Advanced search options

Advanced Search Options 🞨

Browse by author name (“Author name starts with…”).

Find ETDs with:

in
/  
in
/  
in
/  
in

Written in Published in Earliest date Latest date

Sorted by

Results per page:

Sorted by: relevance · author · university · dateNew search

You searched for subject:(Rocket engine). Showing records 1 – 30 of 52 total matches.

[1] [2]

Search Limiters

Last 2 Years | English Only

Levels

Country

▼ Search Limiters


University of KwaZulu-Natal

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

Degree: 2017, University of KwaZulu-Natal

 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)

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

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th 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 (16th 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 (7th 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


University of Adelaide

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

Degree: 2012, University of Adelaide

 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)

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

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th 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 (16th 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 (7th 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


University of KwaZulu-Natal

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

Degree: 2018, University of KwaZulu-Natal

 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)

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

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th 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 (16th 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 (7th 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

4. Chetty, Creason. The hydrodynamic design and analysis of an RP-1 pump for a liquid rocket engine.

Degree: 2018, University of KwaZulu-Natal

 South Africa has a fledgling satellite industry but lacks the ability to launch spacecraft into low Earth orbit. As a result, the University of KwaZulu-Natal’s… (more)

Subjects/Keywords: Hydrodynamic Design.; Pumps.; Liquid rocket engine.

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th Edition):

Chetty, C. (2018). The hydrodynamic design and analysis of an RP-1 pump for a liquid rocket engine. (Thesis). University of KwaZulu-Natal. Retrieved from https://researchspace.ukzn.ac.za/handle/10413/16627

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

Chicago Manual of Style (16th Edition):

Chetty, Creason. “The hydrodynamic design and analysis of an RP-1 pump for a liquid rocket engine.” 2018. Thesis, University of KwaZulu-Natal. Accessed February 28, 2021. https://researchspace.ukzn.ac.za/handle/10413/16627.

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

MLA Handbook (7th Edition):

Chetty, Creason. “The hydrodynamic design and analysis of an RP-1 pump for a liquid rocket engine.” 2018. Web. 28 Feb 2021.

Vancouver:

Chetty C. The hydrodynamic design and analysis of an RP-1 pump for a liquid rocket engine. [Internet] [Thesis]. University of KwaZulu-Natal; 2018. [cited 2021 Feb 28]. Available from: https://researchspace.ukzn.ac.za/handle/10413/16627.

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

Council of Science Editors:

Chetty C. The hydrodynamic design and analysis of an RP-1 pump for a liquid rocket engine. [Thesis]. University of KwaZulu-Natal; 2018. Available from: https://researchspace.ukzn.ac.za/handle/10413/16627

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


University of Tennessee – Knoxville

5. Akiki, Georges. On the Bidirectional Vortex Engine Flowfield with Arbitrary Endwall Injection.

Degree: MS, Aerospace Engineering, 2011, University of Tennessee – Knoxville

  In an attempt to generalize previous models of the bidirectional vortex mean flow, a new solution is presented that can cope with arbitrary injections… (more)

Subjects/Keywords: bidirectional; vortex; exact solution; rocket engine

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th Edition):

Akiki, G. (2011). On the Bidirectional Vortex Engine Flowfield with Arbitrary Endwall Injection. (Thesis). University of Tennessee – Knoxville. Retrieved from https://trace.tennessee.edu/utk_gradthes/945

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

Chicago Manual of Style (16th Edition):

Akiki, Georges. “On the Bidirectional Vortex Engine Flowfield with Arbitrary Endwall Injection.” 2011. Thesis, University of Tennessee – Knoxville. Accessed February 28, 2021. https://trace.tennessee.edu/utk_gradthes/945.

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

MLA Handbook (7th Edition):

Akiki, Georges. “On the Bidirectional Vortex Engine Flowfield with Arbitrary Endwall Injection.” 2011. Web. 28 Feb 2021.

Vancouver:

Akiki G. On the Bidirectional Vortex Engine Flowfield with Arbitrary Endwall Injection. [Internet] [Thesis]. University of Tennessee – Knoxville; 2011. [cited 2021 Feb 28]. Available from: https://trace.tennessee.edu/utk_gradthes/945.

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

Council of Science Editors:

Akiki G. On the Bidirectional Vortex Engine Flowfield with Arbitrary Endwall Injection. [Thesis]. University of Tennessee – Knoxville; 2011. Available from: https://trace.tennessee.edu/utk_gradthes/945

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


Brno University of Technology

6. 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

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th 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 (16th 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 (7th 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

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

Degree: 2014, 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

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th 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 (16th 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 (7th 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


Delft University of Technology

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

Degree: 2017, Delft University of Technology

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 DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th 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 (16th 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 (7th 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

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

Degree: 2019, Brno University of Technology

 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 DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th 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 (16th 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 (7th 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


University of KwaZulu-Natal

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

Degree: 2018, University of KwaZulu-Natal

 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)

Subjects/Keywords: CFD.; Centrifugal pumps.; Liquid oxygen.; Mean-line design.; Rocket engine.

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th 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 http://hdl.handle.net/10413/16064

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

Chicago Manual of Style (16th Edition):

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. http://hdl.handle.net/10413/16064.

