subject:(developement of rocket engines)

Brno University of Technology

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

Degree: 2019, Brno University of Technology

► 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

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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

2. 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

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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

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

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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

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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

Ryerson University

5. 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

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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

Oregon State University

6. 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

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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

Texas Tech University

7. Grimes, Montgomery Dean. Design and construction of a multimode, regulated power supply for use on a 30 kilowatt arcjet.

Degree: 1990, Texas Tech University

URL: http://hdl.handle.net/2346/11798

► The power supply, used in this experiment, was designed from the start as a power source for a laboratory arcjet experiment. Therefore, it was never… (more)

Subjects/Keywords: Arcjet rocket engines

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APA (6^th Edition):

Grimes, M. D. (1990). Design and construction of a multimode, regulated power supply for use on a 30 kilowatt arcjet. (Thesis). Texas Tech University. Retrieved from http://hdl.handle.net/2346/11798

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):

Grimes, Montgomery Dean. “Design and construction of a multimode, regulated power supply for use on a 30 kilowatt arcjet.” 1990. Thesis, Texas Tech University. Accessed February 28, 2021. http://hdl.handle.net/2346/11798.

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

MLA Handbook (7^th Edition):

Grimes, Montgomery Dean. “Design and construction of a multimode, regulated power supply for use on a 30 kilowatt arcjet.” 1990. Web. 28 Feb 2021.

Vancouver:

Grimes MD. Design and construction of a multimode, regulated power supply for use on a 30 kilowatt arcjet. [Internet] [Thesis]. Texas Tech University; 1990. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/2346/11798.

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

Council of Science Editors:

Grimes MD. Design and construction of a multimode, regulated power supply for use on a 30 kilowatt arcjet. [Thesis]. Texas Tech University; 1990. Available from: http://hdl.handle.net/2346/11798

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

University of Arizona

8. Sekhon, Kalwant Singh, 1938-. Thrust vectoring experiments with gas injection .

Degree: 1964, University of Arizona

URL: http://hdl.handle.net/10150/319830

Subjects/Keywords: Rocket engines – Thrust.

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APA (6^th Edition):

Sekhon, Kalwant Singh, 1. (1964). Thrust vectoring experiments with gas injection . (Masters Thesis). University of Arizona. Retrieved from http://hdl.handle.net/10150/319830

Chicago Manual of Style (16^th Edition):

Sekhon, Kalwant Singh, 1938-. “Thrust vectoring experiments with gas injection .” 1964. Masters Thesis, University of Arizona. Accessed February 28, 2021. http://hdl.handle.net/10150/319830.

MLA Handbook (7^th Edition):

Sekhon, Kalwant Singh, 1938-. “Thrust vectoring experiments with gas injection .” 1964. Web. 28 Feb 2021.

Vancouver:

Sekhon, Kalwant Singh 1. Thrust vectoring experiments with gas injection . [Internet] [Masters thesis]. University of Arizona; 1964. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/10150/319830.

Council of Science Editors:

Sekhon, Kalwant Singh 1. Thrust vectoring experiments with gas injection . [Masters Thesis]. University of Arizona; 1964. Available from: http://hdl.handle.net/10150/319830

Brno University of Technology

9. Říha, Jaroslav. Historie motorů BMW: History of BMW engines.

Degree: 2019, Brno University of Technology

URL: http://hdl.handle.net/11012/6250

► This bachelor thesis deals with the foundantion of the company BMW in Munich, the development of air, motorcycle and car engines, from their beginning to… (more)

Subjects/Keywords: Historický přehled vývoje; BMW; technická specifikace motorů; výkonnostní parametry.; Historical view of the developement; BMW; technical specifications of the engines; performance parameters.

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APA (6^th Edition):

Říha, J. (2019). Historie motorů BMW: History of BMW engines. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/6250

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):

Říha, Jaroslav. “Historie motorů BMW: History of BMW engines.” 2019. Thesis, Brno University of Technology. Accessed February 28, 2021. http://hdl.handle.net/11012/6250.

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

MLA Handbook (7^th Edition):

Říha, Jaroslav. “Historie motorů BMW: History of BMW engines.” 2019. Web. 28 Feb 2021.

Vancouver:

Říha J. Historie motorů BMW: History of BMW engines. [Internet] [Thesis]. Brno University of Technology; 2019. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/11012/6250.

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

Council of Science Editors:

Říha J. Historie motorů BMW: History of BMW engines. [Thesis]. Brno University of Technology; 2019. Available from: http://hdl.handle.net/11012/6250

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

Brno University of Technology

10. Kříž, Tomáš. Hybridní raketové motory pro přesné provedení vesmírných manévrů: Throttleable hybrid rocket engines for precise aerospace manoeuvres.

Degree: 2019, Brno University of Technology

URL: http://hdl.handle.net/11012/176633

► Aim of this bachelor thesis is to describe current knowledge of hybrid rocket propulsion. Thesis describes the development of hybrid rocket engine, including its precise… (more)

Subjects/Keywords: Hybridní raketové motory (HRM); vesmírné manévry; paliva pro hybridní motory; okysličovadla pro hybridní motory; parametry raketových motorů; srovnání HRM s tradičními; vývoj HRM.; Hybrid rocket engines (HRE); space manoeuvres; propellants for hybrid engines; oxidizers for hybrid engines; parameters of hybrid engines; development of HRE.

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APA (6^th Edition):

Kříž, T. (2019). Hybridní raketové motory pro přesné provedení vesmírných manévrů: Throttleable hybrid rocket engines for precise aerospace manoeuvres. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/176633

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):

Kříž, Tomáš. “Hybridní raketové motory pro přesné provedení vesmírných manévrů: Throttleable hybrid rocket engines for precise aerospace manoeuvres.” 2019. Thesis, Brno University of Technology. Accessed February 28, 2021. http://hdl.handle.net/11012/176633.

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

MLA Handbook (7^th Edition):

Kříž, Tomáš. “Hybridní raketové motory pro přesné provedení vesmírných manévrů: Throttleable hybrid rocket engines for precise aerospace manoeuvres.” 2019. Web. 28 Feb 2021.

Vancouver:

Kříž T. Hybridní raketové motory pro přesné provedení vesmírných manévrů: Throttleable hybrid rocket engines for precise aerospace manoeuvres. [Internet] [Thesis]. Brno University of Technology; 2019. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/11012/176633.

