面向作战效能的弹载卫星导航抗干扰指标分析方法
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- 英文论文题名：Study on Anti-Jamming Indexes of Satellite Navigation Receivers Equipped in Missiles Based on Battle Effectiveness
- 论文作者：吴向宇 ; 高志刚
- 英文论文作者：Wu Xiangyu ; Gao Zhigang ; Troops 95899 of PLA
- 年：2016
- 作者机构：95899部队;
- 论文关键词：导弹 ; 卫星导航 ; 抗干扰 ; 指标分析
- 英文论文关键词：missiles ; antenna arrays ; anti-jamming ; index analysis
- 会议召开时间：2016-10-31
- 会议录名称：探索 创新 交流（第7集）——第七届中国航空学会青年科技论坛文集（上册）
- 英文会议录名称：Discovery,Innovation and Communication——Proceedings of 7th CSAA Science and Technology Youth Forum
- 语种：中文
- 分类号：TJ765
- 学会代码：ZGHU
- 会议名称：探索 创新 交流（第7集）——第七届中国航空学会青年科技论坛
- 会议地点：中国广东中山
- 主办单位：中国航空学会
- 学会名称：中国航空学会
- 页数：5
- 文件大小：1429k
- 原文格式：O
- 会议级别：全国
摘要
导弹的导航系统通常由卫星导航和惯性导航组合而成,两者可起到优势互补的作用。但是,导弹在飞行末端极有可能面临强干扰,此时卫星导航将不能正常工作,只能依靠惯性导航继续飞行,而惯性导航又存在累积误差。本文分析了导弹的打击精度与弹载卫星导航抗干扰指标、导弹飞行速度、惯性导航位置偏差之间的关系,并进行了数值仿真。
Navigation system of missiles is usually constituted with a satellite navigation system and an inertial navigation system,both of which play the role with complementary advantages for each other.However,missiles are likely to face strong interference during the end of flight,the satellite navigation system would not work properly,which could only rely on inertial navigation to complete the terminal flight.It is noteworthy that the inertial navigation has accumulated error.Therefore,in this paper,the relationships of the hit precision of missile with the anti-jamming indexes of satellite navigation,with the flight speeds of the missiles and the position deviation of inertial navigation are analyzed,and the numerical simulations are also conducted.
Navigation system of missiles is usually constituted with a satellite navigation system and an inertial navigation system,both of which play the role with complementary advantages for each other.However,missiles are likely to face strong interference during the end of flight,the satellite navigation system would not work properly,which could only rely on inertial navigation to complete the terminal flight.It is noteworthy that the inertial navigation has accumulated error.Therefore,in this paper,the relationships of the hit precision of missile with the anti-jamming indexes of satellite navigation,with the flight speeds of the missiles and the position deviation of inertial navigation are analyzed,and the numerical simulations are also conducted.
引文
[1]王鹏.高动态飞行器INS/GNSS深耦合系统精度分析与优化技术[D].成都:电子科技大学,2015.
[2]姚兴太.惯性导航系统定位精度与试验路径的关系[J].火炮发射与控制学报,2007,12(4):27-29.
[3]卢鑫.长航时高精度惯性导航系统重力补偿研究[D].长沙:国防科技大学,2010.
[4]张妍.空空导弹制导与控制问题研究[D].哈尔滨:哈尔滨工业大学.2003.
[5]聂俊伟.GNSS天线阵抗干扰算法及性能评估技术研究[D].长沙:国防科技大学,2011.
[6]张安柯,孔繁峨.空空导弹射后动态攻击区的计算及信息提示[J].光电与控制,2016,23(1):75-78.
[7]马晓明,丁平.基于MATLAB的某型反舰导弹攻击范围计算[J].计算机光盘软件与应用,2013,3:219-220.
[8]高倩.未来巡航导弹——速度更快精度更高[J].飞行导弹,2000(6):1-6.
[9]杜毅民,李立坤.空空导弹惯性制导系统设计的几个问题[J].制导与引信,2003,24(1):1-5.
[2]姚兴太.惯性导航系统定位精度与试验路径的关系[J].火炮发射与控制学报,2007,12(4):27-29.
[3]卢鑫.长航时高精度惯性导航系统重力补偿研究[D].长沙:国防科技大学,2010.
[4]张妍.空空导弹制导与控制问题研究[D].哈尔滨:哈尔滨工业大学.2003.
[5]聂俊伟.GNSS天线阵抗干扰算法及性能评估技术研究[D].长沙:国防科技大学,2011.
[6]张安柯,孔繁峨.空空导弹射后动态攻击区的计算及信息提示[J].光电与控制,2016,23(1):75-78.
[7]马晓明,丁平.基于MATLAB的某型反舰导弹攻击范围计算[J].计算机光盘软件与应用,2013,3:219-220.
[8]高倩.未来巡航导弹——速度更快精度更高[J].飞行导弹,2000(6):1-6.
[9]杜毅民,李立坤.空空导弹惯性制导系统设计的几个问题[J].制导与引信,2003,24(1):1-5.