| 纯惯导中制导误差分析 |
| |
| 引用本文： | 李刚,鲜勇.纯惯导中制导误差分析[J].飞行力学,2007,25(2):50-52. |
| |
| 作者姓名： | 李刚 鲜勇 |
| |
| 作者单位： | 第二炮兵工程学院603教研室,陕西,西安,710025 |
| |
| 摘 要： | 针对洲际弹道导弹,在分析加速度计测量误差和陀螺漂移误差对导弹视加速度影响的基础上,给出了中制导段惯性系统对速度和位置的误差传递模型,对给定的惯组误差系数偏差进行了纯惯性导航制导误差计算。仿真结果表明,纯惯导中制导对洲际导弹落点精度影响比较大。该算法可用于纯惯性中制导方案设计。
|
| 关 键 词： | 惯性导航 中制导 落点偏差 |
| 文章编号： | 1002-0853（2007）02-0050-03 |
| 修稿时间： | 2006-03-132006-12-30 |
Analysis on Error of Midcourse Guidance Based on Inertial Navigation |
| |
| LI Gang,XIAN Yong.Analysis on Error of Midcourse Guidance Based on Inertial Navigation[J].Flight Dynamics,2007,25(2):50-52. |
| |
| Authors: | LI Gang XIAN Yong |
| |
| Abstract: | Taking intercontinental ballistic missiles as objects under research,and based on the analysis of the influence of accelerometer measurement error and gyroscope excursion error on the apparent acceleration,the error transfer model of the inertial system in a midcourse guidance segment for velocity and location is given,and the pure inertial navigation guidance error is computed with the given IMU error coefficient deviations.The simulation result shows that the influence of the midcourse guidance based on the inertial navigation on the missile's impact point is remarkable.The proposed algorithm can be used in the design of pure inertial midcourse guidance scheme. |
| |
| Keywords: | inertial navigation midcourse guidance impact point deviation |
| 本文献已被 CNKI 维普 万方数据 等数据库收录！ |