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

Council of Science Editors:

Kříž T. Hybridní raketové motory pro přesné provedení vesmírných manévrů: Throttleable hybrid rocket engines for precise aerospace manoeuvres. [Thesis]. Brno University of Technology; 2019. Available from: http://hdl.handle.net/11012/176633

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

Ryerson University

11. Baczynski, Christopher. Effects Of Grain Geometry And Vibration On The Suppression Of Combustion Instability In A Solid Rocket Motor.

Degree: 2008, Ryerson University

URL: https://digital.library.ryerson.ca/islandora/object/RULA%3A1697

► A comprehensive numerical model for internal ballistic simulation under dynamic flow, combustion and structural vibration conditions is used to investigate the effectiveness of grain port… (more)

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

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APA (6^th Edition):

Baczynski, C. (2008). Effects Of Grain Geometry And Vibration On The Suppression Of Combustion Instability In A Solid Rocket Motor. (Thesis). Ryerson University. Retrieved from https://digital.library.ryerson.ca/islandora/object/RULA%3A1697

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):

Baczynski, Christopher. “Effects Of Grain Geometry And Vibration On The Suppression Of Combustion Instability In A Solid Rocket Motor.” 2008. Thesis, Ryerson University. Accessed February 28, 2021. https://digital.library.ryerson.ca/islandora/object/RULA%3A1697.

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

MLA Handbook (7^th Edition):

Baczynski, Christopher. “Effects Of Grain Geometry And Vibration On The Suppression Of Combustion Instability In A Solid Rocket Motor.” 2008. Web. 28 Feb 2021.

Vancouver:

Baczynski C. Effects Of Grain Geometry And Vibration On The Suppression Of Combustion Instability In A Solid Rocket Motor. [Internet] [Thesis]. Ryerson University; 2008. [cited 2021 Feb 28]. Available from: https://digital.library.ryerson.ca/islandora/object/RULA%3A1697.

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

Council of Science Editors:

Baczynski C. Effects Of Grain Geometry And Vibration On The Suppression Of Combustion Instability In A Solid Rocket Motor. [Thesis]. Ryerson University; 2008. Available from: https://digital.library.ryerson.ca/islandora/object/RULA%3A1697

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

Georgia Tech

12. Lioi, Christopher. Linear combustion stabiliy analysis of oxidizer-rich staged combustion engines.

Degree: PhD, Aerospace Engineering, 2019, Georgia Tech

URL: http://hdl.handle.net/1853/62579

► This thesis concerns the consistent linear acoustic stability analysis of an engine modeled on the RD-170, a prototypical example of an Oxidizer Rich Staged Combustion… (more)

▼ This thesis concerns the consistent linear acoustic stability analysis of an engine modeled on the RD-170, a prototypical example of an Oxidizer Rich Staged Combustion (ORSC) engine. Both the preburner-turbine assembly as well as the main combustion chamber are studied. The theoretical basis for the stability analysis is an inhomogeneous acoustic wave equation in the pressure. Boundary effects are accounted for by means of impedance boundary conditions. Theoretical impedance models are employed to describe the physics of various components: the turbine inlet blade row in the preburner assembly, and the flow distributor in the main chamber. In the main chamber, mean flow and combustion response effects are accounted for by means of right hand side source terms in the wave equation. Two cases are considered for mean flow: piecewise uniform and swirl flow. The swirl flow is generated by time averaging the results from LES of the main chamber injectors. It is found that the mean flow contributes significant damping to the system by means of convecting acoustic energy out of the domain. The swirl flow additionally provides acoustic refraction which further increases the damping. Overall the mean flow is found to far eclipse the other sources of damping. The response of the combustion to acoustic perturbations is quantified by means of a Flame Transfer Function (FTF). Spatially distributed fields for both the FTF gain and phase are computed from LES data using POD reduction for three different injector recess lengths. A chamber-level response field is constructed as a superposition of fields for individual injectors. It is found that as the recess length decreases, the system becomes more unstable, due to the fact that the base of the injector nonpremixed flame becomes more exposed to the transverse oscillations in the main chamber. A sensitivity analysis is conducted on a reduced set of scalar quantities which characterize the distributed combustion response fields. The eigenvalue results are found to be most sensitive to the maximum of the gain field, the axial spread of the gain about this maximum value, and the maximum axial slope of the phase field. The radial location of the maximum gain also affects the stability to a lesser extent. The results suggest that to maximize the stability margin of the engine the recess length of the injector should be maximized and the fluid conditions should be such that the flame is wide and combustion is distributed over as large an axial extent as possible. Advisors/Committee Members: Yang, Vigor (advisor), Ahuja, Krish (committee member), Sankar, Lakshmi (committee member), Lieuwen, Timothy (committee member), Funk, Robert (committee member).

Subjects/Keywords: Combustion instabilities; Acoustics; Liquid rocket engines; ORSC engines; Finite element analysis; LES; Flame transfer function

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APA (6^th Edition):

Lioi, C. (2019). Linear combustion stabiliy analysis of oxidizer-rich staged combustion engines. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/62579

Chicago Manual of Style (16^th Edition):

Lioi, Christopher. “Linear combustion stabiliy analysis of oxidizer-rich staged combustion engines.” 2019. Doctoral Dissertation, Georgia Tech. Accessed February 28, 2021. http://hdl.handle.net/1853/62579.

MLA Handbook (7^th Edition):

Lioi, Christopher. “Linear combustion stabiliy analysis of oxidizer-rich staged combustion engines.” 2019. Web. 28 Feb 2021.

Vancouver:

Lioi C. Linear combustion stabiliy analysis of oxidizer-rich staged combustion engines. [Internet] [Doctoral dissertation]. Georgia Tech; 2019. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/1853/62579.

Council of Science Editors:

Lioi C. Linear combustion stabiliy analysis of oxidizer-rich staged combustion engines. [Doctoral Dissertation]. Georgia Tech; 2019. Available from: http://hdl.handle.net/1853/62579

Ryerson University

13. Wongyai, Potchara. Fuel regression rate estimation model for swirling-flow hybrid rocket engines.

Degree: 2015, Ryerson University

URL: https://digital.library.ryerson.ca/islandora/object/RULA%3A3644

► In the current study, an analytical model to estimate the fuel surface regression rate of hybrid rocket engines with head-end swirling flow oxidizer injection is… (more)

Subjects/Keywords: Rocket engines – Fluid dynamics.; Fluid mechanics.; Propulsion systems – Mathematical models.

