, i.e. sails able to perfectly reflect the impinging radiation. Normally, for low-thrust interplanetary missions the propellant consumption and time of flight required for the transfers to take place play a crucial role. However, since solar sails do not exploit any propellant, the traditional and laser-enhanced sailcraft performances have been compared by analyzing their flight-time optimal trajectories, focusing on three different mission scenarios: a Mercury orbit rendezvous, Mars orbit rendezvous and Neptune flyby. These trajectories have been computed by taking advantage of an evolutionary neurocontrol optimizer, in which newly added functionalities have been implemented with the purpose of optimizing laser-enhanced solar sail trajectories. The trajectory analysis results have shown that, if laser-enhanced sailcraft are used instead of traditional sailcraft, flight time gains in the order of 8-11% can be achieved for the missions to Mercury and Mars orbits, while a smaller 2.5% gain is achieved for the flyby mission to Neptune. Advisors/Committee Members: Noomen, Ron (mentor), Dachwald, Bernd (graduation committee), Stam, Daphne (graduation committee), Sundaramoorthy, Prem (graduation committee), Delft University of Technology (degree granting institution).

Subjects/Keywords: Laser-enhanced; Solar Sail; Ideal; Trajectory; Optimization; Machine Learning; Evolutionary Neurocontrol

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APA (6^th Edition):

Carzana, L. (. (2017). Laser-Enhanced Solar Sailing: Modeling and Trajectory Optimization for Interplanetary Missions. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:2c79c372-52d8-4489-93ae-1e2f7c673469

Chicago Manual of Style (16^th Edition):

Carzana, Livio (author). “Laser-Enhanced Solar Sailing: Modeling and Trajectory Optimization for Interplanetary Missions.” 2017. Masters Thesis, Delft University of Technology. Accessed January 24, 2021. http://resolver.tudelft.nl/uuid:2c79c372-52d8-4489-93ae-1e2f7c673469.

MLA Handbook (7^th Edition):

Carzana, Livio (author). “Laser-Enhanced Solar Sailing: Modeling and Trajectory Optimization for Interplanetary Missions.” 2017. Web. 24 Jan 2021.

Vancouver:

Carzana L(. Laser-Enhanced Solar Sailing: Modeling and Trajectory Optimization for Interplanetary Missions. [Internet] [Masters thesis]. Delft University of Technology; 2017. [cited 2021 Jan 24]. Available from: http://resolver.tudelft.nl/uuid:2c79c372-52d8-4489-93ae-1e2f7c673469.

Council of Science Editors:

Carzana L(. Laser-Enhanced Solar Sailing: Modeling and Trajectory Optimization for Interplanetary Missions. [Masters Thesis]. Delft University of Technology; 2017. Available from: http://resolver.tudelft.nl/uuid:2c79c372-52d8-4489-93ae-1e2f7c673469

Cal Poly

8. Smiroldo, Jordan. Investigation into the Mitigation of the Effects of Uncertain Optical Degradation on an Interplanetary Solar Sail Mission Using a Single Model Update.

Degree: MS, Aerospace Engineering, 2013, Cal Poly

URL: https://digitalcommons.calpoly.edu/theses/1135 ; 10.15368/theses.2013.215

► The renewed academic interest in using solar sails as a source of spacecraft propulsion has been accompanied by a recent fervor of investigations into… (more)

Subjects/Keywords: Solar; Sail; Trajectory; Collocation; Non-ideal; Performance; Astrodynamics

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APA (6^th Edition):

Smiroldo, J. (2013). Investigation into the Mitigation of the Effects of Uncertain Optical Degradation on an Interplanetary Solar Sail Mission Using a Single Model Update. (Masters Thesis). Cal Poly. Retrieved from https://digitalcommons.calpoly.edu/theses/1135 ; 10.15368/theses.2013.215

Chicago Manual of Style (16^th Edition):

Smiroldo, Jordan. “Investigation into the Mitigation of the Effects of Uncertain Optical Degradation on an Interplanetary Solar Sail Mission Using a Single Model Update.” 2013. Masters Thesis, Cal Poly. Accessed January 24, 2021. https://digitalcommons.calpoly.edu/theses/1135 ; 10.15368/theses.2013.215.

MLA Handbook (7^th Edition):

Smiroldo, Jordan. “Investigation into the Mitigation of the Effects of Uncertain Optical Degradation on an Interplanetary Solar Sail Mission Using a Single Model Update.” 2013. Web. 24 Jan 2021.

Vancouver:

Smiroldo J. Investigation into the Mitigation of the Effects of Uncertain Optical Degradation on an Interplanetary Solar Sail Mission Using a Single Model Update. [Internet] [Masters thesis]. Cal Poly; 2013. [cited 2021 Jan 24]. Available from: https://digitalcommons.calpoly.edu/theses/1135 ; 10.15368/theses.2013.215.

Council of Science Editors:

Smiroldo J. Investigation into the Mitigation of the Effects of Uncertain Optical Degradation on an Interplanetary Solar Sail Mission Using a Single Model Update. [Masters Thesis]. Cal Poly; 2013. Available from: https://digitalcommons.calpoly.edu/theses/1135 ; 10.15368/theses.2013.215

9. Gonzales, Jorell Salazar. Finite element analysis of a solar sail affected by celestial bodies.

Degree: MS, Mechanical Engineering, 2013, California State University – Sacramento

URL: http://hdl.handle.net/10211.9/2095

► Solar sails are spacecrafts that use light propulsion to push their large sails to accelerate forward. Just like how sailboats use the wind to move… (more)

Subjects/Keywords: Membrane; Deformation; Solar sail

…7 3. SOLAR SAIL DEFORMATION… …13 3.1. Solar Sail Construction… …13 4. Table 3.2: Applied Forces on Solar Sail… …3.3: 10 m Solar Sail Viewed in the x-y Plane. ��…..…....................….15 10. Figure… …Figure 3.5: Solar Sail with Applied Solar Pressure…

10 more images…

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APA (6^th Edition):

Gonzales, J. S. (2013). Finite element analysis of a solar sail affected by celestial bodies. (Masters Thesis). California State University – Sacramento. Retrieved from http://hdl.handle.net/10211.9/2095

Chicago Manual of Style (16^th Edition):

Gonzales, Jorell Salazar. “Finite element analysis of a solar sail affected by celestial bodies.” 2013. Masters Thesis, California State University – Sacramento. Accessed January 24, 2021. http://hdl.handle.net/10211.9/2095.

MLA Handbook (7^th Edition):

Gonzales, Jorell Salazar. “Finite element analysis of a solar sail affected by celestial bodies.” 2013. Web. 24 Jan 2021.

Vancouver:

Gonzales JS. Finite element analysis of a solar sail affected by celestial bodies. [Internet] [Masters thesis]. California State University – Sacramento; 2013. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/10211.9/2095.

Council of Science Editors:

Gonzales JS. Finite element analysis of a solar sail affected by celestial bodies. [Masters Thesis]. California State University – Sacramento; 2013. Available from: http://hdl.handle.net/10211.9/2095

Delft University of Technology

10. van den Oever, Tom (author). Solar-sail transfers to Earth-Moon L2-displaced vertical Lyapunov orbits.

Degree: 2018, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:066162cd-c531-4400-8e0f-3b3d6dedb5b9

► This thesis presents the design of solar-sail transfer trajectories to a constellation of two spacecraft in displaced vertical Lyapunov orbits at the L2 point of… (more)

Subjects/Keywords: Collocation; Trajectory; Discretization; Earth-Moon; Astrodynamics; Solar sail; Solar-sail; Solar sailing; Mesh control; Error estimation; Soyuz; Transfer trajectory; vertical Lyapunov; orbit; Gauss-Lobatto; Gauss-Newton

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APA (6^th Edition):

van den Oever, T. (. (2018). Solar-sail transfers to Earth-Moon L2-displaced vertical Lyapunov orbits. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:066162cd-c531-4400-8e0f-3b3d6dedb5b9

Chicago Manual of Style (16^th Edition):

van den Oever, Tom (author). “Solar-sail transfers to Earth-Moon L2-displaced vertical Lyapunov orbits.” 2018. Masters Thesis, Delft University of Technology. Accessed January 24, 2021. http://resolver.tudelft.nl/uuid:066162cd-c531-4400-8e0f-3b3d6dedb5b9.

