Reentry vehicles such as the space shuttle are subject to severe heating loads during significant portions of their flight trajectories. The conventional design of such vehicles is composed of several sequential design tasks. First, the trajectory is optimized to reduce the heat load and aerodynamic loads on the vehicle. Second, the structure is designed to carry the loads. Third, a thermal protection system is designed to absorb the heat loads without exceeding the allowable temperature in the infrastructure. Such a design procedure is very time consuming and also may not always yield the optimum design. In particular, there are situations where it is advantageous to design the thermal protection system to provide more protection so that temperatures in the infrastructure are well below the allowable. While the mass of the thermal protection system is increased, the mass of the structure may be reduced because the stress allowables are higher at lower temperatures . The present paper continues this line of investigation for thermal buckling constraints is treated in a novel way which does not require any eigenvalue analysis. An example of an application to the design of a wing bay on the orbiter of the space shuttle is presented. It demonstrates the design procedures and some of its benefits.
Simultaneous structural / thermal optimization
Simultane Optimierung von Konstruktion und thermischer Beanspruchung
Computers in Engineering 1982. Proc. of the Second Int. ASME Conf. ; 3 , Aug ; 93-97
1982
5 Seiten, 2 Bilder, 2 Tabellen, 21 Quellen
Aufsatz (Konferenz)
Englisch
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