| 运载火箭全捷联惯性/星光复合制导研究 |
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| 引用本文： | 张力军,张士峰,钱山.运载火箭全捷联惯性/星光复合制导研究[J].固体火箭技术,2011,34(5):553-558. |
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| 作者姓名： | 张力军 张士峰 钱山 |
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| 作者单位： | 1. 国防科技大学航天与材料工程学院,长沙,410073
2. 中国西安卫星测控中心,西安,710043 |
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| 基金项目： | 国防科学技术大学优秀研究生创新项目(S100104) |
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| 摘 要： | 全捷联惯性/星光复合制导是运载火箭空间快速响应发射的重要途径.针对捷联惯性制导系统中初始定位定向误差、初始调平对准误差及惯性器件漂移等3类主要误差因素,建立了运载火箭的数字平台基准偏差模型和导航误差模型,并提出了一种双星修正策略方案.数值仿真分析了各误差因素对捷联惯性导航精度的影响,并进一步验证了该复合制导方案的可行性...
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| 关 键 词： | 空间快速响应 惯性制导 星光制导 复合制导 双星修正 |
Study on strapdown stellar-inertial integrated guidance system for launch vehicle |
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| ZHANG Li-jun,ZHANG Shi-feng,QIAN Shan.Study on strapdown stellar-inertial integrated guidance system for launch vehicle[J].Journal of Solid Rocket Technology,2011,34(5):553-558. |
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| Authors: | ZHANG Li-jun ZHANG Shi-feng QIAN Shan |
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| Institution: | ZHANG Li-jun1,ZHANG Shi-feng1,QIAN Shan2 1.College of Aerospace and Material Engineering,National University of Defence Technology,Changsha 410073,China,2.China Xi'an Satellite Control Center,Xi'an 710043,China) |
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| Abstract: | In this paper,a strapdown stellar-inertial integrated guidance system was presented to satisfy the requirement of space rapid reaction for launch vehicle.The major errors derived from initial localization and orientation,initial attitude alignment and the drift of inertial sensors were analyzed.Both error angle model of digital platform and navigation error model were established,and a dual star correction scheme was presented subsequently.Numerical examples were given for the analysis of the influence of e... |
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| Keywords: | space rapid reaction inertial guidance stellar guidance integrated guidance dual star correction |
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