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

MLA Handbook (7th 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: http://hdl.handle.net/10413/16064.

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: http://hdl.handle.net/10413/16064

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


Colorado State University

11. Miller, Nathan A. Development of a model for baffle energy dissipation in liquid fueled rocket engines.

Degree: MS(M.S.), Mechanical Engineering, 2010, Colorado State University

 In this thesis the energy dissipation from a combined hub and blade baffle structure in a combustion chamber of a liquid-fueled rocket engine is modeled… (more)

Subjects/Keywords: baffle; rocket engine; dissipation

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th Edition):

Miller, N. A. (2010). Development of a model for baffle energy dissipation in liquid fueled rocket engines. (Masters Thesis). Colorado State University. Retrieved from http://hdl.handle.net/10217/68387

Chicago Manual of Style (16th Edition):

Miller, Nathan A. “Development of a model for baffle energy dissipation in liquid fueled rocket engines.” 2010. Masters Thesis, Colorado State University. Accessed February 28, 2021. http://hdl.handle.net/10217/68387.

MLA Handbook (7th Edition):

Miller, Nathan A. “Development of a model for baffle energy dissipation in liquid fueled rocket engines.” 2010. Web. 28 Feb 2021.

Vancouver:

Miller NA. Development of a model for baffle energy dissipation in liquid fueled rocket engines. [Internet] [Masters thesis]. Colorado State University; 2010. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/10217/68387.

Council of Science Editors:

Miller NA. Development of a model for baffle energy dissipation in liquid fueled rocket engines. [Masters Thesis]. Colorado State University; 2010. Available from: http://hdl.handle.net/10217/68387


Univerzitet u Beogradu

12. Nauparac, Dragan B., 1962-. Прилог теорији пројектовања актуатора за управљање вектором потиска ракетног мотора са флексибилним млазником.

Degree: Mašinski fakultet, 2016, Univerzitet u Beogradu

Машинство - Ваздухопловство / Mechanical Engineering - Aerospace Engineering

Пројектовање актуационих система, посебно електро хидрауличних, предмет је обимних истраживања већ дуги низ година, може се… (more)

Subjects/Keywords: electro hydraulic actuator; flexible nozzle; rocket engine; thrust vector control

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th Edition):

Nauparac, Dragan B., 1. (2016). Прилог теорији пројектовања актуатора за управљање вектором потиска ракетног мотора са флексибилним млазником. (Thesis). Univerzitet u Beogradu. Retrieved from https://fedorabg.bg.ac.rs/fedora/get/o:13800/bdef:Content/get

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

Chicago Manual of Style (16th Edition):

Nauparac, Dragan B., 1962-. “Прилог теорији пројектовања актуатора за управљање вектором потиска ракетног мотора са флексибилним млазником.” 2016. Thesis, Univerzitet u Beogradu. Accessed February 28, 2021. https://fedorabg.bg.ac.rs/fedora/get/o:13800/bdef:Content/get.

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

MLA Handbook (7th Edition):

Nauparac, Dragan B., 1962-. “Прилог теорији пројектовања актуатора за управљање вектором потиска ракетног мотора са флексибилним млазником.” 2016. Web. 28 Feb 2021.

Vancouver:

Nauparac, Dragan B. 1. Прилог теорији пројектовања актуатора за управљање вектором потиска ракетног мотора са флексибилним млазником. [Internet] [Thesis]. Univerzitet u Beogradu; 2016. [cited 2021 Feb 28]. Available from: https://fedorabg.bg.ac.rs/fedora/get/o:13800/bdef:Content/get.

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

Council of Science Editors:

Nauparac, Dragan B. 1. Прилог теорији пројектовања актуатора за управљање вектором потиска ракетног мотора са флексибилним млазником. [Thesis]. Univerzitet u Beogradu; 2016. Available from: https://fedorabg.bg.ac.rs/fedora/get/o:13800/bdef:Content/get

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


Delft University of Technology

13. Denies, L. (author). Regenerative cooling analysis of oxygen/methane rocket engines.

Degree: 2015, Delft University of Technology

 Methane is a promising propellant for future liquid rocket engines. In the cooling channels of a regeneratively cooled engine, it would be close to the… (more)

Subjects/Keywords: rocket engine; regenerative cooling; methane; CFD; OpenFOAM; aluminium; copper

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th Edition):

Denies, L. (. (2015). Regenerative cooling analysis of oxygen/methane rocket engines. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:90c8d527-7214-47ac-8a0b-0f03c40625cc

Chicago Manual of Style (16th Edition):

Denies, L (author). “Regenerative cooling analysis of oxygen/methane rocket engines.” 2015. Masters Thesis, Delft University of Technology. Accessed February 28, 2021. http://resolver.tudelft.nl/uuid:90c8d527-7214-47ac-8a0b-0f03c40625cc.

MLA Handbook (7th Edition):

Denies, L (author). “Regenerative cooling analysis of oxygen/methane rocket engines.” 2015. Web. 28 Feb 2021.

Vancouver:

Denies L(. Regenerative cooling analysis of oxygen/methane rocket engines. [Internet] [Masters thesis]. Delft University of Technology; 2015. [cited 2021 Feb 28]. Available from: http://resolver.tudelft.nl/uuid:90c8d527-7214-47ac-8a0b-0f03c40625cc.

