一种基于加速度计和天文的卫星自主导航新方法  

New method of satellite autonomous navigation based on accelerometer and celestial navigation

作　　者：王鹏[1,2] 张迎春[3] 

机构地区：[1]东南大学仪器科学与工程学院,南京210096 [2]东南大学微惯性仪表与先进导航技术教育部重点实验室,南京210096 [3]哈尔滨工业大学航天学院,哈尔滨150001

出　　处：《中国惯性技术学报》2013年第4期489-494,523,共7页Journal of Chinese Inertial Technology

基　　金：江苏省自然科学基金(BK20130636);中国航天科技集团公司卫星应用研究院创新基金项目(2012-1510);东南大学微惯性仪表与先进导航技术教育部重点实验室开放基金项目(201211);东南大学基于教师科研的SRTP项目(T13222002)

摘　　要：直接敏感地平是一种典型自主天文导航方法,该方法简单可靠,易于实现,但是由于常用卫星轨道动力学J2模型精度有限,地球敏感器精度较低,因此导航精度不高。加速度计是测量运载体线加速度的常用惯性导航设备,当航天器在轨运行时,星载加速度计能够测量航天器所受发散力。结合上述两种方法的特点,提出一种将加速度计和天文相结合的自主天文导航新方法。在常用卫星轨道动力学模型基础上,引入大气阻力和太阳光压系数模型作为自主导航系统状态方程的一部分,并建立近地空间环境下星载加速度计的测量模型,将其与直接敏感地平均作为导航系统观测方程。设计基于信息融合的自主导航滤波方法,通过对多种导航模式进行数值仿真及结果分析,结果表明所设计方法提高了系统定位精度62.8%和速度精度63.9%,增强了系统可靠性。Directly sensing horizon is a typical autonomous celestial navigation method which is reliable and simply. But its navigation precision is low due to mainly depending on satellite orbit dynamics J2 model and earth sensor. Accelerometer is a typical navigation equipment to measure vehicle linear acceleration. For a satellite moving on orbit, the accelerometer can be used to measure the divergent forces acted on satellite. This paper presents a new method of satellite autonomous navigation based on accelerometer and celestial navigation. The coefficient model of atmospheric drag and solar radiation pressure are proposed as part of autonomous navigation system state equation. The accelerometer measurement equation is established on space environment. The autonomous navigation method and algorithm are designed, and the simulations are made which show that the location precision and the velocity precision can be improved 62.8%63.9% re- spectively by the proposed system.

关 键 词：加速度计 天文 自主导航 信息融合 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]