双模态冲压发动机导弹的弹道设计及仿真计算

Trajectory Design and Simulation for a Dual-mode Ramjet Missile

根据固体火箭助推器和双模态冲压发动机的特点,对双模态冲压发动机导弹的飞行弹道进行了设计,建立了弹道计算的数学模型,并进行了弹道仿真计算。结果表明,飞行弹道设计合理,数学模型正确,可以用于导弹的初步设计。

Trajectory design for a dual-mode ramjet missile was accomplished based on the characteristics of the solid propellant booster rocket and the dual-mode ramjet. Mathematical model for trajectory calculation was established, and trajectory simulation result was achieved. Result shows that the trajectory design is reasonable, and the mathematical model is correct, and they can be used in the missile preliminary design.