Council of Science Editors:

Denies L(. Regenerative cooling analysis of oxygen/methane rocket engines. [Masters Thesis]. Delft University of Technology; 2015. Available from: http://resolver.tudelft.nl/uuid:90c8d527-7214-47ac-8a0b-0f03c40625cc


Brno University of Technology

14. Černoch, Jakub. Vědecké mise vesmírných sond nejen v naší Sluneční soustavě: Science missions of spacecraft in our Solar System and beyond.

Degree: 2018, Brno University of Technology

 This bachelor thesis is aimed on the space probe missions, that landed on objects in our Solar system. First part of this thesis is aimed… (more)

Subjects/Keywords: Mars; hopper; hybridní raketový motor; Mars; hopper; hybrid rocket engine

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th Edition):

Černoch, J. (2018). Vědecké mise vesmírných sond nejen v naší Sluneční soustavě: Science missions of spacecraft in our Solar System and beyond. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/81576

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

Chicago Manual of Style (16th Edition):

Černoch, Jakub. “Vědecké mise vesmírných sond nejen v naší Sluneční soustavě: Science missions of spacecraft in our Solar System and beyond.” 2018. Thesis, Brno University of Technology. Accessed February 28, 2021. http://hdl.handle.net/11012/81576.

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

MLA Handbook (7th Edition):

Černoch, Jakub. “Vědecké mise vesmírných sond nejen v naší Sluneční soustavě: Science missions of spacecraft in our Solar System and beyond.” 2018. Web. 28 Feb 2021.

Vancouver:

Černoch J. Vědecké mise vesmírných sond nejen v naší Sluneční soustavě: Science missions of spacecraft in our Solar System and beyond. [Internet] [Thesis]. Brno University of Technology; 2018. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/11012/81576.

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

Council of Science Editors:

Černoch J. Vědecké mise vesmírných sond nejen v naší Sluneční soustavě: Science missions of spacecraft in our Solar System and beyond. [Thesis]. Brno University of Technology; 2018. Available from: http://hdl.handle.net/11012/81576

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


University of Maryland

15. Maqbool, Daanish. Development of an Experiment for Measuring Film Cooling Performance in Supersonic Flows.

Degree: Aerospace Engineering, 2011, University of Maryland

 This thesis describes the development of an experiment for acquiring supersonic film cooling performance data in canonical configurations suitable for code validation. A methodology for… (more)

Subjects/Keywords: Aerospace engineering; cooling; engine; film; nozzle; rocket; supersonic

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th Edition):

Maqbool, D. (2011). Development of an Experiment for Measuring Film Cooling Performance in Supersonic Flows. (Thesis). University of Maryland. Retrieved from http://hdl.handle.net/1903/12075

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

Chicago Manual of Style (16th Edition):

Maqbool, Daanish. “Development of an Experiment for Measuring Film Cooling Performance in Supersonic Flows.” 2011. Thesis, University of Maryland. Accessed February 28, 2021. http://hdl.handle.net/1903/12075.

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

MLA Handbook (7th Edition):

Maqbool, Daanish. “Development of an Experiment for Measuring Film Cooling Performance in Supersonic Flows.” 2011. Web. 28 Feb 2021.

Vancouver:

Maqbool D. Development of an Experiment for Measuring Film Cooling Performance in Supersonic Flows. [Internet] [Thesis]. University of Maryland; 2011. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/1903/12075.

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

Council of Science Editors:

Maqbool D. Development of an Experiment for Measuring Film Cooling Performance in Supersonic Flows. [Thesis]. University of Maryland; 2011. Available from: http://hdl.handle.net/1903/12075

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


Colorado State University

16. Browne, Elizabeth C. Modeling ablative and regenerative cooling systems for an ethylene/ethane/nitrous oxide liquid fuel rocket engine.

Degree: MS(M.S.), Mechanical Engineering, 2020, Colorado State University

Rocket engines create extreme conditions for any material to withstand. The combustion temperatures in rocket engines are substantially greater than the melting points of metals,… (more)

Subjects/Keywords: CFD; regenerative cooling; liquid rocket engine; ablative cooling

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th Edition):

Browne, E. C. (2020). Modeling ablative and regenerative cooling systems for an ethylene/ethane/nitrous oxide liquid fuel rocket engine. (Masters Thesis). Colorado State University. Retrieved from http://hdl.handle.net/10217/212046

Chicago Manual of Style (16th Edition):

Browne, Elizabeth C. “Modeling ablative and regenerative cooling systems for an ethylene/ethane/nitrous oxide liquid fuel rocket engine.” 2020. Masters Thesis, Colorado State University. Accessed February 28, 2021. http://hdl.handle.net/10217/212046.

MLA Handbook (7th Edition):

Browne, Elizabeth C. “Modeling ablative and regenerative cooling systems for an ethylene/ethane/nitrous oxide liquid fuel rocket engine.” 2020. Web. 28 Feb 2021.

Vancouver:

Browne EC. Modeling ablative and regenerative cooling systems for an ethylene/ethane/nitrous oxide liquid fuel rocket engine. [Internet] [Masters thesis]. Colorado State University; 2020. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/10217/212046.

