吸气式飞行器爬升段轨迹与速度在线规划及制导律设计  

Design of Driving Down-Phase Guidance Law for Air-Breathing Vehicles Based on Single Attack Angle Characteristics

作　　者：赵长见[1,2] 梁卓[2] 严佳民[2] 周国峰[2] 韩英宏[2] 

机构地区：[1]国防科学技术大学,长沙410073 [2]中国运载火箭技术研究院,北京100076

出　　处：《导弹与航天运载技术》2016年第4期8-11,共4页Missiles and Space Vehicles

摘　　要：由于吸气式飞行器全程在大气层内飞行,飞行弹道极易受到发动机性能偏差、气动偏差和风干扰等影响,导致爬升段初始条件具有较大的不确定性。针对该问题,将轨迹控制回路与速度控制回路作为2个相互独立的回路进行设计,建立了在线轨迹规划与速度规划和导引模型,并以射程最大化为目标,采用拟牛顿法进行多变量寻优,得到需用最优爬升时间和加速时间。最后以典型工况为例进行数学仿真,验证了该方法的合理性与有效性。Considering endo-atmosphere flight, the air-breathing vehicles is liable to be affected by the engine performance, aerodynamic force, windage, etc. Therefore, initialization of climb trajectory is uncertain. Aiming at this question, trajectory control loop and speed control loop are designed independently. In order to achieve maximum range, a quasi-Newton algorithm is proposed to automatically optimize the climb time and stepped-up time. Then simulations are carried out under some typical conditions, and the simulation results confirm its validity and rationality.

关 键 词：吸气式飞行器 爬升段 轨迹规划与控制 速度规划与控制 

分 类 号：V448[航空宇航科学与技术—飞行器设计]