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

APA (6^th Edition):

Wongyai, P. (2015). Fuel regression rate estimation model for swirling-flow hybrid rocket engines. (Thesis). Ryerson University. Retrieved from https://digital.library.ryerson.ca/islandora/object/RULA%3A3644

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):

Wongyai, Potchara. “Fuel regression rate estimation model for swirling-flow hybrid rocket engines.” 2015. Thesis, Ryerson University. Accessed February 28, 2021. https://digital.library.ryerson.ca/islandora/object/RULA%3A3644.

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

MLA Handbook (7^th Edition):

Wongyai, Potchara. “Fuel regression rate estimation model for swirling-flow hybrid rocket engines.” 2015. Web. 28 Feb 2021.

Vancouver:

Wongyai P. Fuel regression rate estimation model for swirling-flow hybrid rocket engines. [Internet] [Thesis]. Ryerson University; 2015. [cited 2021 Feb 28]. Available from: https://digital.library.ryerson.ca/islandora/object/RULA%3A3644.

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

Council of Science Editors:

Wongyai P. Fuel regression rate estimation model for swirling-flow hybrid rocket engines. [Thesis]. Ryerson University; 2015. Available from: https://digital.library.ryerson.ca/islandora/object/RULA%3A3644

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

Cranfield University

14. Tucker, J. A whole life assessment of extruded double base propellants.

Degree: PhD, 2013, Cranfield University

URL: http://dspace.lib.cranfield.ac.uk/handle/1826/8032

► The manufacturing process for solventless extruded double base propellants involves a number of rolling and reworking stages. Throughout these processes a decrease in weight average… (more)

▼ The manufacturing process for solventless extruded double base propellants involves a number of rolling and reworking stages. Throughout these processes a decrease in weight average molecular weight was observed, this was attributed to denitration. Differential scanning calorimetery data indicated that the reworking stages of extruded double base propellant manufacture were crucial to the homogenisation of the propellant mixture. To determine the homogeneity of the final extruded product, a sample was analysed across its diameter. No variations in stabiliser concentration, molecular weight, or Vickers hardness were detected. An accelerated thermal ageing trial simulating up to 8 years of ageing at 25°C was carried out to evaluate the storage characteristics. Reductions in stabiliser concentration, number average molecular weight, weight average molecular weight and polydispersity compared with un-aged samples were observed. The glass transition temperature measured using differential scanning calorimetery decreased by ~3°C. The decrease was attributed to the initial denitration reducing the energy of bond rotation and shortening the polymer chains, both factors reducing the energy required for movement. Modulus values determined from dynamic mechanical analysis temperature scanning experiments, did not detect significant variation between un-aged and aged samples. Though it was considered that variations would be likely if a more extensive ageing program was completed. In order to evaluate propellant behaviour at very high and low frequencies, time temperature superposition (TTS) and creep testing were carried out. The TTS technique superpositioned data well, allowing future investigation of high frequency propellant properties. Creep testing was considered to be an appropriate approach, though the equipment available was not optimised for such testing. This thesis is concerned with understanding how propellants are manufactured from nitrocellulose, nitroglycerine and other constituents. It is also about how the propellants decompose during long periods of time in storage, and how these changes can be measured using thermal and mechanical methods. It is about how the physical, chemical and thermal properties of the propellant composition change throughout the manufacture. This is relevant as it could be used to develop more efficient manufacturing processes, allow operators to adjust processes to tailor product properties or be used to re-design manufacturing to compensate for a different starting material. The thesis also considers how and why the properties of the product change over the course of years of storage. A specific focus on whether changes in mechanical and thermal properties occur, and if so how they can be detected.

Subjects/Keywords: Nitrocellulose; Double-based rocket propellants; Propulsion, engines and fuels

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

APA (6^th Edition):

Tucker, J. (2013). A whole life assessment of extruded double base propellants. (Doctoral Dissertation). Cranfield University. Retrieved from http://dspace.lib.cranfield.ac.uk/handle/1826/8032

Chicago Manual of Style (16^th Edition):

Tucker, J. “A whole life assessment of extruded double base propellants.” 2013. Doctoral Dissertation, Cranfield University. Accessed February 28, 2021. http://dspace.lib.cranfield.ac.uk/handle/1826/8032.

MLA Handbook (7^th Edition):

Tucker, J. “A whole life assessment of extruded double base propellants.” 2013. Web. 28 Feb 2021.

Vancouver:

Tucker J. A whole life assessment of extruded double base propellants. [Internet] [Doctoral dissertation]. Cranfield University; 2013. [cited 2021 Feb 28]. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/8032.

Council of Science Editors:

Tucker J. A whole life assessment of extruded double base propellants. [Doctoral Dissertation]. Cranfield University; 2013. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/8032

Cranfield University

15. Tucker, J. A whole life assessment of extruded double base propellants.

Degree: PhD, 2013, Cranfield University

URL: http://dspace.lib.cranfield.ac.uk/handle/1826/8032 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.578041

► The manufacturing process for solventless extruded double base propellants involves a number of rolling and reworking stages. Throughout these processes a decrease in weight average… (more)

▼ The manufacturing process for solventless extruded double base propellants involves a number of rolling and reworking stages. Throughout these processes a decrease in weight average molecular weight was observed, this was attributed to denitration. Differential scanning calorimetery data indicated that the reworking stages of extruded double base propellant manufacture were crucial to the homogenisation of the propellant mixture. To determine the homogeneity of the final extruded product, a sample was analysed across its diameter. No variations in stabiliser concentration, molecular weight, or Vickers hardness were detected. An accelerated thermal ageing trial simulating up to 8 years of ageing at 25°C was carried out to evaluate the storage characteristics. Reductions in stabiliser concentration, number average molecular weight, weight average molecular weight and polydispersity compared with un-aged samples were observed. The glass transition temperature measured using differential scanning calorimetery decreased by ~3°C. The decrease was attributed to the initial denitration reducing the energy of bond rotation and shortening the polymer chains, both factors reducing the energy required for movement. Modulus values determined from dynamic mechanical analysis temperature scanning experiments, did not detect significant variation between un-aged and aged samples. Though it was considered that variations would be likely if a more extensive ageing program was completed. In order to evaluate propellant behaviour at very high and low frequencies, time temperature superposition (TTS) and creep testing were carried out. The TTS technique superpositioned data well, allowing future investigation of high frequency propellant properties. Creep testing was considered to be an appropriate approach, though the equipment available was not optimised for such testing. This thesis is concerned with understanding how propellants are manufactured from nitrocellulose, nitroglycerine and other constituents. It is also about how the propellants decompose during long periods of time in storage, and how these changes can be measured using thermal and mechanical methods. It is about how the physical, chemical and thermal properties of the propellant composition change throughout the manufacture. This is relevant as it could be used to develop more efficient manufacturing processes, allow operators to adjust processes to tailor product properties or be used to re-design manufacturing to compensate for a different starting material. The thesis also considers how and why the properties of the product change over the course of years of storage. A specific focus on whether changes in mechanical and thermal properties occur, and if so how they can be detected.

