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Dissertations / Theses on the topic 'Engine thrust'

Author: Grafiati

Published: 4 June 2025

Last updated: 1 August 2025

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1

Hackaday, Gary L. "Thrust augmentation for a small turbojet engine." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1999. http://handle.dtic.mil/100.2/ADA362981.

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Thesis (M.S. in Aeronautical Engineering) Naval Postgraduate School, March 1999.<br>Thesis advisor(s): Garth V. Hobson. "March 1999". Includes bibliographical references (p. 75). Also available online.

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2

MEDICI, GIOVANNI. "Thrust vectoring on an UCAV airplane (thrust vectoring engine model): advanced control system." Doctoral thesis, Politecnico di Torino, 2013. http://hdl.handle.net/11583/2508286.

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Since the early development of the Sky-X UAV demonstra- tor, Alenia Aermacchi has been studying a thrust vectored version of that airplane. For this reason, in 2010, Alenia Aermacchi offered a three years PhD funding to the Depart- ment of Aerospace Engineering of Politecnico di Torino. In particular a vane based thrust vectoring system had to be studied, the development of open and flexible software tools was a priority in the project. The tools had to be cus- tomizable and a general estimation model of the system had to be developed. The research analysis took place during three years and

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3

Yarlagadda, Santosh. "Performance Analysis of J85 Turbojet Engine Matching Thrust with Reduced Inlet Pressure to the Compressor." University of Toledo / OhioLINK, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=toledo1271367584.

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4

Bartosh, Brady J. "Thrust measurement of a split-path, valveless pulse detonation engine." Thesis, Monterey, Calif. : Naval Postgraduate School, 2007. http://bosun.nps.edu/uhtbin/hyperion-image.exe/07Dec%5FBartosh.pdf.

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Thesis (M.S. in Astronautical Engineering)--Naval Postgraduate School, December 2007.<br>Thesis Advisor(s): Brophy, Christopher M. "December 2007." Description based on title screen as viewed on January 17, 2008. Includes bibliographical references (p. 95-96). Also available in print.

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5

Boggs, George Lemuel IV. "Turbine Engine Thrust Measurements Using a Non-Intrusive Acoustic Technique." Thesis, Virginia Tech, 2019. http://hdl.handle.net/10919/90299.

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Experiments were conducted to measure the thrust generated from a commercial jet engine. This thrust estimation was done using a pneumatic horn as the sound source with two arrays of microphones directly across the exhaust stream. The two arrays were separated by an axial distance downstream. Exhaust centerline measurements were taken at varying engine conditions, specifically; 30%, 50%, 60%, 70%, 80% and 100% engine power. An acoustic thrust estimation showed good agreement with measured thrust during the test campaign. In addition, a full traverse of the acoustic rig through the exhaust stre

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6

Schaefermeyer, M. Ryan. "Aerodynamic Thrust Vectoring For Attitude Control Of A Vertically Thrusting Jet Engine." DigitalCommons@USU, 2011. https://digitalcommons.usu.edu/etd/1237.

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NASA’s long range vision for space exploration includes human and robotic missions to extraterrestrial bodies including the moon, asteroids and the martian surface. All feasible extraterrestrial landing sites in the solar system are smaller and have gravitational fields of lesser strength than Earth’s gravity field. Thus, a need exists for evaluating autonomous and human-piloted landing techniques in these reduced-gravity situations. A small-scale, free-flying, reduced-gravity simulation vehicle was designed by a group of senior mechanical engineering students with the help of faculty and grad

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7

Dunn, Francis X. "Thrust modulated multivariable control of the GE21 engine using the LQG/LTR method." Thesis, Massachusetts Institute of Technology, 1986. http://hdl.handle.net/1721.1/15000.

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Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Electrical Engineering and Computer Science, 1986.<br>MICROFICHE COPY AVAILABLE IN ARCHIVES AND ENGINEERING<br>Bibliography: leaves 173-175.<br>by Francis X. Dunn.<br>M.S.

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8

Alves, Wilton Fernandes. "Development of experimental firing test stand to study the rocket engine thrust characteristics." Instituto Tecnológico de Aeronáutica, 2008. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=2324.

