吸气式超声速导弹爬升段多约束轨迹优化

Climb Trajectory Optimization with Multiple Constraints for Air-Breathing Supersonic Missile

针对吸气式超声速导弹飞行过程多约束及强耦合的特性,研究了超声速导弹爬升段的轨迹优化设计问题。考虑吸气式推进系统与气动力、飞行轨迹的耦合,对超声速导弹冲压发动机的性能进行分析,揭示了吸气式发动机推力、静压裕度以及余气系数随飞行状态的变化规律;在考虑过载、动压、终端弹道参数及发动机参数等约束的条件下,建立多约束条件下的轨迹优化模型,提出一种适用于此类飞行器飞行轨迹与推力规律的优化设计方法,并对最小油耗的爬升弹道进行优化设计分析。仿真结果表明,该方法能有效解决吸气式超声速导弹多约束轨迹优化问题,可为吸气式超声速导弹的弹道规划与制导律设计提供参考。

The purpose of the present paper is to investigate the optimization design of climb trajectory with multiple constraints for an air-breathing supersonic missile, and a trajectory/ramjet optimal design method which is suitable for this kind of aircraft is proposed under the condition that considering multiple constraints and strong coupling of the air-breathing supersonic missile in flight process. The performance of the air-breathing ramjet is analyzed and the law of thrust, static margin and excess coefficient varying with the flight condition is ascertained in climb trajectory. A multi-constraint trajectory optimization model is established with the constraints of ramjet, overload, dynamic pressure and terminal parameters, and a numerical example that minimizes the fuel consumption of the climb trajectory is presented. Numerical simulation results indicate the effectiveness of the proposed method in solving the trajectory optimization design problem with multiple constraints and provide reference for the trajectory planning and guidance law design of the air-breathing supersonic missile.