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Method for improving bipropellant attitude control thruster pulse control precision

A pulse control and thruster technology, which is applied in the direction of the guidance device of space navigation aircraft, can solve the problems of insufficient pulse control accuracy of the dual-element attitude control thruster, and achieve the goal of improving development quality, improving pulse control accuracy and reducing design difficulty. Effect

Active Publication Date: 2017-03-22
BEIJING INST OF CONTROL ENG
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Problems solved by technology

[0004] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, to propose a method for improving the pulse control accuracy of the dual-component attitude control thruster, and to solve the problem of insufficient pulse control accuracy of the existing dual-component attitude control thruster

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  • Method for improving bipropellant attitude control thruster pulse control precision

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Embodiment Construction

[0019] Specific embodiments of the present invention are further described in detail below.

[0020] In this embodiment, the design process of a two-component attitude control thruster with high pulse control precision is taken as an example. Firstly, according to the requirements of thruster pulse control precision, the relationship between thruster pulse control precision, thrust level and valve closing response time is established. Among them, the thruster pulse control accuracy requirements include the minimum pulse impulse index and the minimum pulse impulse repeatability mean square error index, the minimum pulse impulse index is represented by ΔI, and the unit is mN.s, and the minimum pulse impulse repeatability mean square error is represented by δ; The magnitude is the rated steady-state thrust of the thruster, expressed in F, and the unit is N; the valve closing response time is the time required for the thruster switch control valve to cut off the propellant flow in...

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Abstract

The invention discloses a method for improving the bipropellant attitude control thruster pulse control precision. By establishing the relation between the bipropellant attitude control thruster pulse control precision and the propellant control valve switch response time as well as the relation between the injector liquid collection cavity volume and the filling time, the method for effectively improving the bipropellant attitude control thruster pulse control precision is put forward. Quantitative design and analysis of the pulse control precision of a bipropellant attitude control thruster can be achieved, the design difficulty of the bipropellant attitude control thruster high in pulse control precision can be lowered, and the product development quality is improved.

Description

technical field [0001] The invention belongs to the technical field of space liquid rocket engines, and in particular relates to a method for improving the pulse control precision of a two-component thruster. Background technique [0002] The dual-component attitude control thruster is the most important active execution part of spacecraft attitude control, and the pulse control accuracy has a crucial impact on the spacecraft attitude control accuracy. With the increasing complexity and precision requirements of space missions, the requirements for the attitude accuracy and stability of the spacecraft platform are also getting higher and higher, which in turn requires the bicomponent thruster to further improve the pulse control accuracy. However, the pulse working process of the bicomponent attitude control thruster is very complicated, involving various complex physical and chemical processes such as electromagnetic, transient flow, non-equilibrium chemical reaction and un...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24
CPCB64G1/24
Inventor 毛晓芳汪凤山张榛蔡坤王平姚兆普官长斌陈磊卢国权杨尚峰张凤何孟琪杨柳
Owner BEIJING INST OF CONTROL ENG
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