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You searched for subject:(Liquid Propellant Rocket). Showing records 1 – 9 of 9 total matches.

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Luleå University of Technology

1. Phing, Anselm Ho Yen. Simulating combustion flow in a rocket chamber.

Degree: 2008, Luleå University of Technology

Liquid propellant rocket engines are very complex machinery and require immense research time to obtain the best performance possible. Therefore its performance efficiency has… (more)

Subjects/Keywords: Technology; Computational fluid; Simulation; Liquid propellant rocket; Teknik

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APA (6th Edition):

Phing, A. H. Y. (2008). Simulating combustion flow in a rocket chamber. (Thesis). Luleå University of Technology. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-44807

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):

Phing, Anselm Ho Yen. “Simulating combustion flow in a rocket chamber.” 2008. Thesis, Luleå University of Technology. Accessed October 23, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-44807.

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

MLA Handbook (7th Edition):

Phing, Anselm Ho Yen. “Simulating combustion flow in a rocket chamber.” 2008. Web. 23 Oct 2019.

Vancouver:

Phing AHY. Simulating combustion flow in a rocket chamber. [Internet] [Thesis]. Luleå University of Technology; 2008. [cited 2019 Oct 23]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-44807.

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

Council of Science Editors:

Phing AHY. Simulating combustion flow in a rocket chamber. [Thesis]. Luleå University of Technology; 2008. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-44807

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


Indian Institute of Science

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

Degree: 2012, Indian Institute of Science

 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)

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 (6th Edition):

Biju Kumar, K. S. (2012). Role Of Hydrogen Injection Temperature On The Combustion Instability Of Cryogenic Rocket Engine. (Thesis). Indian Institute of Science. Retrieved from http://hdl.handle.net/2005/2297

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):

Biju Kumar, K S. “Role Of Hydrogen Injection Temperature On The Combustion Instability Of Cryogenic Rocket Engine.” 2012. Thesis, Indian Institute of Science. Accessed October 23, 2019. http://hdl.handle.net/2005/2297.

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

MLA Handbook (7th Edition):

Biju Kumar, K S. “Role Of Hydrogen Injection Temperature On The Combustion Instability Of Cryogenic Rocket Engine.” 2012. Web. 23 Oct 2019.

Vancouver:

Biju Kumar KS. Role Of Hydrogen Injection Temperature On The Combustion Instability Of Cryogenic Rocket Engine. [Internet] [Thesis]. Indian Institute of Science; 2012. [cited 2019 Oct 23]. Available from: http://hdl.handle.net/2005/2297.

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

Council of Science Editors:

Biju Kumar KS. Role Of Hydrogen Injection Temperature On The Combustion Instability Of Cryogenic Rocket Engine. [Thesis]. Indian Institute of Science; 2012. Available from: http://hdl.handle.net/2005/2297

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


Indian Institute of Science

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

Degree: 2012, Indian Institute of Science

 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)

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

APA (6th Edition):

Biju Kumar, K. S. (2012). Role Of Hydrogen Injection Temperature On The Combustion Instability Of Cryogenic Rocket Engine. (Thesis). Indian Institute of Science. Retrieved from http://etd.iisc.ernet.in/handle/2005/2297 ; http://etd.ncsi.iisc.ernet.in/abstracts/2956/G25322-Abs.pdf

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):

Biju Kumar, K S. “Role Of Hydrogen Injection Temperature On The Combustion Instability Of Cryogenic Rocket Engine.” 2012. Thesis, Indian Institute of Science. Accessed October 23, 2019. http://etd.iisc.ernet.in/handle/2005/2297 ; http://etd.ncsi.iisc.ernet.in/abstracts/2956/G25322-Abs.pdf.

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

MLA Handbook (7th Edition):

Biju Kumar, K S. “Role Of Hydrogen Injection Temperature On The Combustion Instability Of Cryogenic Rocket Engine.” 2012. Web. 23 Oct 2019.

Vancouver:

Biju Kumar KS. Role Of Hydrogen Injection Temperature On The Combustion Instability Of Cryogenic Rocket Engine. [Internet] [Thesis]. Indian Institute of Science; 2012. [cited 2019 Oct 23]. Available from: http://etd.iisc.ernet.in/handle/2005/2297 ; http://etd.ncsi.iisc.ernet.in/abstracts/2956/G25322-Abs.pdf.