MLA Handbook (7^th Edition):

van den Oever, Tom (author). “Solar-sail transfers to Earth-Moon L2-displaced vertical Lyapunov orbits.” 2018. Web. 24 Jan 2021.

Vancouver:

van den Oever T(. Solar-sail transfers to Earth-Moon L2-displaced vertical Lyapunov orbits. [Internet] [Masters thesis]. Delft University of Technology; 2018. [cited 2021 Jan 24]. Available from: http://resolver.tudelft.nl/uuid:066162cd-c531-4400-8e0f-3b3d6dedb5b9.

Council of Science Editors:

van den Oever T(. Solar-sail transfers to Earth-Moon L2-displaced vertical Lyapunov orbits. [Masters Thesis]. Delft University of Technology; 2018. Available from: http://resolver.tudelft.nl/uuid:066162cd-c531-4400-8e0f-3b3d6dedb5b9

Rochester Institute of Technology

11. Schuster, Daniel George, Jr. Dynamic Response of Dielectric Lenses Influenced By Radiation Pressure.

Degree: MS, Mechanical Engineering, 2014, Rochester Institute of Technology

URL: https://scholarworks.rit.edu/theses/8318

► Through analytical modeling and numerical simulations the dynamic response and stability of dielectric lenses that are influenced by radiation pressure forces and torques is… (more)

Subjects/Keywords: Dielectric lenses; Gyroscopic motion; Mathieu equation; Radiation pressure; Solar sail; Stability and control

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APA (6^th Edition):

Schuster, Daniel George, J. (2014). Dynamic Response of Dielectric Lenses Influenced By Radiation Pressure. (Masters Thesis). Rochester Institute of Technology. Retrieved from https://scholarworks.rit.edu/theses/8318

Chicago Manual of Style (16^th Edition):

Schuster, Daniel George, Jr. “Dynamic Response of Dielectric Lenses Influenced By Radiation Pressure.” 2014. Masters Thesis, Rochester Institute of Technology. Accessed January 24, 2021. https://scholarworks.rit.edu/theses/8318.

MLA Handbook (7^th Edition):

Schuster, Daniel George, Jr. “Dynamic Response of Dielectric Lenses Influenced By Radiation Pressure.” 2014. Web. 24 Jan 2021.

Vancouver:

Schuster, Daniel George J. Dynamic Response of Dielectric Lenses Influenced By Radiation Pressure. [Internet] [Masters thesis]. Rochester Institute of Technology; 2014. [cited 2021 Jan 24]. Available from: https://scholarworks.rit.edu/theses/8318.

Council of Science Editors:

Schuster, Daniel George J. Dynamic Response of Dielectric Lenses Influenced By Radiation Pressure. [Masters Thesis]. Rochester Institute of Technology; 2014. Available from: https://scholarworks.rit.edu/theses/8318

University of Colorado

12. Guerrant, Daniel Vernon. Performance Quantification of Heliogyro Solar Sails Using Structural, Attitude, and Orbital Dynamics and Control Analysis.

Degree: PhD, Aerospace Engineering Sciences, 2015, University of Colorado

URL: https://scholar.colorado.edu/asen_gradetds/101

► Solar sails enable or enhance exploration of a variety of destinations both within and without the solar system. The heliogyro solar sail architecture divides… (more)

Subjects/Keywords: attitude control; dynamics; heliogyro; solar sail; structural dynamics; Astrodynamics; Propulsion and Power; Space Vehicles

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APA (6^th Edition):

Guerrant, D. V. (2015). Performance Quantification of Heliogyro Solar Sails Using Structural, Attitude, and Orbital Dynamics and Control Analysis. (Doctoral Dissertation). University of Colorado. Retrieved from https://scholar.colorado.edu/asen_gradetds/101

Chicago Manual of Style (16^th Edition):

Guerrant, Daniel Vernon. “Performance Quantification of Heliogyro Solar Sails Using Structural, Attitude, and Orbital Dynamics and Control Analysis.” 2015. Doctoral Dissertation, University of Colorado. Accessed January 24, 2021. https://scholar.colorado.edu/asen_gradetds/101.

MLA Handbook (7^th Edition):

Guerrant, Daniel Vernon. “Performance Quantification of Heliogyro Solar Sails Using Structural, Attitude, and Orbital Dynamics and Control Analysis.” 2015. Web. 24 Jan 2021.

Vancouver:

Guerrant DV. Performance Quantification of Heliogyro Solar Sails Using Structural, Attitude, and Orbital Dynamics and Control Analysis. [Internet] [Doctoral dissertation]. University of Colorado; 2015. [cited 2021 Jan 24]. Available from: https://scholar.colorado.edu/asen_gradetds/101.

Council of Science Editors:

Guerrant DV. Performance Quantification of Heliogyro Solar Sails Using Structural, Attitude, and Orbital Dynamics and Control Analysis. [Doctoral Dissertation]. University of Colorado; 2015. Available from: https://scholar.colorado.edu/asen_gradetds/101

University of Toronto

13. Choi, Mirue. Flexible Dynamics and Attitude Control of a Square Solar Sail.

Degree: PhD, 2015, University of Toronto

URL: http://hdl.handle.net/1807/69253

► This thesis presents a comprehensive analysis of attitude and structural dynamics of a square solar sail. In particular, this research examines the use of corner-attached… (more)

▼ This thesis presents a comprehensive analysis of attitude and structural dynamics of a square solar sail. In particular, this research examines the use of corner-attached reflective vanes to control the attitude of the spacecraft. An introduction to known solar sail designs is given, then the mathematics involved in calculating solar radiation pressure forces are presented. A detailed derivation and implementation of the unconstrained nonlinear flexible structural dynamics with Finite Element Method (FEM) models are explored, with several sample simulations of published large deflection experiments used as verification measures. To simulate the inability of a thin membrane to resist compression, the sail membrane elements are augmented with a method that approximates the wrinkling and the slacking dynamics, which is followed by a simulation of another well-known experiment as a verification measure.Once the structural dynamics are established, the usage of the tip vanes is explored. Specifically, a control allocation problem formed by having two degrees of freedom for each tip vane is defined and an efficient solution to this problem is presented, allowing desired control torques to be converted to appropriate vane angles. A randomized testing mechanism is implemented to show the efficacy of this algorithm. The sail shadowing problem is explored as well, where a component of the spacecraft casts shadow upon the sail and prevents solar radiation pressure force from being produced. A method to calculate the region of shadow is presented, and two different shadowing examples are examined - due to the spacecraft bus, and due to the sail itself.Combining all of the above, an attitude control simulation of the sail model is presented. A simple PD controller combined with the control allocation scheme is used to provide the control torque for the sail, with which the spacecraft must orient towards a number of pre-specified attitude targets. Several attitude orientations are simulated, then a number of modifications to the control are explored. The controllability of the rigid and the elastic modes of the sail at different stable states is demonstrated as well, showing that the sail is controllable for all its modes in its stable state. Advisors/Committee Members: Damaren, Christopher J., Aerospace Science and Engineering.

Subjects/Keywords: Attitude Control; Control Allocation; Finite Element Method; Flexible Dynamics; Solar Sail; Wrinkling; 0538

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APA (6^th Edition):

Choi, M. (2015). Flexible Dynamics and Attitude Control of a Square Solar Sail. (Doctoral Dissertation). University of Toronto. Retrieved from http://hdl.handle.net/1807/69253

Chicago Manual of Style (16^th Edition):

Choi, Mirue. “Flexible Dynamics and Attitude Control of a Square Solar Sail.” 2015. Doctoral Dissertation, University of Toronto. Accessed January 24, 2021. http://hdl.handle.net/1807/69253.

MLA Handbook (7^th Edition):

Choi, Mirue. “Flexible Dynamics and Attitude Control of a Square Solar Sail.” 2015. Web. 24 Jan 2021.