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The main aim of this work is to present the specification of an experimental firing test stand of liquid rocket engine (LRE), comprising the main design, the instrumentation of measurement system, the data acquisition system, the operating manual, as well as the methodology to perform laboratory work for determination of a LRE thrust characteristics in atmospheric conditions. Initially it is presented a theoretical basement of LRE in general and concerning the laboratory work. After that it is proposed a methodology for execution of laboratory work using resources of information technology, wh

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9

MacLeod, James D. (James Donald) Carleton University Dissertation Engineering Aeronautical. "A derivation of gross thrust for a sea-level jet engine test cell." Ottawa, 1988.

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10

Gullia, Alessandro. "Thrust and Flow Prediction in Gas Turbine Engine Indoor Sea-Level Test Cell Facilities." Thesis, Cranfield University, 2006. http://dspace.lib.cranfield.ac.uk/handle/1826/7496.

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The principal aim of this research was to provide a detailed understanding of the performance of gas turbine engines inside indoor sea-level test beds. In particular the evaluation of both thrust correction factors and the estimation of the mass flow entering the test cell were at the core of the research. The project has been fully sponsored by Rolls-Royce pIc. Initially, their principal objective was to assess the relevance and accuracy of CFD when applied to thrust measurement inside indoor test beds with an intended outcome of minimising the use of expensive experimental measurements. The

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11

Wu, Fuh-Eau. "Aero engine life evaluated for combined creep and fatigue, and extended by trading-off excess thrust." Thesis, Cranfield University, 1994. http://dspace.lib.cranfield.ac.uk/handle/1826/10517.

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This thesis investigates the concept of thrust rating as a means towards reducing the life cycle costs of engine ownership. Towards this end, this thesis has discussed the concept of thrust rating, developed computer programs for mechanical load type failures, which include creep, LCF, and combinations thereof, and conducted simulations of improving life usage and reducing life cycle costs. A study was performed on a military engine, under an original design mission mix, that showed significant gains in creep-LCF life of the HPT blade could be achieved, especially With the recently proposed an

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12

Sarwade, Rohit Foster Winfred A. "Life prediction analysis of a subscale rocket engine combustor using a fluid-thermal-structural model." Auburn, Ala., 2006. http://repo.lib.auburn.edu/2006%20Spring/master's/SARWADE_ROHIT_49.pdf.

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13

Allenstein, Jacob T. "An Investigation in Gold-Plating Scaled Turbofan Engine Simulators through Means of Aerodynamic and Load Cell Thrust Measurements with Comparisons to Full-Scale Engine Results." The Ohio State University, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=osu1386061117.

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14

Wu, F.-E. "Aero engine life evaluated for combined creep and fatigue, and extended by trading-off excess thrust." Thesis, Cranfield University, 1994. http://dspace.lib.cranfield.ac.uk/handle/1826/10517.

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This thesis investigates the concept of thrust rating as a means towards reducing the life cycle costs of engine ownership. Towards this end, this thesis has discussed the concept of thrust rating, developed computer programs for mechanical load type failures, which include creep, LCF, and combinations thereof, and conducted simulations of improving life usage and reducing life cycle costs. A study was performed on a military engine, under an original design mission mix, that showed significant gains in creep-LCF life of the HPT blade could be achieved, especially With the recently proposed an

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15

Wittmers, Nicole K. "Direct-connect performance evaluation of a valveless pulse detonation engine." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2004. http://library.nps.navy.mil/uhtbin/hyperion/04Dec%5FWittmers.pdf.

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16

Sakai, Tadashi. "A Study of Variable Thrust, Variable Specific Impulse Trajectories for Solar System Exploration." Diss., Georgia Institute of Technology, 2004. http://hdl.handle.net/1853/4904.

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A study has been performed to determine the advantages and disadvantages of variable thrust and variable specific impulse (Isp) trajectories for solar system exploration. There have been several numerical research efforts for variable thrust, variable Isp, power-limited trajectory optimization problems. All of these results conclude that variable thrust, variable Isp (variable specific impulse, or VSI) engines are superior to constant thrust, constant Isp (constant specific impulse, or CSI) engines. However, most of these research efforts assume a mission from Earth to Mars, and some of them

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17

Micklewright, Alan J. "An analysis of single-engine rate-of-climb capabilities and thrust requirements of the S-3 and ES-3 aircraft in support of the TF34 Engine Component Improvement Program." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1995. http://handle.dtic.mil/100.2/ADA302899.

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18

Martinez, Anna. "Design and manufacturing of a thrust measurement system for a micro jet engine : Enabling in-flight drag estimation for subscale aircraft testing." Thesis, Linköpings universitet, Fluida och mekatroniska system, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-149288.