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

Council of Science Editors:

Biju Kumar KS. Role Of Hydrogen Injection Temperature On The Combustion Instability Of Cryogenic Rocket Engine. [Thesis]. Indian Institute of Science; 2012. Available from: http://etd.iisc.ernet.in/handle/2005/2297 ; http://etd.ncsi.iisc.ernet.in/abstracts/2956/G25322-Abs.pdf

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

4. Giusti, Oreste. Titan I Propulsion System Modeling and Possible Performance Improvements.

Degree: MS, Mechanical and Aerospace Engineering, 2013, San Jose State University

  This thesis features the Titan I propulsion systems and offers data-supported suggestions for improvements to increase performance. The original propulsion systems were modeled both… (more)

Subjects/Keywords: CAD; CFD; Liquid Bi-Propellant; Propulsion; Rocket; Titan I

…because it marks the start of large scale, liquid, bi-propellant rocket vehicles. Originally… …Liquid-Propellant Rocket Engines. The final sets of 24 values were compared to the published… …to the Titan I there had been a long history of liquid rocket technology development, which… …bipropellant rocket propulsion system that utilized liquid oxygen and refined petroleum – 1 (RP… …propellant rocket engines. Other 8 contemporary systems such as the SM-65 Atlas had a smaller… 

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APA (6th Edition):

Giusti, O. (2013). Titan I Propulsion System Modeling and Possible Performance Improvements. (Masters Thesis). San Jose State University. Retrieved from https://doi.org/10.31979/etd.hsrk-f44z ; https://scholarworks.sjsu.edu/etd_theses/4339

Chicago Manual of Style (16th Edition):

Giusti, Oreste. “Titan I Propulsion System Modeling and Possible Performance Improvements.” 2013. Masters Thesis, San Jose State University. Accessed October 23, 2019. https://doi.org/10.31979/etd.hsrk-f44z ; https://scholarworks.sjsu.edu/etd_theses/4339.

MLA Handbook (7th Edition):

Giusti, Oreste. “Titan I Propulsion System Modeling and Possible Performance Improvements.” 2013. Web. 23 Oct 2019.

Vancouver:

Giusti O. Titan I Propulsion System Modeling and Possible Performance Improvements. [Internet] [Masters thesis]. San Jose State University; 2013. [cited 2019 Oct 23]. Available from: https://doi.org/10.31979/etd.hsrk-f44z ; https://scholarworks.sjsu.edu/etd_theses/4339.

Council of Science Editors:

Giusti O. Titan I Propulsion System Modeling and Possible Performance Improvements. [Masters Thesis]. San Jose State University; 2013. Available from: https://doi.org/10.31979/etd.hsrk-f44z ; https://scholarworks.sjsu.edu/etd_theses/4339


Indian Institute of Science

5. Rakesh, P. A Study of the Characteristics of Gas-On-Liquid Impinging Injectors.

Degree: 2014, Indian Institute of Science

 The work presented here pertains to investigations on gas-on-liquid type of impinging injectors with a generic approach with prospective applications in several areas, and at… (more)

Subjects/Keywords: Impinging Injectors; Impinging Atomizers; Gas-On-Liquid Impinging Injectors; Liquid Propellant Rockets; Impinging Jet Injectors; Atomizers; Cryogenic Rocket Injectors; Impinging Fuel Injector Atomization; Impinging Injectors Spraying; Image Processing - Spraying; Gas-On-Liquid Impinging Sprays; Liquid-on Liquid Impingement; Aerospace Engineering

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APA (6th Edition):

Rakesh, P. (2014). A Study of the Characteristics of Gas-On-Liquid Impinging Injectors. (Thesis). Indian Institute of Science. Retrieved from http://hdl.handle.net/2005/3126

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):

Rakesh, P. “A Study of the Characteristics of Gas-On-Liquid Impinging Injectors.” 2014. Thesis, Indian Institute of Science. Accessed October 23, 2019. http://hdl.handle.net/2005/3126.

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

MLA Handbook (7th Edition):

Rakesh, P. “A Study of the Characteristics of Gas-On-Liquid Impinging Injectors.” 2014. Web. 23 Oct 2019.

Vancouver:

Rakesh P. A Study of the Characteristics of Gas-On-Liquid Impinging Injectors. [Internet] [Thesis]. Indian Institute of Science; 2014. [cited 2019 Oct 23]. Available from: http://hdl.handle.net/2005/3126.

