临近空间飞行器相变吸热式充排气装置的设计及其性能仿真

The venting holes of the conventional passive pressure control system of near space vehicles may cause the high temperature gas outside to flow back into the cabin, thus disabling the instruments inside the cabin. To solve this problem, a pressure control device filled with phase change materials is proposed in this paper. This device can balance the pressure difference inside and outside the cabin, and ensure vehicle safety by cooling the high-temperature backflow. The device performance is analyzed and structure optimized through numerical simulation. The optimized device is then used during rapid ascent, maneuvering flight and rapid descent of a near space vehicle. Numerical simulation results show that the mass of the phase change material and the volume of the optimized device are reduced by about 45% and 10% respectively. Moreover, the pressure difference inside and outside the cabin is maintained below 50 Pa and the backflow temperature is reduced to 340 K after the optimized pressure control device is used on the near space vehicle. Therefore, the proposed pressure control device can both control the pressure and lower the temperature, promising good application prospects in the field of aerospace.