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Spacecraft attitude control semi-physical simulation system

A semi-physical simulation and attitude control technology, applied in attitude control, general control system, control/regulation system, etc., can solve problems such as poor generality and poor systemicity, and achieve the effect of simple application, strong generality, and avoiding repeated design.

Inactive Publication Date: 2011-01-05
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The present invention aims to solve the problems of the poor versatility and poor systematicness of the existing spacecraft attitude control semi-physical simulation system, thereby proposing a spacecraft attitude control semi-physical simulation system

Method used

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  • Spacecraft attitude control semi-physical simulation system
  • Spacecraft attitude control semi-physical simulation system
  • Spacecraft attitude control semi-physical simulation system

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specific Embodiment approach 1

[0008] Specific implementation mode 1. Combination figure 1 Describe this specific embodiment, the spacecraft attitude control semi-physical simulation system, which includes the execution device on the spacecraft air-floating turntable, and the execution device on the spacecraft air-floating turntable includes an on-board computer 2, an optical fiber gyroscope 3, a star sensor Device simulator 4, jet simulator 5, reaction flywheel 6 and magnetic torque device 7, the signal input or output end of jet simulator 5 is connected with No. 1 signal output or input end of onboard computer 2, and the signal input of reaction flywheel 6 Or the output end is connected with the No. 2 signal output or input end of the on-board computer 2, and the signal input or output end of the magnetic torque device 7 is connected with the No. 3 signal output or input end of the on-board computer 2; it also includes a real-time simulator 1 , wireless communication module 8 on the stage, wireless commun...

specific Embodiment approach 2

[0024] Specific embodiment two, the difference between this specific embodiment and the spacecraft attitude control semi-physical simulation system described in specific embodiment one is that it also includes a console 13, and the control signal output end of the signal console 13 communicates with the ground wirelessly. The control signal input end of the communication module 9 is connected.

[0025] In this embodiment, at first in the ground computer, utilize the m function GUI of Matlab to write code or utilize Visual C++6.0 to write code and generate control interface, the spacecraft attitude track system model built under Matlab / Simulink is compiled into C code , through the wireless data transmission device, download the compiled code to the real-time simulator 1 on the air bearing turntable, send the start and stop simulation commands to the real-time simulator 1, send the target attitude command in real time, change the attitude flight mode in real time, and change the...

specific Embodiment approach 3

[0026] Specific embodiment three, combine figure 2 Describe this embodiment, the difference between this embodiment and the spacecraft attitude control semi-physical simulation system described in Embodiment 1 or 2 is that the flight simulation display module 11 is composed of a single-chip microcomputer 111 and an LED light 112, and the single-chip microcomputer 111 The data signal input end of the flight simulation display module 11 is the data signal input end of the flight simulation display module 11, and the power signal output end of the single-chip microcomputer 111 is connected with the power signal input end of the LED lamp.

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Abstract

The invention discloses a spacecraft attitude control semi-physical simulation system which relates to a spacecraft control semi-physical simulation system. The invention solves the problems of poor universality and systematicness in the prior spacecraft attitude control semi-physical simulation system. The simulation signal input or output end of a real-time simulation machine of the system is connected with the simulation signal output or input end of an onboard spacecraft computer; the wireless signal output or output end of a system wireless communication module is connected with the wireless signal input or output end of the real-time simulation machine; the signal output end of a ground wireless communication module is connected with the signal input end of a data storage module; the data signal output end 1 of the data storage module is connected with the data signal input end of a flight simulation display module; and the data signal output end 2 of the data storage module is connected with the data signal input end of an animation and graphic display module. The invention is suitable for simulation of spacecraft attitude control.

Description

technical field [0001] The invention relates to a semi-physical simulation system for spacecraft control. Background technique [0002] The semi-physical simulation of spacecraft control system is a unique simulation method in the process of developing spacecraft. It uses the air-bearing turntable as a motion simulator and combines some real objects to build a semi-physical simulation environment for simulation verification of control system schemes and algorithms. The air-floating turntable uses compressed air to form an air film between the air-floating bearing and the bearing seat to make the table float in the air, so as to realize the approximately frictionless relative rotation between the air-floating turntable table and the table body, so as to simulate the spacecraft in outer space. A mechanical environment in which the disturbance moment is small. On the ground, the rotation of the air bearing turntable can be used to simulate the attitude motion of the rigid body...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B17/02G05D1/08
Inventor 陈雪芹王峰耿云海曹喜滨孙兆伟王继河叶东
Owner HARBIN INST OF TECH
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