Abstract
Changes in aerodynamic characteristics of a space vehicle model due to interaction of the control thruster plume with the incoming flow are numerically studied. Parameters of the plume escaping from the thruster nozzle and flight data (velocity and altitude) are taken to be the parameters of the Intermediate eXperimental Vehicle. Simulations are performed by the Direct Simulation Monte Carlo Method. A multizone approach is used for combined modeling of the dense plume and the rarefied incoming flow. If the control thruster plume is fairly close to the space vehicle surface, flow interference is possible, which may alter the force and moment characteristics. In the problem considered in this paper, the pitching moment changes approximately by 10 % at altitudes below 120 km due to this interference.
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