飞推一体化飞行器多模态计力体系及升阻性能研究

Research on Multi-mode Lift-drag Performance of Airframe Integrated Propulsion System Hypersonic Vehicle

针对推进系统采用TBCC组合循环发动机的飞推一体化高超声速飞行器,进行气动/推进力计算方法研究;分析并建立飞行器运动力学体系及计力体系,推导出推进系统双通道模式下一体化飞行器气动/推进力计算公式;针对TBCC推进系统的涡轮模态、涡轮冲压过渡模态及冲压模态三种工作模态,研究计力方法并计算分析飞行器在不同工作模态下升阻性能随攻角的变化趋势,研究飞行器各部件对升阻力性能影响贡献。研究表明:高超声速飞推一体化飞行器进行跨声速飞行时,前体对升力影响较大,机身阻力在很大程度上决定着飞推一体化高超声速飞行器的阻力大小。

The aerodynamic/propulsion calculation method is studied for the airframe integrated propulsion system hypersonic vehicle with TBCC combined cycle engine in the propulsion system.The aircraft motion mechanics system and force calculation system are analyzed and established,and the aerodynamic/propulsion calculation formula of the integrated aircraft in the dual-channel mode of the propulsion system is deduced.For the three working modes of the TBCC propulsion system like turbine mode,turbine stamping transition mode and stamping mode,the force counting method is elaborated and used to calculate the variation trend of lift and drag performance with attack angle of aircraft in different working modes,and the influence of various components of aircraft contributing to lift and drag performance is studied.The reserch results show that the forebody has greater influence on lift when the airframe integrated propulsion system hypersonic vehicle is flying at transonic speeds,and the drag from the fuselage largely determines the resistance of the airframe integrated propulsion system hypersonic vehicle.