In order to effectively control the flying attitude and integrity of the rod-type killing element,combined with the rotation mechanism of the rod-type killing element,the influence of the oblique angle on the flying posture of the rod-type killing element was analyzed,and a product design method that can control the flying posture of the rod-type killing element was obtained.Combining the theoretical analysis and simulation calculation of the integrity of the rod-type killing element,by adjusting the pressure distribution and energy distribution on the rod-type killing element,the velocity vector distribution on the rod-type killing element is improved,and the deformation of the rod-type killing element is reduced,the rod-type killing element integrity control method was carried out.The rod-type killing element controllable flying test was carried out to verify the effectiveness of the rod-type killing element flying attitude and integrity control method.

To study the dynamic response characteristics of charge structure under two types of penetration loads,the models of warhead penetrating integral concrete target and multi-layer interval concrete target are constructed respectively.Using LS-DYNA software,the process of dynamic penetrating concrete target is simulated.The difference of impact load,the distribution of plastic deformation area in charge,and the change of the gap between charge tail and shell are compared and analyzed.The results show that the charge mainly bears the axial overload,plastic deformation occurs at the front section of charge for the integral concrete target.For the multi-layer interval concrete target,the lateral overload is greatly increased.The charge tail,the local side of the charge and the corner point between charge and shell become the area with large plastic deformation.Under the condition of penetration,there are repeated contact collision and separation between charge tail and shell.Compared with the integral target,the dynamic collision between charge and shell is more frequent,more intense and lasts longer in the penetration process of multi-layer interval target.

Electrostatic protection is the rigid requirement of missile development.Described the main ways of electrostatic charge deposition in missile;introduced three typical forms of missile electrostatic discharge;analyzed the different effects of electrostatic discharge current effect and electrostatic discharge electromagnetic pulse effect on the sensor radiation signal and system signal-to-noise ratio of missile;studied the effects of electrostatic dischargers on the safety and functional performance of missile;introduced the typical application of electrostatic dischargers,proved the necessity of installing electrostaic protective device in missile.

The height of evaporation duct is an important parameter to represent the duct intensity.The sensitivity of evaporation duct detection system based on Paulus-Jeskes (PJ) model is analysed to the air-sea temperature difference (ASTD) and relative humity and wind speed and sensor errors.Based on the test results,the sensitivity factors affecting the height of the evaporation duct were analyzed.Considering the sensor errors all,the relative diagnostic error of the evaporation duct height are 14.3%、4.22%、8.05% respectively in the stable condition and unstable condition and neutral condition.The parabolic equation of electromagnetic wave propagation in the evaporation duct is solved,and the maximum detection distance in the evaporating duct environment is calculated by radar theory.

In order to solve the problem that energy accumulation cannot be realized effectively due to several kinds of range migration and Doppler migration of high-speed maneuvering target,a coherent accumulation algorithm for moving target with variable acceleration was proposed,which did not need to search parameters. Firstly, made a sequence reversing transform along the slow time of pulse compression echo signal in frequency domain and multiplied them with ones untransformed,which could simultaneously correct linear range migration caused by velocity, third-order range migration and Doppler bending caused by acceleration. Secondly, the second-order keystone transform was used to correct the range bending caused by acceleration.Finally, the slow time signal was regarded as a linear frequency modulation signal, and the coherent accumulation was realized with the biothogonal Fourier transform to estimate the chirp rate. The simulation result proves that this method can effectively realize accumulation and multi-target detection, which is superior than other algorithms.

Aiming at the problem that the vehicle odometer scale factor changes in real time due to the influence of tire pressure and temperature, a method of SINS (strap down inertial navigation system)/odometer integrated navigation based on strong tracking filter is presented. The property that the residual sequences of Kalman filter are mutually orthogonal is used to adjust fading factor adaptively. The strong tracking filter has the ability to track the sudden change state. The average velocity matching method is proposed to eliminate the influence of vehicle vibration and odometer quantization error on integrated navigation. The lever arm error is adopted into the state variables to eliminate the influence of inaccurate lever arm on integrated navigation when the vehicle is turning. The SINS/odometer integrated navigation model is built. The actual vehicle integrated navigation experiment is carried out. The results show that the positioning accuracy of integrated navigation is better than 1‰D.