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Performance analysis of lobed nozzle ejectors for high altitude simulation of rocket engines

International Journal of Modeling, Simulation, and Scientific Computing 2014年第4期5卷 139-157页

作者： J.Bruce Ralphin Rose J.Veni Grace Department of Aeronautical Engineering Regional Centre of Anna University Tirunelveli India627007

Ejectors are used in high altitude testing of rocket engines to create vacuum for simulat-ing the engine test in vacuum *** performance of an ejector plays a vital role in creating vacuum at the exit of the engine nozzle and the nozzle design exit pressure at the time of ***,the performance of ejectors has to be improved to reduce the consumption of active *** this investigation,the performance of an ejector has been improved by changing the exit shear plane of the ***,conical nozzles are used for creating the required *** of 4 no’s,6 no’s and 8 numbers for an equivalent area ratio=5.88 are used to increase the shear *** influence of shear plane variation in the suction pressure is studied by a detailed CFD analysis.

关键词： High altitude testing lobed nozzles ejector performance thrust augmentation

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Effect of inlet-valve structures on thrust of airbreathing pulse detonation engines

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Propulsion and Power Research 2021年第4期10卷 332-346页

作者： Wenjuan Chen Wei Fan Feiteng Luo Gaohu Tang Yaosong Long School of Aerospace Engineering Huazhong University of Science and TechnologyWuhan430074China School of Power and Energy Northwestern Polytechnical UniversityXi’an710072China

Experimental studies were conducted in order to improve the understanding of the thrust generation and the pressure/flame reverse propagation of the air-breathing pulse detonation engines(APDEs)with self-designed inlets and valves *** present experimental research utilized a gasoline/air APDE(with 68 mm inner-diameter,2050 mm length and maximum operating frequency not less than 40 Hz which was as a benchmark structure)at different operating frequencies,with freestream air inflow of 1.1 atm and 0℃.The theoretical equivalence ratio of gasoline/air was *** kinds of inlets with centerbody or without were considered and combined with two kinds of self-designed valves(the elastic-valve and the convergent aero-valve)specially designed for comparative *** the test,the inflow parameters,the pressure along the longitudinal direction inside the engine and the thrust force were measured for the APDE operating characteristic analysis,including the detonation combustion,the aerodynamic drag,the pressure/flame reverse propagation and the thrust *** research results indicate that:The inlet centerbody does not increase drag but plays a positive effect on airflow stability and operation *** elastic-valve and the convergent aero-valve,though increase the inlet aerodynamic drag,have obvious effects on suppressing the detonation wave and pressure forward propagation,resulting in effective thrust *** of the convergent aero-valve are the best when the flow choked,while the effects of elastic-valve are better and continuously stable in a wider range of *** wmaximum nondimensional thrust increases with the elastic-valve is reached about 1.12 at the frequency of 8-9 Hz,and about 0.97 with the convergent aero-valve at the frequency of 7 *** maximum fuel specific impulse is 2514.6 s when using the convergent *** this study provides technical reserve for the APDE optimization design.

关键词： Air-breathing pulse detonation engine Elastic-valve Convergent aero-valve thrust augmentation Pressure/flame reverse propagation

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Experimental and Theoretical Research Review of Hybrid Rocket Motor Techniques and Applications

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Advances in Aerospace Science and Technology 2016年第3期1卷 71-82页

作者： Entidhar A. Alkuam Wissam M. Alobaidi Department of Physics and Astronomy College of Arts Letters and Sciences University of Arkansas at Little Rock Little Rock AR USA Systems Engineering Department Donaghey College of Engineering & Information Technology University of Arkansas at Little Rock Little Rock AR USA Department of Engineering Technology Donaghey College of Engineering & Information Technology University of Arkansas at Little Rock Little Rock AR USA

A hybrid rocket motor combines components from both solid fuel and liquid fuel rocket motors. The fuel itself is a solid grain, (often paraffin or hydroxyl-terminated polybutadiene, known as HTPB) while the oxidizing agent is liquid (often hydrogen peroxide or liquid oxygen). These components are combined in the fuel chamber which doubles as the combustion chamber for the hybrid motor. This review looks at the advances in techniques that have taken place in the development of these motors since 1995. Methods of testing the thrust from rocket motors and of measuring the rocket plume spectroscopically for combustion reaction products have been developed. These assessments allow researchers to more completely understand the effects of additives and physical changes in design, in terms of regression rates and thrust developed. Hybrid rocket motors have been used or tested in many areas of rocketry, including tactical rockets and large launch vehicles. Several additives have shown significant improvements in regression rates and thrust, including Guanidinium azotetrazolate (GAT), and various Aluminum alloys. The most recent discoveries have come from research into nano-particle additives. The nano-particles have been shown to provide enhancements to many parameters of hybrid rocket function, and research into specific areas continues in the sub-field of nano-additives for fuel grains.

关键词： Hybrid Rocket Motor Sounding Rockets Tactical Rockets Space Engines thrust augmentation Large Launch Boosters Fuel Additives Regression Rate

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