Miniature assembled gesture measuring system for mini-satellite

A measurement system and micro-satellite technology, applied in the direction of space navigation vehicle guidance devices, etc., can solve the problems of long response time, existence of field of view, easy to receive external influences, etc., to improve attitude measurement accuracy, overcome drift, and reduce volume. Effect

Inactive Publication Date: 2005-07-27
TSINGHUA UNIV
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Problems solved by technology

However, they work with relatively long response times and issues such as field of view
At the same time, they are all susceptible to external influences, so short-term failures may occur during maneuvers such as satellite orbit changes
In addition, GPS and other technologies currently used for orbit control are more dependent on external information such as navigation stars, and are more likely to be affected.

Method used

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  • Miniature assembled gesture measuring system for mini-satellite
  • Miniature assembled gesture measuring system for mini-satellite
  • Miniature assembled gesture measuring system for mini-satellite

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Embodiment Construction

[0016] The present invention will be further described below in conjunction with the accompanying drawings.

[0017] Such as figure 1 As shown, the present invention provides a kind of miniature combined attitude measurement system for micro-satellites, comprising inertial / magnetic combined measurement unit, signal processing circuit and the on-board computer of stored data processing program, wherein, the inertial / magnetic combined measurement unit structured as figure 2 As shown, it consists of three sets of MEMS-based sensor groups installed on three orthogonal surfaces of a high-precision hexahedral substrate, and each sensor group includes a micro-gyroscope 1, a micro-accelerometer 2 and a micro-magnetometer 3. The signals output by each of the sensors are analog voltage signals, respectively corresponding to the angular velocity of the star around the three orthogonal axes, the linear acceleration along the three orthogonal directions, and the magnetic field strength....

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Abstract

A miniature combined attitude measuring system for small satellite is composed of a combined inertial-magnetic measuring unit, a signal processing circuit and a satellite carried computer for storing data and program. Said measuring unit has 3 sensor sets based on microelectromachinal system. Each sensor set has microgyroscope, microaccelerometer and micromagnetometer. Its advantages are high real-time performance, high reliability and high anti-interference power.

Description

technical field [0001] The invention belongs to the technical field of miniature spacecraft and aerospace measurement and control. Background technique [0002] Microsatellites have been developed rapidly in recent years. They have the advantages of light weight, small size, low cost, short development cycle, low risk, and advanced technology. They have broad application prospects in scientific experiments, communications, meteorology, and environmental testing. It is an important development direction of satellite technology. As an important part of small satellite technology, it is of great significance to research and develop attitude measurement and control technology with high pointing accuracy and stability. [0003] At present, the attitude measurement system of micro-satellites mainly uses sensors including sun sensors, star sensors, infrared earth sensors, and magnetic sensors. The accuracy of the sensor is high. However, they work with relatively long response t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/36
Inventor 任大海尤政苏琨
Owner TSINGHUA UNIV
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