Abstract
Using a rather general formulation of the problem representing a large class of space platforms with flexible, extensible members, the paper attempts to study complex interactions between deployment, attitude dynamics and flexural rigidity. The governing nonlinear, nonautonomous and coupled equations of motion are extremely difficult to solve even with the help of a computer, not to mention the cost involved. Effectiveness of the versatile formulation is demonstrated through its application to dynamical situations of practical interest involving beam-type appendages. Response of the hybrid systems is obtained over a range of physical parameters and external disturbances. Both transient as well as postdeployment phases are considered. Results suggest significant influence of flexibility, inertia, deployment time history and orbital parameters on the system stability. The presence of free molecular and solar radiation induced environmental forces may further accentuate this tendency. The study represents a necessary first step towards development of a suitable control strategy. (Author)