飞行器/发动机一体化是制约吸气式高超声速飞行器的核心和关键技术，本文针对高超声速飞发一体化构型开展了算力体系划分及算力参数敏感性研究。通过将一体化飞行器不同部件划分至气动和推进系统，研究了算力体系划分对气动/推进性能指标的影响，结果表明对于飞发一体化构型，在不同算力体系下表征的飞行器气动/推进性能可能存在较大差异，横向比较飞行器气动/推进性能必须在明确算力体系条件下进行。采用正交试验设计+方差分析的方法分析了飞行器算力对空域、速域、飞行姿态、气动热效应、真实气体效应5个因素的敏感性，结果表明壁面温度是影响飞行器轴向力计算的敏感参数，马赫数和攻角几乎影响所有气动指标。在研究范围内，雷诺数和气体比热比是飞行器气动性能的不敏感参数。
Integration of aircraft and engine is the core and key technology for air-breathing hypersonic aircraft. In this paper, propulsion system force accounting and sensitivity analysis are carried out for the typical integrated configurations. Firstly, the axisymmetric integrated aircraft with abdomen inlet and the integrated aircraft with back inlet wing-body fusion were designed. By dividing the different parts of the integrated aircraft into aerodynamic or propulsion systems, the influence of force accounting on the aerodynamic/propulsion performance is studied. The results show that the aerodynamic/propulsion performance of the aircraft characterized by different force accounting systems maybe quite different. Comparison of the aerodynamic/propulsion performance of the aircraft must be carried out with a clear force accounting system. By using the method of orthogonal experimental design + variance analysis, the sensitivity of the aircraft force accounting to five factors, including airspace, speed domain, flight attitude, aerothermal effect, and real gas effect, is analyzed. The results show that the wall temperature is a sensitive parameter that can affect the calculation of axial force of the aircraft, and the Mach number and the attack angle affect almost all aerodynamic indicators. In the research range, the Reynolds number and gas specific heat ratio are insensitive parameters of aircraft aerodynamic performance.
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