| 引用本文: | 黄文博,张银辉,师帅,等.运载火箭摄动制导导引系数实时计算方法.[J].国防科技大学学报,2013,35(1):19-23.[点击复制] |
| HUANG Wenbo,ZHANG Yinhui,SHI Shuai,et al.Research on the real-time calculation of perturbation guidance coefficients for the launch vehicle[J].Journal of National University of Defense Technology,2013,35(1):19-23[点击复制] |
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| 运载火箭摄动制导导引系数实时计算方法 |
| 黄文博1,2, 张银辉1, 师帅3, 张为华1 |
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(1.国防科技大学 航天科学与工程学院，湖南 长沙 410073;2.
2.北京系统工程研究所 复杂系统仿真总体重点实验室，北京 100101;3.2.北京系统工程研究所 复杂系统仿真总体重点实验室，北京 100101)
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| 摘要: |
| 对于新型运载火箭，没有相近型号导引系数数据供参考，采用传统试探法计算量大，在制导方案初期论证中不能满足多方案快速计算的需求。在引入理想弹道剩余飞行速度概念的基础上，提出导引系数实时计算方法。本方法对当前实时状态参数和后续飞行段弹道进行了综合考虑，通过数字仿真表明导引精度高于传统常系数导引方法。由于本方法对导引能力进行了预估，因而制导指令不会剧烈变化，易于姿态控制系统的设计实现。同时，由于采用完全解析法，对箭载计算机计算能力要求几乎没有增加，易于工程实现。 |
| 关键词: 运载火箭 摄动制导 导引系数 实时计算 |
| DOI： |
| 投稿日期：2012-08-24 |
| 基金项目:国家863计划资助项目 |
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| Research on the real-time calculation of perturbation guidance coefficients for the launch vehicle |
| HUANG Wenbo1,2, ZHANG Yinhui1, SHI Shuai3, ZHANG Weihua1 |
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(1.College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China;2.
2.Science and Technology on Complex Systems Simulation Laboratory, Beijing 100101, China;3.2.Science and Technology on Complex Systems Simulation Laboratory, Beijing 100101, China)
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| Abstract: |
| The guidance precision of the launch vehicle during the flight stage within the atmosphere is greatly affected by the guidance coefficients of perturbation guidance. However, there is no comparable database for the guidance coefficients selection in the argumentation of a new launch vehicle, which cannot meet the demand for rapid calculation using the traditional test method. A real-time calculation method for the guidance coefficient which considers both the real-time status and the follow-up flight trajectory is proposed, based on introducing the concept of remaining flight speed in the standard trajectory. Through the numerical simulation, it is proved that higher guidance precision is achieved by the proposed method in comparison with the traditional method with constant coefficients. Since the guide capacity was predicted by this method, the guidance instruction do not change dramatically, which contributes to easy design for the attitude control system. Meanwhile, a fully analytical method was developed, so there is no additional calculation requirement for the rocket-born computer, giving rise to convenient engineering realization. |
| Keywords: launch vehicle perturbation guidance guidance coefficient real-time calculation |
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