Council of Science Editors:

Browne EC. Modeling ablative and regenerative cooling systems for an ethylene/ethane/nitrous oxide liquid fuel rocket engine. [Masters Thesis]. Colorado State University; 2020. Available from: http://hdl.handle.net/10217/212046


Vanderbilt University

17. -3216-7628. Compact Augmented Spark Igniters For Liquid Rocket Engines.

Degree: PhD, Mechanical Engineering, 2021, Vanderbilt University

 The objective of this dissertation is to characterize augmented spark impinging (torch) igniters. Torch igniters inject propellants into a small prechamber where a spark igniter… (more)

Subjects/Keywords: Combustion; Liquid Rocket Engine; Torch Igniter; Augmented Spark Igniter

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th Edition):

-3216-7628. (2021). Compact Augmented Spark Igniters For Liquid Rocket Engines. (Doctoral Dissertation). Vanderbilt University. Retrieved from http://hdl.handle.net/1803/16419

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

Chicago Manual of Style (16th Edition):

-3216-7628. “Compact Augmented Spark Igniters For Liquid Rocket Engines.” 2021. Doctoral Dissertation, Vanderbilt University. Accessed February 28, 2021. http://hdl.handle.net/1803/16419.

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

MLA Handbook (7th Edition):

-3216-7628. “Compact Augmented Spark Igniters For Liquid Rocket Engines.” 2021. Web. 28 Feb 2021.

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

Vancouver:

-3216-7628. Compact Augmented Spark Igniters For Liquid Rocket Engines. [Internet] [Doctoral dissertation]. Vanderbilt University; 2021. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/1803/16419.

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

Council of Science Editors:

-3216-7628. Compact Augmented Spark Igniters For Liquid Rocket Engines. [Doctoral Dissertation]. Vanderbilt University; 2021. Available from: http://hdl.handle.net/1803/16419

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


Brno University of Technology

18. Cejpek, Jakub. Návrh raketového motoru: Rocket Engine Design.

Degree: 2019, Brno University of Technology

 The objective of this study is to design a solid rocket fuel engine with sufficient power to propel 500 grams to 1500 meters of altitude.… (more)

Subjects/Keywords: raketa; tuhá pohonná hmota; raketový motor; impulsní raketový budič; rocket; solid propellant; rocket engine; vibration exciter

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th Edition):

Cejpek, J. (2019). Návrh raketového motoru: Rocket Engine Design. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/12306

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

Chicago Manual of Style (16th Edition):

Cejpek, Jakub. “Návrh raketového motoru: Rocket Engine Design.” 2019. Thesis, Brno University of Technology. Accessed February 28, 2021. http://hdl.handle.net/11012/12306.

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

MLA Handbook (7th Edition):

Cejpek, Jakub. “Návrh raketového motoru: Rocket Engine Design.” 2019. Web. 28 Feb 2021.

Vancouver:

Cejpek J. Návrh raketového motoru: Rocket Engine Design. [Internet] [Thesis]. Brno University of Technology; 2019. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/11012/12306.

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

Council of Science Editors:

Cejpek J. Návrh raketového motoru: Rocket Engine Design. [Thesis]. Brno University of Technology; 2019. Available from: http://hdl.handle.net/11012/12306

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


The Ohio State University

19. Gordon, Kayleigh Elizabeth. Analysis of Chinese Cryogenic Long March Launch Vehicles and YF-100 Liquid Rocket Engine.

Degree: MS, Aero/Astro Engineering, 2018, The Ohio State University

 This research synthesizes the technical capabilities of the currently developing fleet of Chinese liquid fuel launch vehicles, specifically the Long March 5, 6, and 7… (more)

Subjects/Keywords: Aerospace Engineering; Public Policy; China; space; launch vehicles; long march; cryogenic; yf-100; rocket; liquid rocket engine; Chinese; chang zheng

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th Edition):

Gordon, K. E. (2018). Analysis of Chinese Cryogenic Long March Launch Vehicles and YF-100 Liquid Rocket Engine. (Masters Thesis). The Ohio State University. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=osu1524154852226897

Chicago Manual of Style (16th Edition):

Gordon, Kayleigh Elizabeth. “Analysis of Chinese Cryogenic Long March Launch Vehicles and YF-100 Liquid Rocket Engine.” 2018. Masters Thesis, The Ohio State University. Accessed February 28, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=osu1524154852226897.

MLA Handbook (7th Edition):

Gordon, Kayleigh Elizabeth. “Analysis of Chinese Cryogenic Long March Launch Vehicles and YF-100 Liquid Rocket Engine.” 2018. Web. 28 Feb 2021.

Vancouver:

Gordon KE. Analysis of Chinese Cryogenic Long March Launch Vehicles and YF-100 Liquid Rocket Engine. [Internet] [Masters thesis]. The Ohio State University; 2018. [cited 2021 Feb 28]. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1524154852226897.

