摘要
Abstract
For the aircraft in pure inertial navigation condition has the computing problem of self⁃control endpoint distribu⁃tion,a new quantitative analysis research method for SINS(strapdown inertial navigation system)error propagation characteris⁃tic is proposed. The three error angles of the initial alignment are taken as the system state initial value,and the generating navi⁃gation error propagation is taken as the zero input response; the three gyro constant drifts and three acceleration zero offsets in body coordinate system are taken as the system input,and the generating navigation error propagation is taken as the zero state response. The single variable method is adopted to orderly study the error propagation characteristic causing by the above 9 fac⁃tors through navigation simulation,and the analytical expression of the navigation error causing by each variable is obtained by means of polynomial fitting. According to the superposition principle,the analytical expression that the navigation error is changed with time is obtained,in which nine factors effect on it together. Simulation results show this method is feasible,and the position error and attitude error obtained from the analytical expression have high precision. Compared with the actual value, the position estimation error is 0.2″(3σ),and the attitude estimation error is 0.2″(3σ). This method has certain predictive ability for navigation error.关键词
捷联惯导系统/误差传播/自控终点散布/定量分析Key words
SINS/error propagation/self-control endpoint distribution/quantitative analysis分类
信息技术与安全科学
