Shortest path attitude maneuver control method for satellite around space axis

A shortest path, space axis technology, applied in the direction of motor vehicles, space navigation equipment, space navigation aircraft, etc., can solve the problem of cumbersome rotation control process and so on

Active Publication Date: 2017-01-04
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

Therefore, the time required for maneuvering at a large angle is relatively long, and the rotation control process is cumbersome; in addition, if the attitude measurement device on the star is a star sensor, the direct measu

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  • Shortest path attitude maneuver control method for satellite around space axis
  • Shortest path attitude maneuver control method for satellite around space axis
  • Shortest path attitude maneuver control method for satellite around space axis

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Embodiment Construction

[0056] The present invention will be further elaborated below by describing a preferred specific embodiment in detail in conjunction with the accompanying drawings.

[0057] like figure 2 As shown, a shortest path attitude maneuver control method for satellites around the space axis can simultaneously adapt to the recapture control of the earth in the security mode against the sun and the attitude maneuver control of any target, as shown in image 3 As shown, the shortest path attitude maneuver control method includes the following steps:

[0058] S1. A quaternion is used to describe the current attitude and the target attitude of the satellite respectively.

[0059] (1) Using quaternion to describe the current attitude of the satellite includes:

[0060] Integrate the initial value of the attitude quaternion according to the quaternion kinematics equation to obtain the gyro integral quaternion. If the star sensor is valid, the star sensor quaternion will replace the gyro i...

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Abstract

The invention discloses a shortest path attitude maneuver control method for a satellite around a space axis. The method comprises the following steps: describing the current attitude and target attitude of the satellite by a quaternion respectively; calculating a deviation quaternion according to the current attitude quaternion and target attitude quaternion of the satellite, and configuring the deviation quaternion into attitude information for control; calculating the angular velocity of the satellite relative to the orbital coordinate system according to the gyro measured angular velocity and the current attitude quaternion of the satellite, and configuring the angular velocity as angular velocity information for control; and calculating the instruction speed of a flywheel according to the attitude information for control and the angular velocity information for control to finish attitude maneuver control. According to the method, based on the around-space axis shortest path attitude maneuver control thought and by adopting quaternion to describe the target attitude reference and simplifying the attitude for control, a flywheel attitude maneuver control algorithm is designed; and the method is suitable for the conversion of sun-oriented attitude maneuver into earth-oriented attitude maneuver, the attitude maneuver around any space axis and the like.

Description

technical field [0001] The invention relates to the technical field of satellite attitude maneuver control, in particular to a shortest path attitude maneuver control method for a satellite around a space axis. Background technique [0002] In the scheme design of the satellite attitude and orbit control analysis system, the stellar solar cell array is often controlled to be irradiated to face the sun. Can be used as a safe mode for satellite attitude. In the sun-oriented safety mode, if the sensor is available and the energy meets the requirements, it will automatically switch from the sun-oriented safety mode to the conventional ground-oriented control mode to ensure the normal operation of the load. Due to the arbitrariness of the attitude of the security mode towards the sun relative to the orientation towards the ground, the star is required to have the large-angle maneuverability of any target attitude, such as figure 1 shown. [0003] The satellite platform in the ...

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Application Information

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IPC IPC(8): B64G1/24
CPCB64G1/24B64G1/245
Inventor 杜宁陈占胜尹海宁陈璟朱虹
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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