【作者】 杨会军；

【导师】 张合；

【作者基本信息】 南京理工大学 ， 机械电子工程， 2007， 博士

【摘要】 随着战争形态从机械化向信息化转变，精确制导弹药在战争中发挥的作用越来越重要。敌方空袭的主要目标将是一些重点城市和要地，为了有效地开展城市和要地防空，必须研制一批能适应这些地理环境的武器装备以形成一套完善的陆上防空反导体系。本文研究的对象就是近程反导武器系统中的多管火箭弹引信电磁感应装定系统。本文从引信能量和信息非接触同步传输理论研究出发，对多管火箭弹引信感应装定技术开展了研究，设计了多管火箭弹引信感应装定系统。另一方面，应用加速度修正法在主动段的末端修正火箭弹的飞行时间，提高了炸点精度。本文首先研究了引信能量和信息非接触同步传输理论中的关键技术：引信感应装定技术、高效率功率放大技术和信息双向传输技术，作为本论文的理论基础。根据多管火箭武器系统的特点，选用了火箭弹发射前管内静态电磁感应装定方式来对火箭弹引信进行装定，从装定器电路的设计、引信接收与控制电路的设计、软件模块的设计和引信的小型化、低功耗、抗冲击技术等几个方面详细论述了多管火箭弹引信感应装定技术，该技术是火箭弹近程反导武器系统中的关键技术。研究了基于金属管的引信感应装定系统，提出了基于金属管的引信感应装定系统的概念。通过其与基于非金属管的引信感应装定系统的比较，得出了基于金属管的引信感应装定系统中初、次级线圈间能量和信息的耦合主要是通过电场的结论，分析了存在问题的原因，给出了解决方法，通过试验验证了该方法的可行性。火箭弹初速低、散布大的特点降低了火箭弹的命中概率，应用加速度修正法对引信飞行时间进行自适应修正。在对火箭弹外弹道数学模型分析的基础上，提出了影响火箭弹飞行时间的三个特征参数，经计算和曲线拟合，得出了修正公式。设计了火箭弹引信飞行时间自适应修正电路。抗干扰能力是衡量火箭弹引信感应装定系统的重要指标，本文从电磁兼容的定义出发，分析了电磁干扰传播的机理，接着从硬件和软件两方面介绍了多管火箭弹引信感应装定系统的抗干扰技术，给出了抗干扰的具体措施，设计了多管火箭弹引信感应装定系统的电磁屏蔽。在论文最后，以某多管火箭弹引信感应装定系统为应用平台，对设计的感应装定系统进行了静态试验和动态试验，试验结果表明多管火箭弹引信感应装定系统原理上是正确的，技术上是可行的。更多还原

【Abstract】 With the transformation of war form from mechanization to informationization, precisionguided munition has become more and more important in warfare. The enemy’s air attacktargets are main cities and key area. The ordnance equipment adaptive to the condition must bedeveloped to form a suit of perfect land air defense and antimissile system for main cities andkey area air defense. The research object of the dissertation is the electromagnetic inductivesetting system of multi-tube rocket fuze used in the field of close-in antimissile weapon system.The dissertation started with the theory study of fuze contactless synchronous transmissionof power and data. Research on inductive setting technique of multi-tube rocket fuze wasdeveloped and inductive setting system of multi-tube rocket fuze was designed. On the otherhand, the flying time of rocket was corrected at the end of active phase by accelerationcorrecting method to improve burst point precision.The key techniques of fuze contactless synchronous transmission of power and data theorywere studied first which are fuze inductive setting technique, efficient power amplifyingtechnique and information dual-direction transmission technique. The research items are used astheory foundation of the dissertation.Statically electromagnetic inductive setting method in tube before launching was selectedaccording to thecharacteristics of multi-tube rocket ordnance system. The inductive settingtechnique was introduced in detail from the followed aspects: design of setter circuit, design offuze’s receiving and controlling circuit, design of software module and miniaturization, lowpower dissipation, shock resistant techniques of fuze. The technique is the key technique forclose-in antimissile ordnance system of rocket.Inductive setting system based on metal firing tube was studied and the concept ofinductive setting system based on metal firing tube was brought forward. By comparison withinductive setting system based on nonmetal firing tube, the conclusion was drawn that thecoupling of power and data between primary coil and secondary coil of inductive setting systembased on metal firing tube is mainly transmitted by electric field. Causation of the existedproblems was analyzed and solving methods were presented. The methods were proved to befeasible by experiment.The rocket is characterized by low launch speed and much dispersion, which result in lowhit probability. Acceleration correcting method was applied to correct flying time adaptively.Three characteristic parameters affecting rocket flying time were presented on the basis of the analysis of rocket’s exterior ballistic model. Empirical formula was summarized by means ofcalculation and curve fitting. Flying time adaptive correcting circuit was designed.Anti-jamming capability is the important target to judge the performance of the inductivesetting system of multi-tube rocket fuze. Started with the definition of electromagneticcompatibility, transmitting mechanism of electromagnetic interference was elaborated.Anti-jamming technique of inductive setting system of multi-tube rocket fuze was clarifiedfrom both hardware aspect and software aspect. The anti-jamming measures were presented andthe electromagnetic screen of setting system was designed.The application target of the dissertation is the inductive setting system of multi-tuberocket fuze of a certain caliber. Static experiment and dynamic experiment were done and theresult indicated that the inductive setting system is correct in principle and feasible in technique.更多还原