Modeling and Vibration Suppression of Flexible Spacecraft Using Higher-Order Sandwich Panel Theory

Azimi, Milad; Shahravi, Morteza; Fard, K. Malekzadeh

doi:10.20855/ijav.2017.22.2459

Cited by 6 publications

(6 citation statements)

References 15 publications

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“…A common approach is to have a detailed structural model that is fitted to a pristine structure over the frequency range of interest. 17,31 Furthermore, for practical consideration, spacecraft must have limited vibrations in the system. Therefore, it is justifiable to consider the change in combined disturbance to be upper bounded by an unknown constant.…”

Section: Sliding Mode Disturbance Observer Designmentioning

confidence: 99%

“…For instance, a control scheme to suppress vibrations in the system was presented using distributed actuator, 16 while a higher-order sand switch and PZT-based control scheme was presented for flexible spacecraft attitude control. 17 However, the approach has some drawbacks; first, it requires the network of PZT along with appropriate power source to be distributed across the spacecraft structure with the relevant harness, demanding significant consideration during the structure design phase. Second, the materials are not effective when low frequencies are involved.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Robust adaptive attitude control of flexible spacecraft using a sliding mode disturbance observer

Javaid

Zhen

Xue

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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A composite control scheme based on a disturbance observer is presented in this paper to deal with the attitude control problem of flexible spacecraft. Specifically, a sliding mode disturbance observer (SMDO) is developed to attenuate the unmodeled system dynamics, parameter uncertainties, and multiple external disturbances. The key feature of this approach is to relax the assumption imposed on disturbance to be constant or changing at a slow rate, which is a typical assumption in this class of problems involving a disturbance observer. Then, an exclusive adaptive integral sliding mode controller is combined with the SMDO to get the improved closed-loop control performance of the system. The underlying benefit of the proposed control scheme is improved robustness against time-dependent external disturbances and system model uncertainties. The stability analysis of the closed-loop system is provided using Lyapunov’s stability theory. Simulation results are provided to show the effectiveness of the proposed control scheme, especially in comparison with existing results.

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Section: Sliding Mode Disturbance Observer Designmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Robust adaptive attitude control of flexible spacecraft using a sliding mode disturbance observer

Javaid

Zhen

Xue

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

show abstract

“…Therefore, it is desirable to maximize the actuator's vibration suppression capability. The sliding mode control [34,35], the fuzzy logic [36], and the artificial algorithm [37] were investigated and integrated into the vibration control strategy design for the space flexible appendages. Bonding the piezoelectric actuator to the flexible panel, Liu et al [38] developed a hybrid control scheme for the attitude stabilization and vibration suppression of the flexible spacecraft by considering model parameter uncertainty, measurement error, actuator faults, and other factors.…”

Section: Introductionmentioning

confidence: 99%

Envelope-Based Variable-Gain Control Strategy for Vibration Suppression of Solar Array Using Reaction Wheel Actuator

Tang

Chen

2022

International Journal of Aerospace Engineering

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The orbital operation of spacecraft can excite the long-drawn and low-frequency vibration of the solar array, which is prone to affecting the task execution of the system. To address this issue, an envelope-based variable-gain control strategy is proposed to suppress vibration of the solar array using the reaction wheel (RW) actuator. The RW actuator is individually mounted on the solar array to provide reaction torque through the speed change of its rotor. The governing equation of motion of the solar array actuated by a RW actuator is deduced with the state space representation. The control relation between the measured bending moment and the rotational speed of the RW actuator with the constant-gain coefficient is firstly developed and demonstrated in numerical simulation. Changing the gain coefficient to be inversely proportional to the envelope function of vibration, a variable-gain control strategy is proposed to improve the damping effect of the RW actuator. Simulation results show that the vibration suppression performance of the RW actuator is improved compared to the constant-gain control. As the actual on-orbit natural frequency of the solar array is not always exactly known, the robustness of the control system is analyzed for the deviation between the estimated and the actual natural frequency values. The proposed variable-gain control is also experimentally verified using a simplified elastic plate model. Experimental results indicate that the vibration attenuation time is decreased to 29.1% and 50.22% compared to the uncontrolled and the constant-gain controlled states, respectively.

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“…To effectively suppress the vibrations of flexible solar panels, the fuzzy logic control with piezoelectric smart structure is studied by Xu et al 20 A fuzzy logic controller which uses universal fuzzy sets is designed, and the effectiveness of the controller is demonstrated by finite element analysis. Azimi et al 21 investigated the vibration suppression of a flexible spacecraft during a large angle attitude maneuver. The solar panel appendages with surface bounded piezoelectric patches are investigated.…”

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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Modeling and Vibration Suppression of Flexible Spacecraft Using Higher-Order Sandwich Panel Theory

Cited by 6 publications

References 15 publications

Robust adaptive attitude control of flexible spacecraft using a sliding mode disturbance observer

Robust adaptive attitude control of flexible spacecraft using a sliding mode disturbance observer

Envelope-Based Variable-Gain Control Strategy for Vibration Suppression of Solar Array Using Reaction Wheel Actuator

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

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