طراحی و تحلیل عملکردی مکانیزم استقرار پنل‌های خورشیدی با قابلیت حذف خرابی‌های تک‌نقطه‌ای

Ensuring functional reliability in deployable space structures constitutes a fundamental challenge in the development of microsatellites. This study presents the design and analysis of a novel integrated all‑mechanical mechanism intended for the locking, commanded release, and deployment of a satellite solar panel. The proposed architecture is developed with the strategic objective of eliminating single‑point failures. In this configuration, the principle of functional redundancy is systematically implemented across the primary locking subsystem, the release command interface, and the force‑generating deployment actuators, thereby ensuring operational continuity even in the event of failure in critical subcomponents.

To maximize kinematic robustness, the mechanism geometry is deliberately formulated around rotational degrees of freedom, which significantly reduces the system’s sensitivity to dimensional tolerances and mitigates the risk of jamming commonly associated with linear linkage mechanisms. Verification of the operational sequence and characterization of the transient dynamic behavior were conducted through a hybrid analytical–numerical approach. Specifically, the kinematic and dynamic governing equations were formulated and solved in MATLAB, while detailed multi‑body dynamic simulations were carried out in the ANSYS environment to capture contact interactions and transient responses during deployment.

Furthermore, structural integrity assessments and load‑distribution analyses along parallel force‑transfer paths demonstrate the high mechanical reliability of the proposed architecture under both static launch loads and dynamic deployment conditions. The numerical and analytical results collectively indicate that the developed mechanism provides a robust and reliable solution for deployable solar array systems, particularly for space missions with stringent mass and volume constraints.