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Good estimation of aerodynamic coefficients is of fundamental importance in the design and development process of an aircraft. Generally, these parameters are obtained using analytical, numerical and experimental methods, which are sometimes either inaccurate or very expensive. The use of subscale aircraft is becoming increasingly common in the study and evaluation of new aircraft concepts. Flight testing results in an efficient solution for obtaining parameters that can define drag characteristics. This project presents a solution for achieving the drag aerodynamic model from the design and m

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19

Oliver, Michael James. "A STUDY ON THE PHYSICS OF ICE ACCRETION IN A TURBOFAN ENGINE ENVIRONMENT." Case Western Reserve University School of Graduate Studies / OhioLINK, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=case1363875844.

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20

Bulut, Jane. "Design and CFD analysis of the demonstrator aerospike engine for a small satellite launcher application." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2020.

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Starting with a brief overview of thrust generation for launchers, this study focuses on the design process of the demonstrator aerospike engine, DEMOP-1, of the Pangea Aerospace's commercial grade engine and its flow field analysis. The primary goal of the study is to obtain the plug nozzle design delivers 30 kN thrust using cryogenic liquid oxygen (LOX) as the oxidizer and cryogenic liquid methane (LCH4) as the fuel, with the mixture ratio of 3.4. Design parameters considered as 30 bar of combustion chamber pressure (Po) and expansion ratio as 15 for an optimum expanded nozzle. On the basi

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21

Mutschall, Marcel. "Die Genauigkeit einer vereinfachten Berechnung der Steigzeit von Flugzeugen." Aircraft Design and Systems Group (AERO), Department of Automotive and Aeronautical Engineering, Hamburg University of Applied Sciences, 2018. http://d-nb.info/1175497711.

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Ziel - Die Zeit die ein Flugzeug benötigt, um auf eine bestimmte Höhe zu steigen (die Steigzeit) kann mit einer Formel berechnet werden, die vereinfachend annimmt, dass die Steiggeschwindigkeit über dem gesamten Steigflug mit zunehmender Höhe linear abnimmt. Ziel der Untersuchung ist, zu ermitteln, ob die Annahme einer linear abnehmenden Steiggeschwindigkeit realistisch ist bzw. welche Fehler sich aus der Annahme ergeben. ----- Methode - Mit der Höhe ändern sich Parameter wie Luftdichte, Widerstand, Schub und damit auch die optimale Fluggeschwindigkeit für den Steigflug. Die Parameter beeinflu

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22

Harl, Nathan Robert. "Low-thrust control of a lunar orbiter." Diss., Rolla, Mo. : University of Missouri-Rolla, 2007. http://scholarsmine.mst.edu/thesis/pdf/Thesis_09007dcc80318673.pdf.

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Thesis (M.S.)--University of Missouri--Rolla, 2007.<br>Vita. The entire thesis text is included in file. Title from title screen of thesis/dissertation PDF file (viewed October 24, 2007) Includes bibliographical references (p. 95-98).

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23

Bensel, Artur. "Characteristics of the Specific Fuel Consumption for Jet Engines." Aircraft Design and Systems Group (AERO), Department of Automotive and Aeronautical Engineering, Hamburg University of Applied Sciences, 2018. http://d-nb.info/1175791237.

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Purpose of this project is a) the evaluation of the Thrust Specific Fuel Consumption (TSFC) of jet engines in cruise as a function of flight altitude, speed and thrust and b) the determination of the optimum cruise speed for maximum range of jet airplanes based on TSFC characteristics from a). Related to a) a literature review shows different models for the influence of altitude and speed on TSFC. A simple model describing the influence of thrust on TSFC seems not to exist in the literature. Here, openly available data was collected and evaluated. TSFC versus thrust is described by the so-call

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24

Weber, Fabian. "Optical Analysis of the Hydrogen Cooling Film in High Pressure Combustion Chambers." Thesis, Luleå tekniska universitet, Rymdteknik, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-76872.