Vancouver:

Choi M. Flexible Dynamics and Attitude Control of a Square Solar Sail. [Internet] [Doctoral dissertation]. University of Toronto; 2015. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/1807/69253.

Council of Science Editors:

Choi M. Flexible Dynamics and Attitude Control of a Square Solar Sail. [Doctoral Dissertation]. University of Toronto; 2015. Available from: http://hdl.handle.net/1807/69253

14. -3389-7219. Uncertainty management in solar sail attitude control.

Degree: PhD, Aerospace engineering, 2016, University of Texas – Austin

URL: http://hdl.handle.net/2152/46779

► Solar sails are emerging as a viable alternative to conventional forms of propulsion. Still at their infancy and relatively untested, many sources of uncertainty remain… (more)

▼ Solar sails are emerging as a viable alternative to conventional forms of propulsion. Still at their infancy and relatively untested, many sources of uncertainty remain that are unique to solar sails and which will continue to affect their design as solar sails increase in performance and size. Controlling their attitude in the context of these uncertainties therefore becomes critical to spaceflight missions that will explore our solar system and beyond from new, previously-unattainable perspectives. Two distinct frameworks are developed to manage these uncertainties to control the attitude of solar sails. The first utilizes a provided system model and utilizes an observation of the control history to operate the sail about an equilibrium position that is passively stable. The approach utilizes past information about controller input for the purposes of rejecting disturbances that arise from several sources of uncertainty. The second approach is forward-looking and is inspired by trajectory-based reachability analysis. This approach was developed in the context of six degree-of-freedom supervised control of an unmanned aerial vehicle whose faster dynamics in a disturbance-rich environment provide a computational challenge and thus require machine-learned approximations to a reachable set of safe inputs. These methodologies are then applied to the original solar sail attitude control problem. Predictions are made about the future state of the sail after performing a minimum-time large angle maneuver. Uncertainty distributions are assumed a priori and are then used to create a buffer angle for the maneuver such that no overshoot occurs within a tunable statistical measure of safety. Uncertainties handled in this way include the sail effective reflectivity, flexural rigidity, and moment of inertia. However, the framework is designed to be very adaptable and so is able to accommodate arbitrary sources of uncertainties and flexible modeling techniques. Utilization of machine learning allows for arbitrary complexity in the simulation and modeling framework without impacting the on-board computational requirements of the solar sail hardware. Advisors/Committee Members: Fowler, Wallace T. (advisor), Lightsey, Glenn (committee member), Claudel, Christian (committee member), Bakolas, Efstathios (committee member), Jones, Brandon (committee member).

Subjects/Keywords: Solar sail; Attitude control; Uncertainty

…5 Chapter 2 Propellantless Attitude Control of a Nonplanar Solar Sail… …sailing which shifted towards design of a solar sail that could rendezvous with the Halley comet… …orbits, the ratio of solar sail area to overall spacecraft mass must remain high and in fact… …effort to increase solar sail size and performance as highlighted by NASA’s technology roadmap… …decreased due to miniaturization technologies. Current solar sail designs have been modestly sized…

11 more images…

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APA (6^th Edition):

-3389-7219. (2016). Uncertainty management in solar sail attitude control. (Doctoral Dissertation). University of Texas – Austin. Retrieved from http://hdl.handle.net/2152/46779

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete

Chicago Manual of Style (16^th Edition):

-3389-7219. “Uncertainty management in solar sail attitude control.” 2016. Doctoral Dissertation, University of Texas – Austin. Accessed January 24, 2021. http://hdl.handle.net/2152/46779.

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete

MLA Handbook (7^th Edition):

-3389-7219. “Uncertainty management in solar sail attitude control.” 2016. Web. 24 Jan 2021.

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete

Vancouver:

-3389-7219. Uncertainty management in solar sail attitude control. [Internet] [Doctoral dissertation]. University of Texas – Austin; 2016. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/2152/46779.

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete

Council of Science Editors:

-3389-7219. Uncertainty management in solar sail attitude control. [Doctoral Dissertation]. University of Texas – Austin; 2016. Available from: http://hdl.handle.net/2152/46779

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete

Purdue University

15. Sood, Rohan. Significance of Specific Force Models in Two Applications: Solar Sails to Sun-Earth L4/L5 and GRAIL Data Analysis Suggesting Lava Tubes and Buried Craters on the Moon.

Degree: PhD, Aeronautics and Astronautics, 2016, Purdue University

URL: https://docs.lib.purdue.edu/open_access_dissertations/1374

► In the trajectory design process, gravitational interaction between the bodies of interest plays a key role in developing the over-arching force model. However, non-gravitational forces,… (more)

Subjects/Keywords: buried crater; lava tube; low enery transfer trajectories; moon; solar sail; trajectory design

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APA (6^th Edition):

Sood, R. (2016). Significance of Specific Force Models in Two Applications: Solar Sails to Sun-Earth L4/L5 and GRAIL Data Analysis Suggesting Lava Tubes and Buried Craters on the Moon. (Doctoral Dissertation). Purdue University. Retrieved from https://docs.lib.purdue.edu/open_access_dissertations/1374

Chicago Manual of Style (16^th Edition):

Sood, Rohan. “Significance of Specific Force Models in Two Applications: Solar Sails to Sun-Earth L4/L5 and GRAIL Data Analysis Suggesting Lava Tubes and Buried Craters on the Moon.” 2016. Doctoral Dissertation, Purdue University. Accessed January 24, 2021. https://docs.lib.purdue.edu/open_access_dissertations/1374.

MLA Handbook (7^th Edition):

Sood, Rohan. “Significance of Specific Force Models in Two Applications: Solar Sails to Sun-Earth L4/L5 and GRAIL Data Analysis Suggesting Lava Tubes and Buried Craters on the Moon.” 2016. Web. 24 Jan 2021.

Vancouver:

Sood R. Significance of Specific Force Models in Two Applications: Solar Sails to Sun-Earth L4/L5 and GRAIL Data Analysis Suggesting Lava Tubes and Buried Craters on the Moon. [Internet] [Doctoral dissertation]. Purdue University; 2016. [cited 2021 Jan 24]. Available from: https://docs.lib.purdue.edu/open_access_dissertations/1374.

Council of Science Editors:

Sood R. Significance of Specific Force Models in Two Applications: Solar Sails to Sun-Earth L4/L5 and GRAIL Data Analysis Suggesting Lava Tubes and Buried Craters on the Moon. [Doctoral Dissertation]. Purdue University; 2016. Available from: https://docs.lib.purdue.edu/open_access_dissertations/1374

16. Maria Cecilia Pereira de Faria. Dinâmica orbital e controle de orientação de um veículo espacial com uma vela solar composta.

Degree: 2009, Instituto Nacional de Pesquisas Espaciais

URL: http://urlib.net/sid.inpe.br/[email protected]/2009/06.17.20.21

►

Neste trabalho foi realizado um estudo das propriedades dinâmicas de um sistema propulsor que utiliza radiação solar. Foram desenvolvidos modelos de força e torque para… (more)

▼

Neste trabalho foi realizado um estudo das propriedades dinâmicas de um sistema propulsor que utiliza radiação solar. Foram desenvolvidos modelos de força e torque para dois esquemas de tais velas: velas solares compostas simples (SSPT) e velas solares compostas de dupla reflexão (DR SPT). O estudo deste tipo de estrutura foi feito a partir de uma revisão dos modelos propostos e de conceitos básicos, como pressão de radiação solar, equações de movimento orbital e de atitude, e controle. A partir destes conceitos, expressões para força e torques atuantes nas velas compostas foram deduzidas, considerando reflexões não ideais. O movimento de atitude de uma vela solar composta simples foi estudado, e a partir da suas equações, as condições de estabilidade foram avaliadas, assim como métodos para estabilizar o eixo de rolamento. Também é apresentando o controle de atitude de tal vela. Para considerar efeitos de reflexões múltiplas, sombra, desalinhamento em relação à condição nominal de operação e irregularidades na superfície da vela foram desenvolvidos modelos numéricos. Por este motivo, foram desenvolvidos modelos numéricos para as velas solares compostas, tanto simples como de dupla reflexão. As circunstâncias citadas foram avaliadas, sendo que não são particularmente prejudiciais ao funcionamento da vela composta simples. As velas solares compostas de dupla reflexão, no entanto, mostraram-se menos robustas quando operando em condições diferentes das nominais, o que dificulta ou até inviabiliza seu uso em missões. Foram realizadas simulações de missões para Marte e Vênus a fim de comparar os desempenhos das velas solares compostas simples com resultados obtidos com a vela plana. Resultados mostram que para a maior parte das geometrias da SSPT, esta configuração é mais eficiente do que uma vela solar plana. Ainda, seu controle demanda menos recursos por não precisar gerar toda a estrutura da vela.

