Thermocontrol for a space tourism vehicle model

For the experimental verification of the design methods of tourist-class suborbital spacecraft, missiles taken out of service may be useful. These missiles can serve as scaled-down flying models, but in some cases, they need to be accelerated in speed to achieve the level of thermal loads corresponding to suborbital flights. Forcing in speed will require upgrade of the rocket design - increasing engine thrust and fuel on board. In turn, after modernization, the model will be suitable for flight testing of critical elements of an expensive reusable space structure and thereby save significant money. In the work we study the temperature state of a hypothetical flying model, forced by the flight speed. The simulation was carried out in ANSYS Fluent in a non-stationary formulation with simultaneous solution of the problems of supersonic flow around the body and heat transfer processes in the internal volume of the front compartment.