subject:(rocket)

Kingston University

1. Karaveckas, Linas. Development of low-cost pressurisation system for rocket engines.

Degree: PhD, 2019, Kingston University

URL: http://eprints.kingston.ac.uk/id/eprint/43962/ ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.789357

► Increasing demand for low-cost satellites requires new affordable launch vehicles. Rocket turbopump systems are deemed to be one of the most complex and expensive components… (more)

▼ Increasing demand for low-cost satellites requires new affordable launch vehicles. Rocket turbopump systems are deemed to be one of the most complex and expensive components of conventional rockets, thus cost reduction of these parts is essential to business success. The aim of this research was to evaluate existing rocket turbopumps and identify options for significant cost reductions. Alternative pressurisation options were also considered which could meet low-cost targets for a small satellite launch vehicle. Four pressurisation systems were identified which could meet the requirements for a low-cost launch vehicle were shortlisted for further studies. These were turbopumps, piston pumps, pressure-fed and pistonless pumps. A mass model was developed to estimate the Gross Lift off Mass (GLOM) of the launch vehicle and to carry out a mass sensitivity analysis. Based on these findings, the feasibility of the piston pump was explored for a low-cost launch vehicle. To test the concept and to evaluate the manufacturing techniques, two prototypes were built. The first demonstrator (Mark I) was used to evaluate the feasibility of the valves and to optimise performance. To avoid the complexities associated with cryogenic and oxidising liquids, the tests were carried out with water. Further trials were conducted on the Mark II to assess compatibility at cryogenic temperatures. The prototype has successfully demonstrated that selected components have functioned as intended at low temperatures. Through the process of development, it was determined that the piston pump is a very simple system - only a few parts require a high precision of manufacturing, such as the piston bore and piston. The project novelty and achievement are 1) Various modern pressurisation systems were critically evaluated and it was concluded that a piston pump could offer a low-cost alternative to the turbopump. 2) It was demonstrated that a piston pump could be used in a small launch vehicle, but further work is required to extend the validation. 3) Demonstrators were used to show which components and parts could be used with Liquid Oxygen in small launch vehicles.

Subjects/Keywords: rocket piston pump; rocket pressurisation systems; rocket turbopump; rocket reciprocating pump; low-cost rocket pump

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Karaveckas, L. (2019). Development of low-cost pressurisation system for rocket engines. (Doctoral Dissertation). Kingston University. Retrieved from http://eprints.kingston.ac.uk/id/eprint/43962/ ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.789357

Chicago Manual of Style (16^th Edition):

Karaveckas, Linas. “Development of low-cost pressurisation system for rocket engines.” 2019. Doctoral Dissertation, Kingston University. Accessed February 28, 2021. http://eprints.kingston.ac.uk/id/eprint/43962/ ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.789357.

MLA Handbook (7^th Edition):

Karaveckas, Linas. “Development of low-cost pressurisation system for rocket engines.” 2019. Web. 28 Feb 2021.

Vancouver:

Karaveckas L. Development of low-cost pressurisation system for rocket engines. [Internet] [Doctoral dissertation]. Kingston University; 2019. [cited 2021 Feb 28]. Available from: http://eprints.kingston.ac.uk/id/eprint/43962/ ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.789357.

Council of Science Editors:

Karaveckas L. Development of low-cost pressurisation system for rocket engines. [Doctoral Dissertation]. Kingston University; 2019. Available from: http://eprints.kingston.ac.uk/id/eprint/43962/ ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.789357

University of KwaZulu-Natal

2. Balmogim, Udil. Design and development of the Phoenix-1B hybrid rocket.

Degree: 2017, University of KwaZulu-Natal

URL: http://hdl.handle.net/10413/16062

► In August 2014, South Africa’s first university-based hybrid rocket, Phoenix-1A, was launched at the Overberg Test Range near Cape Agulhas. The vehicle suffered nozzle and… (more)

▼ In August 2014, South Africa’s first university-based hybrid rocket, Phoenix-1A, was launched at the Overberg Test Range near Cape Agulhas. The vehicle suffered nozzle and parachute failures during flight which, together with a reduced oxidiser load, reduced the nominal design apogee of 10 km to 2.5 km. The aim of this research was to improve on the design and performance of the prototype demonstrator and thereby develop a workhorse hybrid sounding rocket, named Phoenix-1B, to serve as a reliable platform for future hybrid rocket research at the University of KwaZulu-Natal (UKZN). Analysis of Phoenix-1A shortcomings served as the starting point for the new design, which utilises a paraffin wax and nitrous oxide propellant combination. The focus of this research was the propulsion system, with specific attention being paid to the nozzle and injector designs. In addition, an aerodynamic study was applied to the 1 m long ¾ parabolic nose cone and four tapered swept fins. Final design of the aluminium oxidiser tank and combustion chamber bulkheads incorporated finite element analyses to ensure an operational safety factor greater than 1.5. The oxidiser tank and combustion chamber assemblies were pressure tested to 80 and 60 bars respectively. A key output of the present work is an analysis of the effect of aluminium loading in the paraffin wax fuel grain, which indicated a potential rocket mass reduction of 23 kg when transitioning from a pure paraffin grain to one containing 40% aluminium by mass. The analysis also indicated that combustion temperature rises with aluminium loading, increasing from 3300 K for pure paraffin to 3600 K for 40% aluminised fuel. Consequently, an iterative transient thermo-structural analysis was conducted on the nozzle, resulting in an optimised design able to sustain the higher operating temperatures as well as mitigate the risk of failure as seen with Phoenix-1A. The final manufactured composite nozzle has a throat diameter of 32 mm, an expansion ratio of 6.38, and a length of 156 mm. The nozzle has a steel casing which provides structural support to the silica phenolic insulation and graphite throat insert. A two phase CFD analysis, coupled with analytical mass flow rate models, was used to configure the axial injector and reduce the potential for combustion instabilities associated with the nitrous oxide flow. The Phoenix-1B motor has a design thrust of 5 kN to propel the fully loaded vehicle, with a mass of 70 kg, a length of 4.3 m and a diameter of 164 mm, to an altitude of 16 km. Advisors/Committee Members: Brooks, Michael John. (advisor), Veale, Kirsty Lynn. (advisor), De La Beaujardiere, Jean-Francois Pitot. (advisor).

Subjects/Keywords: Rocket design.; Rocket engine.; Hybrid rocket.; Pheonix-1B hybrid rocket.; Hybrid propultasion system.

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Balmogim, U. (2017). Design and development of the Phoenix-1B hybrid rocket. (Thesis). University of KwaZulu-Natal. Retrieved from http://hdl.handle.net/10413/16062

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):

Balmogim, Udil. “Design and development of the Phoenix-1B hybrid rocket.” 2017. Thesis, University of KwaZulu-Natal. Accessed February 28, 2021. http://hdl.handle.net/10413/16062.

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

MLA Handbook (7^th Edition):

Balmogim, Udil. “Design and development of the Phoenix-1B hybrid rocket.” 2017. Web. 28 Feb 2021.

Vancouver:

Balmogim U. Design and development of the Phoenix-1B hybrid rocket. [Internet] [Thesis]. University of KwaZulu-Natal; 2017. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/10413/16062.

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

Council of Science Editors:

Balmogim U. Design and development of the Phoenix-1B hybrid rocket. [Thesis]. University of KwaZulu-Natal; 2017. Available from: http://hdl.handle.net/10413/16062

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

Ryerson University

3. Lu, Zhiliu. Comparison of cylindrical and non-cylindrical grain internal ballistic behavior of hybrid rocket engines and solid rocket motors.

Degree: 2017, Ryerson University

URL: https://digital.library.ryerson.ca/islandora/object/RULA%3A7274

► Hybrid rocket engines (HREs) are a chemical propulsion system that nominally combine the advantages of liquid-propellant rocket engines (LREs) and solid-propellant rocket motors (SRMs). HREs… (more)

▼ Hybrid rocket engines (HREs) are a chemical propulsion system that nominally combine the advantages of liquid-propellant rocket engines (LREs) and solid-propellant rocket motors (SRMs). HREs in some cases can have a higher specific impulse and better controllability than SRMs, and lower cost and engineering complexity than LREs. For HREs and SRMs, both kinds of rocket engine employ a solid fuel grain, and the chosen grain configuration is a crucial point of their design. Different grain configurations have different internal ballistic behavior, which in turn can deliver different engine performance. A cylindrical grain design is a very common design for SRMs and HREs. A non-cylindrical-grain is a more complex grain configuration (than cylindrical) that has been used in many SRMs, and is also a choice for some HREs. However, while an HRE and an SRM can employ the same fuel grain configuration, the resulting internal ballistic behavior would not be expected to be the same. Pressure-dependent burning tends to dominate in SRMs, while axial flow-dependent burning tends to dominate in HREs. To help demonstrate in a more direct manner the influence of the differing combustion processes on the same fuel grain configuration used by an HRE and SRM, a number of internal ballistic simulations are undertaken for the present study. For the reference SRM cases looked at, an internal ballistic simulation program that has the capability of predicting head-end pressure and thrust as a function of time into a simulated firing is utilized for the present investigation; for the corresponding HRE cases, a simulation program is used to simulate the burning and flow process of these engines. For the present investigation, the two simulation programs are used to simulate the internal ballistic performance of various HREs and SRMs employing comparable cylindrical and non-cylindrical fuel grain configurations. The predicted performance results, in terms of pressure and thrust, are consistent with expectations that one would have for both propulsion system types.

Subjects/Keywords: Rocket engines – Combustion – Mathematical models; Rocket engines – Thrust – Mathematical models; Ballistics; Rocket engines

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Lu, Z. (2017). Comparison of cylindrical and non-cylindrical grain internal ballistic behavior of hybrid rocket engines and solid rocket motors. (Thesis). Ryerson University. Retrieved from https://digital.library.ryerson.ca/islandora/object/RULA%3A7274

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):

Lu, Zhiliu. “Comparison of cylindrical and non-cylindrical grain internal ballistic behavior of hybrid rocket engines and solid rocket motors.” 2017. Thesis, Ryerson University. Accessed February 28, 2021. https://digital.library.ryerson.ca/islandora/object/RULA%3A7274.

