有末端姿态角约束的机载布撒器导引律设计  

Guidance Law Design with Terminal Attitude Constraint for Airborne Dispenser

作　　者：林波[1] 孟秀云[1] 刘藻珍[1] 

机构地区：[1]北京理工大学机电工程学院,北京100081

出　　处：《弹箭与制导学报》2005年第2期18-20,共3页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：根据布撒器的作战要求,推导了一种闭环形式的具有末端角度约束的导引规律,并分析了工程实用性。该导引律保证了布撒器在飞抵目标点上方抛撒点时具有合适的末端姿态角。在不同飞行条件下的全弹道仿真结果表明,该导引律均能同时满足布撒器在抛撒点精度和期望姿态角要求。According to the requirements of airborne dispenser, a closed form guidance law with angular constraint is derived and its project feasibility is analyzed in detail. This guidance law ensure the appropriate terminal attitude angle when dispenser arrives at the open-cabin-point upon the target. Finally, full envelope simulation results from different flight conditions show that the guidance law can meet the requirement of both precision and angular constraint of airborne dispenser.

关 键 词：导引律 姿态角 机载布撒器 设计 作战要求 导引规律 闭环形式 仿真结果 飞行条件 实用性 度约束 目标点 全弹道 抛撒 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程] TJ765.2