Experimental study on plume impingement effects of satellite attitude control thruster nozzle

Experimental study has been performed for the plume impingement effects of the satellite attitude control thruster plume to a flat plate. The impingement effects include plate surface force and heat payload. The whole experimentation is performed in the supersonic low density wind tunnel and the test gas is heated nitrogen. Ten experimental cases are measured for two different geometry satellite thrusters and different plate s locations. The parameters such as plate' s surface pressure and heat flux distribution are obtained. The heat flux distribution of plate in the plume backflow is also measured. The laws of distribution of surface pressure and heat flux are obtained by comparing the experimental results, by which it can be judged to form the backflow. The results analysis demonstrates that the experimental results are effective and reasonable. The study provides the experimental foundation for the layout of attitude control thrusters on satellites.