Research On Performance Enhancement Technology Of Micro Inertial Measurement System For High Speed Rotating Rocket

Conventional ammunition urgently needs to be modified to improve its strike accuracy and First-round hit rate,enhance strike effectiveness and improve the operational survival rate of gunners.As a conventional ammunition with huge stockpiles,the guidance requirement of high-speed rotating rocket is more urgent.The reliable measurement of fully autonomous and high precision of the navigation parameters such as the attitude and position of the missile is the primary solution to its guidance transformation.Restricted by the special application environment such as high spin,high dynamic,narrow available space and low cost of high-speed rotating rocket,mature inertial measurement systems in missiles can not be transplanted and applied,while missile-borne test systems using satellite and geomagnetic methods are always difficult to be popularized and applied because of their fatal weaknesses of poor autonomy and reliability.The micro-inertial measurement system based on MEMS inertial device is widely used at home and abroad due to its strong autonomy,high reliability,small size,light weight,low cost,low power consumption,short startup time and good environmental adaptability.It is considered to be the first solution to achieve the guidance reform of conventional missile.However,affected by high-speed rotating rocket's axial rotation and low precision of micro-electro-mechanical inertial devices,existing micro-inertial measurement system's accuracy can not meet the practical application requirements.In view of the mismatch between the range selection of the sensor and the accuracy required by the system measurement caused by high rotation,the research and design of the roll-isolated inertial measurement system developed by NUC in the early stage mainly solves the measurementproblem of adapting to the high rotation of the projectile,but the measurement accuracy and performance enhancements need to be further improved.Therefore,the research on performance enhancement technology of micro-inertial measurement system for high-speed rotating rockets is carried out,and it has important theoretical significance and engineering application to solve the problem of fully independent high-precision and high-reliability measurement of navigation parameters in the process of high-speed rotating rocket guidance transformation.Based on the research of roll-isolated micro-inertial measurement system developed in the early stage of this project,this dissertation systematically studies the performance enhancement technology of micro-inertial measurement system for high-speed rotating rockets based on how to further improve the system precision performance.In-depth research on device-level,component-level,system-level error compensation and accuracy improvement of the roll-isolated micro-inertial measurement system has been carried out.The ground semi-physical simulation and live-fire flight test have been used to verify the effectiveness of the proposed method.Firstly,starting from the improvement of inertial component level measurement accuracy,the static calibration accuracy of traditional inertial components can not meet the dynamic test requirements of missile environment.A dynamic parameter comprehensive identification compensation method for inertial components is proposed,and a mathematical model of dynamic parameter identification is established.Compared with the traditional static parameter identification method,this method compensates for the lever arm error caused by the size effect in the high-speed rotation environment,and significantly improves the measurement accuracy of the inertial component.The effectiveness of the identification method is verified by semi-physical experiments.Secondly,starting from the improvement of system-level measurement accuracy,the roll-isolated micro-inertial measurement system solves the problem of accurate measurement of the missile parameters in the high-rotation environment,different axialproblems are analyzed.A compensation method for axial angle installation error based on grading compensation is designed.Combining the theory with the test,by analyzing the generation mechanism,characteristics and propagation mode of the system axial angle installation error,the axial angle installation error suppression method based on the grading compensation is realized.The ground semi-physical test was verified to improve the accuracy performance of the roll-isolated micro-inertial measurement system.Thirdly,starting from the improvement of device-level measurement accuracy,aiming at the problem of low system accuracy due to the low precision of existing micro-inertial devices,a method for system accuracy performance enhancement based on rotational modulation technology with high dynamics and short time is proposed.The rotary modulation technology is added into the design of the roll-isolated micro-inertial measurement system.The theoretical research and experimental verification are combined.Based on the analysis of the system navigation parameter error model and the error modulation mechanism,the system rotation modulation is elaborated.The specific design and implementation process of the scheme,in which the system focuses on the optimal rotational modulation angular rate determination method and the modulation angular rate error suppression method,and the rotation modulation problem unique to the high dynamic short-time missile borne environment has been studied in depth.Finally,through the ground semi-physical test,the effectiveness of the proposed method to further enhance the accuracy performance of the system is verified.Finally,aiming at the problem of environmental adaptability,the semi-physical experiment of the method proposed in this dissertation is carried out,and the missile-borne test of the system is completed on the platform of rocket.The rocket's axial maximum speed is 16.5r/s and the flight time is 60 s.Within a range of about 15 km,the maximum measurement error of the rolling isolation micro-inertial measurement system is 26.9 meters,and the measurement error of the attitude is less than 1 degree,which verifies the applicability and effectiveness of the system in the missile borne environment.In this dissertation,the high-precision measurement of the high-speed rotating rocket projectile's navigation parameters is carried out,and the performance enhancement technology of the micro-inertial measurement system for high-speed rotating rockets is studied to solve the problem of low precision of the micro-inertial measurement system caused by high rotation and low precision of the micro inertial components.