Rigid–elastic-thermal coupling dynamics and its application

Abstract

Spacecraft dynamics belongs to rigid–elastic coupling dynamics in general. If thermal stress and thermal effect are further considered, it will cause the more complex rigid–elastic-thermal coupling dynamics. For the aforementioned kind of coupling dynamics, it is difficult to establish the basic equations directly. It has proved that a suitable way to study complex coupling problems is by work–energy theorem and the law of conversation of energy. Using the energy method, Hamilton principle of rigid–elastic-thermal coupling dynamics is established. The stationary value conditions of Hamilton principle of rigid–elastic-thermal coupling dynamics are derived. The physical meaning of the stationary value conditions is indicated. As an application of rigid–elastic-thermal coupling dynamics, the actual example of spacecraft is given to reveal that there existed thermal stiffening or softening problems in rigid–elastic-thermal coupling dynamics, just like dynamic hardening or softening problems in spacecraft dynamics.