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For performance optimisation of modern liquid cryogenic bipropellant rocket combustion chambers, one component which plays an important role in reducing the wall side heat flux, is the behaviour of the cooling film. At the Institute of Space Propulsion of the German Aerospace Center (DLR) in Lampoldshausen, hot test runs have been performed using the experimental combustion chamber BKM, to investigate the wall side heat flux which is -- among other factors -- dependent on cooling film properties. To gain more insight into the film behaviour under real rocket-like conditions, optical diagnostic

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25

Dwyer, Michael E. "Quasi-optimal steady state and transient maneuvers with and without thrust vectoring." Thesis, This resource online, 1993. http://scholar.lib.vt.edu/theses/available/etd-09292009-020230/.

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26

Ragozin, Konstantin. "Thrust Performance and Heat Load Modelling of Pulse Detonation Engines." Thesis, Luleå tekniska universitet, Institutionen för system- och rymdteknik, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-82438.

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Pulse Detonation Engines (PDEs) are propulsion systems that use repeated detonations to generate thrust. Currently in early stages of development, PDEs have been theorised to have advantages over current deflagration based engines. Air-breathing PDEs could attain higher specific impulse values and operate at higher Mach numbers than today's air-breathing engines, while Pulse Detonation Rocket Engines (PDREs) could become a lighter, cheaper, and more reliable alternative to traditional rocket engines. There are still however, many technological hurdles to overcome before PDEs can be developed i

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27

Josselyn, Scott B. "Optimization of low thrust trajectories with terminal aerocapture." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2003. http://library.nps.navy.mil/uhtbin/hyperion-image/03Jun%5FJosselyn.pdf.

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Thesis (Aeronautical and Astronautical Engineer)--Naval Postgraduate School, June 2003.<br>Thesis advisor(s): I. Michael Ross, Steve Matousek. Includes bibliographical references (p. 149-150). Also available online.

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28

Rust, Jack W. "Fuel optimal low thrust trajectories for an asteroid sample return mission." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2005. http://library.nps.navy.mil/uhtbin/hyperion/05Mar%5FRust.pdf.

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29

Miller, Robert E. Hartfield Roy J. "Design and testing of a gas distribution method for pulsed inductive thruster." Auburn, Ala, 2008. http://hdl.handle.net/10415/1405.

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30

Ho, Ivan Chin Kian. "Investigation on novel methods to increase specific thrust in pulse detonation engines via imploding detonations." Thesis, Monterey, California : Naval Postgraduate School, 2009. http://edocs.nps.edu/npspubs/scholarly/theses/2009/Dec/09Dec%5FHo%5FIvan.pdf.

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Thesis (M.S. in Mechanical Engineering and M.S. in Applied Physics)--Naval Postgraduate School, December 2009.<br>Thesis Advisor(s): Sinibaldi, Jose. O. ; Brophy, Christopher M. "December 2009." Description based on title screen as viewed on January 27, 2010. Author(s) subject terms: Pulse Detonation Engines, Shock Wave, Detonation Implosions, Induction Length, Detonation Cell Width, Deflagration-to-Detonation Transition, Specific Thrust. Includes bibliographical references (p. 93-94). Also available in print.

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31

Tsiotras, Panagiotis. "Goddard-problem variants." Thesis, Virginia Polytechnic Institute and State University, 1987. http://hdl.handle.net/10919/80041.

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The problem of maximizing the altitude of a rocket in vertical flight has been extensively analyzed by many writers since the early days of rocketry. In the beginning, solutions were obtained using the classical theory of the Calculus of Variations, and later using Optimal Control theory. For strict assumptions on the drag law and the thrust, solutions were found, even in a closed, analytic form. Nevertheless, for more realistic conditions, the problem becomes a very complex one, and the solution is far from complete. In addition to this, complexity increases if an isoperimetric constraint is

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32

Phillips, Craig Alan. "Energy management for a multiple-pulse missile." Thesis, Virginia Polytechnic Institute and State University, 1986. http://hdl.handle.net/10919/91058.

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A nonlinear programming technique is applied to the optimization of the thrust and lift control histories for missiles. The first problem considered is that of determining the thrust history which maximizes the range of a continuously-variable (non-pulsed) thrust rocket in horizontal lifting flight. The optimal control solution for this problem is developed. The problem is then approximated by a parameter optimization problem which is solved using a second-order, quasi-Newton method with constraint projection. The two solutions are found to compare well. This result allows confidence in the us

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33

Krolak, Matthew Joseph. "Optimization of a magnetoplasmadynamic arc thruster." Link to electronic thesis, 2007. http://www.wpi.edu/Pubs/ETD/Available/etd-042607-155701/.

