Firstlythe definition of detectability was presentedwhich is a new physical quantifier used to describe the difficulty level for detecting a target.Analysis was given to the influence of target flight altitude and velocity on its detectability in infrared bandand the regularity of detectability changing was obtained based on a mount of simulating calculations.The analysis result shows that:1) Under normal weather conditionthe active detecting range will increase by 5 km for the same infrared detector when the speed of target improves by 0.5 Mach;2) The detectability of a target will increase with the increasing of its flying height when the height is under 8 kilometersdecrease with the height when it is beyond 10 kmand reach the max at the height of 8 to 10 km.

The gravity gradient data is used in the navigation system through the Unscented Kalman Filter (UKF) to study the feasibility and superiority of the gravity gradient aided navigation system.The paper first analyzes how to simulate the gradiometer signal with the given gravity gradient map dataand presents a method that uses an interpolation method first and then adds noise to this data with a final lowpass filterer operation.According to the necessity of UKFthe system dynamics of the gravity gradient aided navigation system is providedand how to use the UKF in this model is described.At the end of the paperthe simulation analysis is given to the gravity gradient aided navigation systemmainly through the comparative study of no external aided and the gravity gradient aided navigation systemto demonstrate the availability and feasibility of applying the gravity gradient data to the navigation system.

The incremental dynamic inverse robust control law was designed for hypersonic reentry vehicle.Firsttwo loop control modelsfast and slowwere established for the hypersonic vehicle.The reentry foreign strong disturbance was estimated through nonlinear disturbance observer for feedforward compensation.Thenthe incremental dynamic inversion control laws were designed respectively for the fast and slow loop through the state rate feedback.Nonsmooth control lawwith high antiinterference ability and fast convergence speedwas used to improve the system robustness.Finallythe linear trackingdifferentiator was introduced to solve the problem that the state rate required by the incremental dynamic inversion control law cant be measured.The simulation verifies the effectiveness of the proposed algorithm.

Aiming at subjective weight determination of warship formation in overthehorizon antimissile threat estimationwe established a threat estimation index systemand built up the optimal index subjective weight determination models of linguistic typeutility typeorder relationship typefuzzy preference relationship typemultiplicative preference relationship type and interval utility type information given by the experts.The subjective weight determination was then transformed into a multiobjective constraint problemand the normalization coefficients for the index weight information matrices were obtained.Thenlinear weighting method was used to turn it into single objective constraint modelsand the index subjective weights were obtained.A numerical example was given to illustrate the method.The result demonstrates that this method can concentrate multitype index weight informationand can obtain warship formation overthehorizon antimissile threat estimation index subjective weight precisely.The method is easy for engineering realizationand provides a theoretical support for the design of overthehorizonantimissileassistant decisionmaking system for warship formation.

A sliding mode control law is presented for nearspace vehicle (NSV) with backlashlike hysteresis to eliminate the influence of the input hysteresis.Firstlythrough analysis of backlashlike hysteresisthe hysteresis was decomposed into a certain linear part and an uncertain nonlinear part with known upper limit.Thenthe sliding mode control law was designed by tracking the desired output trajectory to eliminate the influence of the hysteresis.And the stability of the system was proved by using Lyapunov method.Finallythe control law was applied to NSV attitude control.The sliding mode control law is presented for NSV with backlashlike hysteresis.Simulation results illustrate that the proposed control scheme can achieve effective performance.

A novel adaptive integral sliding mode tracking controller is proposed for a morphing aircraft.The adaptive compensation algorithm is used to dispel the effect of parametric uncertainty on system stability.The perturbation can be projected into the matched and unmatched spaces.The additional integral term in the sliding surface reduces the steady state error and also provides one more degree of freedomwhich minimizes the Hinfinity norm of unmatched perturbation.It is shown that the stability of the closedloop system can be guaranteed with the proposed adaptive sliding mode control strategy.The feasibility of designed control scheme is demonstrated by a morphing aircraft model application.

The energy coupling of effects of High Power Microwave Weapon (HPMW) on radio fuze is mainly antenna coupling.The induced voltage of high power microwave on fuze antenna was chosen as criterion for the damage simulation model.Parameters of fuze electric components and circuits were also taken into accountwhich could be used for evaluating the destruction effect of the HPMW.The simulation results show that:within height of 1000 metersthe 1 GW coincidence HPMW can achieve the voltage to destroy the receiver and cause radio fuze failure.The result also shows that the method is feasible.

