直升机载导弹初始弹道影响因素分析  

Analysis on Factors Influencing Initial Trajectory of Missiles Onboard Helicopter

作　　者：吴震[1,2] 吴彤薇[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳471009 [2]西北工业大学,西安710072

出　　处：《电光与控制》2009年第3期63-67,共5页Electronics Optics & Control

摘　　要：武装直升机作战多在低空或超低空,所发射的导弹常常掠地飞行,如果导弹初始弹道出现波动,轻则影响命中精度,重则坠地或擦碰障碍物。因此需要对影响初始弹道的干扰因素进行分析并设法消除其影响。通过建立导弹运动学、动力学数学模型,构建了导弹数字仿真环境;建立各种干扰环节的数学模型,并将扰动模型代入导弹仿真环境中进行单项和综合影响仿真分析。分析结果认为导弹陀螺零位、发动机推力偏心、导弹发射方式、直升机旋翼下洗流场等因素的影响是显著的,特别是在这些因素的综合影响下,初始弹道将出现很大的偏离。提出了消除或减小各种因素影响的途径,并进行了仿真验证,结果证明是可行的。Helicopter combat often happens at low-altitude or very low-altitude. If the missile＇s initial trajectory fluctuates, the guidance precision will decrease, and the missile may even fall down on the ground or bump into impediment. So it is necessary to analyze the disturbance factors that have effect on the initial trajectory and take measures to eliminate them. First, missile digital simulation environment was established based on its dynamic and kinematics model, and then multi-disturbance models were established and substituted into the simulation environment, simple or integrated influence of these disturbance were analyzed through simulation. It showed that the influences from gyro zero-position, rocket thrust eccentricity, launch mode and downwash flow field caused by helicopter are evident. Especially, under the integrated influence of these factors, missile initial trajectory departure was serious. The approaches to eliminate or minish these influences were presented, and the availability of which were proved through simulation.

关 键 词：武装直升机 机载导弹 初始弹道 推力偏心 陀螺零位 下洗流场 发射方式 

分 类 号：V271.4[航空宇航科学与技术—飞行器设计]