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34

Gruber, J. R. "A study of erosion due to low-energy sputtering in the discharge chamber of the Kaufman ion thruster." Thesis, University of Oxford, 2002. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.249396.

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35

Hennig, Christian [Verfasser]. "Improvements in thrust and fuel consumption for future jet engines for unmanned aerial vehicles (UAV) using variable cycle technology / Christian Hennig." München : Verlag Dr. Hut, 2017. http://d-nb.info/1139539094/34.

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36

Botha, Johannes Rudolf. "Design of an RF ion thruster." Thesis, Stellenbosch : Stellenbosch University, 2014. http://hdl.handle.net/10019.1/86267.

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Thesis (MEng)--Stellenbosch University, 2014.<br>ENGLISH ABSTRACT: Recent years have seen a decline in the rate of space exploration due to the inefficiency of chemical rockets. Therefore alternative fuel efficient propulsion methods are being sought to enable cost effective deep space exploration. The high fuel efficiency of electric thrusters enable a spacecraft to travel further, faster and cheaper than any other propulsion technology available. Thus electric propulsion has become the propulsion of choice for scientists and engineers. A typically electric thruster contains some sort of

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37

Magklaras, Georgios Vasilios. "An insider misuse threat detection and prediction language." Thesis, University of Plymouth, 2012. http://hdl.handle.net/10026.1/1024.

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Numerous studies indicate that amongst the various types of security threats, the problem of insider misuse of IT systems can have serious consequences for the health of computing infrastructures. Although incidents of external origin are also dangerous, the insider IT misuse problem is difficult to address for a number of reasons. A fundamental reason that makes the problem mitigation difficult relates to the level of trust legitimate users possess inside the organization. The trust factor makes it difficult to detect threats originating from the actions and credentials of individual users. A

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38

Thrun, Alexander [Verfasser]. "Investigation of the laminar and turbulent combustion behavior in a one-cylinder internal combustion engine / Alexander Thrun." Kiel : Universitätsbibliothek Kiel, 2016. http://d-nb.info/1117540421/34.

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39

Ogunjobi, Taiwo A. "Computational Study of Ring-Cusp Magnet Configurations that Provide Maximum Electron Confinement." Wright State University / OhioLINK, 2006. http://rave.ohiolink.edu/etdc/view?acc_num=wright1166226698.

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40

Penkal, Bryan James. "Steps in the Development of a Full Particle-in-Cell, Monte Carlo Simulation of the Plasma in the Discharge Chamber of an Ion Engine." Wright State University / OhioLINK, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=wright1367586856.

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41

PAISSONI, CHRISTOPHER ANDREA. "Comprehensive approach to electric propulsion for innovative space platforms." Doctoral thesis, Politecnico di Torino, 2021. http://hdl.handle.net/11583/2945189.

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42

He, JHIH-JHONG, and 何志忠. "Numerical Thermo-Fluids Analysis of High Thrust Engine''s Hush House." Thesis, 2009. http://ndltd.ncl.edu.tw/handle/76647740259186616780.

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碩士<br>逢甲大學<br>航太與系統工程所<br>97<br>The major objective of this research is to develop a numerical simulation process to study an engine hush house and assure the temperature, velocity and pressure of the internal flow and house wall can meet the hush house regulation. We also adopt three different kinds of noise-reducing pipe installed at the augmenter inlet to understand their influences on the flow fields. Firstly, we create a hush house model included a F100-PW-100 turbojet engine by using ANSYS Design Modeler software. Meantime, in order to simulate the engine’s jet flow and reflection wave i

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43

Shehadeh, Ra'fat. "Study of ejector geometry on thrust augmentation for pulse detonation engine ejector systems." 2007. http://www.etda.libraries.psu.edu/theses/approved/WorldWideIndex/ETD-1961/index.html.

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44

BETTI, BARBARA. "Flow field and heat transfer analysis of oxygen/methane liquid rocket engine thrust chambers." Doctoral thesis, 2012. http://hdl.handle.net/11573/917591.

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This study is devoted to the characterization and analysis of the ﬂow ﬁeld and heat transfer in oxygen/methane liquid rocket engines. Attention is focused on the hot gas side of the thrust chamber, where highly energetic ﬂows have to be managed en- suring the safe operation of the thrust chamber and of the entire engine. Diﬀerent technological solutions to handle such ﬂows are here investigated by means of CFD numerical simulations. As a compromise between details and computational cost, the attention is focused on capturing the basic phenomena involved which drive the main heat transfer proc

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45

Lung-Da, Wang, and 王隆達. "Assessment for the Effects of Reduced Thrust Taking-off on Airport Environment and Engine Performace." Thesis, 2009. http://ndltd.ncl.edu.tw/handle/57438662384310431924.