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

MLA Handbook (7^th Edition):

Lu, Zhiliu. “Comparison of cylindrical and non-cylindrical grain internal ballistic behavior of hybrid rocket engines and solid rocket motors.” 2017. Web. 28 Feb 2021.

Vancouver:

Lu Z. Comparison of cylindrical and non-cylindrical grain internal ballistic behavior of hybrid rocket engines and solid rocket motors. [Internet] [Thesis]. Ryerson University; 2017. [cited 2021 Feb 28]. Available from: https://digital.library.ryerson.ca/islandora/object/RULA%3A7274.

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

Council of Science Editors:

Lu Z. Comparison of cylindrical and non-cylindrical grain internal ballistic behavior of hybrid rocket engines and solid rocket motors. [Thesis]. Ryerson University; 2017. Available from: https://digital.library.ryerson.ca/islandora/object/RULA%3A7274

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

Ryerson University

4. Velliaris, Alexander. Scale effects on hybrid rocket engine performance.

Degree: 2017, Ryerson University

URL: https://digital.library.ryerson.ca/islandora/object/RULA%3A6782

► In the current study, the effects of scaling up a hybrid rocket engine (HRE) in size has on its performance is investigated. A HRE design… (more)

Subjects/Keywords: Rocket engines – Thrust – Mathematical models; Rocket engines – Combustion – Mathematical models; Rocket engines – Propulsion systems; Rocket engines – Design and construction

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Velliaris, A. (2017). Scale effects on hybrid rocket engine performance. (Thesis). Ryerson University. Retrieved from https://digital.library.ryerson.ca/islandora/object/RULA%3A6782

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):

Velliaris, Alexander. “Scale effects on hybrid rocket engine performance.” 2017. Thesis, Ryerson University. Accessed February 28, 2021. https://digital.library.ryerson.ca/islandora/object/RULA%3A6782.

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

MLA Handbook (7^th Edition):

Velliaris, Alexander. “Scale effects on hybrid rocket engine performance.” 2017. Web. 28 Feb 2021.

Vancouver:

Velliaris A. Scale effects on hybrid rocket engine performance. [Internet] [Thesis]. Ryerson University; 2017. [cited 2021 Feb 28]. Available from: https://digital.library.ryerson.ca/islandora/object/RULA%3A6782.

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

Council of Science Editors:

Velliaris A. Scale effects on hybrid rocket engine performance. [Thesis]. Ryerson University; 2017. Available from: https://digital.library.ryerson.ca/islandora/object/RULA%3A6782

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

Mississippi State University

5. Patterson, William Ray. DEVELOPMENT OF A ROCKET MOTOR TEST SYSTEM AND A STUDY OF HYBRID ROCKET FUEL GRAINS.

Degree: MS, Aerospace Engineering, 2009, Mississippi State University

URL: http://sun.library.msstate.edu/ETD-db/theses/available/etd-07062009-120546/ ;

► A rocket test system was developed and fabricated for the purpose of testing hybrid rocket motors. The test system includes a rocket test stand, load… (more)

Subjects/Keywords: hybrid; rocket

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Patterson, W. R. (2009). DEVELOPMENT OF A ROCKET MOTOR TEST SYSTEM AND A STUDY OF HYBRID ROCKET FUEL GRAINS. (Masters Thesis). Mississippi State University. Retrieved from http://sun.library.msstate.edu/ETD-db/theses/available/etd-07062009-120546/ ;

Chicago Manual of Style (16^th Edition):

Patterson, William Ray. “DEVELOPMENT OF A ROCKET MOTOR TEST SYSTEM AND A STUDY OF HYBRID ROCKET FUEL GRAINS.” 2009. Masters Thesis, Mississippi State University. Accessed February 28, 2021. http://sun.library.msstate.edu/ETD-db/theses/available/etd-07062009-120546/ ;.

MLA Handbook (7^th Edition):

Patterson, William Ray. “DEVELOPMENT OF A ROCKET MOTOR TEST SYSTEM AND A STUDY OF HYBRID ROCKET FUEL GRAINS.” 2009. Web. 28 Feb 2021.

Vancouver:

Patterson WR. DEVELOPMENT OF A ROCKET MOTOR TEST SYSTEM AND A STUDY OF HYBRID ROCKET FUEL GRAINS. [Internet] [Masters thesis]. Mississippi State University; 2009. [cited 2021 Feb 28]. Available from: http://sun.library.msstate.edu/ETD-db/theses/available/etd-07062009-120546/ ;.

Council of Science Editors:

Patterson WR. DEVELOPMENT OF A ROCKET MOTOR TEST SYSTEM AND A STUDY OF HYBRID ROCKET FUEL GRAINS. [Masters Thesis]. Mississippi State University; 2009. Available from: http://sun.library.msstate.edu/ETD-db/theses/available/etd-07062009-120546/ ;

University of Kashmir

6. Arora, Amar Jit. Combustion studies on solid Rocket Propellants Phenol Formaldehyde composite Systems;.

Degree: 2014, University of Kashmir

URL: http://shodhganga.inflibnet.ac.in/handle/10603/23982

►

This thesis deals with the propellant chemistry has made an unprecedented progress in the last two decades The important topics in composite propellant research are… (more)

Subjects/Keywords: Rocket-Propellants; Phenol-Formaldehyde

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Arora, A. J. (2014). Combustion studies on solid Rocket Propellants Phenol Formaldehyde composite Systems;. (Thesis). University of Kashmir. Retrieved from http://shodhganga.inflibnet.ac.in/handle/10603/23982

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):

Arora, Amar Jit. “Combustion studies on solid Rocket Propellants Phenol Formaldehyde composite Systems;.” 2014. Thesis, University of Kashmir. Accessed February 28, 2021. http://shodhganga.inflibnet.ac.in/handle/10603/23982.

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

MLA Handbook (7^th Edition):

Arora, Amar Jit. “Combustion studies on solid Rocket Propellants Phenol Formaldehyde composite Systems;.” 2014. Web. 28 Feb 2021.

Vancouver:

Arora AJ. Combustion studies on solid Rocket Propellants Phenol Formaldehyde composite Systems;. [Internet] [Thesis]. University of Kashmir; 2014. [cited 2021 Feb 28]. Available from: http://shodhganga.inflibnet.ac.in/handle/10603/23982.

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

Council of Science Editors:

Arora AJ. Combustion studies on solid Rocket Propellants Phenol Formaldehyde composite Systems;. [Thesis]. University of Kashmir; 2014. Available from: http://shodhganga.inflibnet.ac.in/handle/10603/23982

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

Texas A&M University

7. Thomas, James C. Hybrid Rocket Burning Rate Enhancement by Nano-Scale Additives in HTPB Fuel Grains.

Degree: MS, Mechanical Engineering, 2014, Texas A&M University

URL: http://hdl.handle.net/1969.1/154244

► Low regression rates in hybrid rockets limit their use and capability, but additive aluminum nano-particles represent a possible solution to this problem. In this thesis,… (more)

Subjects/Keywords: Hybrid; Rocket; HTPB; Aluminum; Regression

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Thomas, J. C. (2014). Hybrid Rocket Burning Rate Enhancement by Nano-Scale Additives in HTPB Fuel Grains. (Masters Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/154244

Chicago Manual of Style (16^th Edition):

Thomas, James C. “Hybrid Rocket Burning Rate Enhancement by Nano-Scale Additives in HTPB Fuel Grains.” 2014. Masters Thesis, Texas A&M University. Accessed February 28, 2021. http://hdl.handle.net/1969.1/154244.

MLA Handbook (7^th Edition):

Thomas, James C. “Hybrid Rocket Burning Rate Enhancement by Nano-Scale Additives in HTPB Fuel Grains.” 2014. Web. 28 Feb 2021.

Vancouver:

Thomas JC. Hybrid Rocket Burning Rate Enhancement by Nano-Scale Additives in HTPB Fuel Grains. [Internet] [Masters thesis]. Texas A&M University; 2014. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/1969.1/154244.

Council of Science Editors:

Thomas JC. Hybrid Rocket Burning Rate Enhancement by Nano-Scale Additives in HTPB Fuel Grains. [Masters Thesis]. Texas A&M University; 2014. Available from: http://hdl.handle.net/1969.1/154244

Texas A&M University

8. Appel, Bradley. Multiphysics Design and Simulation of a Tungsten-Cermet Nuclear Thermal Rocket.

Degree: MS, Nuclear Engineering, 2012, Texas A&M University

URL: http://hdl.handle.net/1969.1/ETD-TAMU-2012-08-11649

► The goal of this research is to apply modern methods of analysis to the design of a tungsten-cermet Nuclear Thermal Rocket (NTR) core. An NTR… (more)

▼ The goal of this research is to apply modern methods of analysis to the design of a tungsten-cermet Nuclear Thermal Rocket (NTR) core. An NTR is one of the most viable propulsion options for enabling piloted deep-space exploration. Concerns over fuel safety have sparked interest in an NTR core based on tungsten-cermet fuel. This work investigates the capability of modern CFD and neutronics codes to design a cermet NTR, and makes specific recommendations for the configuration of channels in the core. First, the best CFD practices available from the commercial package Star-CCM+ are determined by comparing different modeling options with a hot-hydrogen flow experiment. Next, through grid convergence and sensitivity studies, numerical uncertainty is shown to be a small contributor to overall uncertainty; while fuel thermal conductivity, hydrogen specific heat, and fission energy deposition are found to have a large impact on simulation uncertainty. The model-form error is then estimated by simulation of a NERVA fuel element from an NRX-A6 engine test, where the peak temperature matches measured data to within 2.2%. Using a combination of Star-CCM+ and MCNP for neutronics, typical uncertainties are estimated at 3% for predicting fuel temperature, 2% for hydrogen temperature, and 5% for pressure. The second part uses the aforementioned analysis methods in a parametric study to determine what coolant channel size and distribution is optimum for a 10 klbf-thrust cermet NTR core. By varying the channel diameter and pitch-to-diameter ratio (p/d), it is found that a diameter of 0.12 cm with a p/d of 1.8 results in the lightest core with a peak temperature of 2850 K. The study also shows that element-by-element mass flow rate zoning is the best method for handling radial power peaking. In addition, a detailed simulation of a cermet design developed at the Argonne National Laboratory shows that modifications to the historical fuel element design are required to avoid overheating. The final part investigates the ability of Star-CCM+ to model fuel element failure modes. Through a combination of uncertainty quantification and a parametric analysis, this thesis ultimately lays a groundwork for future detailed design of cermet NTR fuel elements. Advisors/Committee Members: Vierow, Karen (advisor), Bragg-Sitton, Shannon (advisor), Cizmas, Paul (committee member).

