Abstract: To deal with the problems of ablation, erection and retraction when using the deflector for exhaust conduction during thermal launching process of vehicular missiles, a new exhaust conduction scheme where carbon dioxide is ejected to impact gas jet so as to lower the temperatures of the launch vehicle and the missile is proposed. Taking the computational fluid dynamics(CFD) as the main research method, a three-dimensional steady model is established, and the characteristics of the cross flow field of gas jet and carbon dioxide are analyzed. The conclusions are drawn as follows: the temperatures of the launch vehicle and the missile decrease and then increase with the increase of the length of lower pipes; their temperatures decrease as the angle between the upper pipes and the launch vehicle wall decreases; the temperatures decrease with the decreasing height between the upper pipe orifices and the lower pipes. As the scheme remains meaningful when the distance between the nozzle exit and the ground is changed, this study provides a feasible new idea to design the exhaust conduction system for the thermal launching of vehicular missiles.

Key words: thermallaunchingofmissiles, gasjet, carbondioxideejection, exhaustconduction