English

DTIC ADA005265: Mathematical Modelling of the Royal Aircraft Establishment (RAE) Lightweight Flexible Solar Array

The paper describes the development of a mathematical model for the attitude dynamics of a spacecraft equipped with a lightweight flexible solar array. The theory has been developed using a continuous mechanics approach and a computer program prepared to generate the lateral bending modes of a spacecraft comprising a rigid central structure carrying a pair of solar arrays symmetrically situated about the central body. Furthermore, the program will generate the effective inertia and mass as a function of the forcing frequency. These are then formulated in the form of transfer functions which are more convenient for control problem analysis.

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