摘要
围绕制式火箭弹精确制导改造的需求,提出了一种采用捷联激光探测器和比例导引的火箭弹制导控制方案。针对捷联探测器只能测量弹轴相对于目标的偏差角而无法提供比例导引所需的惯性视线角速度信号的难题,研究了基于捷联探测器测量的误差角和弹体姿态角速度信号的弹目视线角速度信号提取算法。在制导控制系统内部,基于自动驾驶仪与制导律相匹配的原则,设计了两回路过载自动驾驶仪。无量纲脱靶量分析与攻击静止目标的弹道仿真结果验证了所提方案的可行性。
A guidance control scheme based on strapdown laser detector and proportional navigation guidance （PNG） for rocket projectile was presented in details since the precise guidance improvement requirement. Because the strapdown detector can only measure the error angle between airframe axis and target directly and could not provide the inertial line-of-sight （LOS） angular rate necessarily to PNG, a LOS rate algorithm using detector′s error angle and airframe attitude rate from onboard gyro was proposed. A two-loop acceleration autopilot was designed with respect to the autopilot-guidance match principle. The non-dimensional miss distance analysis and trajectory simulation results validate that the proposed approach is feasible.
出处
《红外与激光工程》
EI
CSCD
北大核心
2013年第12期3245-3248,共4页
Infrared and Laser Engineering
基金
国家自然科学基金(61204117)
关键词
捷联激光探测器
制导火箭
制导控制系统
过载自动驾驶仪
比例导引
strapdown laser detector
guided rocket
guided control system
acceleration autopilot
proportional navigation
