摘要
研究了基于"速度+方位角"匹配的弹载捷联惯导系统的传递对准问题。首先介绍了方位角测量偏置产生的原因,以及与方位失准角的关系。推导了主、子惯导方位失准角的计算方法,并对方位失准角估计进行了仿真试验。在此基础上分析建立了传递对准卡尔曼滤波方程,并对弹载捷联惯导系统的传递对准进行了仿真。仿真结果表明,该"速度+方位角"匹配的捷联惯导系统精度控制在0.05°内,能够满足空射制导武器初始对准精度的要求。
SINS transfer alignment based on the ＂Speed ＋ Azimuth＂ matching is studied. The causes for the azimuth measurement bias as well as its relationship with the azimuth misalignment angle are firstly introduced. Calculation method about azimuth misalignment angle of the primary sub-INS is derived, and azimuth the simulation experiment is estimated. Based on misalignment in this analysis, we established the transfer alignment Kalman filtering equation, and simulated the transfer alignment of missile carried SINS in VC ＋ ＋. Through the simulation we found that the accuracy of SINS with ＂Speed ＋ Azimuth＂ matched is controlled within0. 05 °, which can meet the requirements for initial alignment accuracy of air-launched guided weanons.
出处
《飞行力学》
CSCD
北大核心
2012年第5期428-431,435,共5页
Flight Dynamics
基金
航空科技基金资助(20115189003)