Subjects/Keywords: nuclear; rocket; CFD; propulsion

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Appel, B. (2012). Multiphysics Design and Simulation of a Tungsten-Cermet Nuclear Thermal Rocket. (Masters Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/ETD-TAMU-2012-08-11649

Chicago Manual of Style (16^th Edition):

Appel, Bradley. “Multiphysics Design and Simulation of a Tungsten-Cermet Nuclear Thermal Rocket.” 2012. Masters Thesis, Texas A&M University. Accessed February 28, 2021. http://hdl.handle.net/1969.1/ETD-TAMU-2012-08-11649.

MLA Handbook (7^th Edition):

Appel, Bradley. “Multiphysics Design and Simulation of a Tungsten-Cermet Nuclear Thermal Rocket.” 2012. Web. 28 Feb 2021.

Vancouver:

Appel B. Multiphysics Design and Simulation of a Tungsten-Cermet Nuclear Thermal Rocket. [Internet] [Masters thesis]. Texas A&M University; 2012. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/1969.1/ETD-TAMU-2012-08-11649.

Council of Science Editors:

Appel B. Multiphysics Design and Simulation of a Tungsten-Cermet Nuclear Thermal Rocket. [Masters Thesis]. Texas A&M University; 2012. Available from: http://hdl.handle.net/1969.1/ETD-TAMU-2012-08-11649

Delft University of Technology

9. Powell, S.J. (author). CubeSatMicro-Propulsion: Design and Validation of a Micro Bi-Propellant Rocket Motor.

Degree: 2015, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:a6de0cf0-a562-41e0-8b34-b53b839385d6

►

In this MSc thesis, a 4N Bi-Propellant rocket motor was designed using numerical analysis tools. Four motors were built and tested. The results are presented… (more)

Subjects/Keywords: Micro Bi-Propellant Rocket Motor

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Powell, S. J. (. (2015). CubeSatMicro-Propulsion: Design and Validation of a Micro Bi-Propellant Rocket Motor. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:a6de0cf0-a562-41e0-8b34-b53b839385d6

Chicago Manual of Style (16^th Edition):

Powell, S J (author). “CubeSatMicro-Propulsion: Design and Validation of a Micro Bi-Propellant Rocket Motor.” 2015. Masters Thesis, Delft University of Technology. Accessed February 28, 2021. http://resolver.tudelft.nl/uuid:a6de0cf0-a562-41e0-8b34-b53b839385d6.

MLA Handbook (7^th Edition):

Powell, S J (author). “CubeSatMicro-Propulsion: Design and Validation of a Micro Bi-Propellant Rocket Motor.” 2015. Web. 28 Feb 2021.

Vancouver:

Powell SJ(. CubeSatMicro-Propulsion: Design and Validation of a Micro Bi-Propellant Rocket Motor. [Internet] [Masters thesis]. Delft University of Technology; 2015. [cited 2021 Feb 28]. Available from: http://resolver.tudelft.nl/uuid:a6de0cf0-a562-41e0-8b34-b53b839385d6.

Council of Science Editors:

Powell SJ(. CubeSatMicro-Propulsion: Design and Validation of a Micro Bi-Propellant Rocket Motor. [Masters Thesis]. Delft University of Technology; 2015. Available from: http://resolver.tudelft.nl/uuid:a6de0cf0-a562-41e0-8b34-b53b839385d6

Delft University of Technology

10. Engelen, F.M. (author). Quantitative risk analysis of unguided rocket trajectories.

Degree: 2012, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:2dfae5a6-809e-484d-8b3e-ebd146d891f3

► These days more and more rockets are developed by companies, students and other amateurs. To assess the safety of these rockets, a method is necessary… (more)

▼ These days more and more rockets are developed by companies, students and other amateurs. To assess the safety of these rockets, a method is necessary to estimate the risk of these vehicles quantitatively. Because tools to do so are not freely available, the goal of this thesis is to research methods to quantitatively estimate the risk of nominal flight of unguided rockets. The first step to do so, is to develop a trajectory simulator. To incorporate the effect of wind (weather cocking) and spinning, it is necessary to develop a simulator with three translational degrees of freedom, and three rotational degrees of freedom. The position and velocity of the rocket are described in a Cartesian coordinate system. To prevent singularities in the orientation, quaternions are used to describe the orientation of the rocket. To propagate these through time, classical equations of motion for a rigid body can be used. To do so the impulse thrust force and the jet damping moment are considered as an external force and external moment. The gravity force, the aerodynamic force, and the aerodynamic moment are the other external influences. To calculate these, the Earth is modeled as a flatted sphere (both shape and gravity field) with a US 1976 standard atmosphere, and a tabulated wind profile. The aerodynamic forces and moments are calculated based on this environment and a limited set of aerodynamic coefficients, obtained from the Missile Datcom 97 program. Because the problem’s nature it is not solvable analytically. Furthermore, in some parts of the flight the state rocket’s state changes rapidly, while in others parts the system behaves very smoothly. Therefore a Runge-Kutta-Fehlberg 56 variable time step integrator is used to solve the equations of motion numerically. As a result of this decision it is necessary to implement an event handling algorithm to execute discrete behavior (e.g. stage ignition) at the right time. To validate the in C++ developed program ROSIE, a small amateur rocket’s flight (2m long, apogee at 1 km) is simulated. The results show similar behavior as observed in the real flight data of the simulated rocket, indicating that the simulator is valid for the simulation of small amateur rockets. When comparing a single simulated impact point with a measured impact point, they will most likely not coincide. This can be explained by errors in the flight’s modeling, and can be due to randomness in what is simulated. By stating that these errors are due to uncertainties in the analysis, and modeling these uncertainties as random (input) variables, the result of the analysis will also be a random variable. An advantage of such a variable is that the result is not a single point, but a probability distribution. This distribution can be used to determine the risk to each individual, or the area which needs to be evacuated. To determine the probability distribution different methods are used. These methods can be grouped in parameterized and non-parameterized methods. With parameterized methods, a known type of… Advisors/Committee Members: Mooij, E. (mentor), Verhoeven, C. (mentor), Ambrosius, B.A.C. (mentor).

Subjects/Keywords: Rocket trajectory Stratos simulation

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Engelen, F. M. (. (2012). Quantitative risk analysis of unguided rocket trajectories. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:2dfae5a6-809e-484d-8b3e-ebd146d891f3

Chicago Manual of Style (16^th Edition):

Engelen, F M (author). “Quantitative risk analysis of unguided rocket trajectories.” 2012. Masters Thesis, Delft University of Technology. Accessed February 28, 2021. http://resolver.tudelft.nl/uuid:2dfae5a6-809e-484d-8b3e-ebd146d891f3.

MLA Handbook (7^th Edition):

Engelen, F M (author). “Quantitative risk analysis of unguided rocket trajectories.” 2012. Web. 28 Feb 2021.

Vancouver:

Engelen FM(. Quantitative risk analysis of unguided rocket trajectories. [Internet] [Masters thesis]. Delft University of Technology; 2012. [cited 2021 Feb 28]. Available from: http://resolver.tudelft.nl/uuid:2dfae5a6-809e-484d-8b3e-ebd146d891f3.

Council of Science Editors:

Engelen FM(. Quantitative risk analysis of unguided rocket trajectories. [Masters Thesis]. Delft University of Technology; 2012. Available from: http://resolver.tudelft.nl/uuid:2dfae5a6-809e-484d-8b3e-ebd146d891f3

Brno University of Technology

11. Marcinko, Peter. Vývoj raketových motorů: Development of rocket engines.

Degree: 2019, Brno University of Technology

URL: http://hdl.handle.net/11012/33320

► This thesis describes the development of rocket engines since the beginning to present time. The thesis is divided into three parts. The first describes the… (more)

Subjects/Keywords: Raketový motor; raketa; technické parametre; vývoj raketových motorov; raketový program; Rocket engine; rocket; technical parameters; developement of rocket engines; rocket programe

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Marcinko, P. (2019). Vývoj raketových motorů: Development of rocket engines. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/33320

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):

Marcinko, Peter. “Vývoj raketových motorů: Development of rocket engines.” 2019. Thesis, Brno University of Technology. Accessed February 28, 2021. http://hdl.handle.net/11012/33320.

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

MLA Handbook (7^th Edition):

Marcinko, Peter. “Vývoj raketových motorů: Development of rocket engines.” 2019. Web. 28 Feb 2021.

Vancouver:

Marcinko P. Vývoj raketových motorů: Development of rocket engines. [Internet] [Thesis]. Brno University of Technology; 2019. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/11012/33320.

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

Council of Science Editors:

Marcinko P. Vývoj raketových motorů: Development of rocket engines. [Thesis]. Brno University of Technology; 2019. Available from: http://hdl.handle.net/11012/33320

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

Brno University of Technology

12. Marcinko, Peter. Vývoj raketových motorů: Development of rocket engines.

Degree: 2014, Brno University of Technology

URL: http://hdl.handle.net/11012/27145

► This thesis describes the development of rocket engines since the beginning to present time. The thesis is divided into three parts. The first describes the… (more)

Subjects/Keywords: Raketový motor; raketa; technické parametre; vývoj raketových motorov; raketový program; Rocket engine; rocket; technical parameters; developement of rocket engines; rocket programe

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Marcinko, P. (2014). Vývoj raketových motorů: Development of rocket engines. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/27145

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):

Marcinko, Peter. “Vývoj raketových motorů: Development of rocket engines.” 2014. Thesis, Brno University of Technology. Accessed February 28, 2021. http://hdl.handle.net/11012/27145.