Council of Science Editors:

Gordon KE. Analysis of Chinese Cryogenic Long March Launch Vehicles and YF-100 Liquid Rocket Engine. [Masters Thesis]. The Ohio State University; 2018. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1524154852226897


Brno University of Technology

20. Koutník, Tomáš. Letecké pohonné jednotky: Aircraft Power Units.

Degree: 2018, Brno University of Technology

 This bachelor’s thesis deals with review of today most used aircraft power units. Briefly explains their purpose, working principle and most important influences on their… (more)

Subjects/Keywords: letecká pohonná jednotka; letecký motor; tah; vrtule; pístový motor; tryskový motor; proudový motor; raketový motor; aircraft power unit; aircraft engine; thrust; propeller; piston engine; jet engine; turbojet engine; rocket engine

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th Edition):

Koutník, T. (2018). Letecké pohonné jednotky: Aircraft Power Units. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/8604

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

Chicago Manual of Style (16th Edition):

Koutník, Tomáš. “Letecké pohonné jednotky: Aircraft Power Units.” 2018. Thesis, Brno University of Technology. Accessed February 28, 2021. http://hdl.handle.net/11012/8604.

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

MLA Handbook (7th Edition):

Koutník, Tomáš. “Letecké pohonné jednotky: Aircraft Power Units.” 2018. Web. 28 Feb 2021.

Vancouver:

Koutník T. Letecké pohonné jednotky: Aircraft Power Units. [Internet] [Thesis]. Brno University of Technology; 2018. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/11012/8604.

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

Council of Science Editors:

Koutník T. Letecké pohonné jednotky: Aircraft Power Units. [Thesis]. Brno University of Technology; 2018. Available from: http://hdl.handle.net/11012/8604

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


Penn State University

21. Locke, Justin M. HIGH SPEED DIAGNOSTICS FOR CHARACTERIZATION OF OXYGEN / HYDROGEN ROCKET INJECTOR FLOWFIELDS.

Degree: 2011, Penn State University

 Temporally-resolved diagnostics are needed to characterize the highly-turbulent flowfields of rocket engine combustors. Two different high speed diagnostic techniques have been applied successfully to study… (more)

Subjects/Keywords: liquid propulsion; TDLAS; absorption spectroscopy; rocket engine testing; hydrogen oxygen combustion; high pressure systems

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th Edition):

Locke, J. M. (2011). HIGH SPEED DIAGNOSTICS FOR CHARACTERIZATION OF OXYGEN / HYDROGEN ROCKET INJECTOR FLOWFIELDS. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/11344

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

Chicago Manual of Style (16th Edition):

Locke, Justin M. “HIGH SPEED DIAGNOSTICS FOR CHARACTERIZATION OF OXYGEN / HYDROGEN ROCKET INJECTOR FLOWFIELDS.” 2011. Thesis, Penn State University. Accessed February 28, 2021. https://submit-etda.libraries.psu.edu/catalog/11344.

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

MLA Handbook (7th Edition):

Locke, Justin M. “HIGH SPEED DIAGNOSTICS FOR CHARACTERIZATION OF OXYGEN / HYDROGEN ROCKET INJECTOR FLOWFIELDS.” 2011. Web. 28 Feb 2021.

Vancouver:

Locke JM. HIGH SPEED DIAGNOSTICS FOR CHARACTERIZATION OF OXYGEN / HYDROGEN ROCKET INJECTOR FLOWFIELDS. [Internet] [Thesis]. Penn State University; 2011. [cited 2021 Feb 28]. Available from: https://submit-etda.libraries.psu.edu/catalog/11344.

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

Council of Science Editors:

Locke JM. HIGH SPEED DIAGNOSTICS FOR CHARACTERIZATION OF OXYGEN / HYDROGEN ROCKET INJECTOR FLOWFIELDS. [Thesis]. Penn State University; 2011. Available from: https://submit-etda.libraries.psu.edu/catalog/11344

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


University of Miami

22. Yenawine, Alec William. Hybrid Rocket Engines: Development of Composite Fuels with Complex 3D Printed Ports.

Degree: MS, Mechanical Engineering (Engineering), 2019, University of Miami

  Hybrid rocket engines provide many advantages over current solid and liquid systems including: throttling capability, good specific impulse, and relatively low cost due to… (more)

Subjects/Keywords: hybrid rocket engine; 3D printing; complex fuel port; energetic additives; aluminum; additive manufacturing

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th Edition):

Yenawine, A. W. (2019). Hybrid Rocket Engines: Development of Composite Fuels with Complex 3D Printed Ports. (Thesis). University of Miami. Retrieved from https://scholarlyrepository.miami.edu/oa_theses/777

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

Chicago Manual of Style (16th Edition):

Yenawine, Alec William. “Hybrid Rocket Engines: Development of Composite Fuels with Complex 3D Printed Ports.” 2019. Thesis, University of Miami. Accessed February 28, 2021. https://scholarlyrepository.miami.edu/oa_theses/777.

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

MLA Handbook (7th Edition):

Yenawine, Alec William. “Hybrid Rocket Engines: Development of Composite Fuels with Complex 3D Printed Ports.” 2019. Web. 28 Feb 2021.

Vancouver:

Yenawine AW. Hybrid Rocket Engines: Development of Composite Fuels with Complex 3D Printed Ports. [Internet] [Thesis]. University of Miami; 2019. [cited 2021 Feb 28]. Available from: https://scholarlyrepository.miami.edu/oa_theses/777.

