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Attitude control method, device and system for satellite platform with rotating load

A satellite platform and attitude control technology, applied in the field of satellites, can solve the problems of satellite platform attitude interference, difficulty in satellite platform attitude control, large amount of calculation and difficulty in control, etc., and achieve simple control, reduced control difficulty, and high control accuracy Effect

Active Publication Date: 2018-11-06
HARBIN INST OF TECH
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

If the satellite load needs to rotate, the rotating satellite load will interfere with the attitude of the satellite platform. At this time, the attitude control of the satellite platform is extremely difficult. In the prior art, there is no good method to accurately rotate the satellite platform of the load. Attitude control, or, the calculation amount and control difficulty in the attitude control process are large

Method used

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  • Attitude control method, device and system for satellite platform with rotating load
  • Attitude control method, device and system for satellite platform with rotating load
  • Attitude control method, device and system for satellite platform with rotating load

Examples

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example 1

[0109] This example provides an attitude control method for a satellite platform, including two parts:

[0110] A part, using a PID controller to obtain an initial control instruction; the initial control instruction here is the aforementioned first control instruction;

[0111] Step 1: Measure the actual attitude angle θ and actual angular velocity ω of the satellite platform by using the sensor on the satellite platform;

[0112] Step 2: Compare the actual attitude angle θ and the actual angular velocity ω with the known target attitude angle θ h , target angular velocity ω h Compare to get the angle deviation e θ , angular velocity deviation e ω ;

[0113] The third step: use the obtained deviation value as the input quantity of the PID controller, and the design parameter k of the PID controller p 、k i 、k d Combined to get the PID controller output control torque u 1 =k p e θ +k i ∫e θ dt+k d e ω ;k p is the proportional parameter of the PID controller; k i...

example 2

[0136] The control system of this example includes: a PID controller and a repeating controller independent of the PID controller.

[0137] The satellite platform control system is designed according to the PID controller, and its parameters are:

[0138] k d =diag([157.62 157.62 157.62]);

[0139] k p =diag([12.42 12.42 12.42]);k i =diag([0.02 0.02 0.02]);

[0140] k r =1, N=3600.

[0141] The motion period of the rotating load is 36s, and the simulation step is 0.01s, so N=36 / 0.01=3600.

[0142] The initial attitude parameter of satellite attitude is ω b0 = [0 0 0]; theta b0 = [0 00];

[0143] The target attitude parameter is ω bt = [000]; θ bt =[000];

[0144] Mass of satellite platform: 1200kg;

[0145] Mass of rotating load: 800kg;

[0146] The moment of inertia of the satellite platform:

[0147] Moment of inertia of rotating load:

[0148] Maximum speed of flywheel: 6000r / min;

[0149] Maximum angular momentum of flywheel: 50N m s;

[0150] Maximum...

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Abstract

The embodiment of the invention discloses an attitude control method, device and system for a satellite platform with a rotating load. The attitude control method of the satellite platform includes: measuring an actual attitude parameter of the satellite platform; comparing the actual attitude parameter and a target attitude parameter, and determining an attitude deviation; generating a first control instruction based on the attitude deviation; determining a learning period parameter of a repeating controller of the satellite platform according to a motion law parameter of the rotating load, wherein the repeating controller generates a second control instruction according to the learning period parameter and the first control instruction; and controlling the attitude of the satellite platform by using the second control instruction.

Description

technical field [0001] The invention relates to the field of satellite technology, in particular to an attitude control method, device and system for a satellite platform with a rotating load. Background technique [0002] A satellite can be composed of a satellite platform and a satellite payload. When the satellite load is working, the satellite platform must have a certain attitude control stability and accuracy. The higher the requirements for payload working accuracy, the higher the requirements for satellite platform attitude control. When the mass of the satellite payload is large, the moment of inertia of the satellite payload is also large. If the satellite load needs to rotate, the rotating satellite load will interfere with the attitude of the satellite platform. At this time, the attitude control of the satellite platform is extremely difficult. In the prior art, there is no good method to accurately rotate the satellite platform of the load. Attitude control,...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
CPCB64G1/244
Inventor 王峰柴利鹏谢一菲曹喜滨陈雪芹原超叶东
Owner HARBIN INST OF TECH
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