Subjects/Keywords: 662; Nitrocellulose; Double-based rocket propellants; Propulsion, engines and fuels

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APA (6^th Edition):

Tucker, J. (2013). A whole life assessment of extruded double base propellants. (Doctoral Dissertation). Cranfield University. Retrieved from http://dspace.lib.cranfield.ac.uk/handle/1826/8032 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.578041

Chicago Manual of Style (16^th Edition):

Tucker, J. “A whole life assessment of extruded double base propellants.” 2013. Doctoral Dissertation, Cranfield University. Accessed February 28, 2021. http://dspace.lib.cranfield.ac.uk/handle/1826/8032 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.578041.

MLA Handbook (7^th Edition):

Tucker, J. “A whole life assessment of extruded double base propellants.” 2013. Web. 28 Feb 2021.

Vancouver:

Tucker J. A whole life assessment of extruded double base propellants. [Internet] [Doctoral dissertation]. Cranfield University; 2013. [cited 2021 Feb 28]. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/8032 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.578041.

Council of Science Editors:

Tucker J. A whole life assessment of extruded double base propellants. [Doctoral Dissertation]. Cranfield University; 2013. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/8032 ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.578041

16. Arunachalam, Swaminath Adi. The drag resistance of burning drops.

Degree: PhD, 1965, Imperial College London

URL: http://hdl.handle.net/10044/1/16980

► An experimental study has been made of the drag resistance of burning drops. Distance-time records of single freely falling drops of iso-pentane n-heptane and benzene,… (more)

Subjects/Keywords: 629.134; Rocket engines, Combustion

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APA (6^th Edition):

Arunachalam, S. A. (1965). The drag resistance of burning drops. (Doctoral Dissertation). Imperial College London. Retrieved from http://hdl.handle.net/10044/1/16980

Chicago Manual of Style (16^th Edition):

Arunachalam, Swaminath Adi. “The drag resistance of burning drops.” 1965. Doctoral Dissertation, Imperial College London. Accessed February 28, 2021. http://hdl.handle.net/10044/1/16980.

MLA Handbook (7^th Edition):

Arunachalam, Swaminath Adi. “The drag resistance of burning drops.” 1965. Web. 28 Feb 2021.

Vancouver:

Arunachalam SA. The drag resistance of burning drops. [Internet] [Doctoral dissertation]. Imperial College London; 1965. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/10044/1/16980.

Council of Science Editors:

Arunachalam SA. The drag resistance of burning drops. [Doctoral Dissertation]. Imperial College London; 1965. Available from: http://hdl.handle.net/10044/1/16980

Kristianstad University

17. Alwandi, Roaa. From "Abnormal" Orphan to Celebrated Hero: A discussion of Harry's development in J.K. Rowling's Harry Potter and the Philosopher's Stone.

Degree: Kristianstad University, 2012, Kristianstad University

URL: http://urn.kb.se/resolve?urn=urn:nbn:se:hkr:diva-10216

► This essay will exlopre the character of one of our times most beloved fictional characters, Harry Potter. The purpose of this esay is to… (more)

Subjects/Keywords: Harry Potter; Developement of character; characterisation analysis

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APA (6^th Edition):

Alwandi, R. (2012). From "Abnormal" Orphan to Celebrated Hero: A discussion of Harry's development in J.K. Rowling's Harry Potter and the Philosopher's Stone. (Thesis). Kristianstad University. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:hkr:diva-10216

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):

Alwandi, Roaa. “From "Abnormal" Orphan to Celebrated Hero: A discussion of Harry's development in J.K. Rowling's Harry Potter and the Philosopher's Stone.” 2012. Thesis, Kristianstad University. Accessed February 28, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:hkr:diva-10216.

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

MLA Handbook (7^th Edition):

Alwandi, Roaa. “From "Abnormal" Orphan to Celebrated Hero: A discussion of Harry's development in J.K. Rowling's Harry Potter and the Philosopher's Stone.” 2012. Web. 28 Feb 2021.

Vancouver:

Alwandi R. From "Abnormal" Orphan to Celebrated Hero: A discussion of Harry's development in J.K. Rowling's Harry Potter and the Philosopher's Stone. [Internet] [Thesis]. Kristianstad University; 2012. [cited 2021 Feb 28]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:hkr:diva-10216.

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

Council of Science Editors:

Alwandi R. From "Abnormal" Orphan to Celebrated Hero: A discussion of Harry's development in J.K. Rowling's Harry Potter and the Philosopher's Stone. [Thesis]. Kristianstad University; 2012. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:hkr:diva-10216

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

Indian Institute of Science

18. Biju Kumar, K S. Role Of Hydrogen Injection Temperature On The Combustion Instability Of Cryogenic Rocket Engine.

Degree: PhD, Faculty of Engineering, 2014, Indian Institute of Science

URL: http://etd.iisc.ac.in/handle/2005/2297

► Physical mechanism for high frequency instability in cryogenic engines at low hydrogen injection temperature has been a subject of debate for long time. Experimental and… (more)