A study of dynamical properties of a propulsion system using solar radiation was carried out in the present work. Models of force and momentum were developed for two schemes of such sailcraft: simple solar photon thruster (SSPT) and dual reflection solar photon thruster (DR SPT). The study of such structure was developed by reviewing previously presented models and basic concepts, such as solar radiation pressure, orbital and attitude dynamics and control. Starting from these concepts, expressions for force and torques were derived, considering both ideal and non ideal reflections. Attitude dynamics of a simple solar photon thruster was studied, and, using its equations, stability conditions were analised, and so were methods for stabilizing roll axis. The attitude control of such sailcraft is also presented here. In order to consider effects such as multiple reflections, shadowing, misalignment from nominal position and irregularities on the shape of sail collector, numerical models were developed for both SSPT and DR SPT. Such circunstances were analised, and it was shown that they are not that harmful for SSPT…

Advisors/Committee Members: Valdemir Carrara, Hans-Ulrich Pilchowski, Anna D. Guerman, Carlos Renato Solorzano, Gueorgui Smirnov, Maria Cecília França de Paula Zanardi.

Subjects/Keywords: vela solar; dinâmica orbital; atitude; controle; baixo empuxo; solar sail; orbital dynamics; attitude; control; low thrust

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APA (6^th Edition):

Faria, M. C. P. d. (2009). Dinâmica orbital e controle de orientação de um veículo espacial com uma vela solar composta. (Thesis). Instituto Nacional de Pesquisas Espaciais. Retrieved from http://urlib.net/sid.inpe.br/[email protected]/2009/06.17.20.21

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Faria, Maria Cecilia Pereira de. “Dinâmica orbital e controle de orientação de um veículo espacial com uma vela solar composta.” 2009. Thesis, Instituto Nacional de Pesquisas Espaciais. Accessed January 24, 2021. http://urlib.net/sid.inpe.br/[email protected]/2009/06.17.20.21.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Faria, Maria Cecilia Pereira de. “Dinâmica orbital e controle de orientação de um veículo espacial com uma vela solar composta.” 2009. Web. 24 Jan 2021.

Vancouver:

Faria MCPd. Dinâmica orbital e controle de orientação de um veículo espacial com uma vela solar composta. [Internet] [Thesis]. Instituto Nacional de Pesquisas Espaciais; 2009. [cited 2021 Jan 24]. Available from: http://urlib.net/sid.inpe.br/[email protected]/2009/06.17.20.21.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Faria MCPd. Dinâmica orbital e controle de orientação de um veículo espacial com uma vela solar composta. [Thesis]. Instituto Nacional de Pesquisas Espaciais; 2009. Available from: http://urlib.net/sid.inpe.br/[email protected]/2009/06.17.20.21

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Penn State University

17. Davis, Elizabeth. SOLAR SAIL TRAJECTORY OPTIMIZATION USING COLLOCATION AND NSGA II.

Degree: 2008, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/8407

► Solar sail spacecraft rely solely on solar radiation pressure for propulsion. Since the acceleration received by radiation pressure increases as the spacecraft nears the Sun,… (more)

Subjects/Keywords: solar sail; collocation; evolutionary algorithm; trajectory optimization; NAGA II

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APA (6^th Edition):

Davis, E. (2008). SOLAR SAIL TRAJECTORY OPTIMIZATION USING COLLOCATION AND NSGA II. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/8407

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Davis, Elizabeth. “SOLAR SAIL TRAJECTORY OPTIMIZATION USING COLLOCATION AND NSGA II.” 2008. Thesis, Penn State University. Accessed January 24, 2021. https://submit-etda.libraries.psu.edu/catalog/8407.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Davis, Elizabeth. “SOLAR SAIL TRAJECTORY OPTIMIZATION USING COLLOCATION AND NSGA II.” 2008. Web. 24 Jan 2021.

Vancouver:

Davis E. SOLAR SAIL TRAJECTORY OPTIMIZATION USING COLLOCATION AND NSGA II. [Internet] [Thesis]. Penn State University; 2008. [cited 2021 Jan 24]. Available from: https://submit-etda.libraries.psu.edu/catalog/8407.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Davis E. SOLAR SAIL TRAJECTORY OPTIMIZATION USING COLLOCATION AND NSGA II. [Thesis]. Penn State University; 2008. Available from: https://submit-etda.libraries.psu.edu/catalog/8407

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Colorado

18. Rizvi, Farheen. Solar Sail Attitude Dynamics and Coning Control: On Developing Control Methods for Solar Sail Coning at Orbit Rate to Attain Desired Orbital Effects.

Degree: MS, Aerospace Engineering Sciences, 2010, University of Colorado

URL: https://scholar.colorado.edu/asen_gradetds/8

► In this thesis, a control method is developed for the solar sail normal vector to trace a desired circular coning trajectory at orbit rate.… (more)

▼ In this thesis, a control method is developed for the solar sail normal vector to trace a desired circular coning trajectory at orbit rate. The coning trajectory is defined in the local vertical local horizontal (LVLH) frame and the coning occurs about an LVLH equilibrium sail attitude. Past research has shown that sail attitude equilibria exist in the LVLH frame under the influence of aerodynamic, gravity gradient and solar torques. Precession of the sail normal from these equilibria causes sail normal coning about that equilibrium attitude. If the coning happens at orbit rate, wide variety of orbital effects can be induced with minimum excitation of the sailcraft structure. This results in an inexpensive spacecraft with a longer duration mission as compared to other conventional efforts. A special case of analyzing circular cones (at orbit rate coning) revealed that new Sun-synchronous orbits were created and launch injection errors were overcome by employing the sail coning method. The control method herein minimizes the angular momentum error between the sail and desired angular momentum vectors at orbit rate. Since angular momentum is a function of sail normal, angular momentum error reduction raises hope in reducing the sail normal error between the sail normal and desired sail normal vector as well. The results show that even though the control method enables the sail angular momentum to track the desired angular momentum on the coning trajectory, the sail normal tracing can only occur about certain LVLH equilibrium points, for small cones and small initial condition angular position/velocity errors. The control method is robust for tracking the desired angular momentum at orbit rate, but not always for tracking the desired sail normal. The case where the sail normal does track the desired at orbit rate corresponds to tracing a 1° circular cone about an orbit lowering LVLH equilibrium point. Even though the control torques are on the order of 10-6 Nm (acceptable on small sailcraft) for both a spinning and non-spinning sail, a spinning sail (spun at a specific rate) requires less control torque (4 times lower than a non-spinning sail) to yield the desired orbit rate circular coning. The control torques can be applied to the sailcraft to enable orbit rate cone tracing of the sail normal and yield the desired orbital effects. Advisors/Committee Members: Dale A Lawrence, Hanspeter Schaub, Eric Frew.

Subjects/Keywords: attitude dynamics and control; coning control; control methods; Solar sail; Aerospace Engineering; Navigation, Guidance, Control and Dynamics; Space Vehicles

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APA (6^th Edition):

Rizvi, F. (2010). Solar Sail Attitude Dynamics and Coning Control: On Developing Control Methods for Solar Sail Coning at Orbit Rate to Attain Desired Orbital Effects. (Masters Thesis). University of Colorado. Retrieved from https://scholar.colorado.edu/asen_gradetds/8

Chicago Manual of Style (16^th Edition):

Rizvi, Farheen. “Solar Sail Attitude Dynamics and Coning Control: On Developing Control Methods for Solar Sail Coning at Orbit Rate to Attain Desired Orbital Effects.” 2010. Masters Thesis, University of Colorado. Accessed January 24, 2021. https://scholar.colorado.edu/asen_gradetds/8.

