The Inductive Setting Technique Of Multi-tube Rocket Fuze And Flying Time Correcting Method

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.