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Calculation method of satellite closed-loop test jet thrust control

A closed-loop testing and thrust control technology, applied in general control systems, control/regulation systems, instruments, etc., to solve problems such as jet thrust modeling

Active Publication Date: 2012-07-18
哈尔滨工大卫星技术有限公司
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  • Abstract
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  • Application Information

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Problems solved by technology

[0007] The purpose of the present invention is to propose a calculation method for satellite closed-loop test jet thrust control, solve the problem of how to calculate the jet thrust in each dynamic calculation cycle, and solve how to model the valve characteristics of the jet thrust, and Its nonlinear description is introduced into the closed-loop test system to make the closed-loop simulation test more accurate, more credible, and more similar to the actual situation

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  • Calculation method of satellite closed-loop test jet thrust control
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Embodiment Construction

[0040] The above and other technical features and advantages of the present invention will be described in more detail below with reference to the accompanying drawings.

[0041] like figure 1 As shown, the present invention discloses a closed-loop test system for satellite jet thrust control, comprising:

[0042] The on-star part and the terrestrial part, of which,

[0043] The ground part includes a dynamics computer 103, and the on-board part includes a jet thrust controller 102, an attitude and orbit control computer 101;

[0044] The output end of the jet thrust controller 102 and the input end of the dynamics computer 103 are connected through a first communication;

[0045] The output end of the dynamics computer 103 and the input end of the attitude and orbit control computer 101 are connected through a second communication;

[0046] The output end of the attitude and orbit control computer 101 and the input end of the jet thrust controller 102 are connected through...

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Abstract

The invention provides a calculation method of satellite closed-loop test jet thrust control, which comprises the following steps of: step S1, establishing a jet thrust density distribution function and carrying out piecewise linearization description; step S2, converting a jet instruction opening and closing moment into a jet valve opening and closing moment through the jet thrust density distribution function; step S3, determining the distribution of the jet thrust instruction opening and closing moment in a plurality of dynamic calculation cycles; step S4, establishing a relation between the jet valve opening and closing moment and a dynamic calculation moment; and step S5, calculating the engine thrust of each dynamic calculation cycle in one attitude and orbit control cycle. With the adoption of the calculation method, the calculation problem of jet thrust of each dynamic calculation cycle in the attitude and orbit control cycle as well as the problem that a jet thrust valve switch is nonlinearly modeled, and the nonlinear description of the jet thrust valve switch is introduced into a closed loop test system, so that the closed loop simulation test is more accurate are solved.

Description

technical field [0001] The invention relates to the field of satellite testing, in particular to a calculation method for satellite closed-loop testing jet thrust control, and belongs to the field of closed-loop testing of satellite attitude and orbit control subsystems. Background technique [0002] The closed-loop test of the satellite attitude and orbit parameter control subsystem is an important part of the satellite test. The purpose is to verify the rationality and correctness of the control system scheme, control algorithm and software design. Jet thrust is a common control method for satellite attitude and orbit parameter control. [0003] The closed-loop test system generally includes attitude and orbit control computers, actuators, sensor simulators, and dynamics computers. The sensor simulators can be simulated by mathematical models in the dynamics computer. The attitude and orbit control computer calculates the control torque and thrust, the actuator receives t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B17/02
Inventor 李化义李冬柏耿云海曹喜滨徐国栋吴丽娜管宇王峰
Owner 哈尔滨工大卫星技术有限公司
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