▼ Physical mechanism for high frequency instability in cryogenic engines at low hydrogen injection temperature has been a subject of debate for long time. Experimental and early developmental studies revealed no instabilities and it was only much later when liquid hydrogen at lower initial temperature (~50 to 100 K) was injected into the combustion chamber that instabilities were detected. From the compilations of the experimental data related to the instability of cryogenic engines by Hulka and Hutt, it was found that the instability was strongly connected to the temperature of hydrogen. Experiments conducted with hydrogen temperature ramping from a higher value to lower values indicated that the temperatures in excess of 90 K favor stability under most practical operating conditions. Even though this has been known for over forty years, there has been no clear and simple explanation for this. Many physical mechanisms have been hypothesized to explain how temperature ramping causes instability, but all appear to have limited range of applicability. Current understanding of cryogenic engine combustion instability has been achieved through a combination of experimental investigation and approximate analytical models as well as CFD tools. Various researchers have tried to link the low hydrogen injection temperature combustion instability phenomena with various potential mechanisms for combustion instability. They involve coupling of combustion acoustics with atomization, vaporization, mixing, chemical kinetics or any combination of these processes. Various studies related to the effect of recess, injector hydrodynamics, acoustic damping of gas liquid scheme injectors and effect of drop size distribution on the stability characteristics of cryogenic engines were compiled in the thesis. Several researchers examined fuel droplet vaporization as the rate controlling mechanism. Recently a new method for the evaluation of stability characteristics of the engine using model chamber were proposed by Russians and this is based on mixing as the rate controlling mechanism. Pros and cons of this method were discussed. Some people examined the combustion instability of rocket engines based on chemistry dynamics. A considerable amount of analytical and numerical studies were carried out by various researchers for finding out the cause of combustion instability. Because of the limitations of their analysis, they could not successfully explain the cause of combustion instability at low hydrogen injection temperature. A compilation of previous numerical studies were carried out. A number of researchers have applied CFD in the study of combustion instabilities in liquid propellant rocket engines. In the present thesis, a theoretical model has been developed based on the vaporization of droplets to predict the stability characteristics of the engine. The proposed concept focuses on three dimensional simulation of combustion instability for giving some meaningful explanations for the experimental work presented in the literature. In the… Advisors/Committee Members: Paul, P J (advisor), Ranjan, N K S (advisor).

Subjects/Keywords: Liquid Propellant Rocket; Cryogenic Rocket Engines; Combustion Instability; Cryogenic Engines - Combustion Instability; Hydrogen Injection Temperature Combustion Instability; Cryogenic Engines - Combustion Modeling; Combustion Instability; Heat Engineering

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APA (6^th Edition):

Biju Kumar, K. S. (2014). Role Of Hydrogen Injection Temperature On The Combustion Instability Of Cryogenic Rocket Engine. (Doctoral Dissertation). Indian Institute of Science. Retrieved from http://etd.iisc.ac.in/handle/2005/2297

Chicago Manual of Style (16^th Edition):

Biju Kumar, K S. “Role Of Hydrogen Injection Temperature On The Combustion Instability Of Cryogenic Rocket Engine.” 2014. Doctoral Dissertation, Indian Institute of Science. Accessed February 28, 2021. http://etd.iisc.ac.in/handle/2005/2297.

MLA Handbook (7^th Edition):

Biju Kumar, K S. “Role Of Hydrogen Injection Temperature On The Combustion Instability Of Cryogenic Rocket Engine.” 2014. Web. 28 Feb 2021.

Vancouver:

Biju Kumar KS. Role Of Hydrogen Injection Temperature On The Combustion Instability Of Cryogenic Rocket Engine. [Internet] [Doctoral dissertation]. Indian Institute of Science; 2014. [cited 2021 Feb 28]. Available from: http://etd.iisc.ac.in/handle/2005/2297.

Council of Science Editors:

Biju Kumar KS. Role Of Hydrogen Injection Temperature On The Combustion Instability Of Cryogenic Rocket Engine. [Doctoral Dissertation]. Indian Institute of Science; 2014. Available from: http://etd.iisc.ac.in/handle/2005/2297

Georgia Tech

19. Wright, James Glynn. A study of clutches for use in a clutchoperated power screw actuator for space applications.

Degree: PhD, Mechanical engineering, 1968, Georgia Tech

URL: http://hdl.handle.net/1853/17399

Subjects/Keywords: Clutches (Machinery); Rocket engines Control systems

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APA (6^th Edition):

Wright, J. G. (1968). A study of clutches for use in a clutchoperated power screw actuator for space applications. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/17399

Chicago Manual of Style (16^th Edition):

Wright, James Glynn. “A study of clutches for use in a clutchoperated power screw actuator for space applications.” 1968. Doctoral Dissertation, Georgia Tech. Accessed February 28, 2021. http://hdl.handle.net/1853/17399.

MLA Handbook (7^th Edition):

Wright, James Glynn. “A study of clutches for use in a clutchoperated power screw actuator for space applications.” 1968. Web. 28 Feb 2021.

Vancouver:

Wright JG. A study of clutches for use in a clutchoperated power screw actuator for space applications. [Internet] [Doctoral dissertation]. Georgia Tech; 1968. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/1853/17399.

Council of Science Editors:

Wright JG. A study of clutches for use in a clutchoperated power screw actuator for space applications. [Doctoral Dissertation]. Georgia Tech; 1968. Available from: http://hdl.handle.net/1853/17399

Georgia Tech

20. Lores, Manuel Edward. A theoretical study of nonlinear longitudinal combustion instability in liquid propellant rocket engines.

Degree: PhD, Aerospace Engineering, 1972, Georgia Tech

URL: http://hdl.handle.net/1853/12440

Subjects/Keywords: Rocket engines Combustion; Liquid propellant rockets

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APA (6^th Edition):

Lores, M. E. (1972). A theoretical study of nonlinear longitudinal combustion instability in liquid propellant rocket engines. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/12440

Chicago Manual of Style (16^th Edition):

Lores, Manuel Edward. “A theoretical study of nonlinear longitudinal combustion instability in liquid propellant rocket engines.” 1972. Doctoral Dissertation, Georgia Tech. Accessed February 28, 2021. http://hdl.handle.net/1853/12440.

MLA Handbook (7^th Edition):

Lores, Manuel Edward. “A theoretical study of nonlinear longitudinal combustion instability in liquid propellant rocket engines.” 1972. Web. 28 Feb 2021.

Vancouver:

Lores ME. A theoretical study of nonlinear longitudinal combustion instability in liquid propellant rocket engines. [Internet] [Doctoral dissertation]. Georgia Tech; 1972. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/1853/12440.

