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Testing device and method applicable for spacecraft high-stability pointing control

A space vehicle, a high-stability technology, applied to the simulation device of space navigation conditions, transportation and packaging, space navigation equipment, etc.

Active Publication Date: 2015-03-04
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The Chinese invention patent "A Method for Controlling the Pointing of Dual-Axis Antennas of Lunar Satellites" (application number 200710301746.6) discloses a method of controlling the pointing of dual-axis antennas of orbiting satellites to the ground, which overcomes the shortcomings of the existing technology and adopts simple development The ring program tracking method meets the pointing accuracy requirements, but does not involve the research of ground physical simulation devices and methods

Method used

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  • Testing device and method applicable for spacecraft high-stability pointing control

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Effect test

Embodiment 1

[0022] Such as figure 1 As shown, a high-stability pointing control test device suitable for space vehicles includes a base 1, an air bearing 2, an instrument platform 3, an aircraft pointing unit 4, an aircraft attitude control unit 5, and a data command sending and receiving system 6 on the platform. Marking point 7, target probe unit 8, reflective prism 9, reaction momentum wheel system 10, image processing unit 11, photoelectric autocollimator 12, laser tracker 13, off-stage data command sending and receiving system 14 and camera 15; its features That is, the lower end of the air bearing 2 is installed on the base 1, the upper end of the air bearing 2 is fixedly connected with the instrument platform 3, the target measuring head unit 8, the marker point 7, the aircraft attitude control unit 5, the reflecting prism 9, and the aircraft pointing unit 4 1. On-stage data command transceiving system 6 and reaction momentum wheel system 10 are installed on instrument platform 3, ...

Embodiment 2

[0024]A high-stability pointing control test method suitable for space vehicles, the specific steps are as follows:

[0025] Step 1: Confirm the final expected orientation and initial position of the aircraft pointing unit 4 on the instrument platform 3 according to the test target, install the photoelectric autocollimator 12 according to the final orientation position and the position of the reflecting prism 9, and ensure that the instrument platform 3 When the upper aircraft pointing unit 4 moves to the vicinity of the final desired pointing, the reflective prism 9 can enter the effective field of view of the photoelectric autocollimator 12;

[0026] Step 2: Power on the whole device and supply air to the air bearing 2, and move the aircraft pointing unit 4 on the instrument platform 3 to the initial position required for the test;

[0027] Step 3: Confirm that the target probe unit 8 is in the field of view of the laser tracker 13, and the marker point 7 should not be block...

Embodiment 3

[0035] The pose measurement technology of the air bearing table is explained as follows:

[0036] For the single-axis air bearing table, the 360° full-range measurement can be completed by the camera and its image processing unit with the marker point, or it can be completed by the grating measurement system installed on the axis of the single-axis air bearing table, medium range (±60°) It can be completed by a laser tracker, and a photoelectric autocollimator for high-precision measurement in a small range (typically ±1800 arc seconds), or it can be completed by a grating measurement system;

[0037] For the three-axis air bearing table, the angle measurement can be completed by the camera and its image processing unit in conjunction with the marker points during the 360° full range of motion (for details, please refer to the patent "Binocular Stereo Vision Measuring Device for Three-axis Air Bearing Table Attitude Angle and Its Measurement method", the application number is ...

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Abstract

The invention provides a testing device and a method applicable for spacecraft high-stability pointing control. The testing device comprises a base, an air bearing, an instrument platform, a spacecraft pointing unit, a spacecraft attitude control unit, a platform data instruction transmitting-receiving system, a mark point, a target measuring head unit, a reflection prism, a counteractive momentum wheel system, an image processing unit, a photoelectric auto-collimator, a laser tracker, an off-platform data instruction transmitting-receiving system and a camera. According to the device and the method, the characteristics of a micro-interference moment environment are simulated by fully using the air bearing; as the high-precision position and attitude measuring techniques of equipment such as the image measuring unit, the laser tracker and the photoelectric auto-collimator are combined, the goal of spacecraft high-stability pointing control test can be realized; the precision is high; the stability is good; and the engineering realization is facilitated. The device and the method can be used for a high-precision pointing control test on spacecraft such as various high-precision weather and military reconnaissance satellites and space-based offense and defense platforms.

Description

technical field [0001] The invention relates to a high-stability pointing control test device and method suitable for space vehicles. Background technique [0002] Modern space missions put forward high requirements on the high stability of the aircraft pointing, especially for the space vehicle, its pointing accuracy is often the most critical technical index of the system, and the expensive development cost and special operating environment of the aircraft require that it must be carried out before launch. Sufficient ground tests are needed to ensure the success of the mission, so the research on space vehicle high-stability pointing control tests has important application prospects and value. [0003] The air bearing table relies on compressed air to form an air film between the air bearing and the bearing seat, and installs the payload through the instrument platform to float the simulated table body, so as to realize the relative motion condition of approximately fricti...

Claims

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Application Information

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IPC IPC(8): B64G7/00
Inventor 王常虹夏红伟马广程李莉宋效正
Owner HARBIN INST OF TECH
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