Abstract
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.
Highlights
Solar array, which provides necessary power for the whole system, is a vital component of the spacecraft widely used in space applications.[1]
Muvengei et al.[12] numerically investigated the parametric effects of differently located frictionless revolute clearance joints on the overall dynamic characteristics of a multibody system, and the results showed that location of the clearance revolute joint, the clearance size, and the operating speed of a mechanical system play crucial roles in predicting accurately the dynamic responses of the system
This article establishes the dynamics model of solar array system with clearances, which consists of a main body, a flexible yoke and two flexible panels connected with clearance joints, torque springs, close cable loop (CCL), and lock mechanisms
Summary
Solar array, which provides necessary power for the whole system, is a vital component of the spacecraft widely used in space applications.[1]. This article establishes the dynamics model of solar array system with clearances, which consists of a main body, a flexible yoke and two flexible panels connected with clearance joints, torque springs, CCLs, and lock mechanisms.
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