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Calculation method of satellite closed-loop test jet thrust control

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

Active Publication Date: 2014-06-04
哈尔滨工大卫星技术有限公司
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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 in conjunction with the accompanying drawings.

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

[0042] The part on the star and the part on the ground, in which,

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

[0044] Between the output end of described jet propulsion controller 102 and the input end of described dynamics computer 103, be connected by first communication;

[0045] The output end of the dynamics computer 103 and the input end of the attitude and track 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 10...

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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 jet thrust control of satellite closed-loop testing, 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 test 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] A closed-loop test system generally includes an attitude and orbit control computer, an actuator, a sensor simulator, and a dynamics computer. The sensor simulator can be simulated by a mathematical model in the dynamics computer. The attitude and orbit control computer calculates the control torque and thrust, the actuator recei...

Claims

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Application Information

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Patent Type & Authority Patents(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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