MLA Handbook (7^th Edition):

Rizvi, Farheen. “Solar Sail Attitude Dynamics and Coning Control: On Developing Control Methods for Solar Sail Coning at Orbit Rate to Attain Desired Orbital Effects.” 2010. Web. 24 Jan 2021.

Vancouver:

Rizvi F. Solar Sail Attitude Dynamics and Coning Control: On Developing Control Methods for Solar Sail Coning at Orbit Rate to Attain Desired Orbital Effects. [Internet] [Masters thesis]. University of Colorado; 2010. [cited 2021 Jan 24]. Available from: https://scholar.colorado.edu/asen_gradetds/8.

Council of Science Editors:

Rizvi F. Solar Sail Attitude Dynamics and Coning Control: On Developing Control Methods for Solar Sail Coning at Orbit Rate to Attain Desired Orbital Effects. [Masters Thesis]. University of Colorado; 2010. Available from: https://scholar.colorado.edu/asen_gradetds/8

Delft University of Technology

19. Duran Ventas, Javier (author). Solar Sail Periodic Orbits using Taylor Series Integration: Computation and applications of solar sail periodic orbit families in the Earth-Moon and binary asteroid systems.

Degree: 2017, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:ada9b18c-c006-481a-bc31-b8551c2afd99

►

Solar sailing is an innovative space propulsion system based solely on the exchange of momentum between a reflective surface and the photons radiated as light… (more)

Subjects/Keywords: Solar Sail; Orbit; Taylor Series Integration; TSI; Periodic Orbits; Earth-Moon; Binary asteroids; Differential correction; Multiple shooting

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APA (6^th Edition):

Duran Ventas, J. (. (2017). Solar Sail Periodic Orbits using Taylor Series Integration: Computation and applications of solar sail periodic orbit families in the Earth-Moon and binary asteroid systems. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:ada9b18c-c006-481a-bc31-b8551c2afd99

Chicago Manual of Style (16^th Edition):

Duran Ventas, Javier (author). “Solar Sail Periodic Orbits using Taylor Series Integration: Computation and applications of solar sail periodic orbit families in the Earth-Moon and binary asteroid systems.” 2017. Masters Thesis, Delft University of Technology. Accessed January 24, 2021. http://resolver.tudelft.nl/uuid:ada9b18c-c006-481a-bc31-b8551c2afd99.

MLA Handbook (7^th Edition):

Duran Ventas, Javier (author). “Solar Sail Periodic Orbits using Taylor Series Integration: Computation and applications of solar sail periodic orbit families in the Earth-Moon and binary asteroid systems.” 2017. Web. 24 Jan 2021.

Vancouver:

Duran Ventas J(. Solar Sail Periodic Orbits using Taylor Series Integration: Computation and applications of solar sail periodic orbit families in the Earth-Moon and binary asteroid systems. [Internet] [Masters thesis]. Delft University of Technology; 2017. [cited 2021 Jan 24]. Available from: http://resolver.tudelft.nl/uuid:ada9b18c-c006-481a-bc31-b8551c2afd99.

Council of Science Editors:

Duran Ventas J(. Solar Sail Periodic Orbits using Taylor Series Integration: Computation and applications of solar sail periodic orbit families in the Earth-Moon and binary asteroid systems. [Masters Thesis]. Delft University of Technology; 2017. Available from: http://resolver.tudelft.nl/uuid:ada9b18c-c006-481a-bc31-b8551c2afd99

University of Maryland

20. Ma, Dakang. Measurement of radiation pressure and tailored momentum transfer through switchable photonic devices.

Degree: Electrical Engineering, 2016, University of Maryland

URL: http://hdl.handle.net/1903/19291

► Light carries momentum, which can be transferred to an object upon reflection or absorption. The resulting force per unit area from light, so called radiation… (more)

▼ Light carries momentum, which can be transferred to an object upon reflection or absorption. The resulting force per unit area from light, so called radiation pressure, is rather weak but can have macroscopic consequences. For example, sunlight imparts momentum on dust particles causing a comet's tail to be directed away from the sun. In a microscopic world, micro/nano-mechanical transducers have become sensitive enough that radiation pressure can influence them greatly. However, photothermal effects often accompany and overwhelm the radiation pressure, complicating its measurement. In this thesis, we first show a quantitative measurement of the radiation force on an uncoated silicon nitride microcantilever in an ambient condition. We identify and separate the radiation pressure and photothermal effects through an analysis of the cantilever's frequency response. Further, we demonstrate the first measurement of a wavelength-dependent radiation pressure due to optical interference in a silicon microcantilever. We utilize an in-situ optical transmission measurement at the excitation position to determine the local optical properties. Another interesting application of radiation pressure is a solar sail. Solar sails use solar radiation pressure for propulsion and offer an opportunity for propellant-free space travel, enabling long-term and long-distance missions that are impossible with traditional methods. Although solar sail propulsion alleviates the need to carry chemical fuel, attitude control and steering are still performed using traditional methods involving reaction wheels and propellant ejection. In the second part of the thesis, we present a steerable solar sail concept based on a polymer dispersed liquid crystal (PDLC) device that switches between transparent and scattering states, enabling attitude control without mechanically moving parts or chemical propellant. Devices are fabricated and characterized (transmission, reflection, absorption and scattering) over the visible and near infrared range of the solar spectrum (400 nm - 1100 nm) and are found to outperform previous designs by more than a factor of four in terms of over-all weighted momentum switchablility between on and off states. Devices require no power in the diffusely reflective state and dissipate less than 0.5 mW/cm² while in the on state, showing great potential as a low-power switching mechanism for solar sail attitude control. Advisors/Committee Members: Munday, Jeremy N (advisor).

Subjects/Keywords: Optics; Physics; Electromagnetics; microcantilever; photon momentum; polymer dispersed liquid crystal; radiation pressure; solar sail; switchable material

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Ma, D. (2016). Measurement of radiation pressure and tailored momentum transfer through switchable photonic devices. (Thesis). University of Maryland. Retrieved from http://hdl.handle.net/1903/19291

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Ma, Dakang. “Measurement of radiation pressure and tailored momentum transfer through switchable photonic devices.” 2016. Thesis, University of Maryland. Accessed January 24, 2021. http://hdl.handle.net/1903/19291.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Ma, Dakang. “Measurement of radiation pressure and tailored momentum transfer through switchable photonic devices.” 2016. Web. 24 Jan 2021.

Vancouver:

Ma D. Measurement of radiation pressure and tailored momentum transfer through switchable photonic devices. [Internet] [Thesis]. University of Maryland; 2016. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/1903/19291.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Ma D. Measurement of radiation pressure and tailored momentum transfer through switchable photonic devices. [Thesis]. University of Maryland; 2016. Available from: http://hdl.handle.net/1903/19291

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

The Ohio State University

21. Gero, Ryan Micah. Low-Impact and Damped State Feedback Control of a Solar Sail on an Optimal Non-Keplerian Planet-Centered Orbit.