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

MLA Handbook (7^th Edition):

Marcinko, Peter. “Vývoj raketových motorů: Development of rocket engines.” 2014. Web. 28 Feb 2021.

Vancouver:

Marcinko P. Vývoj raketových motorů: Development of rocket engines. [Internet] [Thesis]. Brno University of Technology; 2014. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/11012/27145.

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

Council of Science Editors:

Marcinko P. Vývoj raketových motorů: Development of rocket engines. [Thesis]. Brno University of Technology; 2014. Available from: http://hdl.handle.net/11012/27145

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

Ryerson University

13. Wozney, Clayton Edward. Comparison Of Solid Rocket Motor Thrust Modulation Technique.

Degree: 2017, Ryerson University

URL: https://digital.library.ryerson.ca/islandora/object/RULA%3A6888

► The thrust profiles of solid rocket motors are usually determined ahead of time by propellant composition and grain design. Traditional techniques for active thrust modulation… (more)

Subjects/Keywords: Rocket engines – Combustion; Solid propellant rockets – Combustion; Rocket engines – Thrust

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Wozney, C. E. (2017). Comparison Of Solid Rocket Motor Thrust Modulation Technique. (Thesis). Ryerson University. Retrieved from https://digital.library.ryerson.ca/islandora/object/RULA%3A6888

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):

Wozney, Clayton Edward. “Comparison Of Solid Rocket Motor Thrust Modulation Technique.” 2017. Thesis, Ryerson University. Accessed February 28, 2021. https://digital.library.ryerson.ca/islandora/object/RULA%3A6888.

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

MLA Handbook (7^th Edition):

Wozney, Clayton Edward. “Comparison Of Solid Rocket Motor Thrust Modulation Technique.” 2017. Web. 28 Feb 2021.

Vancouver:

Wozney CE. Comparison Of Solid Rocket Motor Thrust Modulation Technique. [Internet] [Thesis]. Ryerson University; 2017. [cited 2021 Feb 28]. Available from: https://digital.library.ryerson.ca/islandora/object/RULA%3A6888.

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

Council of Science Editors:

Wozney CE. Comparison Of Solid Rocket Motor Thrust Modulation Technique. [Thesis]. Ryerson University; 2017. Available from: https://digital.library.ryerson.ca/islandora/object/RULA%3A6888

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

University of Adelaide

14. Hardi, Justin S. Experimental investigation of high frequency combustion instability in cryogenic oxygen-hydrogen rocket engines.

Degree: 2012, University of Adelaide

URL: http://hdl.handle.net/2440/82071

► Self-sustaining pressure oscillations in the combustion chamber, or combustion instability, is a commonly encountered and potentially damaging phenomenon in liquid propellant rocket engines (LPREs). In… (more)

▼ Self-sustaining pressure oscillations in the combustion chamber, or combustion instability, is a commonly encountered and potentially damaging phenomenon in liquid propellant rocket engines (LPREs). In the high-frequency variety of combustion instability, the pressure oscillations in the combustion chamber take on the form and frequency of an acoustic resonance mode of the combustion chamber volume. The most common mode in naturally occurring instability, and also the most destructive, is the first tangential mode, with acoustic gas oscillations oriented transversally to the direction of propellant injection. The instability is driven by the coupling between acoustic oscillations and unsteady energy release from combustion. The mechanisms through which injection and combustion firstly respond to the acoustic field, and secondly feed energy back into the acoustic field have not yet been fully characterised. Shear coaxial-type injectors are common in LPREs. Past experimental and numerical research efforts have investigated the interaction between this type of injector and transverse acoustic fields. Some experimental efforts have successfully forced transverse acoustic modes and studied their influence on shear coaxial injection under LPRE-like conditions. Acoustic forcing of coaxially injected LOx/H₂ has previously been conducted only at low pressures and injection performance levels. This work addresses the lack of experimental data available for the interaction of shear coaxial injection of LOx/H₂ with acoustics under conditions representative of industrial engines. A new experimental rocket combustor, designated ‘BKH’, was developed for investigating the response of a reacting spray of coaxially injected LOx/H₂ to an acoustic field. For characterising the response, simultaneous high-speed recordings of both backlit shadowgraph and hydroxyl radical (OH*) chemiluminescence imaging have been captured through optical access windows. The operating conditions of BKH extend to conditions more representative of actual LPREs than has previously been achieved with LOx/H₂ in studies of flame-acoustic interaction. BKH was run at pressures of 40 or 60 bar, which correspond to subcritical and supercritical thermo-physical regimes for oxygen. Hydrogen injection temperature was ambient, around 290 K, or cryogenic, around 50 K. An array of multiple injectors was used to better represent real engines. A system for modulating the nozzle exhaust flow was used to induce acoustic perturbations inside the combustion chamber. Two types of perturbation were applied to the near-injection region; oscillating acoustic pressure, and oscillating transverse acoustic velocity. BKH was used to investigate how subcritical or supercritical pressure level and ambient or cryogenic hydrogen injection temperature influence the interaction of acoustic pressure or velocity with injection and combustion processes. Shadowgraph imaging reveals up to 70% reduction in the length of the oxygen jet when subjected to acoustic velocity of amplitude approaching… Advisors/Committee Members: Dally, Bassam B. (advisor), Oschwald, Michael (advisor), School of Mechanical Engineering (school).

Subjects/Keywords: rocket engine; combustion; cryogenic; instabilities; combustion instabilities; liquid rocket

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Hardi, J. S. (2012). Experimental investigation of high frequency combustion instability in cryogenic oxygen-hydrogen rocket engines. (Thesis). University of Adelaide. Retrieved from http://hdl.handle.net/2440/82071

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):

Hardi, Justin S. “Experimental investigation of high frequency combustion instability in cryogenic oxygen-hydrogen rocket engines.” 2012. Thesis, University of Adelaide. Accessed February 28, 2021. http://hdl.handle.net/2440/82071.

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

MLA Handbook (7^th Edition):

Hardi, Justin S. “Experimental investigation of high frequency combustion instability in cryogenic oxygen-hydrogen rocket engines.” 2012. Web. 28 Feb 2021.

Vancouver:

Hardi JS. Experimental investigation of high frequency combustion instability in cryogenic oxygen-hydrogen rocket engines. [Internet] [Thesis]. University of Adelaide; 2012. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/2440/82071.

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

Council of Science Editors:

Hardi JS. Experimental investigation of high frequency combustion instability in cryogenic oxygen-hydrogen rocket engines. [Thesis]. University of Adelaide; 2012. Available from: http://hdl.handle.net/2440/82071

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

Rochester Institute of Technology

15. Gates, Kevin. CSTARS: Cryogenic CMOS Optical Star Tracking.

Degree: MS, Electrical Engineering, 2020, Rochester Institute of Technology

URL: https://scholarworks.rit.edu/theses/10611

► CMOS and sCMOS image sensors are a cost-effective alternative to the more common CCD based experimental sensors. While often being less favored than CCDs… (more)

Subjects/Keywords: CMOS; Cryogenic; Rocket attitude; sCMOS; Sounding rocket; Star tracker

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Gates, K. (2020). CSTARS: Cryogenic CMOS Optical Star Tracking. (Masters Thesis). Rochester Institute of Technology. Retrieved from https://scholarworks.rit.edu/theses/10611

Chicago Manual of Style (16^th Edition):

Gates, Kevin. “CSTARS: Cryogenic CMOS Optical Star Tracking.” 2020. Masters Thesis, Rochester Institute of Technology. Accessed February 28, 2021. https://scholarworks.rit.edu/theses/10611.

MLA Handbook (7^th Edition):

Gates, Kevin. “CSTARS: Cryogenic CMOS Optical Star Tracking.” 2020. Web. 28 Feb 2021.

Vancouver:

Gates K. CSTARS: Cryogenic CMOS Optical Star Tracking. [Internet] [Masters thesis]. Rochester Institute of Technology; 2020. [cited 2021 Feb 28]. Available from: https://scholarworks.rit.edu/theses/10611.

Council of Science Editors:

Gates K. CSTARS: Cryogenic CMOS Optical Star Tracking. [Masters Thesis]. Rochester Institute of Technology; 2020. Available from: https://scholarworks.rit.edu/theses/10611

Delft University of Technology

16. Hermsen, R.J.G. (author). Cryogenic propellant tank pressurization.

Degree: 2017, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:048e34e9-9af6-4b3c-9249-576d192fa7bd

►

To launch a rocket to the edge of space using a pressure fed rocket system with liquid oxygen as propellant, you need to know exactly… (more)

Subjects/Keywords: cryogenic; high-pressure; propellant; tank pressurization; rocket; Delft Aerospace Rocket Engineering; DARE; pressurant injector; pressure-fed; rocket engine

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Hermsen, R. J. G. (. (2017). Cryogenic propellant tank pressurization. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:048e34e9-9af6-4b3c-9249-576d192fa7bd

Chicago Manual of Style (16^th Edition):

Hermsen, R J G (author). “Cryogenic propellant tank pressurization.” 2017. Masters Thesis, Delft University of Technology. Accessed February 28, 2021. http://resolver.tudelft.nl/uuid:048e34e9-9af6-4b3c-9249-576d192fa7bd.

MLA Handbook (7^th Edition):

Hermsen, R J G (author). “Cryogenic propellant tank pressurization.” 2017. Web. 28 Feb 2021.

Vancouver:

Hermsen RJG(. Cryogenic propellant tank pressurization. [Internet] [Masters thesis]. Delft University of Technology; 2017. [cited 2021 Feb 28]. Available from: http://resolver.tudelft.nl/uuid:048e34e9-9af6-4b3c-9249-576d192fa7bd.

