This paper presents a mathematical simulation of the initial deployment kinetics of a spacecraft solar array panel stack and its primary deployment mechanism. Two methods for achieving initial deployment are considered. The first deployment method involves the motorized deployment of a single hinge. The second deployment method involves the spring actuated deployment of two hinges. In the motorized deployment case, the solar array is predicted to slide against the spacecraft sidewall before separation. In the spring actuated deployment case, the solar array is predicted to separate from the spacecraft sidewall without sliding.
Simulation of the Initial Deployment Kinetics of a Spacecraft Solar Array
1995-04-01
8 pages
Article (Journal)
Electronic Resource
English
Simulation of the initial deployment kinetics of a spacecraft solar array
Online Contents | 1995
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