Spacecraft vibration suppression based on micro-gimbal moment of magnetically suspended flywheel with dynamic feedback and feedforward decoupling control

Chen, Xiaocen; Cai, Yuanwen; Ren, Yuan; Liu, Qiang

doi:10.1177/0954406217745339

Cited by 10 publications

(5 citation statements)

References 23 publications

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“… 21 – 23 A new research hotspot is to use the magnetic bearing clearance support to realize the multi-DOFs momentum exchange and integration of attitude measurement and control by driving the rotor to deflect along the equatorial plane axis in the magnetic clearance, this feature is called the micro-gimbal effect. 24 , 25 Fan et al 26 and Li et al 27 reviewed the structure principle and development status of magnetically suspended micro-gimbal flywheel (MSMGF). Multiple MSMGF solutions is proposed in Liu et al, 28 Gerlach et al 29 and Tang et al 30 However, the rotor of the micro-gimbal effect flywheel is usually a cylinder or cone, rotor deflection capacity is limited, attitude sensitive function is often as a subsidiary function, more importantly, it just stays in the conceptual stage without in-depth study.…”

Section: Introductionmentioning

confidence: 99%

Optimal design and experiment study of the double spherical rotor of the MSCSG

et al. 2021

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The magnetically suspended control and sense gyroscope (MSCSG) integrates spacecraft attitude measurement and control function; this paper proposes a double spherical rotor (DSR) for MSCSG. The DSR realizes the five degrees of freedom (DOFs) full active control and full channel magnetic path decoupling by the following design: the spherical axial/radial reluctance magnetic bearings are adopted to control the 3DOFs translation of rotor in the range of double spherical envelope, Lorentz force magnetic bearing (LFMB) is used to precisely drive the 2DOFs universal deflection of rotor. The optimization model is established based on the structural mechanical analysis, taking the deviation between rotor centroid and shape center as the optimization objective, choosing the first order resonance frequency, maximum equivalent stress, rigid body displacement, polar moment of inertia and inertia ratio as constraints. Then the DSR is optimized and simulated by the finite element, the MSCSG principle prototype based on DSR is successfully developed, the online dynamic balance experiment and modal test of the DSR are conducted, where the vibration amount of the DSR decreases from 20 μm before the experiment to 0.14 μm after the experiment, which decreases by 99.3%, the first test modal is 2881 Hz which is 5% different from the finite element simulation value of 3034 Hz. The results show that the DSR has the good mechanical properties and magnetic circuit decoupling characteristics.

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Section: Introductionmentioning

confidence: 99%

Optimal design and experiment study of the double spherical rotor of the MSCSG

et al. 2021

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“…14 The micro-gimbal moment of magnetically suspended flywheel (MSF) has been employed to realize the active vibration control of spacecraft. 15,16 An integration control method of attitude and vibration is further proposed by magnetically suspended control moment gyros (MSCMG). 17 However, the attitude control and vibration suppression can only be carried out at different times, 17 that is, they cannot be performed simultaneously, which inevitably influences the dynamic performance of spacecraft.…”

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

“…18 However, the complicated situations such as difficult measurement of micro-vibration, unknown moment of inertial of spacecraft and parameter changes have not been considered in the earlier study. [14][15][16][17][18][19] This paper proposes a synchronous control method of spacecraft attitude and micro-vibration based on MSCSG. The attitude control and vibration suppression of spacecraft are realized simultaneously by the gimbal rotation and rotor deflection of MSCSG.…”

Section: Introductionmentioning

confidence: 99%

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Adaptive robust sliding mode simultaneous control of spacecraft attitude and micro-vibration based on magnetically suspended control and sensitive gyro

Ren

Chen

Cai

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper puts forward realizing the synchronous control of spacecraft attitude and micro-vibration by taking advantage of magnetic suspension rotor deflection of magnetically suspended control and sensitive gyro. A disturbance-observer is designed to estimate the complex micro vibration which is hard to measure, and an adaptive robust sliding mode controller is designed as an integrated controller and its stability is proven by Lyapunov stability criterion. The band-pass filters are introduced to separate low frequency and high frequency control signals and takes them as input commands of gyro frame and magnetic suspension rotor, respectively. The semi-physical simulation results testify that the proposed method has good vibration suppression effect as well as improves the attitude convergence rate.

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“…Zheng and Feng [22] introduced a FFC strategy combined with a novel adaptive notch filter to solve the problem of rotor imbalance in high‐speed magnetically suspended centrifugal compressors. Chen et al [23] proposed a dynamic feedback and feedforward decoupling control, including a state‐feedback decoupling controller, a disturbance compensator and a dynamic compensator filter, to solve the spacecraft high‐frequency vibration suppression in a MSCMG.…”

Section: Introductionmentioning

confidence: 99%

Feedforward decoupling control for rigid rotor system of active magnetically suspended high‐speed motors

Zhao

Zhu

2019

IET Electric Power Applications

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In order to eliminate the coupling between of radial four degree-of-freedoms (DOFs) in a rigid rotor supported by two radial active magnetic bearings and to suppress the rotor imbalance vibration, a feedforward decoupling control was proposed, and then the rotor imbalance compensation based on imbalance identification was used after the rotor system had been decoupled. A time-optimal tracking differentiator was used to improve the performances of feedforward decoupling control and imbalance compensation. Numerical simulations and experiment results show that the radial four DOF coupling system could be completely decoupled into four single DOF systems by the feedforward decoupling controller, the imbalance vibration of the decoupled system could be effectively suppressed by the imbalance compensation, the performances of decoupling and imbalance compensation could be improved and the anti-interference ability of the control system could be enhanced by using the time-optimal tracking differentiator.

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Spacecraft vibration suppression based on micro-gimbal moment of magnetically suspended flywheel with dynamic feedback and feedforward decoupling control

Cited by 10 publications

References 23 publications

Optimal design and experiment study of the double spherical rotor of the MSCSG

Optimal design and experiment study of the double spherical rotor of the MSCSG

Adaptive robust sliding mode simultaneous control of spacecraft attitude and micro-vibration based on magnetically suspended control and sensitive gyro

Feedforward decoupling control for rigid rotor system of active magnetically suspended high‐speed motors

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