Spacecraft executing mechanism combining double-frame shear type moment gyroscope and flywheel and control method of spacecraft executing mechanism

A torque gyroscope and actuator technology, applied in attitude control, non-electric variable control, control/adjustment system, etc., can solve the problems of complex control algorithm, small output torque, large calculation amount, etc., and achieve simple use, low cost, Effective torque output ability is strong

Active Publication Date: 2021-07-23
HARBIN INST OF TECH +1
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  • Abstract
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  • Claims
  • Application Information

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Problems solved by technology

[0003] The purpose of the present invention is to solve the problems of small output torque, slow response or complex control algorithm and large amount of calculation in the state control of spacecraft using flywheel or single frame control torque gyroscope, and provides a scissor torque gyro combined with double frame Spacecraft Actuating Mechanism of Gyro and Flywheel and Its Control Method

Method used

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  • Spacecraft executing mechanism combining double-frame shear type moment gyroscope and flywheel and control method of spacecraft executing mechanism
  • Spacecraft executing mechanism combining double-frame shear type moment gyroscope and flywheel and control method of spacecraft executing mechanism
  • Spacecraft executing mechanism combining double-frame shear type moment gyroscope and flywheel and control method of spacecraft executing mechanism

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specific Embodiment approach 1

[0080] Specific implementation mode one: the following combination figure 1 and figure 2 This embodiment is described. A spacecraft actuator combined with a double-frame scissor moment gyroscope and a flywheel described in this embodiment includes a spacecraft attitude maneuver drive assembly, a disturbance torque absorption assembly, and a coordination control unit;

[0081] The spacecraft attitude maneuver drive assembly, disturbance moment absorption assembly and coordination control unit are all installed on the spacecraft body;

[0082] The spacecraft attitude maneuver drive assembly includes a rectangular frame A3, a rectangular frame B4, a scissor moment gyro A1, a scissor moment gyro B2 and four pairs of rotating shafts;

[0083] The rectangular frame A3 is sleeved on the outside of the rectangular frame B4, and the center points of the rectangular frame A3 and the rectangular frame B4 coincide; and the long sides and short sides of the rectangular frame A3 and the ...

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Abstract

The invention discloses a spacecraft executing mechanism combining a double-frame shear type moment gyroscope and a flywheel and a control method thereof, belongs to the technical field of spacecraft attitude control, and solves the problems of small output moment, slow response or complex control algorithm and large calculated amount when a flywheel or a single-frame control moment gyroscope is used for spacecraft state control in the prior art. According to the invention, the double-frame shear type moment gyroscope is adopted to drive the spacecraft to carry out attitude maneuver, three flywheels are adopted to absorb disturbance torque generated by the double-frame shear type moment gyroscope in the process of driving the spacecraft to change the attitude, and the spacecraft always has the maximum maneuvering capability in the Euler axis direction by adjusting the two frame angles of the DGSPCMG. The spacecraft executing mechanism is suitable for spacecraft attitude control.

Description

technical field [0001] The invention belongs to the technical field of spacecraft attitude control. Background technique [0002] Flywheel (RW) and Single Frame Controlled Moment Gyro (SGCMG) are two electrically driven actuators widely used in spacecraft attitude control. The flywheel can be attributed to a variable speed rotor. The mechanism is as follows: image 3 As shown, changing the rotor speed can change the angular momentum of the flywheel, and the angular momentum exchange process with the spacecraft body drives the spacecraft body to move; the control moment gyroscope is composed of the momentum flywheel, the frame supporting the flywheel, and the frame rotation servo system. The rotation of the frame driven by the servo system can change the direction of the angular momentum of the momentum flywheel, which acts as an angular momentum exchange mechanism to drive the spacecraft body to move; when multiple flywheels (RW) are combined to control the attitude of the sp...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
CPCG05D1/0833
Inventor 郭延宁唐搏陆栋宁马广富吕跃勇李传江
Owner HARBIN INST OF TECH
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