Torque compensation control method of DGMSCMG (double-gimbal magnetically suspended control moment gyroscope) system for spacecraft maneuver

A compensation control, spacecraft technology, applied in non-electric variable control, attitude control, control/regulation system and other directions, can solve the problem of increasing the displacement of the magnetic suspension rotor

Active Publication Date: 2012-01-18
BEIHANG UNIV
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Problems solved by technology

[0006] The technical problem of the present invention is: to overcome the existing method to directly improve the closed-loop stiffness of the magnetic bearing, suppress the coupling disturbance torque and the compound compensation control of the DGMSCMG dynamic frame effect under the static base, and propose a DGMSCMG system during maneuvering of the spacecraft The torque compensation control method can effectively suppr...

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  • Torque compensation control method of DGMSCMG (double-gimbal magnetically suspended control moment gyroscope) system for spacecraft maneuver
  • Torque compensation control method of DGMSCMG (double-gimbal magnetically suspended control moment gyroscope) system for spacecraft maneuver
  • Torque compensation control method of DGMSCMG (double-gimbal magnetically suspended control moment gyroscope) system for spacecraft maneuver

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Embodiment Construction

[0025] In order to facilitate the dynamic modeling of the DGMSCMG system when the spacecraft maneuvers, the schematic diagram of the DGMSCMG system and each coordinate system is shown in figure 2 shown. where Ox is defined b the y b z b is the spacecraft body coordinate system, Ox j the y j z j , Ox g the y g z g are the outer frame coordinate system and the inner frame coordinate system of the DGMSCMG system, respectively. Ox d the y d z d , Ox h the y h z h are the stator coordinate system and the inner ring coordinate system of the maglev rotor, respectively.

[0026] (1) Establish the dynamic model of the DGMSCMG system magnetic bearing x direction, magnetic bearing y direction, inner frame axis and outer frame axis during spacecraft maneuvering

[0027]Using the momentum moment theorem, the dynamic models of the maglev rotor, inner frame and outer frame of the DGMSCMG system during maneuvering of the spacecraft are respectively established as follows:

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Abstract

A torque compensation control method of a DGMSCMG system for spacecraft maneuver, which includes the following steps: building the kinetic models of a magnetic suspension rotor, an inner gimbal and an outer gimbal of the DGMSCMG system for the spacecraft maneuver, and designing a torque compensation control method to eliminate coupled disturbing torque in each single kinetic model, guarantee the compensation of the coupled disturbing torque of the DGMSCMG system for the spacecraft maneuver and realize the stability control of the DGMSCMG system, so that the stability and precision of spacecraft attitude control can be increased. The torque compensation control method can effectively eliminate the coupled disturbing torque of the DGMSCMG system for the spacecraft maneuver, guarantee the stability control of the DGMSCMG system and thereby realize the stability and precision of spacecraft attitude control.

Description

technical field [0001] The invention relates to a torque compensation control method of a double gimbal magnetically suspended control moment gyroscope (DGMSCMG) system during maneuvering of a spacecraft, which can be used to compensate the influence of coupling disturbance torque of the DGMSCMG system during maneuvering of a spacecraft, and realize The stability control of the DGMSCMG system can improve the stability and precision of spacecraft attitude control. Background technique [0002] The control moment gyroscope is a key attitude actuator of high-precision, long-life large spacecraft such as the space station. The degree of freedom of the frame and the high-speed rotor support method are the two most important factors that determine the performance of the control moment gyroscope. The double-frame magnetic levitation control moment gyro is composed of a magnetic levitation high-speed rotor supported by a permanent magnetic bias hybrid magnetic bearing and an inner a...

Claims

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Application Information

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IPC IPC(8): G05D1/08G05D13/00
Inventor 崔培玲杨倩房建成魏彤李海涛李文琢
Owner BEIHANG UNIV
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