Image segmentation is an essential step in image analysis.A novel model was proposed for unsupervised segmentation of viewers attention object from natural images by using salient object edge points and localizing regionbased active model (LRAC).The salient edge points were firstly detected by the color boosting Harris detector.The core saliency map was then proposed to obtain the foreground seeds from the salient edge points.Thenthe salient object edge points were determined by the foreground seeds.Finallythe salient object edge points were employed as the seeds of convex hull to generate the initial contour for our automatic object segmentation system.Extensive experiments results on a large variety of natural images prove that the proposed model can provide satisfactory segmentation performance.

In order to improve the localization accuracy for Unmanned Aerial Vehicle（UAV）in flighta localization algorithm is proposed based on machine vision.This algorithm can make UAV fly in the environment where Global Positioning System (GPS) signal is disturbed or is in failure.First of alltwo modified coordinate transformation algorithmsTrf1 and Trf2were obtained based on ScaleInvariant Feature Transform（SIFT）KDTree search image matching algorithm and the transformation between coordinate systems.With the help of Trf1the first coordinate transformation algorithmground coordinates of the target matched points were calculated out to build up a map of the flight environment.The second algorithmTrf2could calculate the realtime locations of UAV.Subsequentlythe localization algorithm in UAV flight was obtained based on the two modified coordinate transformation algorithmsand experiment was carried out based on the algorithms.Experiment results show that errors of calculated UAV positions are within 12 cmwhich demonstrates the accuracy of this method.

In order to compensate for the human visual limitations in energyspectrum and resolution under weak light environmentthe avalanche photodiode (APD) was used to establish a photon counting imaging experimental platform.Under the condition that the set ambient light illumination was 104 lxthe sampling periods were respectively 10 ms2.6 ms and 780 μsthree groups of the photon counting image sequenceswhich could demonstrate the target characteristicswere obtained.The technique of multiframe accumulation was applied to the target detection according to the different detection requirements.The appropriate number of the frames can be selected to ensure higher frame frequency.

In view of the shortage of redundancy when using quaternion to describe attitudethe Modified Rodrigues Parameters (MRPs)which is a threedimensional independent vectoris put forward for attitude estimation.The attitude estimation algorithm based on Square Root Unscented Kalman Filter (SRUKF) is established with the outputs of accelerometer and magnetometer as observation vectors.In order to avoid the accelerometer and magnetometer interference by environmentan expert system is introduced to the SRUKF algorithm.The expert system is designed to estimate the information of acceleration and magnetic field to adjust the measurement noise matrix.The experiment results indicate that the algorithm successfully makes the static attitude accuracy less than 0.05°and static heading accuracy less than 0.1°.And it makes the dynamic attitude accuracy less than 0.5°and dynamic heading accuracy less than 1°.The optimization effect is improved significantly.

Morale has the nature of complexityemotionality and unpredictability.It is difficult to construct a model of the morale that can reflect the complex interaction using traditional simulating method of operation.As a resultmorale in the combat is hard to be explored and evaluated.This paper researches the morale from the sociology theoryincluding its generation and propagationand proposes a hybrid simulation method that combines System Dynamic (SD) with MultiAgent System (MAS) method.MicrocosmicallyMAS method is used to reflect the interaction among fighters and the course of affecting morale:MacrocosmicallySD method was used to reflect the influence of the tactical psychology on morale and whole war in the countercombat process.Moreovera hybrid simulation experiment platform based on Netlogo is proposedso that microscopic and macroscopic experimental data and conclusion can be utilized mutually.It is beneficial to the research on laws of the morale in war and solve the modeling and evaluating of the morale in combat.The experiment shows that it is an effective method.