Degree: MS, Aeronautical and Astronautical Engineering, 2009, The Ohio State University

URL: http://rave.ohiolink.edu/etdc/view?acc_num=osu1243426802

► Consider the most fundamental difference between a solar sail and conventional spacecraft: propellant. In order to effect propulsion, solar sails receive a constant supply… (more)

▼ Consider the most fundamental difference between a solar sail and conventional spacecraft: propellant. In order to effect propulsion, solar sails receive a constant supply of massless photons to reflect while conventional spacecraft must carry a limited supply of fuel. At first glance, solar sails are infinitely more efficient than conventional spacecraft simply because of this fact. However, while certainly an advantage to solar sailing, propellant consumption is not the proper metric for spacecraft comparison or the only appealing facet of the solar sail. It can be shown by a reasonable and straightforward analysis that solar sails have the potential to out-perform conventional spacecraft on the basis of effective specific impulse, a parameter that incorporates launch and payload masses as well as total mission duration via an adaptation of the illustrious rocket equation. Pair an aggressive specific impulse with the orbital possibilities that arise when solar sail performance is at a level capable of producing spacecraft accelerations the same order of magnitude as local solar or planetary gravitational acceleration, and the engineer finds significantly fewer constraints limiting the design of future space missions. Imagine a spacecraft for which a Lagrange equilibrium point becomes a large surface, rather than a singular location, on which it is able to remain at rest. Picture a space vehicle hovering high above an ecliptic plane or perhaps racing along some other non-Keplerian orbit taking measurements and relaying signals from positions previously untenable. Solar sails can do all of these things, and it is the intent of this body of work to generate a proof of concept for one of the most attainable and pertinent capabilities unique to solar sails mentioned thus far. In the pages that follow it will be shown that a solar sail is inherently stable for some of the optimal non-Keplerian family of planet-centered orbits, and can be stabilized by straightforward control schemes for the rest. Beginning from scratch with a radiation pressure model, gain parameters were developed for low-impact and damped state feedback control via sail pitch attitude variation. Optimal orbits are attainable, as these trajectories were designed to minimize the required spacecraft acceleration and thus lower the solar sail performance requirement. Planet-centered orbits are pertinent, since a solar sail must inevitably begin its journey by escaping from the planet Earth and most of NASA’s recent efforts in space are geared towards the exploration of nearby planets and their moons. Uniqueness stems from the specification of the non-Keplerian family of orbits, since solar sails are capable of sustaining them whereas modern conventional spacecraft are not. In today’s day and age, with payload miniaturization and the ability to manufacture extremely light weight reflective materials, solar sailing has the potential to become reality within the next five to ten years. The concepts highlighted in this thesis have a significant… Advisors/Committee Members: Freuler, Richard (Advisor).

Subjects/Keywords: Astrophysics; Engineering; solar sail; optimal non-Keplerian planet-centered orbit; solar sail control; damped state feedback control; astrophysics

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Gero, R. M. (2009). Low-Impact and Damped State Feedback Control of a Solar Sail on an Optimal Non-Keplerian Planet-Centered Orbit. (Masters Thesis). The Ohio State University. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=osu1243426802

Chicago Manual of Style (16^th Edition):

Gero, Ryan Micah. “Low-Impact and Damped State Feedback Control of a Solar Sail on an Optimal Non-Keplerian Planet-Centered Orbit.” 2009. Masters Thesis, The Ohio State University. Accessed January 24, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=osu1243426802.

MLA Handbook (7^th Edition):

Gero, Ryan Micah. “Low-Impact and Damped State Feedback Control of a Solar Sail on an Optimal Non-Keplerian Planet-Centered Orbit.” 2009. Web. 24 Jan 2021.

Vancouver:

Gero RM. Low-Impact and Damped State Feedback Control of a Solar Sail on an Optimal Non-Keplerian Planet-Centered Orbit. [Internet] [Masters thesis]. The Ohio State University; 2009. [cited 2021 Jan 24]. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1243426802.

Council of Science Editors:

Gero RM. Low-Impact and Damped State Feedback Control of a Solar Sail on an Optimal Non-Keplerian Planet-Centered Orbit. [Masters Thesis]. The Ohio State University; 2009. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1243426802

York University

22. Li, Gangqiang. Multibody Dynamics and Control of Tethered Spacecraft Systems.

Degree: PhD, Earth & Space Science, 2019, York University

URL: https://yorkspace.library.yorku.ca/xmlui/handle/10315/36739

► This doctoral research conducts high-fidelity multiphysics modeling for tethered spacecraft systems, such as electrodynamic tether systems, electric solar wind sail systems, and tether transportation systems… (more)

▼ This doctoral research conducts high-fidelity multiphysics modeling for tethered spacecraft systems, such as electrodynamic tether systems, electric solar wind sail systems, and tether transportation systems with climbers. Two models are developed based on nodal position finite element method. The first model deals with the tethered spacecraft system with fixed length tether, while the second model deals with the tethered spacecraft system with variable tether length using an arbitrary Lagrangian-Eulerian description. First, the nodal position finite element method is applied to model the orbital motion of tethered spacecraft systems with fixed tether length over a prolonged period. A Symplectic integration scheme is employed to attenuate the accumulation of error in the numerical analysis due to the long-term integration for tethered spacecraft systems, such as the space debris deorbit by electrodynamic tethers. A high fidelity multiphysics model is developed for electrodynamic tether systems by considering elastic, thermal, and electrical coupling effects of the tether. Most importantly, the calculation of electron collection by the electrodynamic tether is coupled with the tether libration and flexible deformation, where the orbital motion limited theory for electron collection is discretized simultaneously by the same finite element mesh used for the elastodynamic analysis of tether. The model is then used to investigate dynamics and libration stability of bare electrodynamic tethers in deorbiting end-of-mission spacecraft. Second, the model of tethered spacecraft system with fixed tether length is extended for the modeling of electric solar wind sail systems. The coupling effect of orbital and self-spinning motions of electric solar wind sail systems is investigated together with the interaction between the axial/transverse elastic motion of tether and Coulomb force. A modified throttling control algorithm is implemented in the finite element scheme to control the attitude motion of electric solar wind sail systems through the electric voltage modulation of main tethers. Third, the model of tethered spacecraft with variable tether length is applied to handle the tether length variation in tether transportation systems. The tether length variation results from the climber moving along tether and deployment and retrieval of tether at end spacecraft. The dynamic behavior of tether transportation systems with single or multiple climbers in characterized and the effectiveness of libration suppression scheme is tested by the high-fidelity model. Advisors/Committee Members: Zhu, George Z. H. (advisor).

Subjects/Keywords: Computer engineering; Finite element method; Tethered spacecraft systems; Control; Dynamics; Electric solar wind sail; Tether transportation system; Partial space elevator; Space elevator; Electrodynamic tether systems

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Li, G. (2019). Multibody Dynamics and Control of Tethered Spacecraft Systems. (Doctoral Dissertation). York University. Retrieved from https://yorkspace.library.yorku.ca/xmlui/handle/10315/36739

Chicago Manual of Style (16^th Edition):

Li, Gangqiang. “Multibody Dynamics and Control of Tethered Spacecraft Systems.” 2019. Doctoral Dissertation, York University. Accessed January 24, 2021. https://yorkspace.library.yorku.ca/xmlui/handle/10315/36739.

MLA Handbook (7^th Edition):

Li, Gangqiang. “Multibody Dynamics and Control of Tethered Spacecraft Systems.” 2019. Web. 24 Jan 2021.

Vancouver:

Li G. Multibody Dynamics and Control of Tethered Spacecraft Systems. [Internet] [Doctoral dissertation]. York University; 2019. [cited 2021 Jan 24]. Available from: https://yorkspace.library.yorku.ca/xmlui/handle/10315/36739.

Council of Science Editors:

Li G. Multibody Dynamics and Control of Tethered Spacecraft Systems. [Doctoral Dissertation]. York University; 2019. Available from: https://yorkspace.library.yorku.ca/xmlui/handle/10315/36739

23. Hoshi, Kento. Study on Active Spacecraft Charging Model and its Application to Space Propulsion Systeｍ .

Degree: 2018, Kyoto University

URL: http://hdl.handle.net/2433/232002

Subjects/Keywords: Spacecraft Charging; Space Propulsion; Plasma Simulation; Particle-in-cell; Electric Solar Wind Sail

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Hoshi, K. (2018). Study on Active Spacecraft Charging Model and its Application to Space Propulsion Systeｍ . (Thesis). Kyoto University. Retrieved from http://hdl.handle.net/2433/232002

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Hoshi, Kento. “Study on Active Spacecraft Charging Model and its Application to Space Propulsion Systeｍ .” 2018. Thesis, Kyoto University. Accessed January 24, 2021. http://hdl.handle.net/2433/232002.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Hoshi, Kento. “Study on Active Spacecraft Charging Model and its Application to Space Propulsion Systeｍ .” 2018. Web. 24 Jan 2021.

