SINS/GPS/TACAN机载综合导航定位系统设计

在现代空战中，捷联惯性导航系统（SINS）、全球定位系统（GPS）和塔康（TACAN） ，单独利用各导航信息都存在着弊端。为此，提出了3种导航源综合的导航系统设计方案。 信息融合技术采用广义联邦滤波技术来完成，状态矢量为导航参数误差，并建立准确数学模 型。各个子滤波器（局部滤波器）采用间接滤波方式工作，完成状态矢量局部估算；主滤波 器（全局滤波器）进行子滤波器的公共状态矢量融合和时间更新，输出可靠、准确的导航参 数误差的全局最优估计量。利用全局滤波输出作为闭环负反馈校正SINS导航源，实现动态校 正（比力方程积分初始条件重新设置）、动态对准（姿态矩阵微分方程积分初始条件重新设 置）和动态标定，从而提高了组合导航系统性能。系统试验表明，SINS/GPS/TACAN综合导 航定位系统获得了良好的定位精度。

Design of an Airborne Integrated Navigation and Location System Based on SINS/GPS/TACAN

In modern air warfare,independent use of strap down inertial system(SINS), glob al po sition system(GPS) and tactical air navigation system(TACAN) has disadvantages. In this paper the airborne integrated navigation system is proposed based on th ese three navigation equipment . The information fusion is accomplished by using federated filtering technolog y, choosing the error of navigation parameter as the state vector, and construct ing the mathematics model of state equation about integrated system. Each of sub filters gains an estimation of state vector by using work method of indirect f ilter.Primary filter accomplishes the fusion of public state vectors about sub filters and time updating, and outputs the credible, precise and optimal estim ation of navigation parameter error. Using the output of the whole filter as mea ns o f closed loop of feeding back, correct inertial navigation parameter, dynamic calibration(reinstalling the integral initial condition of specific force equat ion) ,dynamic alignment(reinstalling the integral initial conditions of attitude matr ix differential equations), dynamic demarcation are realized, so that the performa nce of integrated navigation is improved. The experiment results show integrate d navigation system based on SINS/GPS/TACAN can gain better location accuracy.