Dynamics and control of spacecraft solar array deployment considering physical contacts between locking mechanisms. (June 2022)

• Record Type: Journal Article
• Authors: Wang, Hongdong; Wang, Jianyao
• Is Part Of: Acta astronautica. Volume 195(2022)
• Page Start: 481
• Page End: 492
• Publication Date: 2022-06
• Subjects: Solar array -- Deployment and locking -- Contact-impact -- Dynamics and control -- Flexible panel; Astronautics -- Periodicals; Outer space -- Exploration -- Periodicals; Astronautics; Periodicals; 629.405
• DOI: 10.1016/j.actaastro.2022.03.028
• Languages: English
• ISSNs: 0094-5765

Abstract

Abstract: The numerical simulation of the deployment and locking process of flexible appendages is an important topic in the overall design of spacecraft. In the existing research, the connecting mechanism between the solar panels is usually regarded as an ideal revolute constraint, and the locking process is simulated by applying a virtual lock torque related to the deployment angle. However, this method cannot obtain the physical contact force history, and because the physical meaning of the stiffness term in the lock torque function is not clear, it is difficult to accurately illustrate the frequency characteristics of the flexural vibration of the panels in the post-lock phase. In fact, the locking process is a frequent contact-impact process between the lock pin and groove. In this study, a typical deployable spacecraft with torsion-spring-driven panels were investigated numerically. The locking mechanism is modeled as a physical entity, and the continuous contact force model between the lock pin and groove is established. The contact stiffness of cylindrical line-contact is given by preloading calculation using the finite element method. Based on the multibody dynamics, rigid body model and flexible body model of the solar panels are established respectively. Through the comparison between the numerical simulation results of the two models, it is found that the rigid body model will produce excessive contact force and false high-frequency vibration. Furthermore, the attitude PD controller of spacecraft is designed, and the difference of system dynamic response in the deployment process under the main-body free state and the main-body controlled state is studied. The vibration frequency under the main-body controlled state is close to the first-order natural frequency of the structural finite element analysis, which verifies the rationality of the calculation results of the model. Highlights: The locking process was modeled using a continuous contact force method instead of virtual angle-related moment. Contact parameters between complex surfaces were determined by a pre-FEM simulation, rather than Hertz contact law. Influence of the panel flexibility on the system dynamic response was investigated, showing that it cannot be ignored. Dynamic characteristics of spacecraft under controlled and uncontrolled states were compared.