| 舰载导弹捷联惯导系统原位标定技术研究 |
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| 引用本文： | 戴邵武,贺毅,徐胜红,郭少军.舰载导弹捷联惯导系统原位标定技术研究[J].舰船电子工程,2011,31(9):47-49,59. |
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| 作者姓名： | 戴邵武 贺毅 徐胜红 郭少军 |
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| 作者单位： | 海军航空工程学院,烟台,264001 |
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| 摘 要： | 文章针对舰载导弹捷联惯导系统，提出了一种原位标定方案。此方案在不需要将惯导系统从导弹上拆下来，且无需借助转台等测试设备的条件下，利用捷联基准提供的速度和姿态信息，采用系统级标定法对惯性器件误差进行了标定。计算机仿真结果表明，文中给出的方法可以有效地完成导弹捷联惯导系统原位标定，且标定精度较高，具有较强的实际意义。
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| 关 键 词： | 捷联惯导系统 原位标定 捷联基准 |
In-situ Calibration Technology Approach for the Ship-launched Missile Strapdown Inertial Navigation System |
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| Dai Shaowu He Yi Xu Shenghong Guo Shaojun.In-situ Calibration Technology Approach for the Ship-launched Missile Strapdown Inertial Navigation System[J].Ship Electronic Engineering,2011,31(9):47-49,59. |
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| Authors: | Dai Shaowu He Yi Xu Shenghong Guo Shaojun |
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| Institution: | Dai Shaowu He Yi Xu Shenghong Guo Shaojun(Naval Aeronautical and Astronautical University,Yantai 264001) |
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| Abstract: | According to the ship-luanched missile SINS,a in-situ calibration scheme is presented in this paper.This scheme can calibrate inertial instrument errors with the velocity and attitude information provided by stapdown attitude and heading reference system,and it dosen't need the test equipment such as turntable and dismantling the SINS from missile.The simulation results show that the new method can calibrate avaliably the errors of missile SINS with acceptable precision and therefore it has practical signif... |
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| Keywords: | strapdown inertial navigation system in-situ calibration strapdown attitude and heading reference system |
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