Hypersonic Vehicle/Deeply Precooled Combined Cycle Engine Integration Analysis

Based on the typical mission requirement of near space aircraft. A performance analysis model of high-speed aircraft/combined power integration is established. Taking the Deeply Precooled Combined Cycle Engine as the evaluation object, evaluates the ability of the power to complete typical missions, and studies the effects of different climbing modes, different wing loads and different takeoff weights on the aircraft. The important performance parameters of high-speed aircraft and engine in the flight profile are obtained. The research results show that the Deeply Precooled Combined Cycle Engine is suitable for completing long-range missions. If the mission purpose is to save fuel, the lower dynamic pressure climbing mode is selected and if the mission purpose is to spend a short flight time, the higher dynamic pressure climbing mode is selected. Larger wing load takes a longer time to reach the cruise altitude, and the flight distance is also longer. However, when the wing load exceeds a certain value, the supersonic cruise angle of attack will exceed the optimal angle of attack, and the maximum lift drag ratio of the cruise point can’t be fully utilized. The benefit brought by the fuel load of large takeoff weight is greater than the increase of fuel consumption brought by the reduction of thrust weight ratio, but the acceleration is poor in the subsonic accelerating climb, so the mobility in the subsonic climb is also an important constraint restricting the upper limit of the takeoff weight of the aircraft.