Abstract
For a long time it has been assumed that the modes of elastic vibration of a controlled slender vehicle in real flight are the same as modes of pure elasticity. In fact, it rather appeared to be an elastic-aerodynamic-control intercoupled complex system. Either the frequencies or shapes of vibration modes as well as the mode of rigid motion would vary due to aerodynamic and control effects. In this paper the problem is investigated in the frame of distributed parameter system theory. The spectrum perturbation has been studied in detail with respect to aerodynamic effect and feedback attitude control. Some stability problems of vibration and rigid motion are investigated from the viewpoint of a perturbation theory of linear operators. The wide-spread engineering approximation method is justified rigorously.
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