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碩士<br>開南大學<br>空運管理學系<br>97<br>Global air transportation is growing up constantly. The environmental protection issue of airborne vehicle is paid attention to continuously by the countries all over the world. There are a lot of methods to reduce the carbon accumulation accompanied with flight energy-conservation at present. However, the reduce thrust take-off was worldwide used by airlines for it neither expanding the cost nor changing the air traffic management. In order to accurately understand the benefit difference of reduced thrust during take-off. This research noted down the materials i

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46

Zheng, Bo-Sheng, and 鄭博升. "The Develpoment of an Engine Powered Ornithopter- The Measurement of Lift and Thrust of the Flapping-Wing -." Thesis, 2004. http://ndltd.ncl.edu.tw/handle/73026875779671131993.

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碩士<br>大同大學<br>機械工程學系(所)<br>93<br>This research takes designing the engine motive to rush toward the wing machine as the target. By nature the birds fly the observation result of the type, designing the different wing type and the plane wing of the area, and carrying on the measurement that rises the power and pushes the power, discussing in the different wind velocity and offending the Cape under, it rises the power, rushes toward the wing frequency and rises the relation of the power efficiency, finding out the best wing type. The engine motive that then designs one big wing exhibition rushes

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47

Zheng, Bo-Sheng, and 鄭博升. "The Development of an Engine Powered Ornithopter ─The Measurement of Lift and Thrust of the Flapping-Wing─." Thesis, 2004. http://ndltd.ncl.edu.tw/handle/84201848984932868160.

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48

Dores, Delfim Zambujo das Collins Emmanuel G. Alvi Farruk S. "Feedback control for counterflow thrust vectoring with a turbine engine experiment design and robust control design and implementation /." Diss., 2005. http://etd.lib.fsu.edu/theses/available/etd-04082005-130006.

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Thesis (Ph. D.)--Florida State University, 2005.<br>Advisors: Dr. Emmanuel G. Collins Jr., and Dr. Farruk S. Alvi, FAMU-FSU College of Engineering, Dept. of Mechanical Engineering. Title and description from dissertation home page (viewed June 15, 2005). Document formatted into pages; contains xvii, 185 pages. Includes bibliographical references.

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49

Lee, Chia-Sung, and 李家崧. "Two-Dimensional Thrust-Vectoring Nozzle Design and Dynamic Model Development for a Micro Turbojet Engine and Its Stability Analysis and Verification of a Horizontal Pendulum." Thesis, 2004. http://ndltd.ncl.edu.tw/handle/72632217690701501669.

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碩士<br>中華大學<br>機械與航太工程研究所<br>92<br>A two-dimensional thrust-vectoring nozzle is designed for a P-80 micro turbojet engine. The dynamic model of the side force of this thrust-vectoring engine is validated through the equilibrium of a horizontal pendulum. First, a test stand is developed to measure the axial and the lateral response of the thrust-vectoring nozzle. The performance of the nozzle is used to determine the length of the side wall. The 60mm length of the side wall gives the best steady-state response overall. The turning angle of the side wall is limited to 20 degree in order to ha

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Терещенко, Юрій Юрійович, Yurii Yurioivych Тereshchenko та Юрий Юрьевич Терещенко. "Концепція інтеграції силової установки з турбовентиляторною приставкою і літального апарату". Thesis, 2019. http://er.nau.edu.ua/handle/NAU/40466.

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Abstract:

У роботі науково обґрунтована концепція аеротермогазодинамічної інте-грації триконтурного газотурбінного двигуна з турбовентиляторною пристав-кою та ступінчастої мотогондоли авіаційної силової установки. Створено нау-ково-методичний апарат для аналізу процесу аеротермогазодинамічної інтегра-ції багатоконтурних турбореактивних двигунів із заднім розташуванням турбо-вентиляторної приставки і мотогондоли авіаційної силової установки. Створено теоретичні основи аеротермогазодинамічної інтеграції багатоконтурного тур-бореактивного двигуна з турбовентиляторою приставкою та мотогондоли сило-вої уста

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