地球同步轨道卫星对低轨卫星的目标引导方法  

Target Guidance Method for Low-Orbit Satellite by Geosynchronous Orbit Satellite

作　　者：陶新龙 金阳辉 陆小科[1] TAO Xinlong;JIN Yanghui;LU Xiaoke(Nanjing Research Institute of Electronics Technology,Nanjing 210039,China)

机构地区：[1]南京电子技术研究所,江苏南京210039

出　　处：《指挥控制与仿真》2024年第3期153-160,共8页Command Control & Simulation

摘　　要：在实际作战中,地球同步轨道卫星通常是最先发现弹道导弹发射的预警装备,然而,其提供的缺维探测信息,使得传统的引导交接方法难以直接应用于其对低轨卫星的目标引导上。针对此问题,对地球同步轨道卫星对低轨卫星的目标引导方法进行研究。首先,根据弹道导弹在发射及主动段飞行过程中产生红外辐射特性时的飞行高度约束,计算在单颗地球同步轨道卫星引导下,低轨卫星红外传感器的方位和俯仰探测范围。其次,对低轨卫星红外传感器的探测距离进行建模和计算,实现低轨卫星对目标的成功探测。最后,通过模拟仿真实验,验证了该方法的有效性和准确性。Geosynchronous orbit satellite is usually the first early warning equipment to catch ballistic missile launches in actual combat.However,the detection information it provides is lack of dimension,which makes the traditional target guidance method hard to be directly applied on the target guidance for low-orbit satellite.Aiming at this point,this paper studies the target guidance method for low-orbit satellite by geosynchronous orbit satellite.First,based on the altitude constraint of infrared radiation during the launch and active flight of the ballistic missile,the azimuth and pitch detection ranges of the infrared sensor of the low-orbit satellite are calculated with the guidance of one geosynchronous orbit satellite.Then,the detection distance of the infrared sensor of the low-orbit satellite is modeled and calculated,which leads to a successful target detection for the low-orbit satellite.Finally,the effectiveness and accuracy of this method are verified through a numerical simulation experiment.

关 键 词：地球同步轨道卫星 低轨卫星 目标引导 弹道导弹 

分 类 号：V474[航空宇航科学与技术—飞行器设计] E919[军事]