基于响应时间约束的敏捷轨道设计方法  

Orbit design method of operationally responsive atellite basing on the time constraints

作　　者：张雅声[1] 冯飞[2] 

机构地区：[1]中国人民解放军装备学院航天装备系,北京101416 [2]中国人民解放军装备学院研究生院,北京101416

出　　处：《国外电子测量技术》2017年第5期37-39,共3页Foreign Electronic Measurement Technology

摘　　要：结合快响卫星在实际任务中的应用背景,研究了响应时间约束中的敏捷轨道设计方法。首先,根据快速响应卫星的发射点和目标点的位置关系,结合快速响应时间约束,得出了响应时间与轨道高度的不等式关系;其次,针对常见的圆形轨道,根据球面三角形公式,构建了敏捷轨道轨道周期、轨道倾角、升交点赤经的解析设计方法;最后,结合STK软件的典型任务仿真,分别设计了当圈响应与第3圈响应的两类敏捷轨道,使卫星分别在入轨10min与200min时星下点通过目标区域,验证了方法的可行性、易操作性和实用性。Basing on the background of operationally responsive satellites in practical missions,the orbital design method is researched in this paper.First,combing with the relation of launch point and objective point position,the inequality relation between the orbital altitude and the operationally responsive time is established,involving the constraints of the operationally responsive time.Then,according to the spherical triangle theory,the equations of orbital inclination and RAAN are established.Furthermore,aiming at an assumed object region,two different types of operationally responsive orbit with different responsive times are simulated in STK.Also,the feasibility has been verified.

关 键 词：快速响应 轨道设计 敏捷轨道 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程] TN02[电子电信—物理电子学]