Deployment Dynamics of a Large-Scale Flexible Solar Array System on the Ground

Guo, Shao-Jing; Hai-quan, LI; Cai, Guo‐Ping

doi:10.1007/s40295-018-0138-8

Cited by 11 publications

(3 citation statements)

References 10 publications

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“…It should be noted that the driving torques of the springdampers in equation (1), the synchronization torques of the CCL mechanisms in equation (2), and the lock torques of the latch mechanisms in equation (3) are regarded as the external forces of the shell. ese torques are then integrated into the generalized external force vector.…”

Section: Formulation Of Rigid-flexible Coupling Spacecraft Systemmentioning

confidence: 99%

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Adaptive Fuzzy Control for Attitude Stabilization of Spacecraft with Deployable Composite Laminated Solar Array

et al. 2020

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Modern spacecraft are often equipped with large-scale, complex, and lightweight solar arrays whose deployment involves a highly dynamic movement. This paper proposed a novel adaptive proportional-derivative typed fuzzy logic control scheme for the attitude stabilization of a flexible spacecraft during the deployment of a composite laminated solar array. First, a constrained rigid-flexible coupling spacecraft model consisting of a rigid main body and a flexible solar array was proposed. The solar array, which is composed of composite laminated shells, was described by the absolute nodal coordinate formulation. Then, the detailed derivation of the adaptive fuzzy PD controller for attitude stabilization of the spacecraft was discussed. In addition, the spacecraft dynamic model which integrated the adaptive fuzzy PD controller was derived as a set of differential-algebraic equations. Several simulations were developed to investigate the solar array deployment dynamics and to verify the effectiveness of the proposed adaptive fuzzy PD controller. The results suggested that the proposed dynamic model is able to exactly describe the deployment dynamics of the composite laminated solar array. The solar array deployment causes obvious translational and rotational motions of the spacecraft. The proposed adaptive fuzzy PD control scheme has better performance in terms of the control precision and time response in stabilizing spacecraft during the deployment of the composite laminated solar array, comparing with that of the conventional PD controller.

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Section: Formulation Of Rigid-flexible Coupling Spacecraft Systemmentioning

confidence: 99%

“…Modern spacecraft often employ large, complex, and lightweight solar arrays to achieve multiple functionalities and to provide sufficient power supply during flight [1]. e solar array deployment is a highly dynamic movement that may affect the spacecraft's motion [2][3][4].…”

Section: Introductionmentioning

confidence: 99%

Adaptive Fuzzy Control for Attitude Stabilization of Spacecraft with Deployable Composite Laminated Solar Array

et al. 2020

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“…e ground modal test is an important approach of the natural frequency of flexible structures. However, due to the environmental differences between ground and space, the modal parameters obtained from ground tests often cannot accurately reflect the natural frequency of spacecraft [7,8]. To obtain usable modal parameters of deployable solar arrays, several mainstream solutions have been developed.…”

Section: Introductionmentioning

confidence: 99%

Encapsulation Based Method for Natural Frequency Identification of Deployable Solar Arrays with Multiple Plates

Zhao

Chen

et al. 2021

Shock and Vibration

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The ground modal test is an important approach to the natural frequency of solar arrays to support the attitude control of spacecraft. However, for the batch production of small satellites, the accuracy and efficiency of traditional ground modal testing methods are limited. This shortcoming restricts the development of satellite constellations. Based on the encapsulation method widely used in the computer field, this paper proposed a natural frequency identification method of deployable solar arrays with multiple plates. This method is of high accuracy and efficiency that meets the demand of attitude control and makes sense to accelerate the batch production of small satellites. First, a suspended modal test system with gravity compensation function is designed. Second, the mathematical model of the test system is established. Abstracting parts of the parameters of the test object into an encapsulated entity, the mathematical model is simplified by equivalent variables. Thus, the direct mapping relationship between the ground test result and the true natural frequency is proposed. Finally, to verify the identification accuracy, finite element analysis (FEA) and the ground modal test of a two-folder solar array simulant are carried out. The results show that the relative error of the first-order natural frequency after correction and the theoretical value is less than 3%. Meanwhile, the identification accuracy of the ground modal test is improved by more than 50%. This method improves the availability of ground test results and reduces the calculation amount, so that it is convenient for engineering applications.

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Deployment dynamics of the solar array system with clearance joints considering interval uncertainties

Jiang,

Bai

2024

Nonlinear Dyn

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Deployment Dynamics of a Large-Scale Flexible Solar Array System on the Ground

Cited by 11 publications

References 10 publications

Adaptive Fuzzy Control for Attitude Stabilization of Spacecraft with Deployable Composite Laminated Solar Array

Adaptive Fuzzy Control for Attitude Stabilization of Spacecraft with Deployable Composite Laminated Solar Array

Encapsulation Based Method for Natural Frequency Identification of Deployable Solar Arrays with Multiple Plates

Deployment dynamics of the solar array system with clearance joints considering interval uncertainties

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