摘要
随着高空探测火箭探测高度的提升,GPS导航系统无法满足其在3 000 km以上的定位需求,且通常应用于卫星精密定轨的传统统计定轨理论也难以实现。从高空探测火箭快速实时定位解算需求出发,针对地基导航、箭上自主解算实时定位方式,结合导航系统误差模型和轨道动力学特性,提出了一种实时高精度定位解算的方法。采用试验数据和误差辨识,完善地基导航系统误差模型,建立动力学卡尔曼滤波算法方程对定位数据进行滤波,实现快速实时高精度定轨。该方法省去了轨道积分过程,提高定位精度和解算效率。
With the increase of altitude detection,GPS navigation system can not meet the positioning needs when the rocket is above 3 000 km. The traditional statistical theory is difficult to apply. This paper starts from the requirement of fast and realtime positioning,combined with the error model of the navigation system and the characteristics of orbit dynamics,a real time and high precision positioning algorithm is proposed for groundbased navigation system. By using some experimental data,the error model is improved and Kalman filter equation is established to smooth the positioning data,realizing fast and real time high precision positioning. This method saves the track integral time and improves the positioning accuracy.
出处
《现代防御技术》
北大核心
2017年第6期124-130,165,共8页
Modern Defence Technology
关键词
高空探测火箭
定位
实时
箭上自主解算
导航系统误差建模
动力学卡尔曼滤波
high-altitude sounding rocket
positioning
real-time
shipboard autonomic computing
navigation system error modeling
dynamics Kalman filter
