Method for building normal gestures of under-actuated high-speed spinning satellite

An underactuated and normal technology, applied in the direction of the guidance device of the space navigation vehicle, can solve the problem of the loss of jet control ability and the underactuated satellite, and achieve the effect of strong engineering achievability

Active Publication Date: 2013-05-22
BEIJING INST OF CONTROL ENG
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Problems solved by technology

[0004] The problem solved by the technology of the present invention is: aiming at the deficiencies of the prior art, a method for establishing a normal attitude of an underactuated high-speed spinning satellite is provided, which solves the problem that an underactuated satellite that has lost its jet control ability in a certain channel returns to a normal attitude

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  • Method for building normal gestures of under-actuated high-speed spinning satellite
  • Method for building normal gestures of under-actuated high-speed spinning satellite
  • Method for building normal gestures of under-actuated high-speed spinning satellite

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Embodiment Construction

[0017] The present invention will be further introduced below in conjunction with the accompanying drawings.

[0018] Such as figure 1 Shown is flow chart of the present invention, and concrete process is as follows:

[0019] (1) Using the attitude sensor to determine the spin axis of the underdriven satellite

[0020] In the embodiment of the present invention, the attitude sensor used to determine the spin axis of the satellite may be a digital sun sensor. The determination content of the spin axis includes its orientation and size, and the determination process includes determining the data adoption interval, judging the validity of the data and determining the spin axis.

[0021] Determine the data adoption interval: the spin angular velocity is large, the effective data output by the attitude sensor is relatively sparse, but the incremental change of adjacent measurement results is large; the spin angular velocity is small, the effective data output by the attitude sens...

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Abstract

The invention discloses a method for building normal gestures of an under-actuated high-speed spinning satellite. The method for building the normal gestures of the under-actuated high-speed spinning satellite comprises the following steps: (1) a spinning shaft of the under-actuated satellite is confirmed by means of output data of a gesture sensor; (2) an under-actuated shaft and a normal shaft are confirmed; (3) under-actuated spinning counteraction of the satellite is conducted and the satellite is controlled until the spinning top breaks away from saturation; (4) after the spinning top breaks away from saturation, under-actuated control is conducted on triaxial angle speeds; (5) quaternions of initial gestures are confirmed and renewed; (6) a momentum wheel is adopted to conduct gesture capture and magnetic torquer unloading, the satellite gestures are confirmed, and the satellite is recovered to normal triaxial stable gestures to the earth. The method for building the normal gestures of the under-actuated high-speed spinning satellite solves the problem that an under-actuated satellite with a certain channel losing air-injecting control ability recovers normal gestures.

Description

technical field [0001] The invention belongs to the technical field of satellite attitude and orbit control, and relates to a method for establishing a normal attitude of an underactuated high-speed spinning satellite. Background technique [0002] Satellites in orbit generally have jet control and control based on angular momentum management devices (such as flywheel / momentum wheel, control moment gyro, etc.). The control based on the angular momentum management device is generally only used for attitude control under normal conditions due to the constraint of limited angular momentum. Jet control has a large torque and no angular momentum constraints, and can effectively damp the initial attitude angular velocity of a large star, so it is often used in the stage of satellite entry, the safety of the system under abnormal conditions, and the normal transition from safe mode to the ground. and other occasions. In the full-drive control mode, the three-axis control of the s...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24
Inventor 袁军王新民张庆君徐福祥宗红姚宁周剑敏赵性颂雷拥军李明群
Owner BEIJING INST OF CONTROL ENG
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