摘要
针对某型靶弹的结构特点和飞行任务，分析了其飞行控制系统的主要功能。合理规划了全程的弹道并进行姿态控制规律的设计，确保靶弹顺利完成爬升、转弯、下滑拉平和定高平飞四个阶段的飞行任务．同时有效的抑制了助推级分离和阵风所引起的干扰。根据真实的气动数据建立了靶弹的空气动力学模型，通过半实物仿真验证了控制规律的实用性和有效性。
According to a target missile structure features and flying task, the functions of the flight control system were analyzed. The trajectory and attitude control law were designed so as to make it completing the flying task which included climbing, turning, flattening out and level flight. The control law also effectively eliminated the separation disturbance of the booster rocket and the wind disturbance. The aerodynamic model was built for the target missile based on the data from the wind tunnel test. A hardware-in-the-loop simulation was given to verify the control law.
基金
国家自然科学基金重大研究计划资助项目（90916003）
关键词
靶弹
弹道设计
姿态控制
半实物仿真
target missile
trajectory design
attitude control
hardware-in-the-loop simulation
