Several Basic Researchs On Spacecraft With Flexible Appendages

Dynamic modeling and control system designing of a flexible spacecraft is a very important subject in the aerospace. The dynamic model of the spacecraft with a flexible appendage has been studied in this paper. The affection of the vibration of solar panels to the spacecraft's attitude has been discussed. Besides, the non-linear dynamic response of extending cantilever-beam has also been studied. The mainresearches enclosed in this paper are as follows:Based on the Newton's law of motion, the law of angular momentum and the variation principle, the dynamic model of spacecraft with flexible appendage has been researched.The translational, rotational dynamics equation and the vibration equation of flexible appendage have been extended by modal coordinate method. The dynamic model of the spacecraft has been established in model coordinate system.Using the dynamic model established, the influences of the flexible solar-array's rotation have been discussed.Coupling coefficient of dynamic equation of multi-body has been calculated by finite element method. Coordinate transformation matrix has also been derived.The dynamic characteristics of extending cantilever-beam in the extensional process have been studied with the consideration of non-linear term. Analytic solution of extending cantilever-beam has been calculated by using the improved averaging method and compared with numerical solution.