Vancouver:

Hoshi K. Study on Active Spacecraft Charging Model and its Application to Space Propulsion Systeｍ . [Internet] [Thesis]. Kyoto University; 2018. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/2433/232002.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Hoshi K. Study on Active Spacecraft Charging Model and its Application to Space Propulsion Systeｍ . [Thesis]. Kyoto University; 2018. Available from: http://hdl.handle.net/2433/232002

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Manchester

24. Wu, Rui. Self-Regulated Centrifugal Deployment of Passive Space Structures.

Degree: 2018, University of Manchester

URL: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:316946

► Large lightweight compliant structures can be spin deployed, utilising centrifugal forces to achieve a compression-free stress distribution. The present research starts from the idea that… (more)

▼ Large lightweight compliant structures can be spin deployed, utilising centrifugal forces to achieve a compression-free stress distribution. The present research starts from the idea that self-regulating passive centrifugal deployment can be achieved when the spinning motion is driven by an environmental torque that is coupled to the deployment condition. In this thesis, the idea is applied to a deployable atmospheric entry heat shield and a heliogyro-type solar sail. The heat shield is based on a flexible fabric shell that induces aerodynamic roll-torque during descent and thus deploys by autorotating. Deployment leads to shape morphing that varies the aerodynamic roll-torque. Passive self-regulated deployment is thereby achieved as the rate of autorotation is determined by the shape, or in other words the deployment condition of the aeroshell. Active deployment modulation using conventional attitude control devices is also proposed, which can provide structural oscillation suppression as well as downrange manoeuvring of over 300 km during simulated re-entry from LEO for vehicles with 3 kg - 5 ton entry mass. Flight characteristics and structural dynamic behaviours are investigated using analytical analyses and numerical simulations. Low-fidelity experiments including low-speed drop test and wind tunnel test are carried out to verify the simulator and validate the design. Owing to its unique operating principle, the design has shown various advantages over existing solutions including inflatable and mechanically deployable systems. Based on the similar principle, the study also proposes a heliogyro that spins up under a torque generated from a meta-structure reflector and thereby deploys centrifugally. The magnitude of the spin-up torque depends on centrifugal-stress and thus realises self-regulated spin and deployment. Meanwhile, the reflector is based on a self-folding origami that can automatically fold up when exposed to sunlight and thus allows fully passive operation. Critical functions of the meta-structure and the heliogyro are proven by numerical simulations, while the self-folding material is validated through laboratory tests. This concept enables a concise system that prevents the structural dynamic issues faced by existing heliogyro designs, and also provides a practical method to realise multi-functional gossamer structures. In conclusion, the study has shown that self-regulated centrifugal deployment could enable new types of deployable space systems that benefit from being lightweight, compact, scalable, concise and robust. Advisors/Committee Members: DIVER, CARL C, SOUTIS, CONSTANTINOS C, Roberts, Peter, Diver, Carl, Soutis, Constantinos.

Subjects/Keywords: deployable space structure; morphing; self regulation; intelligent system; smart material; self folding; aerodynamic decelerator; heat shield; solar sail; gossamer structure; downrange manoeuvre

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Wu, R. (2018). Self-Regulated Centrifugal Deployment of Passive Space Structures. (Doctoral Dissertation). University of Manchester. Retrieved from http://www.manchester.ac.uk/escholar/uk-ac-man-scw:316946

Chicago Manual of Style (16^th Edition):

Wu, Rui. “Self-Regulated Centrifugal Deployment of Passive Space Structures.” 2018. Doctoral Dissertation, University of Manchester. Accessed January 24, 2021. http://www.manchester.ac.uk/escholar/uk-ac-man-scw:316946.

MLA Handbook (7^th Edition):

Wu, Rui. “Self-Regulated Centrifugal Deployment of Passive Space Structures.” 2018. Web. 24 Jan 2021.

Vancouver:

Wu R. Self-Regulated Centrifugal Deployment of Passive Space Structures. [Internet] [Doctoral dissertation]. University of Manchester; 2018. [cited 2021 Jan 24]. Available from: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:316946.

Council of Science Editors:

Wu R. Self-Regulated Centrifugal Deployment of Passive Space Structures. [Doctoral Dissertation]. University of Manchester; 2018. Available from: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:316946

25. Yamaguchi, Kouhei. On Asteroid Deflection Techniques Exploiting Space Plasma Environment : 宇宙プラズマ環境を利用した小惑星の軌道変更手法に関する研究.

Degree: 博士(工学), 2017, Kyoto University / 京都大学

URL: http://hdl.handle.net/2433/225600 ; http://dx.doi.org/10.14989/doctor.k20375

新制・課程博士

甲第20375号

工博第4312号

Subjects/Keywords: Asteroid deflection missions; Electric solar wind sail; Coulomb force attractor; Spacecraft charging; Kinetic impactor

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Yamaguchi, K. (2017). On Asteroid Deflection Techniques Exploiting Space Plasma Environment : 宇宙プラズマ環境を利用した小惑星の軌道変更手法に関する研究. (Thesis). Kyoto University / 京都大学. Retrieved from http://hdl.handle.net/2433/225600 ; http://dx.doi.org/10.14989/doctor.k20375

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Yamaguchi, Kouhei. “On Asteroid Deflection Techniques Exploiting Space Plasma Environment : 宇宙プラズマ環境を利用した小惑星の軌道変更手法に関する研究.” 2017. Thesis, Kyoto University / 京都大学. Accessed January 24, 2021. http://hdl.handle.net/2433/225600 ; http://dx.doi.org/10.14989/doctor.k20375.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Yamaguchi, Kouhei. “On Asteroid Deflection Techniques Exploiting Space Plasma Environment : 宇宙プラズマ環境を利用した小惑星の軌道変更手法に関する研究.” 2017. Web. 24 Jan 2021.

Vancouver:

Yamaguchi K. On Asteroid Deflection Techniques Exploiting Space Plasma Environment : 宇宙プラズマ環境を利用した小惑星の軌道変更手法に関する研究. [Internet] [Thesis]. Kyoto University / 京都大学; 2017. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/2433/225600 ; http://dx.doi.org/10.14989/doctor.k20375.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Yamaguchi K. On Asteroid Deflection Techniques Exploiting Space Plasma Environment : 宇宙プラズマ環境を利用した小惑星の軌道変更手法に関する研究. [Thesis]. Kyoto University / 京都大学; 2017. Available from: http://hdl.handle.net/2433/225600 ; http://dx.doi.org/10.14989/doctor.k20375

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

26. Yamaguchi, Kouhei. On Asteroid Deflection Techniques Exploiting Space Plasma Environment .

Degree: 2017, Kyoto University

URL: http://hdl.handle.net/2433/225600

Subjects/Keywords: Asteroid deflection missions; Electric solar wind sail; Coulomb force attractor; Spacecraft charging; Kinetic impactor

Record Details Similar Records Cite « Share

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Yamaguchi, K. (2017). On Asteroid Deflection Techniques Exploiting Space Plasma Environment . (Thesis). Kyoto University. Retrieved from http://hdl.handle.net/2433/225600

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Yamaguchi, Kouhei. “On Asteroid Deflection Techniques Exploiting Space Plasma Environment .” 2017. Thesis, Kyoto University. Accessed January 24, 2021. http://hdl.handle.net/2433/225600.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Yamaguchi, Kouhei. “On Asteroid Deflection Techniques Exploiting Space Plasma Environment .” 2017. Web. 24 Jan 2021.