Council of Science Editors:

Lores ME. A theoretical study of nonlinear longitudinal combustion instability in liquid propellant rocket engines. [Doctoral Dissertation]. Georgia Tech; 1972. Available from: http://hdl.handle.net/1853/12440

Georgia Tech

21. Kooker, Douglas Edward. Numerical solution of axial-mode instability problems in solid propellant rocket motors.

Degree: PhD, Aerospace Engineering, 1973, Georgia Tech

URL: http://hdl.handle.net/1853/13066

Subjects/Keywords: Solid propellant rockets; Rocket engines Combustion

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APA (6^th Edition):

Kooker, D. E. (1973). Numerical solution of axial-mode instability problems in solid propellant rocket motors. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/13066

Chicago Manual of Style (16^th Edition):

Kooker, Douglas Edward. “Numerical solution of axial-mode instability problems in solid propellant rocket motors.” 1973. Doctoral Dissertation, Georgia Tech. Accessed February 28, 2021. http://hdl.handle.net/1853/13066.

MLA Handbook (7^th Edition):

Kooker, Douglas Edward. “Numerical solution of axial-mode instability problems in solid propellant rocket motors.” 1973. Web. 28 Feb 2021.

Vancouver:

Kooker DE. Numerical solution of axial-mode instability problems in solid propellant rocket motors. [Internet] [Doctoral dissertation]. Georgia Tech; 1973. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/1853/13066.

Council of Science Editors:

Kooker DE. Numerical solution of axial-mode instability problems in solid propellant rocket motors. [Doctoral Dissertation]. Georgia Tech; 1973. Available from: http://hdl.handle.net/1853/13066

Virginia Tech

22. Qian, Xin. Flow field investigation in pulse 1 motor of a two-pulse solid rocket motor.

Degree: MS, Aerospace and Ocean Engineering, 1990, Virginia Tech

URL: http://hdl.handle.net/10919/41483

Subjects/Keywords: Rocket engines; LD5655.V855 1990.Q536

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APA (6^th Edition):

Qian, X. (1990). Flow field investigation in pulse 1 motor of a two-pulse solid rocket motor. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/41483

Chicago Manual of Style (16^th Edition):

Qian, Xin. “Flow field investigation in pulse 1 motor of a two-pulse solid rocket motor.” 1990. Masters Thesis, Virginia Tech. Accessed February 28, 2021. http://hdl.handle.net/10919/41483.

MLA Handbook (7^th Edition):

Qian, Xin. “Flow field investigation in pulse 1 motor of a two-pulse solid rocket motor.” 1990. Web. 28 Feb 2021.

Vancouver:

Qian X. Flow field investigation in pulse 1 motor of a two-pulse solid rocket motor. [Internet] [Masters thesis]. Virginia Tech; 1990. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/10919/41483.

Council of Science Editors:

Qian X. Flow field investigation in pulse 1 motor of a two-pulse solid rocket motor. [Masters Thesis]. Virginia Tech; 1990. Available from: http://hdl.handle.net/10919/41483

Virginia Tech

23. Hetreed, Christopher F. Internal flow investigation of an aft finocyl grain configuration in a solid rocket motor.

Degree: MS, Aerospace Engineering, 1989, Virginia Tech

URL: http://hdl.handle.net/10919/46038

► Cold-flow tests were conducted in mediums of air and water to investigate the internal flow field about the nozzle region of a proposed solid… (more)

Subjects/Keywords: Rocket engines; LD5655.V855 1989.H479

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APA (6^th Edition):

Hetreed, C. F. (1989). Internal flow investigation of an aft finocyl grain configuration in a solid rocket motor. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/46038

Chicago Manual of Style (16^th Edition):

Hetreed, Christopher F. “Internal flow investigation of an aft finocyl grain configuration in a solid rocket motor.” 1989. Masters Thesis, Virginia Tech. Accessed February 28, 2021. http://hdl.handle.net/10919/46038.

MLA Handbook (7^th Edition):

Hetreed, Christopher F. “Internal flow investigation of an aft finocyl grain configuration in a solid rocket motor.” 1989. Web. 28 Feb 2021.

Vancouver:

Hetreed CF. Internal flow investigation of an aft finocyl grain configuration in a solid rocket motor. [Internet] [Masters thesis]. Virginia Tech; 1989. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/10919/46038.

Council of Science Editors:

Hetreed CF. Internal flow investigation of an aft finocyl grain configuration in a solid rocket motor. [Masters Thesis]. Virginia Tech; 1989. Available from: http://hdl.handle.net/10919/46038

Virginia Tech

24. Lupi, Alessandro. CFD analysis and redesign of centrifugal impeller flows for rocket pumps.

Degree: MS, Mechanical Engineering, 1993, Virginia Tech

URL: http://hdl.handle.net/10919/43488

► The analysis and redesign of a centrifugal impeller for a rocket pump is presented in this thesis. A baseline impeller was designed by Rocketdyne… (more)

Subjects/Keywords: Rocket engines; LD5655.V855 1993.L875

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APA (6^th Edition):

Lupi, A. (1993). CFD analysis and redesign of centrifugal impeller flows for rocket pumps. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/43488

Chicago Manual of Style (16^th Edition):

Lupi, Alessandro. “CFD analysis and redesign of centrifugal impeller flows for rocket pumps.” 1993. Masters Thesis, Virginia Tech. Accessed February 28, 2021. http://hdl.handle.net/10919/43488.

MLA Handbook (7^th Edition):

Lupi, Alessandro. “CFD analysis and redesign of centrifugal impeller flows for rocket pumps.” 1993. Web. 28 Feb 2021.

Vancouver:

Lupi A. CFD analysis and redesign of centrifugal impeller flows for rocket pumps. [Internet] [Masters thesis]. Virginia Tech; 1993. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/10919/43488.

Council of Science Editors:

Lupi A. CFD analysis and redesign of centrifugal impeller flows for rocket pumps. [Masters Thesis]. Virginia Tech; 1993. Available from: http://hdl.handle.net/10919/43488

Virginia Tech

25. Doan, Andrew W. 3-D flow and performance of a rocket pump inducer at design and off-design flow rates.

Degree: MS, Mechanical Engineering, 1994, Virginia Tech

URL: http://hdl.handle.net/10919/46018

see document Advisors/Committee Members: Moore, John (committeechair), Brown, Eugene F. (committee member), Dancey, Clinton L. (committee member).