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

Council of Science Editors:

Rakesh P. A Study of the Characteristics of Gas-On-Liquid Impinging Injectors. [Thesis]. Indian Institute of Science; 2014. Available from: http://hdl.handle.net/2005/3126

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

6. Masquelet, Matthieu Marc. Large-eddy simulations of high-pressure shear coaxial flows relevant for H2/O2 rocket engines.

Degree: PhD, Aerospace Engineering, 2013, Georgia Tech

 The understanding and prediction of transient phenomena inside Liquid Rocket Engines (LREs) have been very difficult because of the many challenges posed by the conditions… (more)

Subjects/Keywords: Combustion; Supercritical; Scaling; LES; LRE; CFD; Computational fluid dynamics; Propulsion systems; Rocket engines; Rocket engines Combustion; Liquid propellant rocket engines

…LRE Liquid Rocket Engine. MCC Main Combustion Chamber. MCL Monotonized Central Limiter… …1 Rocket Propellant-1 or Refined Petroleum-1. SML Spatial Mixing Layer. SSME Space… …prediction of transient phenomena inside Liquid Rocket Engines (LREs) have been very… …Conclusions and perspectives . . . . . . . . . . . . . . . . . . . . . . . . . . . 172 LIQUID-GAS… …LIQUID-GAS REACTING SHEAR COAXIAL INJECTOR . . . . . . .208 6.1 Description of the… 

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APA (6th Edition):

Masquelet, M. M. (2013). Large-eddy simulations of high-pressure shear coaxial flows relevant for H2/O2 rocket engines. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/47522

Chicago Manual of Style (16th Edition):

Masquelet, Matthieu Marc. “Large-eddy simulations of high-pressure shear coaxial flows relevant for H2/O2 rocket engines.” 2013. Doctoral Dissertation, Georgia Tech. Accessed October 23, 2019. http://hdl.handle.net/1853/47522.

MLA Handbook (7th Edition):

Masquelet, Matthieu Marc. “Large-eddy simulations of high-pressure shear coaxial flows relevant for H2/O2 rocket engines.” 2013. Web. 23 Oct 2019.

Vancouver:

Masquelet MM. Large-eddy simulations of high-pressure shear coaxial flows relevant for H2/O2 rocket engines. [Internet] [Doctoral dissertation]. Georgia Tech; 2013. [cited 2019 Oct 23]. Available from: http://hdl.handle.net/1853/47522.

Council of Science Editors:

Masquelet MM. Large-eddy simulations of high-pressure shear coaxial flows relevant for H2/O2 rocket engines. [Doctoral Dissertation]. Georgia Tech; 2013. Available from: http://hdl.handle.net/1853/47522


Indian Institute of Science

7. Ganu, Hrishikesh Vidyadhar. A Morphological Technique For Direct Drop Size Measurement Of Cryogenic Sprays.

Degree: 2005, Indian Institute of Science

Subjects/Keywords: Cryogenic Sprays; Atomization; Cryogenic Sprays - Drop Sizing; Cryogenic Sprays - Quantifying; Cryogenic Spray Breakup; Liquid Propellant Rocket Engines; Spray Characterization; Cryogenics

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APA (6th Edition):

Ganu, H. V. (2005). A Morphological Technique For Direct Drop Size Measurement Of Cryogenic Sprays. (Thesis). Indian Institute of Science. Retrieved from http://hdl.handle.net/2005/1481

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):

Ganu, Hrishikesh Vidyadhar. “A Morphological Technique For Direct Drop Size Measurement Of Cryogenic Sprays.” 2005. Thesis, Indian Institute of Science. Accessed October 23, 2019. http://hdl.handle.net/2005/1481.

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

MLA Handbook (7th Edition):

Ganu, Hrishikesh Vidyadhar. “A Morphological Technique For Direct Drop Size Measurement Of Cryogenic Sprays.” 2005. Web. 23 Oct 2019.

Vancouver:

Ganu HV. A Morphological Technique For Direct Drop Size Measurement Of Cryogenic Sprays. [Internet] [Thesis]. Indian Institute of Science; 2005. [cited 2019 Oct 23]. Available from: http://hdl.handle.net/2005/1481.

