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Under-actuated control method suitable for damping angular velocity of satellite attitude

A technology of angular velocity and attitude angle, which is applied in the field of underactuated control of satellite attitude angular velocity damping, and can solve problems such as inability to be sensitive, inaccessible, and system instability

Active Publication Date: 2013-10-16
BEIJING INST OF CONTROL ENG
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Problems solved by technology

The gyroscope used to measure the angular velocity of the satellite has a certain range, that is, when the angular velocity of the star exceeds a certain value, the output of the gyroscope is saturated and cannot be sensitive to the actual angular velocity of the star's attitude.
Without considering the actual engineering constraints, even if the designed underactuated control law can theoretically guarantee system stability and state convergence, it may not be possible to obtain the correct star when the angular velocity of the star exceeds the gyro measurement range during the control dynamic process. The angular velocity causes the system to become unstable

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  • Under-actuated control method suitable for damping angular velocity of satellite attitude
  • Under-actuated control method suitable for damping angular velocity of satellite attitude
  • Under-actuated control method suitable for damping angular velocity of satellite attitude

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Embodiment Construction

[0070] The present invention will be further introduced below in conjunction with the accompanying drawings.

[0071] The present invention aims at the problem of three-axis attitude angular velocity damping control of spacecraft, considering the under-actuated control when a certain channel loses control capability, and based on the dynamic coupling characteristics of the spacecraft, a method of using other normal channels to complete the three-axis control is proposed. The underactuated control method of rate damping is used to achieve the purpose of spacecraft attitude determination.

[0072] According to the angular velocity damping requirements of the star, the expected amplitude Δ of the angular velocity deviation of the three axes is given 2 (Δ 2 >0);

[0073] For satellite systems that are controlled by jet control and angular momentum management devices (such as momentum wheels, control moment gyroscopes, etc.), it is necessary to meet And leave a certain engineer...

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Abstract

The invention discloses an under-actuated control method suitable for damping the angular velocity of a satellite attitude. The method includes firstly determining a satellite control failure shaft and two normally working shafts, and determining the angular velocity offset value of the two normally working shafts according to the size relation between main inertias of the two normally working shafts and the actual attitude angular velocity of the failure shaft; then determining the angular velocity deviation according to the actual attitude angular velocity of the angular velocity offset value of the two normally working shafts, and obtaining control moments of the two normally working shafts according to the angular velocity deviation; and controlling the angular velocities of the three shafts through the control moments until all angular velocity deviations of the three shafts are smaller than an angular velocity deviation expectation amplitude. The control method is simple in algorithm, good in dynamic behavior and high in project operability.

Description

technical field [0001] The invention relates to a satellite attitude control method, in particular to an underdrive control method suitable for satellite attitude angular velocity damping. 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 angular velocity of a large star. Therefore, it is often used in the satellite orbit stage, the sun safety emergency mode under system abnormalities, and the safety mode transition. Normal ground and other occasions. [0003] For a spacecraft with angular momentum bias in the Y-axis direction, the dynamic equation un...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08B64G1/26
Inventor 雷拥军王淑一李明群宗红魏春岭何英姿张笃周袁军王新民柯旗张俊玲
Owner BEIJING INST OF CONTROL ENG
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