Council of Science Editors:

Hermsen RJG(. Cryogenic propellant tank pressurization. [Masters Thesis]. Delft University of Technology; 2017. Available from: http://resolver.tudelft.nl/uuid:048e34e9-9af6-4b3c-9249-576d192fa7bd

Brno University of Technology

17. Kadlec, Jan. Ventily pohonných systémů raketových motorů: Valves of the rocket fuel systems and engines.

Degree: 2019, Brno University of Technology

URL: http://hdl.handle.net/11012/81937

► The main aim of this bachelor thesis is developing a search about rocket valves. For better understanding of the function and position valves is chosen… (more)

Subjects/Keywords: raketový ventil; raketový motor; kapalná raketová paliva; hydraulické ztráty; rocket valve; rocket engine; liquid rocket fuels; hydraulic losses

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Kadlec, J. (2019). Ventily pohonných systémů raketových motorů: Valves of the rocket fuel systems and engines. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/81937

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):

Kadlec, Jan. “Ventily pohonných systémů raketových motorů: Valves of the rocket fuel systems and engines.” 2019. Thesis, Brno University of Technology. Accessed February 28, 2021. http://hdl.handle.net/11012/81937.

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

MLA Handbook (7^th Edition):

Kadlec, Jan. “Ventily pohonných systémů raketových motorů: Valves of the rocket fuel systems and engines.” 2019. Web. 28 Feb 2021.

Vancouver:

Kadlec J. Ventily pohonných systémů raketových motorů: Valves of the rocket fuel systems and engines. [Internet] [Thesis]. Brno University of Technology; 2019. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/11012/81937.

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

Council of Science Editors:

Kadlec J. Ventily pohonných systémů raketových motorů: Valves of the rocket fuel systems and engines. [Thesis]. Brno University of Technology; 2019. Available from: http://hdl.handle.net/11012/81937

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

Technical University of Lisbon

18. Fidalgo, Andreia Filipa Brito. Exposição e acumulação de elementos potencialmente tóxicos em rúcula (Eruca sativa).

Degree: 2014, Technical University of Lisbon

URL: https://www.rcaap.pt/detail.jsp?id=oai:www.repository.utl.pt:10400.5/6786

►

Mestrado em Engenharia Alimentar - Instituto Superior de Agronomia

In this project the effects of the exposure of rocket (Eruca sativa) to potentially toxic elements… (more)

Subjects/Keywords: rocket; Eruca sativa; cadmium; copper; arsenic; salinity

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Fidalgo, A. F. B. (2014). Exposição e acumulação de elementos potencialmente tóxicos em rúcula (Eruca sativa). (Thesis). Technical University of Lisbon. Retrieved from https://www.rcaap.pt/detail.jsp?id=oai:www.repository.utl.pt:10400.5/6786

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):

Fidalgo, Andreia Filipa Brito. “Exposição e acumulação de elementos potencialmente tóxicos em rúcula (Eruca sativa).” 2014. Thesis, Technical University of Lisbon. Accessed February 28, 2021. https://www.rcaap.pt/detail.jsp?id=oai:www.repository.utl.pt:10400.5/6786.

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

MLA Handbook (7^th Edition):

Fidalgo, Andreia Filipa Brito. “Exposição e acumulação de elementos potencialmente tóxicos em rúcula (Eruca sativa).” 2014. Web. 28 Feb 2021.

Vancouver:

Fidalgo AFB. Exposição e acumulação de elementos potencialmente tóxicos em rúcula (Eruca sativa). [Internet] [Thesis]. Technical University of Lisbon; 2014. [cited 2021 Feb 28]. Available from: https://www.rcaap.pt/detail.jsp?id=oai:www.repository.utl.pt:10400.5/6786.

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

Council of Science Editors:

Fidalgo AFB. Exposição e acumulação de elementos potencialmente tóxicos em rúcula (Eruca sativa). [Thesis]. Technical University of Lisbon; 2014. Available from: https://www.rcaap.pt/detail.jsp?id=oai:www.repository.utl.pt:10400.5/6786

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

Anna University

19. Rajesh jesudoss hynes N. Investigation on joining of dissimilar materials in a newly developed low cost friction stud welding machine;.

Degree: Investigation on joining of dissimilar materials in a newly developed low cost friction stud welding machine, 2015, Anna University

URL: http://shodhganga.inflibnet.ac.in/handle/10603/50007

►

Welding of aluminum based materials to steel is of particular interest to the engineers because the resulting products combine the very different but favourable properties… (more)

Subjects/Keywords: Low cost friction; Rocket fuel tanks

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

N, R. j. h. (2015). Investigation on joining of dissimilar materials in a newly developed low cost friction stud welding machine;. (Thesis). Anna University. Retrieved from http://shodhganga.inflibnet.ac.in/handle/10603/50007

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):

N, Rajesh jesudoss hynes. “Investigation on joining of dissimilar materials in a newly developed low cost friction stud welding machine;.” 2015. Thesis, Anna University. Accessed February 28, 2021. http://shodhganga.inflibnet.ac.in/handle/10603/50007.

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

MLA Handbook (7^th Edition):

N, Rajesh jesudoss hynes. “Investigation on joining of dissimilar materials in a newly developed low cost friction stud welding machine;.” 2015. Web. 28 Feb 2021.

Vancouver:

N Rjh. Investigation on joining of dissimilar materials in a newly developed low cost friction stud welding machine;. [Internet] [Thesis]. Anna University; 2015. [cited 2021 Feb 28]. Available from: http://shodhganga.inflibnet.ac.in/handle/10603/50007.

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

Council of Science Editors:

N Rjh. Investigation on joining of dissimilar materials in a newly developed low cost friction stud welding machine;. [Thesis]. Anna University; 2015. Available from: http://shodhganga.inflibnet.ac.in/handle/10603/50007

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

Penn State University

20. Lin, Chia-Yung. IMPORTANT FINDINGS AND OBSERVATIONS OF THE ROCKET NOZZLE EROSION PROCESSES AND THEORETICAL/NUMERICAL SIMULATIONS.

Degree: 2010, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/10841

► Rocket nozzle erosion has been a critical issue when rocket motor operating conditions are at high temperature and pressure. During rocket motor operation, nozzle surface… (more)

▼ Rocket nozzle erosion has been a critical issue when rocket motor operating conditions are at high temperature and pressure. During rocket motor operation, nozzle surface are subjected to thermalchemical erosion by oxidizing gaseous species such as H2O , OH and, CO2 and/or mechanical erosion by impinging aluminum oxides when metallized propellants are used. The throat area undergoes the extreme heat transfer, thereby decreasing the thrust and causing severe performance reduction of the propulsion system. Accordingly, detailed understanding of the erosion mechanism is desirable. Shear and normal forces on the nozzle surface, temperature, pressure, heat transfer to the wall, particle impacts, chemical kinetics, and surface melting are considered primary factors of nozzle erosion. Various aspects that are closely related to the nozzle recession processes conducted by several research groups are summarized. In order to reduce the overall recession rate of the nozzle, the nozzle boundary-layer controlled system (NBLCS) has been introduced and shown the effectiveness in mitigation of the nozzle erosion. This method produces relatively low product gases to be injected into the upstream of the nozzle throat section, which not only reduces the concentration of the oxidizing species but also cools down the hot combustion product gases in the boundary layer region near the throat. Refractory materials like tungsten (W) , plays a significant role in overall nozzle erosion mechanism due to its high melting temperature. However, heterogeneous reaction kinetics must be carefully examined and modeled since tungsten oxidation by several oxidizing species such as CO2, CO and O2 could generate metal compounds with lower vaporization and/or melting temperatures. These compounds may be removed from the nozzle surface as fast as they are forms, either by vaporization or surface forces, thereby expanding the nozzle throat area and reducing overall performance. To increase the operating condition range and performance of a future rocket propulsion system, understanding the rocket nozzle erosion processes and developing methods for nozzle erosion reduction are vitally important. Thus, quantitative and qualitative experimental studies and theoretical simulations are required to be advanced due to the complexity involved in the rocket nozzle erosion characteristics. Advisors/Committee Members: Kenneth K Kuo, Thesis Advisor/Co-Advisor, Kenneth K Kuo, Thesis Advisor/Co-Advisor.

Subjects/Keywords: rocket nozzle erosion

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Lin, C. (2010). IMPORTANT FINDINGS AND OBSERVATIONS OF THE ROCKET NOZZLE EROSION PROCESSES AND THEORETICAL/NUMERICAL SIMULATIONS. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/10841

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):

Lin, Chia-Yung. “IMPORTANT FINDINGS AND OBSERVATIONS OF THE ROCKET NOZZLE EROSION PROCESSES AND THEORETICAL/NUMERICAL SIMULATIONS.” 2010. Thesis, Penn State University. Accessed February 28, 2021. https://submit-etda.libraries.psu.edu/catalog/10841.

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

MLA Handbook (7^th Edition):

Lin, Chia-Yung. “IMPORTANT FINDINGS AND OBSERVATIONS OF THE ROCKET NOZZLE EROSION PROCESSES AND THEORETICAL/NUMERICAL SIMULATIONS.” 2010. Web. 28 Feb 2021.

Vancouver:

Lin C. IMPORTANT FINDINGS AND OBSERVATIONS OF THE ROCKET NOZZLE EROSION PROCESSES AND THEORETICAL/NUMERICAL SIMULATIONS. [Internet] [Thesis]. Penn State University; 2010. [cited 2021 Feb 28]. Available from: https://submit-etda.libraries.psu.edu/catalog/10841.

