A method for quickly estimating the size and weight of an attitude control double-component thrust chamber
A technology of thrust chamber and dual components, which is applied in the fields of instruments, design optimization/simulation, calculation, etc., can solve the problems of long demonstration time period, and achieve the effect of effective design and performance prediction
Active Publication Date: 2019-04-23
XIAN AEROSPACE PROPULSION INST
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Problems solved by technology
[0004] The purpose of the present invention is to provide a method for quickly estimating the size and weight of the dual-component thrust chamber for attitude control, so as to solve the problem of long demonstration time period of the current attitude control power system. Fast iteration of the scheme, under the condition of ensuring the prediction accuracy, quickly predict the performance of the thrust chamber, and support the demonstration of the overall system scheme
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[0087] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.
[0088] 1) Scheme design
[0089] 1.1) Divide the attitude control bicomponent thrust chamber into three main parts: head, body and nozzle.
[0090] 1.2) Carry out thermodynamic calculations according to the overall technical index requirements for propellant type, mixing ratio, thrust, weight and space size envelope, calculate the change of specific impulse under different pressures, and obtain the direct change relationship between specific impulse and pressure. The design chamber pressure; correspondingly obtain the thermal performance parameter data under the chamber pressure.
[0091] 2) Size determination
[0092] The geometric parameters that need to be input or selected by the designer through the interface in the body design stage mainly include: throat radius, characteristic length, arc radius upstream of the throat, arc radius downs...
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The invention provides a method for quickly estimating the size and weight of an attitude control double-component thrust chamber. An attitude control double-component thrust chamber is divided into three main parts; the quantitative description is conducted on the design key size and performance parameters in the design process, the geometric outline of the thrust chamber is obtained through parameter driving, the wall thickness of the thrust chamber is determined according to the selected safety coefficient through an intensity checking formula, and the weight of the thrust chamber is obtained through statistical calculation in combination with the selected material density. And researchers are helped to quickly and effectively carry out thrust chamber design and performance estimation.According to the method, the rapid design and performance prediction of the attitude control double-component thrust chamber product are achieved in the demonstration stage of the power system, the design demonstration efficiency of the product is improved to a great extent, the demonstration period is shortened, and the method has a large application prospect in the field of attitude control system design.
Description
technical field [0001] The invention relates to a method for quickly estimating the size and weight of an attitude control double-component thrust chamber, which can be applied to the design of the double-component thrust chamber. Background technique [0002] Attitude-orbit control power system is an important actuator to achieve precise control of the target, providing power for the related systems to adjust the orbit and attitude. Among them, the dual-component attitude and orbit control power system has become the preferred solution due to its high performance advantages. [0003] At present, an attitude and orbit control dynamic system has a long demonstration time period, and there are multiple rounds of iterations between the overall system and the component design, and the system scheme is optimized by comparing multiple schemes of the system. According to the current method, systematic demonstration requires the cooperation of components. If the detailed design mod...
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Login to View More IPC IPC(8): G06F17/50
CPCG06F30/20Y02T90/00
Inventor 胡海峰李晓瑾肖明杰程奇峰李亮栾叶君胡伟
Owner XIAN AEROSPACE PROPULSION INST