【作者】 叶兵；

【导师】 吴杰；

【作者基本信息】 国防科学技术大学 ， 航空宇航科学与技术， 2008， 硕士

【摘要】 星光/惯性复合制导方法利用星光矢量的测量信息修正惯性平台的漂移误差,能较大地提高弹道导弹的制导精度和快速发射能力,同时降低武器系统的成本,具有较强的环境适应能力,在机动发射和水下发射的弹道导弹的制导中有着重要作用,目前已经在美俄等军事强国的先进战略弹道导弹中得到了成功应用,结果表明星光/惯性复合制导方法能够显著的提高导弹的命中精度。本论文主要针对单星调平台星光/惯性复合制导方案进行研究,论文主要工作包括以下几个方面:首先,通过对星光/惯性复合制导方法的原理分析,提出了单星调平台方案中斜调平台的方法,建立了星敏感器的测量方程以及平台失准角与初始误差和惯导工具误差的关系方程,分析了导弹的落点偏差随恒星方位的变化规律。数值仿真验证了模型的正确性,结果表明单星调平台方案能够有效提高导弹的落点精度。其次,提出了基于单纯形调优法的最佳星快速确定方法,并通过编制最佳测星方位表来提高其全局搜索能力。考虑到导弹实际发射时强光源对测星的影响和可用恒星的分布,导致理论最佳星无法使用的情况,提出了次佳星的快速确定方法,进一步完善了最佳星快速确定问题的研究,为实际最佳导航星的选择提供了参考。数值仿真结果验证了方法的可行性和有效性。最后,考虑到诸元计算时采用的惯导误差模型可能与实际情况不一致的问题,分析了惯导误差模型对复合制导精度的影响,以及最佳星方位和最佳修正系数在不同误差模型下的适应性,为复合制导方案中误差模型的选择提供了参考。同时,分析了星敏感器安装角对复合制导精度的影响,并采用单纯形调优法对星敏感器的安装角进行了优化,在简单假设下分析了星敏感器最佳安装角的变化规律,相关结果能够为星敏感器安装角的优化选择提供借鉴。论文的研究内容与弹道导弹制导的工程实际紧密结合,所做工作和研究成果能为我国相关武器装备的发展提供理论依据和技术支持。更多还原

【Abstract】 The celestial-inertial composite guidance,which combines the advantages of celestial guidance and inertial navigation,plays an important role in the guidance and control of underwater launched maneuverable ballistic missile.Therefore,this method has been widely actualized in America and Russia.This thesis bases on the single-star scheme with altered platform,and the main contents and innovative points are introduced as follows:Firstly,we obtain the mode of platform adjusting,deduce the model of star-light observation and build equation between error angle of platform and various error source,which based on the analyzing of the single-star scheme with altered platform.In addition, the circle error probability of missile changing with the star azimuth is simulated,whose result shows that the hit precision has been improved efficiently.Secondly,as one solution,we propose a method for quick ascertaining of optimal star,and establish the table of reference azimuth to offer the initial position which supports the searching method with better performance in the whole range.Taking into account that the optimal star may be not available or inexistent in the sky,the ascertaining method of sub-optimal star is put forward,which could provide reference for an optimized choice of navigation star,and consummate the study of quick ascertaining method of optimal star.In the end,the rationality and feasibility of the method are validated by simulation results.Finally,the influence of different inertial error model and fixed azimuth angle of star sensor are considered.The former could be referred to build the inertial error model and set coefficients,while the latter is important for the hit precision of the missile system,which has been proved in the simulation,so we propose optimizing solution based on four dimension simplex method,and furthermore,analyze the regularity of fixed azimuth angle of star sensor in case of simple suppose,that is interrelated results could be used for reference in design of star sensor.In short,all contents of this thesis combine compactly with the ballistic missile project requirements,and large amount of simulations conform the conclusions of the research.It is believed that it could supply theoretical and technological reference for the research and development of interrelated weapon equipment.更多还原