Simulation and analysis of flexible solar panels’ deployment and locking processes

Erwei, Gao; Zhang, Xueping; Yao, Zhenqiang

doi:10.1007/s12204-008-0275-5

Cited by 17 publications

(10 citation statements)

References 4 publications

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“…Many references in the literature study the dynamics of spacecrafts with flexible appendages, like solar panels or antennas. [23][24][25][26][27][28] There are three main computational difficulties associated with very flexible space structures, 29 namely the stiff character of the equations of motion, the coupling between axial and bending effects and the problems associated with large deformations. Stiffness is tackled using implicit integration schemes, that usually improve stability introducing numerical damping in the high-frequency range.…”

Section: Satellite's Manoeuvrementioning

confidence: 99%

“…Each panel is hinged to the satellite body by three smooth spherical joints (see Figure 9) and connected by four rigid and massless bars, acting as stiffeners of the panels. The satellite body is equipped with two rockets R 1 and R 2 that provide the necessary thrust, given by (27) expressed in kN, to perform the manoeuvre aimed at changing the attitude of the satellite by 90 . The motion is illustrated in Figure 10.…”

Section: Satellite's Manoeuvrementioning

confidence: 99%

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An energy-consistent integration scheme for flexible multibody systems with dissipation

Martín

Orden

2016

Proceedings of the Institution of Mechanical Engineers, Part K:

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This work is concerned with the numerical solution of the equations of the dynamics of flexible multibody systems with dissipative physical mechanisms. Specifically, we consider systems composed of rigid and deformable bodies made of a viscoelastic continuum, that may experience large displacements and strains, connected by joints. Within this framework, we present a novel integration scheme for these types of systems that intrinsically satisfies the laws of thermodynamics and existing symmetries. The resulting solutions are physically accurate since they preserve the fundamental physical properties of the model. Furthermore, the method gives excellent performance with respect to robustness and stability. Justification of these claims as well as numerical examples that illustrate the performance of the scheme are provided.

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Section: Satellite's Manoeuvrementioning

confidence: 99%

Section: Satellite's Manoeuvrementioning

confidence: 99%

An energy-consistent integration scheme for flexible multibody systems with dissipation

Martín

Orden

2016

Proceedings of the Institution of Mechanical Engineers, Part K:

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“…Joint friction could affect the deploying process of solar arrays. Up to now, the flexibility of solar arrays is another issue that does not receive in-depth study (Gao et al , 2008). Along with the development of space technology, solar arrays become larger, so the flexibility should be paid more attention to in the dynamics analysis of solar array deployment.…”

Section: Introductionmentioning

confidence: 99%

Deployment and control of cable-driven flexible solar arrays

Duan

Liu

et al. 2017

AEAT

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Purpose The purpose of this study is to investigate the deployment and control of cable-driven flexible solar arrays. Design/methodology/approach First, dynamic model of the system is established by using the Jourdain’s velocity variation principle and the single direction recursive construction method, including the dynamic equation of a single flexible body, the kinematical recursive relation of two adjacent flexible bodies and the dynamic equation of the solar array system. Then, the contribution of joint friction to the dynamic equation of the system is derived based on the virtual power principle. A three-dimensional revolute joint model is introduced and discussed in detail. Finally, a proportion-differentiation (PD) controller is designed to control the drift of the system caused by the deployment. Findings Simulation results show that the proposed model is effective to describe the deployment of flexible solar arrays, joint friction may affect the dynamic behavior of the system and the PD controller can effectively eliminate the spacecraft drift. Practical implications This model is useful to indicate the dynamics behavior of the solar array system with friction. Originality/value The relationship between ideal constraint force and Lagrange multipliers is derived. The contribution of joint friction to the dynamic equation of the system is derived based on the virtual power principle. A PD controller is designed to control the drift of the system caused by the deployment of solar arrays.

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“…XS Ge and YZ Liu 5 derived the Euler's equations of forced vibration of two flexible solar arrays and discussed attitude stability of flexible spacecraft. E Gao et al 6 presented the methodology on modeling and simulating the deployment and locking processes of flexible solar panels for a satellite and revealed that the deployment process of flexible solar panels impacted the attitude of satellite. These researches provide a significant foundation for studying the dynamic characteristics of deployable flexible solar array system during deployment.…”

Section: Introductionmentioning

confidence: 99%

Dynamic responses of space solar arrays considering joint clearance and structural flexibility

Wang

Huang

2016

Advances in Mechanical Engineering

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This article numerically investigates the effects of revolute joint clearance and structural flexibility on the overall dynamic characteristics of a deployable solar array system. Considering torque spring, close cable loop configuration, and lock mechanism, a typical mechanism composed of a main body with a yoke and two panels is used as a demonstration case to study the effects of clearance and flexibility on the dynamic response of the deployable solar array system in the deployment and lock process. The normal contact force model and tangential friction model in clearance joint are established using Lankarani Nikravesh model and modified Coulomb friction model, respectively. The numerical simulation results reveal that the coupling of clearance and flexibility makes different effects on the dynamic characteristics of the deployable space solar arrays for different operation stages. Besides, the clearance and flexibility of a mechanical system play crucial roles in predicting accurately the dynamic response of the system, which is the foundation of mechanism design, precision analysis, and control system design.

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Simulation and analysis of flexible solar panels’ deployment and locking processes

Cited by 17 publications

References 4 publications

An energy-consistent integration scheme for flexible multibody systems with dissipation

An energy-consistent integration scheme for flexible multibody systems with dissipation

Deployment and control of cable-driven flexible solar arrays

Dynamic responses of space solar arrays considering joint clearance and structural flexibility

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