With the heat transfer characteristics and mechanical properties of various parts of the nozzle, and the particle phase considered, the thermal deformation variation of the nozzle at high temperatures is analyzed in the paper. The results show that the structure of the nozzle has a great influence on the temperature at the fluid-solid interface and the internal interface; the total deformation and the axial deformation of the nozzle are gradually increased along the axial direction, and the value maximizes at the tail, the radial deformation increases first, then decreases and increases again along the axial direction and reaches the maximum at the tail; the twophase flow has a great influence on the deformation of the nozzle, which is an increase in the deformation.

This paper combines the development status of embedded systems and the characteristics of embedded software for missiles, analyzes the reliability weakness of the missileborne embedded software in order to improve its reliability, and explores the failure modes that may affect the reliability of the missileborne embedded software and classifies them. The development of failure mode and effects analysis (FMEA) is briefly described, and a software and hardware integrated FMEA (S&HFMEA) method for missleborne embedded systems is proposed. Relying on the fivedimensional system of missileborne embedded software reliability guarantee, it uses the S&HFMEA method to analyze the reliability of missileborne embedded software, and explains the principle, implementation process and key points of S&HFMEA. The results show that S&HFMEA has certain effectiveness and practicability for improving the reliability of missileborne embedded software.

A numerical simulation model is established by CFD method for quad tilt rotor aircraft in conversion state. The method can be used to calculate and analyze the aerodynamic characteristics. Firstly, based on the momentum source method, the lift force and power of the isolated rotor are calculated and compared with the experimental results, and the effectiveness of the momentum source method is verified. Then the aerodynamic interference calculation model of the whole aircraft is established, in which the rotors are represented by momentum source and divided by structured grids, and the unstructured grids are applied to the fuselage, wings and nacelles. Finally, the aerodynamic interference characteristics of the rotors and the wings in conversion state are analyzed, some aerodynamic interference laws are obtained and the aircraft overall design is supported.

In this paper, the effect of air launched decoys on the terminal guidance of seekers is analyzed. The echo power and angle error influenced by air launched decoy in the terminal guidance process are modeled. The influence of air launched decoy on the seekers angle tracking is analyzed. By changing the number and distance of air launched decoys, the influence of air launched decoy on the terminal guidance command is simulated. On the one hand, the results of this paper can be used to study the use strategy of air launched decoys, on the other hand, it can be used to provide theoretical support for seekers against air launched decoys.

This paper describes the technical requirements of passive positioning，constructs the state equation and observation equation of singlebase angular measurement & passive positioning system, theoretically analyzes the principles of different nonlinear filtering methods such as recursive least square method, extended Kalman filter method，unscented Kalman filter method, finite difference extended Kalman filter method, as well as adaptive extended Kalman filter method, and gives the recursive algorithm model. Combined with the specific simulation examples, the simulation analysis is carried out from the aspects of initial value estimation error, measurement error, sampling period and observation noise, and the comprehensive evaluation results of different filtering algorithms are given.

In this paper, a classical twocircuit overload autopilot is taken as the research object. The analytical solutions of the design parameters are taken as the initial values. The relative stability of the system is used as the constraint condition. The transition process of the system response is used as the optimization target. A multiobjective optimization model for autopilot parameters with exclusion of initial value interference is established, and a parameter optimization of a typical autopilot is carried out employing genetic algorithm. The simulation results show that the multiobjective optimization model and algorithm used in this paper can improve the dynamic characteristics of the autopilot while maintaining the stability margin of the system, and greatly improve the design efficiency. The practice is preferable to the parameter design of the classical twocircuit overload autopilot.

Aiming at the problems in the defense of near-space high-speed vehicle, this paper studies the motion state estimation algorithm of this kind of vehicle. First, the target maneuvering model is analyzed, then the radar observation model is established, and the fusion algorithm of SRCDKF based on interaction multiple model (IMM) is studied. Finally, based on the typical jumping reentry trajectory of near-space high-speed vehicle, the target tracking error curves of different filtering algorithm are given through simulation, and the effectiveness of IMMSRCDKF filtering algorithm for near-space high-speed vehicle information estimation is proved.

At present, Field Programmable Gate Array (FPGA) is mostly used to implement one-dimensional multiple signal classification (MUSIC) algorithm. In order to make MUSIC algorithm more suitable for direction of arrival (DOA) estimation of incident signal in real environment, this paper uses FPGA to implement the spectrum peak search of twodimensional MUSIC algorithm. The experiment is arranged as follows. First, reasonably design the parallel structure of each step to improve real-time performance. Second, use a two-step search to reduce computational amount and complexity. What's more, reduce resource consumption through module reuse and use pipeline design to improve computational efficiency. So, the estimation accuracy is met and the spectrum peak search time becomes less. The simulation results show that the hardware implementation scheme takes 3.77 μs to realize twodimensional spectrum peak search with the estimation accuracy of 1 degree on FPGA chip at 100 MHz. The main advantages of the twodimensional spectrum peak search architecture include fast speed, high real-time performance and high engineering application value.

The results are multi-valued and unstable in the application of traditional subjective evaluation method in radar antijamming performance evaluation. To solve these problems, a radar anti-jamming performance evaluation method based on AHPcloud model is proposed by combining analytic hierarchy process (AHP) and cloud model method. The method takes the weight obtained by AHP as the input, through backward and forward cloud generator, to produce weight cloud of evaluation indexes. Finally the result cloud is obtained by multiplying with the five radar target values. The radar evaluation score and rank are obtained through cloud similarity measurement. The result of an example shows that the method is accurate and robust. 

Tracking targets stably and precisely is the prior task of the accurate tracking radar. For the problem of instability of tracking filtering in the environment of nonGaussian noise and abnormal values caused by multitargets crossing, this paper starts from target tracking datas residual statistic property analysis, calculates the residual value by iterative ways, comes up with a method doing the trajectory filtering and controlling the target data correlation gate according to the residual value，and eliminates the abnormal values in real time. The simulation results show that the method is better than the compared one in terms of trajectory stability and precision with little computation increase.

Simulation has become the main means of equipment effectiveness evaluation. For the standardization of evaluation, a view-based simulation evaluation process of equipment effectiveness is designed. Firstly, for the key points of evaluation, the simulation evaluation views of equipment effectiveness are given. Secondly, the relationship of views is discussed and the views are compared with DoDAF. Then, a view-based simulation evaluation process of equipment effectiveness is designed, which lays the foundation for the development of equipment effectiveness simulation evaluation. Finally, the effectiveness evaluation process is verified through an example.

The operational mode of anti-TBM in boost-phase based on airborne platform is researched in this paper. The ability of anti-missile is detailed in terms of airborne platform, time sequence and process of action, slant range and velocity of interception, and then, the interception ability of anti-TBM in boost-phase based on airborne platform is simulated against typical ballistic missile target. The research of this paper serves an important reference to the design of airborne anti-missile.

In order to overcome the influence of sensor system error and random measurement error in correlation process, this paper presents a twodimensional track correlation method. The method establish functional relation to explain the influence of sensor system error and random measurement error on position difference between tracks which are formed by one target in different sensors. The first threshold is established based on the range of position difference. And the second threshold is formed based on the range of variance for position difference of a sequence in continuous moments. Simulation results show that the method has higher correct correlation rate than traditional double-threshold correlation.