Subjects/Keywords: Rocket engines; LD5655.V855 1994.D636

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APA (6^th Edition):

Doan, A. W. (1994). 3-D flow and performance of a rocket pump inducer at design and off-design flow rates. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/46018

Chicago Manual of Style (16^th Edition):

Doan, Andrew W. “3-D flow and performance of a rocket pump inducer at design and off-design flow rates.” 1994. Masters Thesis, Virginia Tech. Accessed February 28, 2021. http://hdl.handle.net/10919/46018.

MLA Handbook (7^th Edition):

Doan, Andrew W. “3-D flow and performance of a rocket pump inducer at design and off-design flow rates.” 1994. Web. 28 Feb 2021.

Vancouver:

Doan AW. 3-D flow and performance of a rocket pump inducer at design and off-design flow rates. [Internet] [Masters thesis]. Virginia Tech; 1994. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/10919/46018.

Council of Science Editors:

Doan AW. 3-D flow and performance of a rocket pump inducer at design and off-design flow rates. [Masters Thesis]. Virginia Tech; 1994. Available from: http://hdl.handle.net/10919/46018

Virginia Tech

26. Dwyer, Michael E. Quasi-optimal steady state and transient maneuvers with and without thrust vectoring.

Degree: MS, Aerospace Engineering, 1993, Virginia Tech

URL: http://hdl.handle.net/10919/44931

see document Advisors/Committee Members: Lutze, Frederick H. Jr. (committeechair), Cliff, Eugene M. (committee member), Durham, Wayne C. (committee member).

Subjects/Keywords: Rocket engines; LD5655.V855 1993.D893

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

APA (6^th Edition):

Dwyer, M. E. (1993). Quasi-optimal steady state and transient maneuvers with and without thrust vectoring. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/44931

Chicago Manual of Style (16^th Edition):

Dwyer, Michael E. “Quasi-optimal steady state and transient maneuvers with and without thrust vectoring.” 1993. Masters Thesis, Virginia Tech. Accessed February 28, 2021. http://hdl.handle.net/10919/44931.

MLA Handbook (7^th Edition):

Dwyer, Michael E. “Quasi-optimal steady state and transient maneuvers with and without thrust vectoring.” 1993. Web. 28 Feb 2021.

Vancouver:

Dwyer ME. Quasi-optimal steady state and transient maneuvers with and without thrust vectoring. [Internet] [Masters thesis]. Virginia Tech; 1993. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/10919/44931.

Council of Science Editors:

Dwyer ME. Quasi-optimal steady state and transient maneuvers with and without thrust vectoring. [Masters Thesis]. Virginia Tech; 1993. Available from: http://hdl.handle.net/10919/44931

University of KwaZulu-Natal

27. Sithole, Thando. Monitoring and evaluation of training and development programmes within the office of the premier, KwaZulu-Natal province.

Degree: 2019, University of KwaZulu-Natal

URL: https://researchspace.ukzn.ac.za/handle/10413/17056

► The National Development Plan (NDP) highlights the need for a capable and developmental state. This capable and developmental state will be enabled by, inter alia,… (more)

▼ The National Development Plan (NDP) highlights the need for a capable and developmental state. This capable and developmental state will be enabled by, inter alia, a professional public service that has internalised the developmental state agenda, and the development of technical and specialist skills. Section 195 of the Constitution of the Republic of South Africa of 1996 outlines 10 principles governing public administration. These principles from the Constitution are largely linked to the development of a professional public service. The literature consulted by this study has raised a need for the training of administrators, and the role that can be played by the training initiatives in realising the envisaged NDP priorities and Constitutional mandates. The research had consulted numerous pieces of legislation at national and provincial levels that echoed the NDP and the Constitution of the Republic of South Africa of 1996. The National School of Government (NSG) has the national mandate to provide training to the public service, and the Office of the Premier, KwaZulu-Natal Provincial Public Service Training Academy (PPSTA) has the provincial mandate to provide this training to public servants. The PPSTA has been exceeding annual performance targets in terms of the number of public servants trained in the province over a number of financial years. This study explores the need for a subsequent phase, to measure whether the training provided by PPSTA has an impact to the trainees (public servants) and to the provincial departments. According to the Policy Framework for the Government-wide Monitoring and Evaluation of 2007 (M&E Framework of 2007) that informed the study, the outcomes assessment precedes impact assessment. The study hence conducted outcomes assessment and not impact assessment of training programmes provided by the PPSTA. The term ‘impact assessment’ has been “borrowed” by the study for ease of reference. It transpired in the literature and during the interactions with the respondents that the term ‘outcomes assessment’ was predominantly understood by established Monitoring and Evaluation (M&E) practitioners and aspiring M&E practitioners. The respondents were familiar with the term ‘impact assessment’. In conducting the impact (outcomes) assessment, the study randomly sampled 7 out of the population of 14 provincial departments that had received training in the 4 chosen training programmes during the 2013/14 financial year. The 2013/14 financial year was chosen for the study, given the assumption that the department would have gained sufficient time to monitor and evaluate the impact (outcomes) of training in accordance with M&E Framework of 2007 v outcomes assessment and the Framework for Managing Performance Information of 2007 guidelines. A pragmatism paradigm was chosen by the study to allow for triangulation of quantitative and qualitative techniques through a mixed methods approach. The study discovered that the training programmes conducted by PPSTA could be… Advisors/Committee Members: Subban, Mogesperie. (advisor).

Subjects/Keywords: Monitoring evaluation of training; Developement training; Office of the Premier

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

APA (6^th Edition):

Sithole, T. (2019). Monitoring and evaluation of training and development programmes within the office of the premier, KwaZulu-Natal province. (Thesis). University of KwaZulu-Natal. Retrieved from https://researchspace.ukzn.ac.za/handle/10413/17056

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):

Sithole, Thando. “Monitoring and evaluation of training and development programmes within the office of the premier, KwaZulu-Natal province.” 2019. Thesis, University of KwaZulu-Natal. Accessed February 28, 2021. https://researchspace.ukzn.ac.za/handle/10413/17056.

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

MLA Handbook (7^th Edition):

Sithole, Thando. “Monitoring and evaluation of training and development programmes within the office of the premier, KwaZulu-Natal province.” 2019. Web. 28 Feb 2021.