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

Council of Science Editors:

Yenawine AW. Hybrid Rocket Engines: Development of Composite Fuels with Complex 3D Printed Ports. [Thesis]. University of Miami; 2019. Available from: https://scholarlyrepository.miami.edu/oa_theses/777

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

23. Jensen, Filip. Topology Optimization of Turbine Manifold in the Rocket Engine Demonstrator Prometheus.

Degree: Space Technology, 2018, Luleå University of Technology

  The advantages of Topology Optimization (TO) are realized to a large extent due to the manufacturing freedom that Additive Manufacturing (AM) offer, compared to… (more)

Subjects/Keywords: Additive Manufacturing; Prometheus; Rocket Engine; Topology Optimization; Aerospace Engineering; Rymd- och flygteknik

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th Edition):

Jensen, F. (2018). Topology Optimization of Turbine Manifold in the Rocket Engine Demonstrator Prometheus. (Thesis). Luleå University of Technology. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-69981

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

Chicago Manual of Style (16th Edition):

Jensen, Filip. “Topology Optimization of Turbine Manifold in the Rocket Engine Demonstrator Prometheus.” 2018. Thesis, Luleå University of Technology. Accessed February 28, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-69981.

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

MLA Handbook (7th Edition):

Jensen, Filip. “Topology Optimization of Turbine Manifold in the Rocket Engine Demonstrator Prometheus.” 2018. Web. 28 Feb 2021.

Vancouver:

Jensen F. Topology Optimization of Turbine Manifold in the Rocket Engine Demonstrator Prometheus. [Internet] [Thesis]. Luleå University of Technology; 2018. [cited 2021 Feb 28]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-69981.

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

Council of Science Editors:

Jensen F. Topology Optimization of Turbine Manifold in the Rocket Engine Demonstrator Prometheus. [Thesis]. Luleå University of Technology; 2018. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-69981

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


Delft University of Technology

24. Sanghera, Bhupinder Singh (author). Adjoint Shape Optimisation of Rocket Engine Turbine Blades.

Degree: 2020, Delft University of Technology

Prior to the detailed design of turbines, turbomachinery engineers must rely on mean-line and throughflow models to come to a preliminary design. These models are… (more)

Subjects/Keywords: Adjoint Optimisation; Loss Breakdown; Rocket Engine Turbine Blades; Supersonic Axial Stator Vanes; SU2

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th Edition):

Sanghera, B. S. (. (2020). Adjoint Shape Optimisation of Rocket Engine Turbine Blades. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:4ba54fad-ae63-4659-873f-90a7a9191f86

Chicago Manual of Style (16th Edition):

Sanghera, Bhupinder Singh (author). “Adjoint Shape Optimisation of Rocket Engine Turbine Blades.” 2020. Masters Thesis, Delft University of Technology. Accessed February 28, 2021. http://resolver.tudelft.nl/uuid:4ba54fad-ae63-4659-873f-90a7a9191f86.

MLA Handbook (7th Edition):

Sanghera, Bhupinder Singh (author). “Adjoint Shape Optimisation of Rocket Engine Turbine Blades.” 2020. Web. 28 Feb 2021.

Vancouver:

Sanghera BS(. Adjoint Shape Optimisation of Rocket Engine Turbine Blades. [Internet] [Masters thesis]. Delft University of Technology; 2020. [cited 2021 Feb 28]. Available from: http://resolver.tudelft.nl/uuid:4ba54fad-ae63-4659-873f-90a7a9191f86.

Council of Science Editors:

Sanghera BS(. Adjoint Shape Optimisation of Rocket Engine Turbine Blades. [Masters Thesis]. Delft University of Technology; 2020. Available from: http://resolver.tudelft.nl/uuid:4ba54fad-ae63-4659-873f-90a7a9191f86


Delft University of Technology

25. Akkermans, Christ (author). Ignition modeling in methane-oxygen rocket engines: Design and modeling of a methane-oxygen rocket engine igniter using reacting flows with computational fluid dynamics.

Degree: 2017, Delft University of Technology

 The influence of using different chemistry model and different chemical kinetics schemes on modeling combustion inside a rocket engine igniter are investigated. An igniter for… (more)

Subjects/Keywords: rocket; engine; ignition; CFD; chemistry; oxygen; methane; igniter; model; computational; turbulence; finite rate

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th Edition):

Akkermans, C. (. (2017). Ignition modeling in methane-oxygen rocket engines: Design and modeling of a methane-oxygen rocket engine igniter using reacting flows with computational fluid dynamics. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:b7a76cb1-8dcc-47e1-8e6f-0b46b78f3f50

Chicago Manual of Style (16th Edition):

Akkermans, Christ (author). “Ignition modeling in methane-oxygen rocket engines: Design and modeling of a methane-oxygen rocket engine igniter using reacting flows with computational fluid dynamics.” 2017. Masters Thesis, Delft University of Technology. Accessed February 28, 2021. http://resolver.tudelft.nl/uuid:b7a76cb1-8dcc-47e1-8e6f-0b46b78f3f50.