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

Council of Science Editors:

Lin C. IMPORTANT FINDINGS AND OBSERVATIONS OF THE ROCKET NOZZLE EROSION PROCESSES AND THEORETICAL/NUMERICAL SIMULATIONS. [Thesis]. Penn State University; 2010. Available from: https://submit-etda.libraries.psu.edu/catalog/10841

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

21. Cohen, Ian James. The Study of Ionospheric Response to Precipitation Using Sounding Rocket Observations.

Degree: PhD, 2015, University of New Hampshire

URL: https://scholars.unh.edu/dissertation/2203

► Understanding the role that the ionosphere plays in phenomena such as the development of auroral arcs and ion outflow is basic to the investigation of… (more)

Subjects/Keywords: aurora; ionosphere; magnetosphere; rocket; Aeronomy; Geophysics; Physics

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Cohen, I. J. (2015). The Study of Ionospheric Response to Precipitation Using Sounding Rocket Observations. (Doctoral Dissertation). University of New Hampshire. Retrieved from https://scholars.unh.edu/dissertation/2203

Chicago Manual of Style (16^th Edition):

Cohen, Ian James. “The Study of Ionospheric Response to Precipitation Using Sounding Rocket Observations.” 2015. Doctoral Dissertation, University of New Hampshire. Accessed February 28, 2021. https://scholars.unh.edu/dissertation/2203.

MLA Handbook (7^th Edition):

Cohen, Ian James. “The Study of Ionospheric Response to Precipitation Using Sounding Rocket Observations.” 2015. Web. 28 Feb 2021.

Vancouver:

Cohen IJ. The Study of Ionospheric Response to Precipitation Using Sounding Rocket Observations. [Internet] [Doctoral dissertation]. University of New Hampshire; 2015. [cited 2021 Feb 28]. Available from: https://scholars.unh.edu/dissertation/2203.

Council of Science Editors:

Cohen IJ. The Study of Ionospheric Response to Precipitation Using Sounding Rocket Observations. [Doctoral Dissertation]. University of New Hampshire; 2015. Available from: https://scholars.unh.edu/dissertation/2203

University of KwaZulu-Natal

22. Singh, Nalendran. The hydrodynamic design and analysis of a liquid oxygen pump impeller for a rocket engine.

Degree: 2018, University of KwaZulu-Natal

URL: https://researchspace.ukzn.ac.za/handle/10413/17549

► The deployment of micro- and nanosatellites has greatly increased over the past few decades with advances in miniaturized electronics for communication, imaging and attitude control.… (more)

▼ The deployment of micro- and nanosatellites has greatly increased over the past few decades with advances in miniaturized electronics for communication, imaging and attitude control. The South African satellite industry is now also currently developing two microsatellites and nanosatellites for launch by foreign providers. The outsourcing of launch services to foreign providers is costly and can lead to unanticipated delays. In this context, the UKZN Aerospace Systems Research Group (ASReG), in conjunction with the Council for Scientific and Industrial Research (CSIR) has begun designing a modular and compact liquid propulsion engine (LOX/RP-1) named SAFFIRE (South AFrican First Integrated Rocket Engine). This dissertation details the design and analysis of the liquid oxygen pump that delivers the oxidiser to the SAFFIRE combustion chamber at high pressure, where the propellants are burnt and expelled, generating thrust. The pump is electrically powered as opposed to the conventional turbine-driven turbopump, to further simplify start-stop procedures and reduce the complexity of the engine. The pump’s operating conditions were determined by an engine performance analysis, with these results forming the initial conditions for the pump design process. The oxidiser pump is required to deliver a mass flow rate of 6.13 kg/s at a pressure of 62.8 bar. The pump was designed using conventional centrifugal pump design procedures, with special considerations taken due to the working temperature of liquid oxygen being -183°C. The final one-dimensional design for the impeller was developed using the commercial software PUMPAL™, which was provided by the CSIR. A 3D impeller geometry was developed by importing the one-dimensional design into AxCent™, where quasi-3D Multiple Stream Tube (MST) analysis and full 3D computational fluid dynamics (CFD) simulations were performed. The impeller design was refined multiple times until the parameters set by the engine performance analysis were met. The AxCent™ analyses determined that low-pressure zones occurred at the inlet of the pump impeller. Hence Star-CCM+™, which has a more robust computational solver and allows for a full transient, multiphase CFD to be performed, was employed to analyse any potential cavitation affects. The results from Star-CCM+™ and AxCent™ were compared and designs altered until a final design was realized that met the prescribed performance parameters. The final pump impeller has an outer diameter of 86 mm, delivering a mass flow rate of 6.13 kg/s at a pressure of 64.2 bar. The pump operates at an efficiency of 60.8% requiring a power input of 51.96 kW at a rotational speed of 26000 rpm. Advisors/Committee Members: Brooks, Michael John. (advisor), Smith, Graham Douglas James. (advisor), Snedden, Glen Campbell. (advisor).

Subjects/Keywords: Hydrodynamic.; Liquid oxygen.; Impeller.; Rocket engine.

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Singh, N. (2018). The hydrodynamic design and analysis of a liquid oxygen pump impeller for a rocket engine. (Thesis). University of KwaZulu-Natal. Retrieved from https://researchspace.ukzn.ac.za/handle/10413/17549

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):

Singh, Nalendran. “The hydrodynamic design and analysis of a liquid oxygen pump impeller for a rocket engine.” 2018. Thesis, University of KwaZulu-Natal. Accessed February 28, 2021. https://researchspace.ukzn.ac.za/handle/10413/17549.

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

MLA Handbook (7^th Edition):

Singh, Nalendran. “The hydrodynamic design and analysis of a liquid oxygen pump impeller for a rocket engine.” 2018. Web. 28 Feb 2021.

Vancouver:

Singh N. The hydrodynamic design and analysis of a liquid oxygen pump impeller for a rocket engine. [Internet] [Thesis]. University of KwaZulu-Natal; 2018. [cited 2021 Feb 28]. Available from: https://researchspace.ukzn.ac.za/handle/10413/17549.

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

Council of Science Editors:

Singh N. The hydrodynamic design and analysis of a liquid oxygen pump impeller for a rocket engine. [Thesis]. University of KwaZulu-Natal; 2018. Available from: https://researchspace.ukzn.ac.za/handle/10413/17549

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

University of KwaZulu-Natal

23. Theba, Raisa. The development of a paraffin wax/nitrous oxide hybrid rocket slab motor.

Degree: 2019, University of KwaZulu-Natal

URL: https://researchspace.ukzn.ac.za/handle/10413/18105

► Slab motors are used to determine and investigate the regression rate characteristics of hybrid rocket propellant combinations. This information is fundamental to the overall design… (more)

▼ Slab motors are used to determine and investigate the regression rate characteristics of hybrid rocket propellant combinations. This information is fundamental to the overall design and thus used to determine the payload, altitude and thrust parameters of a rocket. The Phoenix Hybrid Sounding Rocket Programme in the University of KwaZulu-Natal’s (UKZN) Mechanical Engineering Department uses paraffin wax and nitrous oxide in their series of hybrid sounding rockets. The regression rate behaviour of paraffin wax with nitrous oxide has not previously been investigated in slab motors. This study focused on the regression rate behaviour and entrainment mechanism with regards to non-classical fuels including those with metal additives. This was used to gain a greater understanding of the increased regression rates associated with these fuels. The addition of metal additives, such as that of aluminium to fuel grains, was explored since the research suggested that it increases the regression rate of pure paraffin wax by 30%. A hybrid rocket slab motor visualisation test stand was developed to observe and obtain regression rate data. The stand includes a feed system, injector and a combustion chamber. All the components were manufactured using brass and stainless steel materials for their nitrous oxide compatibility, strength, and thermal resistance. Quartz glass windows were incorporated into the combustion chamber design for visualisation purposes. Due to the presence of quartz glass the use of finite element analyses became critical and more complex in order to ensure that the glass could withstand the operating conditions of the slab motor. A side-glass spacer was implemented to minimise the effects of side burning and to observe the influence of regression rate. Tests were conducted at a 130 g/s oxidiser mass flow rate and an atmospheric chamber pressure. A data acquisition system using LabVIEW software was implemented to obtain tank readings for the duration of the burn and to ensure safe motor operation. The regression rate of Sasolwax 0907 fuel was volumetrically determined and observed to be on average 3.74 mm/s. This shows a much higher regression rate than other paraffin wax compositions which have been found to regress at 1.5 mm/s. The characteristics of the entrainment process were validated for the investigated propellants, and the high regression rate mechanism of paraffin wax was observed in the liquid melt layer, droplet entrainment, and roll waves. Tests using aluminised wax fuel grains at atmospheric conditions proved to beunsuccessful with nitrous oxide as the oxidiser. A possible reason for this could be due to the aluminised fuel grains requiring increased heat transfer, therefore not producing sufficient apourisation of the fuel. Moreover, decomposition of the oxidiser appeared to be inhibited by the combination of the oxidiser mass flow rate and the port area which prevented combustion. Advisors/Committee Members: Veale, Kirsty Lynn. (advisor), Bemont, Clinton Pierre. (advisor).

Subjects/Keywords: Paraffin.; Wax / nitrous.; Hybrid rocket.; Slab motors.

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Theba, R. (2019). The development of a paraffin wax/nitrous oxide hybrid rocket slab motor. (Thesis). University of KwaZulu-Natal. Retrieved from https://researchspace.ukzn.ac.za/handle/10413/18105

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):

Theba, Raisa. “The development of a paraffin wax/nitrous oxide hybrid rocket slab motor.” 2019. Thesis, University of KwaZulu-Natal. Accessed February 28, 2021. https://researchspace.ukzn.ac.za/handle/10413/18105.

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

MLA Handbook (7^th Edition):

Theba, Raisa. “The development of a paraffin wax/nitrous oxide hybrid rocket slab motor.” 2019. Web. 28 Feb 2021.

Vancouver:

Theba R. The development of a paraffin wax/nitrous oxide hybrid rocket slab motor. [Internet] [Thesis]. University of KwaZulu-Natal; 2019. [cited 2021 Feb 28]. Available from: https://researchspace.ukzn.ac.za/handle/10413/18105.

