Planet steady state controlling method replacing momentum wheels with control moment gyroscope

A technology for controlling moment gyro and steady-state control, which is applied in the field of satellite attitude control, can solve problems such as loss of precision, achieve the effect of avoiding loss of precision and improving reliability

Active Publication Date: 2014-07-30
BEIJING INST OF CONTROL ENG
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Problems solved by technology

[0003] In summary, when the number of workable momentum wheels in the satellite control system based on hybrid actuators is reduced to three, a new method needs to be proposed,

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  • Planet steady state controlling method replacing momentum wheels with control moment gyroscope
  • Planet steady state controlling method replacing momentum wheels with control moment gyroscope
  • Planet steady state controlling method replacing momentum wheels with control moment gyroscope

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Embodiment Construction

[0036] The specific implementation manners of the present invention will be further introduced below in conjunction with the accompanying drawings.

[0037] The present invention proposes a satellite steady-state control method that controls the moment gyroscope instead of the momentum wheel, such as figure 1 shown, including the following steps:

[0038] (1) For the satellite control system based on the hybrid actuator of control torque gyro and momentum wheel, when the number of normal working momentum wheels is three, calculate the absolute value of the difference between the angular momentum of the high-speed rotor of the backup control torque gyro and the maximum angular momentum of the momentum wheel value, if the absolute value of the difference is greater than 5Nms, then the satellite control system adopts the control method used by three momentum wheels for zero crossing; if the absolute value of the difference is less than 5Nms, then enter step (2);

[0039](2) Dete...

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Abstract

The invention discloses a planet steady state controlling method replacing momentum wheels with a control moment gyroscope. When the number of the momentum wheels which work normally is three, the momentum wheels in a traditional way can only work in an angular momentum zero passing way to realize the state steady controlling, and the controlling precision is lowered. Aiming at the problem, the invention puts forward that a back-up control moment gyroscope high-speed rotor is used as an angular momentum fixing momentum wheel, a fixing bias angular momentum of a certain direction is provided by rotating a low-speed frame angle, so that the rest three momentum wheels can work in a bias state, the system can stay in a steady state controlling mode of a zero-momentum controlling system formed by the back-up control moment gyroscope high-speed rotor and the momentum wheels which work in a bias angular momentum state, and the problem that the precision when the momentum wheels are in zero passing use is damaged is solved. The planet steady state controlling method enables the cold back-up control moment gyroscope to play the back-up role of side-sway maneuver and steady state controlling, and improves the reliability of on-rail use of a planet activating mechanism.

Description

technical field [0001] The invention relates to a satellite steady-state control method for controlling a moment gyroscope instead of a momentum wheel, and belongs to the field of satellite attitude control. Background technique [0002] In order to meet the requirements of fast side-sway maneuver and high-precision attitude stability control, the actuators of the first-class satellites adopt the mixed configuration of control moment gyroscope (CMG) and momentum wheel. Among them, the control moment gyro (CMG) generally includes the main control moment gyro (CMG) and the backup control moment gyro (CMG). Two types of actuators with different characteristics achieve different control functions: the control torque gyro with a large output torque realizes the rapid maneuvering requirements of the satellite, while the momentum wheel with a relatively small output torque but high precision realizes high-precision steady-state control of the satellite Require. Among them, the hi...

Claims

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Application Information

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IPC IPC(8): B64G1/28
Inventor 张春青雷拥军顾斌刘其睿蒋志雄宗红瞿涵綦艳霞王玉爽傅秀涛
Owner BEIJING INST OF CONTROL ENG
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