MLA Handbook (7th Edition):

Akkermans, Christ (author). “Ignition modeling in methane-oxygen rocket engines: Design and modeling of a methane-oxygen rocket engine igniter using reacting flows with computational fluid dynamics.” 2017. Web. 28 Feb 2021.

Vancouver:

Akkermans C(. Ignition modeling in methane-oxygen rocket engines: Design and modeling of a methane-oxygen rocket engine igniter using reacting flows with computational fluid dynamics. [Internet] [Masters thesis]. Delft University of Technology; 2017. [cited 2021 Feb 28]. Available from: http://resolver.tudelft.nl/uuid:b7a76cb1-8dcc-47e1-8e6f-0b46b78f3f50.

Council of Science Editors:

Akkermans C(. Ignition modeling in methane-oxygen rocket engines: Design and modeling of a methane-oxygen rocket engine igniter using reacting flows with computational fluid dynamics. [Masters Thesis]. Delft University of Technology; 2017. Available from: http://resolver.tudelft.nl/uuid:b7a76cb1-8dcc-47e1-8e6f-0b46b78f3f50


Brno University of Technology

26. Špačková, Jana. Přehled současných kosmických prostředků: Overview of current spaceships.

Degree: 2018, Brno University of Technology

 Target of this work is to create an overview of commonly used and in this time developed transports used for carrying payload to space and… (more)

Subjects/Keywords: Nosná raketa; raketový stupeň; raketový motor; oběžná dráha; doprava; užitečné zatížení; nosnost; Launch vehicle; rocket stage; rocket engine; orbit; transport; payload; capacity

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th Edition):

Špačková, J. (2018). Přehled současných kosmických prostředků: Overview of current spaceships. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/81671

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

Chicago Manual of Style (16th Edition):

Špačková, Jana. “Přehled současných kosmických prostředků: Overview of current spaceships.” 2018. Thesis, Brno University of Technology. Accessed February 28, 2021. http://hdl.handle.net/11012/81671.

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

MLA Handbook (7th Edition):

Špačková, Jana. “Přehled současných kosmických prostředků: Overview of current spaceships.” 2018. Web. 28 Feb 2021.

Vancouver:

Špačková J. Přehled současných kosmických prostředků: Overview of current spaceships. [Internet] [Thesis]. Brno University of Technology; 2018. [cited 2021 Feb 28]. Available from: http://hdl.handle.net/11012/81671.

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

Council of Science Editors:

Špačková J. Přehled současných kosmických prostředků: Overview of current spaceships. [Thesis]. Brno University of Technology; 2018. Available from: http://hdl.handle.net/11012/81671

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


University of California – Irvine

27. Nguyen, Tuan. Nonlinear Rocket-Engine Longitudinal Combustion Instability.

Degree: Mechanical and Aerospace Engineering, 2018, University of California – Irvine

 With recent improvements in computer architecture, there are renewed interests in studying combustion instability in rocket engine via Computational Fluid Dynamics (CFD) simulations. Most existing… (more)

Subjects/Keywords: Aerospace engineering; Mechanical engineering; Combustion Instability; Flamelet Model; Hybrid RANS-LES; Liquid rocket engine; Turbulent Combustion

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th Edition):

Nguyen, T. (2018). Nonlinear Rocket-Engine Longitudinal Combustion Instability. (Thesis). University of California – Irvine. Retrieved from http://www.escholarship.org/uc/item/8hv2079w

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

Chicago Manual of Style (16th Edition):

Nguyen, Tuan. “Nonlinear Rocket-Engine Longitudinal Combustion Instability.” 2018. Thesis, University of California – Irvine. Accessed February 28, 2021. http://www.escholarship.org/uc/item/8hv2079w.

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

MLA Handbook (7th Edition):

Nguyen, Tuan. “Nonlinear Rocket-Engine Longitudinal Combustion Instability.” 2018. Web. 28 Feb 2021.

Vancouver:

Nguyen T. Nonlinear Rocket-Engine Longitudinal Combustion Instability. [Internet] [Thesis]. University of California – Irvine; 2018. [cited 2021 Feb 28]. Available from: http://www.escholarship.org/uc/item/8hv2079w.

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

Council of Science Editors:

Nguyen T. Nonlinear Rocket-Engine Longitudinal Combustion Instability. [Thesis]. University of California – Irvine; 2018. Available from: http://www.escholarship.org/uc/item/8hv2079w

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

28. Messineo, Jérôme. Modélisation des instabilités hydrodynamiques dans les moteurs-fusées hybrides : Hydrodynamic instabilities modeling in hybrid rocket engines.

Degree: Docteur es, Energétique et transferts, 2016, Toulouse, ISAE

Les moteurs-fusées hybrides combinent les technologies des deux autres catégories de moteurs à propulsionchimique, et associent un combustible et un oxydant stockés respectivement sous phase… (more)

Subjects/Keywords: Propulsion spatiale; Moteurs-Fusées hybrides; Instabilités; Simulations numériques; Space propulsion; Hybrid rocket engine; Instabilities; Numerical simulations; 621.042

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th Edition):

Messineo, J. (2016). Modélisation des instabilités hydrodynamiques dans les moteurs-fusées hybrides : Hydrodynamic instabilities modeling in hybrid rocket engines. (Doctoral Dissertation). Toulouse, ISAE. Retrieved from http://www.theses.fr/2016ESAE0025

Chicago Manual of Style (16th Edition):

Messineo, Jérôme. “Modélisation des instabilités hydrodynamiques dans les moteurs-fusées hybrides : Hydrodynamic instabilities modeling in hybrid rocket engines.” 2016. Doctoral Dissertation, Toulouse, ISAE. Accessed February 28, 2021. http://www.theses.fr/2016ESAE0025.

