CAJ | 학술논문

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。
위요제식화전탄정학제도개조적수구，제출료일충채용첩련격광탐측기화비례도인적화전탄제도공제방안。침대첩련탐측기지능측량탄축상대우목표적편차각이무법제공비례도인소수적관성시선각속도신호적난제，연구료기우첩련탐측기측량적오차각화탄체자태각속도신호적탄목시선각속도신호제취산법。재제도공제계통내부，기우자동가사의여제도률상필배적원칙，설계료량회로과재자동가사의。무량강탈파량분석여공격정지목표적탄도방진결과험증료소제방안적가행성。
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.