Development of the Aeroelastic Mathematical Model of the STS as an Object of the Flight Control System in the Preliminary Design Phase

Kurzfassung

This paper considers the development of a simplified modular parametrical model of the STS as an aeroelastic object of the flight control system in an iterative process. The first approximation for the materials and mass distribution is based on statistical methods. After a first stress analysis a more precise mass distribu-tion can be obtained. The preliminary design of the control system will consider flight path control as well as the trim and stabili-zation task. The eigenfrequencies analysis of the closed loop "rigid body – control system" allows rejecting of higher eigenvibrations of the elastic structure which are negligible for the control system and thereby allows simplifying of the whole mathematical model. The various aspects of the model applicability, its adequacy and the possible further development of some model components will also be discussed in this paper.