摘要
针对SINS/GPS组合导航系统在军民领域广泛应用的特点,详细建立了基于位置/速度的SINS/GPS松组合模型、基于伪距/伪距率的SINS/GPS紧组合模型。分别在正常GPS信号和加入强干扰后GPS信号的条件下,对比了松组合和紧组合模式的导航结果。仿真验证结果表明,相比于松组合模式,紧组合模式能较快适应强干扰,并使系统振荡减弱,快速收敛,确保高导航定位精度。因此,在强干扰、高动态飞行条件下,更适宜采用SINS/GPS紧组合模式。
The simulation models of SINS/GPS loosely coupled integrated system based on position/velocity and the tightly coupled integrated system based on pseudo-range/pseudo-range rate are explicitly established due to the widely use of SINS/GPS integration system for both civil and military .Intense in-terference is inserted into the simulation system in order to compare and analyze the navigation perform-ance of two models .The result shows that , compared with loosely coupled system , tightly coupled system can adjust to intense noise and leads the system to converge fast with small static error .Thus, it is better to choose SINS/GPS tightly coupled integrated system when the aerobat flies with high maneuverability un-der the influence of intense interference .
出处
《航空兵器》
2014年第4期31-35,53,共6页
Aero Weaponry
基金
国家自然科学基金资助项目(61074157)
航空科学基金资助项目(20130151004)
关键词
SINS/GPS组合导航系统
松组合
紧组合
强干扰
SINS/GPS integration navigation system
loosely coupled
tightly coupled
intense in-terference
