High-precision posture/track integrated measurement device

A measuring device and high-precision technology, applied in directions such as integrated navigators, can solve problems such as unfavorable fusion of on-board sensors sharing orbital attitude information, increasing spacecraft volume, weight, power consumption cost, unfavorable orbital attitude determination accuracy, etc. , to achieve the effect of low power consumption, high reliability, reduced power consumption and volume

Active Publication Date: 2012-06-13
TSINGHUA UNIV
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Problems solved by technology

This divide-and-conquer measurement method and device shows great limitations, which is not conducive to the sharing of on-board sensors and the fusion of orbital attitude information, and is also not conducive to the improvement of the accuracy of orbital attitude determination.
Moreover, the volume, weight, power consumption, cost, etc. of the spacecraft are increased.

Method used

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  • High-precision posture/track integrated measurement device
  • High-precision posture/track integrated measurement device
  • High-precision posture/track integrated measurement device

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Embodiment Construction

[0040] The present invention will be described in further detail below in conjunction with the accompanying drawings and embodiments.

[0041] Such as figure 1 As shown, the present invention is a high-precision attitude / orbit integrated measurement device, which is composed of a sensor subsystem 1, a communication control subsystem 2, and an attitude / orbit calculation and information fusion subsystem 3. The sensor subsystem is composed of APS CMOS star sensor 11, MEMS gyroscope 12, and miniature GPS receiver 13. APS CMOS star sensor 11 realizes the sensitivity and processing of stars and stars, and MEMS gyroscope 12 is sensitive to angles in three mutually perpendicular directions. Velocity information, the miniature GPS receiver 13 collects the three-dimensional position information and velocity information of the spacecraft. The three sensors respectively provide the digital signals of attitude quaternion, inertial angular rate, position and velocity measurement and input ...

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Abstract

The invention relates to a high-precision posture / track integrated measurement device, which is composed of a sensor sub-system, a communication control sub-system and a posture / track resolving and information fusion sub-system; the sensor sub-system is composed of APSCMOS star sensors, an MEMS (Micro Electro Mechanical System) gyroscope and a miniature GPS (Global Position System) receiver; the three sensors are used for respectively providing measured digital signals of posture quaternion, inertia angular rate, position and speed, and then inputting the digital signals to the communication control sub-system in a serial manner; the communication control sub-system is used for framing the received serial digital signals into parallel signals, and outputting the parallel signals to the posture / track resolving and information fusion sub-system to be subjected to a UDEKF-based track deterministic algorithm and an SRSSUKF-based posture deterministic algorithm; and complete posture / track measurement information can be obtained by comprehensively calculating through a posture / track information optimization and fusion method and used by a spacecraft. The high-precision posture / track integrated measurement device disclosed by the invention is small in volume, light in weight, low in power consumption and low in cost and is applied to high-precision posture / track measurement of a tinyspacecraft.

Description

technical field [0001] The invention belongs to the technical field of high-precision attitude / orbit measurement and control of space vehicles, in particular to a high-precision attitude / orbit integrated measurement device. Background technique [0002] The attitude / orbit determination system is one of the key subsystems of the spacecraft. Its task is to realize the attitude / orbit measurement of the spacecraft in each flight stage according to the requirements of the flight plan, and then realize the attitude / orbit control. With the development of aerospace technology, especially the vigorous development of micro-satellite technology, higher requirements are put forward for the accuracy, weight and cost of the satellite attitude / orbit determination system. [0003] GPS receivers are commonly used orbit measurement devices on spacecraft, and attitude sensors such as sun sensors, star sensors, and gyroscopes are high-precision attitude measurement devices that are often equipp...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/24
Inventor 尤政赵开春张高飞于泽江杨子
Owner TSINGHUA UNIV
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