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

Council of Science Editors:

Ganu HV. A Morphological Technique For Direct Drop Size Measurement Of Cryogenic Sprays. [Thesis]. Indian Institute of Science; 2005. Available from: http://hdl.handle.net/2005/1481

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


Indian Institute of Science

8. Ganu, Hrishikesh Vidyadhar. A Morphological Technique For Direct Drop Size Measurement Of Cryogenic Sprays.

Degree: 2005, Indian Institute of Science

Subjects/Keywords: Cryogenic Sprays; Atomization; Cryogenic Sprays - Drop Sizing; Cryogenic Sprays - Quantifying; Cryogenic Spray Breakup; Liquid Propellant Rocket Engines; Spray Characterization; Cryogenics

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

APA (6th Edition):

Ganu, H. V. (2005). A Morphological Technique For Direct Drop Size Measurement Of Cryogenic Sprays. (Thesis). Indian Institute of Science. Retrieved from http://etd.iisc.ernet.in/handle/2005/1481 ; http://etd.ncsi.iisc.ernet.in/abstracts/1901/G19602-Abs.pdf

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):

Ganu, Hrishikesh Vidyadhar. “A Morphological Technique For Direct Drop Size Measurement Of Cryogenic Sprays.” 2005. Thesis, Indian Institute of Science. Accessed October 23, 2019. http://etd.iisc.ernet.in/handle/2005/1481 ; http://etd.ncsi.iisc.ernet.in/abstracts/1901/G19602-Abs.pdf.

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

MLA Handbook (7th Edition):

Ganu, Hrishikesh Vidyadhar. “A Morphological Technique For Direct Drop Size Measurement Of Cryogenic Sprays.” 2005. Web. 23 Oct 2019.

Vancouver:

Ganu HV. A Morphological Technique For Direct Drop Size Measurement Of Cryogenic Sprays. [Internet] [Thesis]. Indian Institute of Science; 2005. [cited 2019 Oct 23]. Available from: http://etd.iisc.ernet.in/handle/2005/1481 ; http://etd.ncsi.iisc.ernet.in/abstracts/1901/G19602-Abs.pdf.

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

Council of Science Editors:

Ganu HV. A Morphological Technique For Direct Drop Size Measurement Of Cryogenic Sprays. [Thesis]. Indian Institute of Science; 2005. Available from: http://etd.iisc.ernet.in/handle/2005/1481 ; http://etd.ncsi.iisc.ernet.in/abstracts/1901/G19602-Abs.pdf

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


University of Florida

9. Kelly, Sean B. Experiments in Thermosensitive Cavitation of a Cryogenic Rocket Propellant Surrogate.

Degree: PhD, Aerospace Engineering - Mechanical and Aerospace Engineering, 2012, University of Florida

 Cavitation is a phase-change phenomenon that may appear in practical devices, often leading to loss of performance and possible physical damage. Of particular interest is… (more)

Subjects/Keywords: Cavitation flow; Fluids; Hydrofoils; Lasers; Liquids; Pressure; Temperature effects; Tunnels; Vapors; Velocity; bubble  – bubbles  – cavitate  – cavitation  – cavity  – cryogenic  – dynamics  – engine  – experimental  – fluid  – fluoroketone  – fuel  – hydrogen  – impeller  – incipient  – inducer  – ketone  – liquid  – multiphase  – nucleation  – phase  – pressure  – propellant  – propulsion  – pump  – rocket  – shuttle  – space  – surrogate  – thermal  – thermosensitive  – vapor  – vaporization  – water

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APA (6th Edition):

Kelly, S. B. (2012). Experiments in Thermosensitive Cavitation of a Cryogenic Rocket Propellant Surrogate. (Doctoral Dissertation). University of Florida. Retrieved from http://ufdc.ufl.edu/UFE0044519

Chicago Manual of Style (16th Edition):

Kelly, Sean B. “Experiments in Thermosensitive Cavitation of a Cryogenic Rocket Propellant Surrogate.” 2012. Doctoral Dissertation, University of Florida. Accessed October 23, 2019. http://ufdc.ufl.edu/UFE0044519.

MLA Handbook (7th Edition):

Kelly, Sean B. “Experiments in Thermosensitive Cavitation of a Cryogenic Rocket Propellant Surrogate.” 2012. Web. 23 Oct 2019.

Vancouver:

Kelly SB. Experiments in Thermosensitive Cavitation of a Cryogenic Rocket Propellant Surrogate. [Internet] [Doctoral dissertation]. University of Florida; 2012. [cited 2019 Oct 23]. Available from: http://ufdc.ufl.edu/UFE0044519.

Council of Science Editors:

Kelly SB. Experiments in Thermosensitive Cavitation of a Cryogenic Rocket Propellant Surrogate. [Doctoral Dissertation]. University of Florida; 2012. Available from: http://ufdc.ufl.edu/UFE0044519

.