Semi-physical simulation system for attitude control of star-arrow integrated spacecraft

A semi-physical simulation and attitude control technology, applied in attitude control, general control system, control/regulation system, etc., can solve problems such as spacecraft simulation

Inactive Publication Date: 2011-03-30
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The present invention aims to solve the problem that the existing spacecraft attitude control semi-physical simulation system cannot simulate the spacecraft from the launch point to the attitude control system in the active operation stage, thus proposing the active operation stage and on-orbit operation of the satellite-rocket integrated spacecraft Phase Attitude Control Semi-Physical Simulation System

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  • Semi-physical simulation system for attitude control of star-arrow integrated spacecraft
  • Semi-physical simulation system for attitude control of star-arrow integrated spacecraft

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specific Embodiment approach 1

[0009] Specific implementation mode 1. Combination figure 1 Describe this specific embodiment, the satellite-rocket integrated spacecraft attitude control semi-physical simulation system, which includes the spacecraft air-floating turntable on-stage device, and the spacecraft air-floating turntable on-stage device includes an on-board computer 2, an optical fiber gyroscope 3, Star sensor simulator 4, inertial measurement combination simulator 5, reaction flywheel 6, magnetic torque device 7 and jet simulator 8, the signal input or output end of reaction flywheel 6 and No. 1 signal output or input end of onboard computer 2 Connection, the signal input or output end of the magnetic torque device 7 is connected with the No. 2 signal output or input end of the on-board computer 2, the signal input or output end of the jet simulator 8 is connected with the No. 3 signal output or input end of the on-board computer 2 Connect; it also includes real-time simulator 1, wireless communica...

specific Embodiment approach 2

[0025] Embodiment 2. The difference between this embodiment and the satellite-rocket integrated spacecraft attitude control semi-physical simulation system described in Embodiment 1 is that it also includes an automatic adjustment device for the center of mass, and the automatic adjustment device for the center of mass is fixed on the spaceflight. on the table of the air flotation turntable.

[0026] In this embodiment, the automatic center-of-mass adjustment device is used to automatically adjust the center of mass of the table top to coincide with its center of gravity after each component is placed on the table top of the air-floating turntable.

specific Embodiment approach 3

[0027] Specific embodiment three, the difference between this specific embodiment and the satellite-rocket integrated spacecraft attitude control semi-physical simulation system described in specific embodiment one or two is that it also includes a serial bus, and the signal input of the fiber optic gyroscope 3 or between the output terminal and the No. 1 signal output or input terminal of the real-time simulator 1, between the signal input or output terminal of the star sensor simulator 4 and the No. 2 signal output or input terminal of the real-time simulator 1, inertial combination The signal input or output terminal of the simulator 5 is connected to the No. 3 signal output or input terminal of the real-time simulator 1 through a serial bus.

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Abstract

The invention discloses a semi-physical simulation system for attitude control of a star-arrow integrated spacecraft, which relates to the semi-physical simulation system for control of the star-arrow integrated spacecraft. The invention solves the problem that the conventional semi-physical simulation system for the attitude control of the spacecraft cannot simulate the spacecraft from a launching point to an active operation stage attitude control system. A simulation signal input or output end of a real-time simulator is connected with a simulation signal output or input end of an onboard computer; a wireless signal input or output end of a stage wireless communication module is connected with a wireless signal output or input end of the real-time stimulator; and a signal output or input end of a ground wireless communication module is connected with a signal input or output end of a ground control module. The system is suitable for the stimulation of the attitude control of the star-arrow integrated spacecraft.

Description

technical field [0001] The invention relates to a satellite-rocket integrated spacecraft control semi-physical simulation system. Background technique [0002] At present, due to the long development cycle of spacecraft, high cost, high launch requirements, and slow response, China is still unable to quickly build a space-based information system, and lacks the ability to observe sudden natural disasters in a timely manner and respond quickly. In order to effectively utilize system resources and reduce assembly and testing time, Harbin Institute of Technology proposed the concept of a satellite-rocket integrated spacecraft that organically combines satellites and carriers. [0003] 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 con...

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张世杰兰盛昌马玉海
Owner HARBIN INST OF TECH
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