Detonation Wave Collision Study During Rotating Detonation Rocket Engine Counter-Propagating Modes
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Rocket engine
Rocket (weapon)
The rockets are special products-variety much,but batch smaller.In this paper, little rockets how to be tested in a lager rocket thrust tester,that is how to widen the measure range of a rocket thrust tester, are presented and studied. It is pointed that the keys are how to install the rocket on a tester,ensure measuring accuracy and the calibration of the rocket thrust tester,the problems are studied in detail theoretically, the mechanical models are established,the measuring errors are analysed, and the steps to solve the problems are presented and demonstrated.As a result,it is pointed that any little rockets could to be tested in a lager rocket thrust tester,but the conditions are little frictions.
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Rocket engine
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Rotating detonation rocket engines (RDREs) exhibit various unsteady phenomena, including modal transitions, that significantly affect their operation, performance and stability. The dynamics of the detonation waves are studied during a descending modal transition (DMT) where four co-rotating detonations waves decrease to three in a gaseous methane-oxygen RDRE. Detonation wave tracking is applied to capture, visualize and analyze unsteady, 3D detonation wave dynamics data within the combustion chamber of the RDRE. The mechanism of a descending modal transition is the failure of a detonation wave in the RDRE, and in this study, the failing wave is identified along with its failure time. The regions upstream of each relative detonation show the mixture and flow-field parameters that drive detonation failure. Additionally, it is shown that descending modal transitions encompass multiple phases of detonation decay and recovery with respect to RDREs. The results show high upstream pressure, heat release and temperature, coupled with insufficient propellants, lead to detonation wave failure and non-recovery of the trailing detonation wave during a descending modal transition. Finally, the Wolanski wave stability criterion regarding detonation critical reactant mixing height provides insight into detonation failure or sustainment.
Rocket engine
Large-Eddy Simulation
Rocket (weapon)
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A short-duration rocket testing technique which exactly duplicates the combustion flows of multi-engine rocket boosters at high altitudes is described. The application of this technique to the investigation of the reverse flow characteristics of a 4-engine rocket cluster model is discussed. The use of a comparatively new diagnostic tool, the electron beam density probe, in mapping the recirculating flow field of a rocket cluster is described and experimental density results presented. Finally, the use of a reflection plane for the examination of reverse flow phenomena, whereby a plane of symmetry is replaced by a solid surface on which measurements may be made,is evaluated and experimental data presented.
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Rocket engine
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Abstract : ;Contents: General information about combined rocket engines; Heat exchange in the combustion chamber of combined rocket engines; Heterogeneous burning in the combined rocket engine; Selection of the basic parameters of combustion chamber of a combined rocket engine; Static characteristics of combined rocket engines; The control of combined rocket engines.
Rocket (weapon)
Rocket engine
Liquid-propellant rocket
Rocket engine nozzle
Rocket propellant
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As a matter of fact, rocket engine technology has developed rapidly in the last 100 years, which plays a crucial role for stellar travelling and detection for astrophysics usages. To be specific, different models, designs and simulation computer software had been developed in order to investigate and explore the dynamic process of the engines as well as evaluate the effectiveness and ability of the rocket engines. With this in mind, this paper gives a basic description of the designs, simulations, and products for rocket engines. In detail, this study will include description of four basic designs of rocket engine systems, a summary of simulation software and, two examples of rocket engine products including nuclear engines. According to the analysis, the current results and the limitations for the advanced facilities will be demonstrated. Overall, these results shed light on guiding further exploration of designs, improvements and implementations for rocket engines based on the state-of-art techniques.
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Rocket engine
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The seal cap design of rocket pod/container(RP/C) is one of the key technical problems in rocket launching device.The impacting force in the whole process of test during fire could not be acquired because of the specialty of this kind of rocket.Due to this reason,the impacting force of rocket to seal cap in a certain rocket pod/container(RP/C) were simulated and tested by use of LS-DYNA explicit center difference method.This method can solve the difficult problem that the instantaneous response of seal cap impacted by rocket can not be tested to obtain during rocket launcher was carrying out the live fire.The numerical simulation results was compared with the test results,and the relative error was less than 12%.The numerical simulation results can provide a correct theory method for proper design of seal cap.According to the numerical simulation results,the improved design of seal cap was verified by means of launching experiment,and it can meet the qualification requirements of rocket launcher system.
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Methods has been developed for calculating corrections to the aerodynamic coefficients of forces and moments acting on a rocket during successive launches, based on processing the results of numerical simulation of a flowing around a rocket from a jet engine ahead of a flying rocket. Using the obtained dependences for aerodynamic coefficients, a study was made of the influence of a jet stream on the accuracy of firing from a moving carrier under various initial launch conditions.
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Rocket engine
Aerodynamic force
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This paper describes a new design of electrically powered rocket engine. A microwave thermal rocket uses microwave energy to heat a propellant, which expands in the rocket chamber and out of the rocket’s nozzle, the reaction of which pushes the rocket forwards. It is shown that by varying the mass flow rate, the exhaust velocity and thrust can be altered arbitrarily, making the rocket theoretically suitable for both atmospheric and orbital propulsion. A performance comparison is done with existing forms of space propulsion and ideas for further development are given.
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Rocket engine nozzle
Rocket engine
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Liquid-propellant rocket
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The traditional and most used method of launching payloads into Earth orbit is to launch a carrier rocket from the surface. An alternative method of space transport is launching payloads into Earth's orbit using air-rocket (air-assisted) systems. The concept of mixed space transport involves launching a space rocket with a payload from an aircraft or other reusable platform-carrier at a specific altitude above the Earth's surface. The air-rocket system enables the launch of small satellites while reducing ground infrastructure and costs. Such a method seems promising in the context of relatively cheap, mobile and responsive small payload launch systems. It is an interesting proposition and beneficial especially for countries without convenient conditions to build their own spaceport. The paper analyses the fundamental requirements for the design of rockets used in this type of system and performs preliminary calculations of a conceptual two- and three-stage rocket capable of lifting a payload of 10 kg into a zero-inclination orbit at an altitude of 500 km. The analyses carried out were based on available research reports in this area.
Rocket (weapon)
Payload (computing)
Space launch
Orbit (dynamics)
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