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

Council of Science Editors:

Theba R. The development of a paraffin wax/nitrous oxide hybrid rocket slab motor. [Thesis]. University of KwaZulu-Natal; 2019. Available from: https://researchspace.ukzn.ac.za/handle/10413/18105

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

University of KwaZulu-Natal

24. Velthuysen, Timothy Johnathan. Closed-loop throttle control of a hybrid rocket motor.

Degree: 2018, University of KwaZulu-Natal

URL: https://researchspace.ukzn.ac.za/handle/10413/17862

► Hybrid rocket motors produce thrust by reacting a solid fuel with a liquid oxidizer inside a combustion chamber. This approach has certain advantages over conventional… (more)

▼ Hybrid rocket motors produce thrust by reacting a solid fuel with a liquid oxidizer inside a combustion chamber. This approach has certain advantages over conventional solid propellant rockets including improved safety and the potential for thrust control, while also being less expensive than liquid propellant engines. Liquefying hybrid fuels, such as paraffin wax, regress at a faster rate than the conventional solid fuels like HTPB that are dominated by vaporization at the solid-gas interface. Non-classical theory is still in its infancy, however, and more work is required to validate performance models experimentally, especially where throttling of the oxidizer mass flowrate is incorporated. While hybrid motor throttlabilty remains a subject of considerable interest, there has been little investigation of throttling in motors that use high regression rate, liquefying fuels such as paraffin wax. This study proposes a closed-loop thrust control scheme for paraffin wax/nitrous oxide hybrid rocket motors using a low-cost ball valve as the controlling hardware element. There are a number of advantages to throttling hybrid rocket motors but the most important is to enforce a constant thrust curve throughout the burn. A test facility and laboratory scale hybrid rocket motor utilizing paraffin wax as fuel and nitrous oxide as oxidiser were used for experimental testing. Using a mathematical model of a laboratory-scale hybrid rocket motor, the controller constants for a PID controller were obtained and tested through experimental testing. Open-loop testing was first done in order to determine the control authority of the ball valve over the oxidiser mass flowrate, as well as characterize the oxidiser mass flowrate in relation to each valve angle value. Closed-loop testing was undertaken to verify and refine the controller constants obtained via the laboratory-scale model. The tests prompted a redesign of the injector and additions to the LabVIEW™ controller regime. Using results from the open-loop tests a feed-forward lookup table was developed to allow for the controller to move to a specified angle quickly and thereby remove nonlinearities present in flow control using ball valves. Three successful closed-loop tests were done where the controller causes the thrust of the motor to track a predetermined thrust or chamber pressure set point with a reasonable degree of accuracy. The set-point profile of the first test was a constant thrust throughout the burn while the second test had a ramp set-point profile. The final test used chamber pressure as the feedback variable and had a step-down set-point profile. This study demonstrates that thrust control can be exercised over a paraffin wax/nitrous oxide hybrid rocket motor, using a low-cost ball valve as the control element to modulate the oxidiser mass flowrate. Advisors/Committee Members: Brooks, Michael John. (advisor), Pitot de la Beaujardiere, Jean-Francois Philippe. (advisor).

Subjects/Keywords: Hybrid rocket motors.; Closed-loop testing.

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Velthuysen, T. J. (2018). Closed-loop throttle control of a hybrid rocket motor. (Thesis). University of KwaZulu-Natal. Retrieved from https://researchspace.ukzn.ac.za/handle/10413/17862

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):

Velthuysen, Timothy Johnathan. “Closed-loop throttle control of a hybrid rocket motor.” 2018. Thesis, University of KwaZulu-Natal. Accessed February 28, 2021. https://researchspace.ukzn.ac.za/handle/10413/17862.

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

MLA Handbook (7^th Edition):

Velthuysen, Timothy Johnathan. “Closed-loop throttle control of a hybrid rocket motor.” 2018. Web. 28 Feb 2021.

Vancouver:

Velthuysen TJ. Closed-loop throttle control of a hybrid rocket motor. [Internet] [Thesis]. University of KwaZulu-Natal; 2018. [cited 2021 Feb 28]. Available from: https://researchspace.ukzn.ac.za/handle/10413/17862.

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

Council of Science Editors:

Velthuysen TJ. Closed-loop throttle control of a hybrid rocket motor. [Thesis]. University of KwaZulu-Natal; 2018. Available from: https://researchspace.ukzn.ac.za/handle/10413/17862

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

Oregon State University

25. Schmitz, Bruce Wayne. An analytical study of the effect of characteristic engine performance parameters on the payload capabilities of various high performance missiles.

Degree: MS, Mechanical Engineering, 1959, Oregon State University

URL: http://hdl.handle.net/1957/50383

Subjects/Keywords: Airplanes – Rocket engines

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Schmitz, B. W. (1959). An analytical study of the effect of characteristic engine performance parameters on the payload capabilities of various high performance missiles. (Masters Thesis). Oregon State University. Retrieved from http://hdl.handle.net/1957/50383

Chicago Manual of Style (16^th Edition):

Schmitz, Bruce Wayne. “An analytical study of the effect of characteristic engine performance parameters on the payload capabilities of various high performance missiles.” 1959. Masters Thesis, Oregon State University. Accessed February 28, 2021. http://hdl.handle.net/1957/50383.

MLA Handbook (7^th Edition):

Schmitz, Bruce Wayne. “An analytical study of the effect of characteristic engine performance parameters on the payload capabilities of various high performance missiles.” 1959. Web. 28 Feb 2021.

Vancouver:

Schmitz BW. An analytical study of the effect of characteristic engine performance parameters on the payload capabilities of various high performance missiles. [Internet] [Masters thesis]. Oregon State University; 1959. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/1957/50383.

Council of Science Editors:

Schmitz BW. An analytical study of the effect of characteristic engine performance parameters on the payload capabilities of various high performance missiles. [Masters Thesis]. Oregon State University; 1959. Available from: http://hdl.handle.net/1957/50383

University of Surrey

26. Sellers, Jerry Jon. Investigation into hybrid rockets and other cost-effective propulsion system options for small satellites.

Degree: PhD, 1996, University of Surrey

URL: http://epubs.surrey.ac.uk/856470/ ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.309201

► Affordable small satellites need affordable propulsion systems. The primary objective of this research was to investigate cost-effective propulsion system options for small satellites. The research… (more)

▼ Affordable small satellites need affordable propulsion systems. The primary objective of this research was to investigate cost-effective propulsion system options for small satellites. The research comprised four interrelated goals: Identify key cost drivers for spacecraft hardware. Characterise propulsion technology costs. Characterise propulsion system costs. Evaluate and compare the cost-effectiveness of system options. Each of these goals was attained. Important results and conclusions emerged. To begin with, key spacecraft hardware cost drivers were shown to occur during each phase of a mission—definition, design and acquisition—and a process for resolving them was advanced. Furthermore, propulsion system costs were shown to include far more than performance and price. A new paradigm for understanding the total cost of propulsion systems was defined that encompasses nine dimensions— mass, volume, time, power, system price, integration, logistics, safety and technical risk. This paradigm was used to characterise propulsion technology options. From this effort, hybrid rockets emerged as a promising but underdeveloped technology with great potential for cost-effective application. To evaluate this potential, a dedicated research program was completed during which a hybrid motor was designed, built and tested using 85% hydrogen peroxide as oxidiser and polythene as fuel. The basic concept for a hybrid upper stage was proven. Excellent combustion performance was measured and characterised. Real total costs for future small satellite applications were assessed. This research demonstrated that hybrid rockets offer a safe, reliable upper stage option that is a versatile, cost-effective alternative to solid rocket motors. In addition, despite negative industry bias, hydrogen peroxide proved itself as a safe, effective oxidiser for hybrid and mono-propellant applications. The characterisation of propulsion system costs led to a complete design case study for a minisatellite aimed at the most cost-effective solution. It was shown that by focusing on the key cost drivers and trading among the cost dimensions, a truly versatile, cost-effective system design can be achieved. Finally, an innovative technique was derived to parametrically combine the diverse cost dimensions into a useful, quantifiable figure of merit for mission and research planning. Overall, it was shown that the most cost-effective solution is found by weighing all options along the nine dimensions of the cost paradigm within the context of a specific mission. Overall, the research advances the state of the art of hybrid rocket technology specifically, and satellite engineering in general.

Subjects/Keywords: 621.4356; Rocket motors

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Sellers, J. J. (1996). Investigation into hybrid rockets and other cost-effective propulsion system options for small satellites. (Doctoral Dissertation). University of Surrey. Retrieved from http://epubs.surrey.ac.uk/856470/ ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.309201

Chicago Manual of Style (16^th Edition):

Sellers, Jerry Jon. “Investigation into hybrid rockets and other cost-effective propulsion system options for small satellites.” 1996. Doctoral Dissertation, University of Surrey. Accessed February 28, 2021. http://epubs.surrey.ac.uk/856470/ ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.309201.

MLA Handbook (7^th Edition):

Sellers, Jerry Jon. “Investigation into hybrid rockets and other cost-effective propulsion system options for small satellites.” 1996. Web. 28 Feb 2021.

Vancouver:

Sellers JJ. Investigation into hybrid rockets and other cost-effective propulsion system options for small satellites. [Internet] [Doctoral dissertation]. University of Surrey; 1996. [cited 2021 Feb 28]. Available from: http://epubs.surrey.ac.uk/856470/ ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.309201.