MLA Handbook (7th Edition):

Messineo, Jérôme. “Modélisation des instabilités hydrodynamiques dans les moteurs-fusées hybrides : Hydrodynamic instabilities modeling in hybrid rocket engines.” 2016. Web. 28 Feb 2021.

Vancouver:

Messineo J. Modélisation des instabilités hydrodynamiques dans les moteurs-fusées hybrides : Hydrodynamic instabilities modeling in hybrid rocket engines. [Internet] [Doctoral dissertation]. Toulouse, ISAE; 2016. [cited 2021 Feb 28]. Available from: http://www.theses.fr/2016ESAE0025.

Council of Science Editors:

Messineo J. Modélisation des instabilités hydrodynamiques dans les moteurs-fusées hybrides : Hydrodynamic instabilities modeling in hybrid rocket engines. [Doctoral Dissertation]. Toulouse, ISAE; 2016. Available from: http://www.theses.fr/2016ESAE0025


Delft University of Technology

29. Mercieca, Edward (author). Spray Characteristics in Gas / Liquid Pintle Injection.

Degree: 2017, Delft University of Technology

In Liquid Rocket Engine (LRE) design, knowledge of how the propellant atomization quality varies with respect to some injector design variables would be useful in… (more)

Subjects/Keywords: LIquid Rocket Engine; Pintle Injector; Drop size distribution; Sauter Mean Diameter; Atomization; Spray; Combustion; Cone Angle

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th Edition):

Mercieca, E. (. (2017). Spray Characteristics in Gas / Liquid Pintle Injection. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:ffcc0e29-e9e7-4042-832b-5bc46e92ef0d

Chicago Manual of Style (16th Edition):

Mercieca, Edward (author). “Spray Characteristics in Gas / Liquid Pintle Injection.” 2017. Masters Thesis, Delft University of Technology. Accessed February 28, 2021. http://resolver.tudelft.nl/uuid:ffcc0e29-e9e7-4042-832b-5bc46e92ef0d.

MLA Handbook (7th Edition):

Mercieca, Edward (author). “Spray Characteristics in Gas / Liquid Pintle Injection.” 2017. Web. 28 Feb 2021.

Vancouver:

Mercieca E(. Spray Characteristics in Gas / Liquid Pintle Injection. [Internet] [Masters thesis]. Delft University of Technology; 2017. [cited 2021 Feb 28]. Available from: http://resolver.tudelft.nl/uuid:ffcc0e29-e9e7-4042-832b-5bc46e92ef0d.

Council of Science Editors:

Mercieca E(. Spray Characteristics in Gas / Liquid Pintle Injection. [Masters Thesis]. Delft University of Technology; 2017. Available from: http://resolver.tudelft.nl/uuid:ffcc0e29-e9e7-4042-832b-5bc46e92ef0d


University of Tennessee – Knoxville

30. Katta, Ajay. Particle Trajectories in Wall-Normal and Tangential Rocket Chambers.

Degree: MS, Aerospace Engineering, 2011, University of Tennessee – Knoxville

  The focus of this study is the prediction of trajectories of solid particles injected into either a cylindrically- shaped solid rocket motor (SRM) or… (more)

Subjects/Keywords: Multiphase flow; Solid rocket motor; Bidirectional vortex engine; Runge–Kutta method; Lagrangian particle tracking; Matched asymptotic expansions; Propulsion and Power

Record DetailsSimilar RecordsGoogle PlusoneFacebookTwitterCiteULikeMendeleyreddit

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

APA (6th Edition):

Katta, A. (2011). Particle Trajectories in Wall-Normal and Tangential Rocket Chambers. (Thesis). University of Tennessee – Knoxville. Retrieved from https://trace.tennessee.edu/utk_gradthes/989

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

Chicago Manual of Style (16th Edition):

Katta, Ajay. “Particle Trajectories in Wall-Normal and Tangential Rocket Chambers.” 2011. Thesis, University of Tennessee – Knoxville. Accessed February 28, 2021. https://trace.tennessee.edu/utk_gradthes/989.

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

MLA Handbook (7th Edition):

Katta, Ajay. “Particle Trajectories in Wall-Normal and Tangential Rocket Chambers.” 2011. Web. 28 Feb 2021.

Vancouver:

Katta A. Particle Trajectories in Wall-Normal and Tangential Rocket Chambers. [Internet] [Thesis]. University of Tennessee – Knoxville; 2011. [cited 2021 Feb 28]. Available from: https://trace.tennessee.edu/utk_gradthes/989.

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

Council of Science Editors:

Katta A. Particle Trajectories in Wall-Normal and Tangential Rocket Chambers. [Thesis]. University of Tennessee – Knoxville; 2011. Available from: https://trace.tennessee.edu/utk_gradthes/989

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

[1] [2]

.