中文摘要：

为充分发挥吸气式超声速导弹巡航性能高的优势，对其巡航段的飞行方案进行了研究。考虑吸气式冲压发动机与飞行轨迹强耦合的特性，建立了以飞行攻角和燃料质量流量为双优化变量的多阶段多约束的弹道优化模型，提出了一种飞行轨迹与推力规律一体化优化设计方法。以射程最大为性能指标，对吸气式超声速导弹的爬升段和巡航段进行了综合优化设计，并着重对不同巡航方案下的弹道性能进行了分析。仿真结果表明,该方法能有效解决吸气式超声速导弹多阶段多约束轨迹优化问题，对于该吸气式超声速导弹而言，巡航的速度不宜太大，高空飞行更有利于增加射程；不等高不等速巡航方案与等高等速巡航方案相比．最大射程提高了12.3％。研究成果可为吸气式超声速导弹总体设计提供参考。

英文摘要：

In order to take advantage of the high performance of the air-breathing supersonic missile, the cruise scheme was investigated. Considering the strong coupling between the air-breathing ramjet and flight profile, a multiple phases and multiple constraints trajectory optimization model was established with double optimization design variables composed of angle of attack and fuel flow rate, anc a trajectory and ramjet integration optimal design method was proposed. The climb and cruise trajectory were optimized syntheti cally by selecting the maximum range as the performance index. Moreover, the performances of trajectory under different cruise schemes were mainly analyzed. The simulation results show that the proposed method is effective in solving the optimization design problem with multiple constraints and phases for air-breathing supersonic missile. In term of this missile, the cruise velocity should not be too high, and it is conducive to increase range at high altitude. The maximum rang of the cruise scheme of nonconstant altitude and non-constant velocity is improved by 12.3% in comparison to the cruise scheme of constant altitude and constant velocity. The research results can provide reference for overall design of the air-breathing supersonic missile.