Council of Science Editors:

Sellers JJ. Investigation into hybrid rockets and other cost-effective propulsion system options for small satellites. [Doctoral Dissertation]. University of Surrey; 1996. Available from: http://epubs.surrey.ac.uk/856470/ ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.309201

27. Badders, Brian David. Developing Hybrid Near-Space Technologies For Affordable Access To Suborbital Space.

Degree: MS, Space Studies, 2013, University of North Dakota

URL: https://commons.und.edu/theses/1502

► High power rockets and high altitude balloons are two near-space technologies that could be combined in order to provide access to the mesosphere and,… (more)

▼ High power rockets and high altitude balloons are two near-space technologies that could be combined in order to provide access to the mesosphere and, eventually, suborbital space. This "rockoon" technology has been used by several large budget space programs before being abandoned in favor of even more expensive, albeit more accurate, ground launch systems. With the increased development of nano-satellites and atmospheric sensors, combined with rising interest in global atmospheric data, there is an increase in desire for affordable access to extreme altitudes that does not necessarily require the precision of ground launches. Development of hybrid near-space technologies for access to over 200k ft. on a small budget brings many challenges within engineering, systems integration, cost analysis, market analysis, and business planning. This research includes the design and simulation testing of all the systems needed for a safe and reusable launch system, the cost analysis for initial production, the development of a business plan, and the development of a marketing plan. This project has both engineering and scientific significance in that it can prove the space readiness of new technologies, raise their technology readiness levels (TRLs), expedite the development process, and also provide new data to the scientific community. It also has the ability to stimulate university involvement in the aerospace industry and help to inspire the next generation of workers in the space sector. Previous development of high altitude balloon/high power rocket hybrid systems have been undertaken by government funded military programs or large aerospace corporations with varying degrees of success. However, there has yet to be a successful flight with this type of system which provides access to the upper mesosphere in a university setting. This project will aim to design and analyze a viable system while testing the engineering process under challenging budgetary constraints. The technical, engineering, and systems integration challenges that will be investigated are rocket design, launch platform design, communications, ignition systems, recovery systems, and stabilization methods. This will be done using rocket performance simulation software, computer-aided design software, and computational fluid dynamic analysis software. The business planning is also an important part of this research. Through detailed market analysis, the needs for the proposed product/services being developed will be assessed. Through the combination of detailed cost analysis and the market needs, the economic viability of this launch system will be determined. Advisors/Committee Members: Ronald A. Fevig.

Subjects/Keywords: balloon; engineering; mesosphere; rocket; rockoon; space

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Badders, B. D. (2013). Developing Hybrid Near-Space Technologies For Affordable Access To Suborbital Space. (Masters Thesis). University of North Dakota. Retrieved from https://commons.und.edu/theses/1502

Chicago Manual of Style (16^th Edition):

Badders, Brian David. “Developing Hybrid Near-Space Technologies For Affordable Access To Suborbital Space.” 2013. Masters Thesis, University of North Dakota. Accessed February 28, 2021. https://commons.und.edu/theses/1502.

MLA Handbook (7^th Edition):

Badders, Brian David. “Developing Hybrid Near-Space Technologies For Affordable Access To Suborbital Space.” 2013. Web. 28 Feb 2021.

Vancouver:

Badders BD. Developing Hybrid Near-Space Technologies For Affordable Access To Suborbital Space. [Internet] [Masters thesis]. University of North Dakota; 2013. [cited 2021 Feb 28]. Available from: https://commons.und.edu/theses/1502.

Council of Science Editors:

Badders BD. Developing Hybrid Near-Space Technologies For Affordable Access To Suborbital Space. [Masters Thesis]. University of North Dakota; 2013. Available from: https://commons.und.edu/theses/1502

University of Bristol

28. Cobbald, T. J. The impingement of underexpanded, axisymmetric, rocket motor exhausts and cold jets on flat plates.

Degree: PhD, 1985, University of Bristol

URL: http://hdl.handle.net/1983/d67c1e71-1605-4bcc-b268-0cdf3ed9f470

Subjects/Keywords: 621.4356; Rocket motors

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Cobbald, T. J. (1985). The impingement of underexpanded, axisymmetric, rocket motor exhausts and cold jets on flat plates. (Doctoral Dissertation). University of Bristol. Retrieved from http://hdl.handle.net/1983/d67c1e71-1605-4bcc-b268-0cdf3ed9f470

Chicago Manual of Style (16^th Edition):

Cobbald, T J. “The impingement of underexpanded, axisymmetric, rocket motor exhausts and cold jets on flat plates.” 1985. Doctoral Dissertation, University of Bristol. Accessed February 28, 2021. http://hdl.handle.net/1983/d67c1e71-1605-4bcc-b268-0cdf3ed9f470.

MLA Handbook (7^th Edition):

Cobbald, T J. “The impingement of underexpanded, axisymmetric, rocket motor exhausts and cold jets on flat plates.” 1985. Web. 28 Feb 2021.

Vancouver:

Cobbald TJ. The impingement of underexpanded, axisymmetric, rocket motor exhausts and cold jets on flat plates. [Internet] [Doctoral dissertation]. University of Bristol; 1985. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/1983/d67c1e71-1605-4bcc-b268-0cdf3ed9f470.

Council of Science Editors:

Cobbald TJ. The impingement of underexpanded, axisymmetric, rocket motor exhausts and cold jets on flat plates. [Doctoral Dissertation]. University of Bristol; 1985. Available from: http://hdl.handle.net/1983/d67c1e71-1605-4bcc-b268-0cdf3ed9f470

Cranfield University

29. Dennis, C. W. A study of rocket exhaust particles.

Degree: PhD, 1996, Cranfield University

URL: http://dspace.lib.cranfield.ac.uk/handle/1826/3583 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.336464

► The exhaust plumes generated by rocket motors are of significant military importance for missile detection, recognition and communication due to their electromagnetic emission and propagation… (more)

Subjects/Keywords: 621.4356; Rocket motors

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Dennis, C. W. (1996). A study of rocket exhaust particles. (Doctoral Dissertation). Cranfield University. Retrieved from http://dspace.lib.cranfield.ac.uk/handle/1826/3583 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.336464

Chicago Manual of Style (16^th Edition):

Dennis, C W. “A study of rocket exhaust particles.” 1996. Doctoral Dissertation, Cranfield University. Accessed February 28, 2021. http://dspace.lib.cranfield.ac.uk/handle/1826/3583 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.336464.

MLA Handbook (7^th Edition):

Dennis, C W. “A study of rocket exhaust particles.” 1996. Web. 28 Feb 2021.

Vancouver:

Dennis CW. A study of rocket exhaust particles. [Internet] [Doctoral dissertation]. Cranfield University; 1996. [cited 2021 Feb 28]. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/3583 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.336464.

Council of Science Editors:

Dennis CW. A study of rocket exhaust particles. [Doctoral Dissertation]. Cranfield University; 1996. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/3583 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.336464

Delft University of Technology

30. Motsyk, O.O. (author). Design of a Solid Rocket Motor for a Transonic Research Vehicle.

Degree: 2015, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:b5480136-5082-44fb-9a42-f29e5a3027c5

►

Hypresearch is a project that has been under development with the collaboration of ATG Europe, TU Delft, TNO for the past 7+ years. The eventual… (more)

▼

Hypresearch is a project that has been under development with the collaboration of ATG Europe, TU Delft, TNO for the past 7+ years. The eventual goal of the project is to fly a hypersonic research vehicle at Mach 6 (2 km/s) at an altitude of 42km for a continuous time interval of 360 seconds. Before this goal can be attained, however, several milestones must be achieved, the first of which is the testing of aircraft controls during launch in the transonic phase. The current Hypresearch mission envisions a first-stage separation and second-stage ignition at transonic velocities, hence it is important that all crucial systems function properly in the transonic regime. To achieve this, the Transonic Research Vehicle (TRV) project was set up. The subject of the thesis was the propulsion system of the TRV-1, with the goal of accelerating a glider payload to Mach-2 in vertical launch, and testing the payload separation mechanism while decelerating through the transonic phase. The goal of the thesis project was to design a solid rocket motor for the TRV-1, and to verify its performance through simulations and static motor tests. Firstly, the project goal was broken down into a series of requirements. Main requirements included the velocity (Mach 2) to be attained by the vehicle, the mass (6.25kg) and pre-defined shape of the glider, as well as limitations on the acceleration (40g) and resources in terms of cost, manpower, and materials/facilities accessible to students. The design process started with the preliminary design during which two design concepts were selected based on ballistic performance and trajectory simulations. In the detailed design phase, materials were selected and a detailed manufacturing, assembly, integration, and testing plan was drafted. In order to test the material properties of the selected design on a limited resources budget, a scaled-down test method—the so-called SGM or Single Grain Motor method was developed. Following a series of SGM tests, the final full-scale test configuration was selected, and several defects of the design were eradicated. However, during the SGM test campaigns, and the subsequent full-scale test, it was discovered that the actual performance in terms of total impulse was notably lower than that predicted by the model. Following the test campaigns, an investigation identified the causes of the performance loss to be excess water absorbed by the propellant during the curing process. A manufacturing method to prevent this in the future, as well as a design iteration of the motor to be performed in order to attain the mission goal, was recommended.

SSE

Space Systems Engineering

Aerospace Engineering

Advisors/Committee Members: Cervone, A. (mentor).

Subjects/Keywords: SRM; rocket; motor; propulsion; design; MAIT

Record Details Similar Records Cite « Share

❌

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

APA (6^th Edition):

Motsyk, O. O. (. (2015). Design of a Solid Rocket Motor for a Transonic Research Vehicle. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:b5480136-5082-44fb-9a42-f29e5a3027c5

Chicago Manual of Style (16^th Edition):

Motsyk, O O (author). “Design of a Solid Rocket Motor for a Transonic Research Vehicle.” 2015. Masters Thesis, Delft University of Technology. Accessed February 28, 2021. http://resolver.tudelft.nl/uuid:b5480136-5082-44fb-9a42-f29e5a3027c5.

MLA Handbook (7^th Edition):

Motsyk, O O (author). “Design of a Solid Rocket Motor for a Transonic Research Vehicle.” 2015. Web. 28 Feb 2021.

Vancouver:

Motsyk OO(. Design of a Solid Rocket Motor for a Transonic Research Vehicle. [Internet] [Masters thesis]. Delft University of Technology; 2015. [cited 2021 Feb 28]. Available from: http://resolver.tudelft.nl/uuid:b5480136-5082-44fb-9a42-f29e5a3027c5.

Council of Science Editors:

Motsyk OO(. Design of a Solid Rocket Motor for a Transonic Research Vehicle. [Masters Thesis]. Delft University of Technology; 2015. Available from: http://resolver.tudelft.nl/uuid:b5480136-5082-44fb-9a42-f29e5a3027c5

		in
And / Or
		in
And / Or
		in
And / Or
		in

Open Access Theses and Dissertations