A New Mechanism for the Vibration Control of Large Flexible Space Structures With Embedded Smart Devices

Li, Dongxu; Jiang, Jianping; Liu, Wang; Fan, Caizhi

doi:10.1109/tmech.2014.2341664

Cited by 25 publications

(16 citation statements)

References 22 publications

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“…Among the researches on active control method, the smart materials such as piezoelectric materials and patches are widely used as actuators. [15][16][17][18] The active electric-magnetic devices are also valid actuators for the active control of solar panel vibration. 19 In addition to the structural design, many researchers conduct researches on the control algorithms.…”

Section: Introductionmentioning

confidence: 99%

Improvement on the passive method based on dampers for the vibration control of spacecraft solar panels

Liu

Zhang

et al. 2022

Advances in Mechanical Engineering

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In this study, a passive vibration control method termed as translational root mounting method is proposed and investigated, for suppressing the low frequency vibrations of spacecraft solar panels. The translational root mounting method employs dampers installed at the roots of solar panels to dissipate the dynamic energy. The key of translational root mounting method is that translational root mounting method modifies the fundamental mode shape of the solar panel, by releasing the translation freedoms at its root. The root of the solar panel then has translational freedom instead of rotational freedom. As a result of mode shape modification, the translational root mounting method enables the root dampers to have sufficient working stroke, however without obviously reducing the solar panel’s fundamental frequency. Finite element model of a satellite solar panel with the length of 7 [Formula: see text] is established. Applying the finite element model, the limitation of a conventional passive vibration control method based on rotational root mounting is illustrated. To verify and illustrate the principle of translational root mounting method, the free vibration of the 7 [Formula: see text]-length satellite solar panel controlled by translational root mounting method is analyzed by finite element method. Finite element analysis (FEA) results indicate that the effect of a conventional passive control method is not obvious unless dampers with quite large damping coefficients are employed. In contrast, applying dampers with much smaller damping coefficients, the effect of translational root mounting method is fantastic comparing with the conventional passive method. To optimize the translational root mounting method and theoretically compare it to the conventional passive vibration control method, the solar panel is simplified into a non-linear one-degree of freedom system, and the analytical solution of its low frequency vibration is derived. Applying the analytical solution, it is found that damping ratio of the whole solar panel system does not increase with the damper’s damping coefficient, instead there are optimum values of damping coefficient. Applying the translational root mounting method, for the discussed 7 [Formula: see text]-length satellite solar panel, the damping ratio of which can be elevated from 0.0027 to 0.326.

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Section: Introductionmentioning

confidence: 99%

Improvement on the passive method based on dampers for the vibration control of spacecraft solar panels

Liu

Zhang

et al. 2022

Advances in Mechanical Engineering

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“…erefore, the investigation of low-frequency vibrations for exible spacecraft is critical [1][2][3][4][5][6].…”

Section: Introductionmentioning

confidence: 99%

Active Vibration Control of a Large Flexible Appendage Using a Novel Joint Mechanism

Hu¹,

Wu²,

Zhu³

et al. 2022

Shock and Vibration

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With the evolution of space exploration, large flexible appendages have been developed in space structures. External perturbation or attitude maneuvering stimulates the vibration (low frequencies) of the aforementioned structures. In this research, a novel joint mechanism was developed in conjunction with active control to inhibit the low-frequency vibration of a large flexible appendage. A compact active joint, based on the idea of electromagnetic direct drive, was designed. The dynamic equations for the large flexible appendage system and the active joint were derived using the Lagrange function with the assumed-modes approach. Single- and multi-frequency excitations were simulated by two noncontact strategies for periodic vibration stimulation along the direction of rotation. The research results revealed that the interference signal had a primary frequency bandwidth of 0.07–0.63 Hz, and the vibration attenuation was prominent between 5.95 and 32.41 dB within the valid bandwidth. Effective inhibition of both the larger and the smaller amplitude vibrations at frequencies lower than 1 Hz could be realized using the proposed active joint without attachment of intelligent materials onto the flexible appendage surface.

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“…Compared to the passive control methods, active controls methods have the advantages of flexibility and strong adaptability, especially for low-frequency vibrations. In recent years, researchers have developed intelligent materials and structures to suppress the vibrations of flexible appendages (Abdeljaber et al, 2016;Li et al, 2015;Pu et al, 2019aPu et al, , 2019bQiu et al, 2018). In the recent literature, piezoelectric intelligent structures have been mainly combined with modern control theories to control the vibration of flexible plates.…”

Section: Introductionmentioning

confidence: 99%

Low-frequency vibration control of two flexible appendages using a joint with actively tunable stiffness

Hu¹,

Wu²,

Zhu³

et al. 2022

Journal of Vibration and Control

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Low-frequency and large-amplitude vibration of flexible appendages in space can be induced when a spacecraft performs attitude maneuvers and thermal alternations during orbit operation. In this paper, a novel joint mechanism combined with a semi-active method for variable stiffness control is proposed to suppress the low-frequency vibrations of flexible jointed appendages. The variable stiffness of the joint is derived from the linear relationship between its output torque and rotation angle when direct current (DC) power is applied to the coils. Based on the Lagrange equation and the assumed mode method, the coupling dynamic relationships of the active joint and two flexible appendages are established, and semi-active vibration control simulations are performed. A ground experimental platform is built to simulate the microgravity environment in space. The frequency shift effect of rigid body motion and elastic vibration under impact disturbance are investigated. In addition, the effect of variable stiffness control on the elastic deformation of flexible appendages is studied. The simulation and experimental results indicated that the proposed method can control both the rigid body motion of the system and the elastic vibration of the appendages. It has been found that the major frequency bandwidth of the interference signal is within 0.3–1.0 Hz with a substantial vibration attenuation of 1.82–16.62 dB for the joint and 4.86–11.48 dB for the flexible appendages.

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A New Mechanism for the Vibration Control of Large Flexible Space Structures With Embedded Smart Devices

Cited by 25 publications

References 22 publications

Improvement on the passive method based on dampers for the vibration control of spacecraft solar panels

Improvement on the passive method based on dampers for the vibration control of spacecraft solar panels

Active Vibration Control of a Large Flexible Appendage Using a Novel Joint Mechanism

Low-frequency vibration control of two flexible appendages using a joint with actively tunable stiffness

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