Attitude control feedback loop based on combined fixed attitude of multi-rate sensor

A feedback loop, multi-rate technology, applied in the direction of the guidance device of the aerospace vehicle, can solve the problem of different output frequencies of the sensors, and achieve the effect of reducing the complexity and improving the accuracy of attitude determination.

Inactive Publication Date: 2011-07-06
BEIHANG UNIV
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Problems solved by technology

[0004] The technical problem of the present invention is: aiming at the problem of different output frequencies of the sensors used on the satellite, the multi-scale analysis method is used to carry out the multi-

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  • Attitude control feedback loop based on combined fixed attitude of multi-rate sensor
  • Attitude control feedback loop based on combined fixed attitude of multi-rate sensor
  • Attitude control feedback loop based on combined fixed attitude of multi-rate sensor

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Embodiment Construction

[0015] Such as figure 1 As shown, the simulation circuit of the present invention is composed of an attitude sensor subsystem 4 , an attitude determination subsystem 5 based on multi-scale modeling and an attitude control subsystem 6 . details as follows:

[0016] 1) The attitude sensor subsystem outputs measurement information with multi-rate characteristics

[0017] The attitude sensor subsystem 4 includes a gyroscope 1, a sun sensor 2 and a magnetometer 3, which respectively generate the attitude angular velocity of the body coordinate system relative to the inertial coordinate system, the sun vector and the geomagnetic vector in the satellite body coordinate system. The gyro, sun sensor, and magnetometer output measurement information at different frequencies, and the output frequency of the gyro and sun sensor is twice the output frequency of the magnetometer, that is, the measurement information output by the attitude sensor subsystem 4 has a multi-rate characteristic ...

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Abstract

The invention relates to a attitude control feedback loop based on a combined fixed attitude of a multi-rate sensor, which comprises an attitude sensor subsystem, an attitude determining subsystem based on multi-scale modeling, and an attitude control subsystem, wherein the attitude sensor subsystem comprises a gyro, a solar sensor and a magnetometer and outputs attitude measurement information with multi-rate characteristics; the attitude determining subsystem is used for describing measurement information of each sensor from different scales by using a multi-scale analyzing method and estimating the satellite attitude angle on the basis of the established multi-scale model; and the attitude control subsystem is used for controlling the satellite attitude and feeding the controlled attitude information back to the attitude sensor subsystem so as to form the attitude control loop. The attitude control feedback loop is used for carrying out multi-scale modeling by using the multi-scaleanalyzing method, thereby improving the attitude determining precision while reducing the complexity of an attitude combining and fixing process.

Description

technical field [0001] The invention relates to an attitude control feedback loop based on multi-rate sensor combination attitude determination, which belongs to the field of spacecraft attitude determination. Background technique [0002] As the main means of space environment detection, satellite technology research is particularly important, and all countries have invested a lot of manpower and material resources in research. With the development of aerospace science and technology, satellites have higher and higher requirements for attitude stability, pointing or maneuvering control capabilities, system functions are becoming more and more complex, longer operating life is required, and the efficiency of satellites is getting higher and higher. ability. Generally speaking, multi-task, high-precision, long-life, and high-reliability satellites have become a new development trend. [0003] One of the most important technologies in the satellite system is the design of th...

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Application Information

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IPC IPC(8): B64G1/36
Inventor 崔培玲张会娟房建成张翠全伟
Owner BEIHANG UNIV
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