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.
ZwanenburgR.The Columbus solar array mechanisms. Proceedings of Fifth European Symposium on Space Mechanisms and Tribology, European Space Technology Centre, Noordwijk, October 1992, pp. 49–54 (ESA).
2.
BurgessS. C.HumphriesM. E.Primary deployment mechanism for the European Polar Platform. Proceedings of Fifth European Symposium on Space Mechanisms and Tribology, European Space Technology Centre, Noordwijk, October 1992, pp. 55–60 (ESA).
3.
CentralJ. L.ReibaldiG. G.The ESA Polar Platform, ESA Bulletin, August 1992, pp. 26–38.
4.
BurgessS. C.A study of the efficiency of a double-action worm gearset, Proc. Instn Mech. Engrs, 1992, 206, 81–91.
5.
FeynmanR. P.Lectures on Physics, Vol. 1, 1963, pp. 9–4 to 9–6 (Addison Wesley).
6.
SpencerA. J. M.Engineering mathematics, Vol. 1. 1977, pp. 369–370 (Van Nostrand Reinhold).
7.
BurgessS. C.StolarskiT. A.KarpS.Mathematical model of an overrunning mechanism in a new one-way clutch, Engng Trans. (Polish Academy of Sciences), 1992, 40, 49–62.
