考虑飞行器动力系统进排气效应的设计参数灵敏度分析研究

According to the propulsion/airframe integrated design of aircraft, the variation study of intake and exhaust boundary condition under the influences of the propulsion system is carried out, making use of the parallelized in-house code and the adjoint equation code PADJ3D. Chain derivation is adopted to avoid the direct variation of the conservative variables. Then intermediate variables are introduced to reduce the variation difficulties of intake and exhaust boundary conditions. The sensitivity analysis method for design variables under the influences of the intake and exhaust effect is proposed. The numerical simulation accuracy of the analysis method is verified by calculation of the TPS standard model and comparison with the finite difference method. The proposed method is able to provide an efficient and reliable way for sensitivity analysis of design variables under intake and exhaust effect. Simulations are carried out for the aerodynamic layout of the engine on the wing. The intake and exhaust influences under various conditions (low speed, high speed/fixed angle of attack, constant lift, with and without propulsion system), as well as the influencing mechanism, are simulated, analyzed and discussed. This research can provide technical support for the integrated design of pneumatic profile/propulsion system.