Abstract: The effect of cable fracture at different locations on solar wing deployment was presented, to identify their key parts and predict their deployment failure mode in orbit. The mechanics models of closed cable loop were established with considering cable fracture effects, and the force and moment at the wheel of closed cable loop (CCL) were formulated. The method of angle trigger constraint elimination (ATCE) was presented to solve the continuous simulation problem of second deployment of solar wing. The dynamics equations of the 2nd deployment of solar wing were derived, and the deployment angle, deployment configuration, and tension forces on other cables were analyzed at the different locations of cable fracture. The analysis indicates that the nearer cable fracture of cable closed loops from satellite body will make bigger effects to solar wing deployment; the fracture of cable closed loop at the yoke may make the solar wing fail to deploy.

Key words: cable fracture, two-dimension two-step deployable solar wing, deployment process, effect analysis, angle trigger constraint elimination (ATCE)