Vancouver:

Sithole T. Monitoring and evaluation of training and development programmes within the office of the premier, KwaZulu-Natal province. [Internet] [Thesis]. University of KwaZulu-Natal; 2019. [cited 2021 Feb 28]. Available from: https://researchspace.ukzn.ac.za/handle/10413/17056.

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

Council of Science Editors:

Sithole T. Monitoring and evaluation of training and development programmes within the office of the premier, KwaZulu-Natal province. [Thesis]. University of KwaZulu-Natal; 2019. Available from: https://researchspace.ukzn.ac.za/handle/10413/17056

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

Penn State University

28. Asif, Mohammed. PROTOTYPING AND OPTIMIZATION OF A MINIATURE MICROWAVE-FREQUENCY ION THRUSTER.

Degree: 2018, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/15219mxa310

► This thesis presents progress on the development of the Miniature Microwave-Frequency Ion Thruster (MMIT), currently being developed at Penn State as a microthruster with high… (more)

Subjects/Keywords: space propulsion; plasma propulsion; propulsion; electric propulsion; rocket propulsion; ion engines; microwave thruster; ion thruster; experimental research on electric propulsion; computational research on electric propulsion; miniaturization of electric propulsion; ion thrusters for CubeSats; electric propulsion for CubeSats

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

APA (6^th Edition):

Asif, M. (2018). PROTOTYPING AND OPTIMIZATION OF A MINIATURE MICROWAVE-FREQUENCY ION THRUSTER. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/15219mxa310

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):

Asif, Mohammed. “PROTOTYPING AND OPTIMIZATION OF A MINIATURE MICROWAVE-FREQUENCY ION THRUSTER.” 2018. Thesis, Penn State University. Accessed February 28, 2021. https://submit-etda.libraries.psu.edu/catalog/15219mxa310.

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

MLA Handbook (7^th Edition):

Asif, Mohammed. “PROTOTYPING AND OPTIMIZATION OF A MINIATURE MICROWAVE-FREQUENCY ION THRUSTER.” 2018. Web. 28 Feb 2021.

Vancouver:

Asif M. PROTOTYPING AND OPTIMIZATION OF A MINIATURE MICROWAVE-FREQUENCY ION THRUSTER. [Internet] [Thesis]. Penn State University; 2018. [cited 2021 Feb 28]. Available from: https://submit-etda.libraries.psu.edu/catalog/15219mxa310.

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

Council of Science Editors:

Asif M. PROTOTYPING AND OPTIMIZATION OF A MINIATURE MICROWAVE-FREQUENCY ION THRUSTER. [Thesis]. Penn State University; 2018. Available from: https://submit-etda.libraries.psu.edu/catalog/15219mxa310

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

Delft University of Technology

29. Wildvank, Roy (author). Launch vehicle structural mass prediction model.

Degree: 2018, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:bb943ec1-1a2a-462d-873e-05338b29235f

►

Accurate dry mass prediction is essential in early design phases of a launch system. To predict structural mass of a launch vehicle more accurate at… (more)

Subjects/Keywords: mass model; Launch Vehicle design; Launch Vehicle optimization; rocket structures; buckling of rocket structures

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

APA (6^th Edition):

Wildvank, R. (. (2018). Launch vehicle structural mass prediction model. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:bb943ec1-1a2a-462d-873e-05338b29235f

Chicago Manual of Style (16^th Edition):

Wildvank, Roy (author). “Launch vehicle structural mass prediction model.” 2018. Masters Thesis, Delft University of Technology. Accessed February 28, 2021. http://resolver.tudelft.nl/uuid:bb943ec1-1a2a-462d-873e-05338b29235f.

MLA Handbook (7^th Edition):

Wildvank, Roy (author). “Launch vehicle structural mass prediction model.” 2018. Web. 28 Feb 2021.

Vancouver:

Wildvank R(. Launch vehicle structural mass prediction model. [Internet] [Masters thesis]. Delft University of Technology; 2018. [cited 2021 Feb 28]. Available from: http://resolver.tudelft.nl/uuid:bb943ec1-1a2a-462d-873e-05338b29235f.

Council of Science Editors:

Wildvank R(. Launch vehicle structural mass prediction model. [Masters Thesis]. Delft University of Technology; 2018. Available from: http://resolver.tudelft.nl/uuid:bb943ec1-1a2a-462d-873e-05338b29235f

30. Perovšek, Jaka. Ray Tracing and Spectral Modelling of Excited Hydroxyl Radiation from Cryogenic Flames in Rocket Combustion Chambers.

Degree: Electrical and Space Engineering, 2018, Luleå University of Technology

URL: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-71277

► A visualisation procedure was developed which predicts excited hydroxyl (OH*) radiation from the Computational Fluid Dynamics (CFD) solutions of cryogenic hydrogen-oxygen rocket flames. The… (more)

Subjects/Keywords: spectral modelling; excited hydroxyl radiation; OH* radiation; ray tracing; spectroscopy; rocket combustion chambers; rocket engines; hydrogen-oxygen combustion; combustion instabilities; Aerospace Engineering; Rymd- och flygteknik

10 more images…

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

APA (6^th Edition):

Perovšek, J. (2018). Ray Tracing and Spectral Modelling of Excited Hydroxyl Radiation from Cryogenic Flames in Rocket Combustion Chambers. (Thesis). Luleå University of Technology. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-71277

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):

Perovšek, Jaka. “Ray Tracing and Spectral Modelling of Excited Hydroxyl Radiation from Cryogenic Flames in Rocket Combustion Chambers.” 2018. Thesis, Luleå University of Technology. Accessed February 28, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-71277.

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

MLA Handbook (7^th Edition):

Perovšek, Jaka. “Ray Tracing and Spectral Modelling of Excited Hydroxyl Radiation from Cryogenic Flames in Rocket Combustion Chambers.” 2018. Web. 28 Feb 2021.

Vancouver:

Perovšek J. Ray Tracing and Spectral Modelling of Excited Hydroxyl Radiation from Cryogenic Flames in Rocket Combustion Chambers. [Internet] [Thesis]. Luleå University of Technology; 2018. [cited 2021 Feb 28]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-71277.

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

Council of Science Editors:

Perovšek J. Ray Tracing and Spectral Modelling of Excited Hydroxyl Radiation from Cryogenic Flames in Rocket Combustion Chambers. [Thesis]. Luleå University of Technology; 2018. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-71277

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

Open Access Theses and Dissertations