重复使用天地往返运载器飞行弹道计算研究

Study on the Calculation of Flight Trajectory of Air Breathing Reusable Launch Vehicle

介绍了应用于吸气式重复使用天地往返运载器的RBCC动力,根据动力学和运动学方程及地球物理方程式,利用数值积分方法,计算并比较了采用RBCC动力水平起飞、垂直起飞及纯火箭动力垂直起飞的运载器飞行弹道。计算结果表明,相比于纯火箭动力,RBCC动力有效地降低了运载器的燃料消耗量,但热环境明显要恶劣。

In this paper, the rocket based combined cycle（RBCC） engine, which is used in air breathing reusable launch vehicle, is introduced. Based on the dynamic and kinematic equations of the launch vehicle and the earth physics equations, the flight trajectories of each launch vehicle using the RBCC engine and pure rocket engine are calculated and compared, by using the numerical integrated method. It is indicated that, compared with using the pure rocket engine, the fuel consumption of this vehicle is reduced by using the RBCC engine, but the heat condition become more atrocious.