Vancouver:

Yamaguchi K. On Asteroid Deflection Techniques Exploiting Space Plasma Environment . [Internet] [Thesis]. Kyoto University; 2017. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/2433/225600.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Yamaguchi K. On Asteroid Deflection Techniques Exploiting Space Plasma Environment . [Thesis]. Kyoto University; 2017. Available from: http://hdl.handle.net/2433/225600

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

27. Ramon, Roger Gutierrez. Model for Touchdown Dynamics of a Lander on the Solar Power Sail Mission.

Degree: Electrical and Space Engineering, 2016, Luleå University of Technology

URL: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-60501

► The ISAS/JAXA Solar Power Sail mission, bound to explore the Jupiter trojans, will face many challenges during its journey. The landing manoeuvre is one… (more)

Subjects/Keywords: ISAS; JAXA; Lander; Solar Sail; Touchdown Dynamics; Jupiter trojans; Aerospace Engineering; Rymd- och flygteknik

…solar sail of the IKAROS spacecraft seen from one of the deployable cameras. Mission sequence… …IKAROS solar sail (front right) and the new solar sail (back)… …Point of departure parameters for the Solar Power Sail lander… …SRP Smart Lander for Investigation Moon Solar Power Sail Solar Radiation Pressure VLBI… …successful interplanetary Solar Power Sail (SPS) technology demonstration in the world…

11 more images…

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APA (6^th Edition):

Ramon, R. G. (2016). Model for Touchdown Dynamics of a Lander on the Solar Power Sail Mission. (Thesis). Luleå University of Technology. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-60501

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Ramon, Roger Gutierrez. “Model for Touchdown Dynamics of a Lander on the Solar Power Sail Mission.” 2016. Thesis, Luleå University of Technology. Accessed January 24, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-60501.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Ramon, Roger Gutierrez. “Model for Touchdown Dynamics of a Lander on the Solar Power Sail Mission.” 2016. Web. 24 Jan 2021.

Vancouver:

Ramon RG. Model for Touchdown Dynamics of a Lander on the Solar Power Sail Mission. [Internet] [Thesis]. Luleå University of Technology; 2016. [cited 2021 Jan 24]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-60501.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Ramon RG. Model for Touchdown Dynamics of a Lander on the Solar Power Sail Mission. [Thesis]. Luleå University of Technology; 2016. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-60501

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

28. Karwas, Alex A. An Unconditionally Stable Method for Numerically Solving Solar Sail Spacecraft Equations of Motion.

Degree: PhD, Aerospace Engineering, 2015, University of Kansas

URL: http://hdl.handle.net/1808/19374

► Solar sails use the endless supply of the Sun's radiation to propel spacecraft through space. The sails use the momentum transfer from the impinging solar… (more)

▼ Solar sails use the endless supply of the Sun's radiation to propel spacecraft through space. The sails use the momentum transfer from the impinging solar radiation to provide thrust to the spacecraft while expending zero fuel. Recently, the first solar sail spacecraft, or sailcraft, named IKAROS completed a successful mission to Venus and proved the concept of solar sail propulsion. Sailcraft experimental data is difficult to gather due to the large expenses of space travel, therefore, a reliable and accurate computational method is needed to make the process more efficient. Presented in this document is a new approach to simulating solar sail spacecraft trajectories. The new method provides unconditionally stable numerical solutions for trajectory propagation and includes an improved physical description over other methods. The unconditional stability of the new method means that a unique numerical solution is always determined. The improved physical description of the trajectory provides a numerical solution and time derivatives that are continuous throughout the entire trajectory. The error of the continuous numerical solution is also known for the entire trajectory. Optimal control for maximizing thrust is also provided within the framework of the new method. Verification of the new approach is presented through a mathematical description and through numerical simulations. The mathematical description provides details of the sailcraft equations of motion, the numerical method used to solve the equations, and the formulation for implementing the equations of motion into the numerical solver. Previous work in the field is summarized to show that the new approach can act as a replacement to previous trajectory propagation methods. A code was developed to perform the simulations and it is also described in this document. Results of the simulations are compared to the flight data from the IKAROS mission. Comparison of the two sets of data show that the new approach is capable of accurately simulating sailcraft motion. Sailcraft and spacecraft simulations are compared to flight data and to other numerical solution techniques. The new formulation shows an increase in accuracy over a widely used trajectory propagation technique. Simulations for two-dimensional, three-dimensional, and variable attitude trajectories are presented to show the multiple capabilities of the new technique. An element of optimal control is also part of the new technique. An additional equation is added to the sailcraft equations of motion that maximizes thrust in a specific direction. A technical description and results of an example optimization problem are presented. The spacecraft attitude dynamics equations take the simulation a step further by providing control torques using the angular rate and acceleration outputs of the numerical formulation. Advisors/Committee Members: Taghavi, Ray (advisor), Farokhi, Saeed (cmtemember), Keshmiri, Shawn (cmtemember), Zheng, Zhongquan Charlie (cmtemember), Yimer, Bedru (cmtemember).

Subjects/Keywords: Aerospace engineering; Finite Element Method; Propagation; Sailcraft; Solar Sail; Spacecraft; Trajectory

…10 Figure 1.5 Summary of Solar Sail Research… …research topic, which includes the motivation of the research, brief details of solar sail… …research and the purpose for conducting the research. 1.1.1 Motivation Solar sail spacecraft… …sailcraft EOM will help increase the success rate of solar sail missions. It will help by… …producing thrust and providing attitude control for the sailcraft. The next solar sail spacecraft…

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Karwas, A. A. (2015). An Unconditionally Stable Method for Numerically Solving Solar Sail Spacecraft Equations of Motion. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/19374

Chicago Manual of Style (16^th Edition):

Karwas, Alex A. “An Unconditionally Stable Method for Numerically Solving Solar Sail Spacecraft Equations of Motion.” 2015. Doctoral Dissertation, University of Kansas. Accessed January 24, 2021. http://hdl.handle.net/1808/19374.

MLA Handbook (7^th Edition):

Karwas, Alex A. “An Unconditionally Stable Method for Numerically Solving Solar Sail Spacecraft Equations of Motion.” 2015. Web. 24 Jan 2021.

Vancouver:

Karwas AA. An Unconditionally Stable Method for Numerically Solving Solar Sail Spacecraft Equations of Motion. [Internet] [Doctoral dissertation]. University of Kansas; 2015. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/1808/19374.

Council of Science Editors:

Karwas AA. An Unconditionally Stable Method for Numerically Solving Solar Sail Spacecraft Equations of Motion. [Doctoral Dissertation]. University of Kansas; 2015. Available from: http://hdl.handle.net/1808/19374

York University

29. Mungo, Mark Julian Adam. Emergence.

Degree: MFA - Master of Fine Arts, Film And Video, 2020, York University

URL: http://hdl.handle.net/10315/38005

► Emergence is a feature-length coming-of-age and science-fiction screenplay set between 2044 and 2059 in Canada and a settlement on Mars. The story follows Nate Ein,… (more)

Subjects/Keywords: Philosophy of science; Screenwriting; Screenplay; Script; Fiction; Science Fiction; Sci-fi; Coming of age; Coming-of-age; Emergence; Mosaic; Mosaicism; Mosaicist; Futurism; Futurist; Marxism; Marxist; Utopia; Utopian; Epistemology; Social Epistemology; Civilization; Capitalism; Imperialism; Corporate; Treeconomics; UN; Sanctum; Automation; Artificial Intelligence; AI; A.I.; Space Elevator; Solar Sail; 3d Printing; 3d Printers; Neural Interface; Brain Interface; Virtual Reality; Simulations; Global Command; Immortality; Collective; Collective Consciousness; Hive Mind; Group Mind; Decision-making; Themes; Spectrums; Contradictions; Power; Balance; Trust; Choice

Record Details Similar Records Cite « Share

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Mungo, M. J. A. (2020). Emergence. (Masters Thesis). York University. Retrieved from http://hdl.handle.net/10315/38005

Chicago Manual of Style (16^th Edition):

Mungo, Mark Julian Adam. “Emergence.” 2020. Masters Thesis, York University. Accessed January 24, 2021. http://hdl.handle.net/10315/38005.

MLA Handbook (7^th Edition):

Mungo, Mark Julian Adam. “Emergence.” 2020. Web. 24 Jan 2021.

Vancouver:

Mungo MJA. Emergence. [Internet] [Masters thesis]. York University; 2020. [cited 2021 Jan 24]. Available from: http://hdl.handle.net/10315/38005.

Council of Science Editors:

Mungo MJA. Emergence. [Masters Thesis]. York University; 2020. Available from: http://hdl.handle.net/10315/38005

Open Access Theses and Dissertations