When rate limiter is saturated in flight control systemtime delay would occur.The pilot induced oscillations (PIO) may come into being on condition that the pilot operates incorrectly.A simplified model of rate limiter was establishedand the switching suppresser designed by using logical conditions method was anatomized.The response properties of the openloop frequency and phase compensation ability of the suppresser were studied by using describing function.The openloop response properties of the suppresser to sine wave and bias input were discussed.A switching suppresser to prevent PIO was proposedand a mathematical model of closedloop aircraftpilot system with the derivative switching suppresser was set up.The step tracking tasks were simulated to study the performance the switching suppresser and DASA anticipatory control suppresser.The simulating results demonstrate that derivative switching suppresser effectively reduces the possibility of PIO.

Micromotion kinetics modeling is a key and fundamental issue of ballistic target microDoppler feature research.At presentthe modeling techniques based on Euler anglesEulerRodrigue formula and homogeneous coordinates have some problems such as “gimbal lock”singularity and computational complexity.Quaternion method can express arbitrary rotation in 3D space intuitively and overcome shortcomings of the existing methods by using 4 values instead of the 9 of the corresponding matrix.The quaternion based precession and wobbling microDoppler frequency expressions of ballistic targets are presented after derivation.It simplifies the calculation of target microDoppler in that reducing matrix operations.The simulation results prove that the quaternion based micromotion modeling method is valid and provides a scientific basis for microDoppler extraction and recognition of ballistic targets.

Comprehensive system error estimation on mobile platform sensor registration is a difficult problem.In order to estimate the comprehensive system error for the mobile platform of shipsthis paper presents two methods using the highprecision GPS information obtained through cooperative target.In the first methodan observation model was built up to decouple error component in equivalent error model based on itand the approximate equivalent value was used to estimate each component of comprehensive system error.The first method can overcome the shortage of equivalent error model.In the second methodthrough analyzing the effect of error component on the location precision and linearizing the influence functionthe observation function was established and estimation of comprehensive system error was implemented.Simulation is made for two situationsand the simulation results demonstrate that each method has its advantages and disadvantages.On the wholethe performance of the second method is better.The position precision is improved greatly after error correction using the estimation results of these methods.

In realtime networkstraffic characteristic with burstiness constraints is one of the key QoS (Quality of Service) factors in the worst case.Using timed automata to model the traffic can reflect the uncertainty under the constraints by arrival curves.We adopted hardware description language to describe timed automata formal modelsand studied correspondence between hardware logic and timed automata model.The method took the advantages of programmable array chipsfully represented the concurrent behaviors between timed automataand then implemented the hardwareintheloop testing and detection.With such a methodwe simulated the virtual link traffic generation in realtime network.Some typical test results indicated that the model can constrain the traffic characteristics of virtual linkwhich proves the feasibility of the hardware implementation method.

This work specifically studies a transformation of morphing aircraft from loitering to dashing.The nonlinear dynamic functions of the morphing aircraft in the different morphing process are derived.By considering the nonlinearity and uncertainties of parameter caused by the variable structurean adaptive attitude control law was designed for two flying models of morphing aircraft.The feasibility and effectiveness of this method were proved based on Lyapunov theory.The flight environment system for simulation was established based on VC++ and OpenGL.And data from Simulink was successfully passed to the simulation system based on VC++/Simulink program.The simulation results shows that the technologies proposed provide an effective way to simulate different flying procedure of morphing aircraft.

In order to make the observer survey intuitively the realtimestereoscopic situation among spacesky and groundan realtime and visualized display system is proposedwhich combines effectively 2D and 3D situation display.This paper describes the requirementsoverall functions and hierarchical structure of the system in detail.Several key technical issues in the system design are discussed：achieving realtime data operation with the AgConnect API interface functions；solving problems such as texture map that can be loaded in 3D model with the help of various means；designing and developing abnormal data preprocessing program by use of a sliding window detection method；and realtime tracking dynamic objects based on the principle of coordinate transformation.This system was tested and applied in a certain information warfare equipment against training successfullywhich shows its superior performance and wide application prospects.

For ADFX network with virtual Link mechanismbandwidth resources can be allocated and isolated effectively so that the realtime performance of AFDX network is greatly improved.In this papera method for testing delayjitter in AFDX network based on virtual links was proposed.The theoretical value was obtained through network calculus theoryand was compared with the actual test value thus comprehensive evaluation was realized and the credibility of analysis results was enhanced.

An adaptive temporal error concealment method is proposed based on H.264/AVC in order to efficiently estimate the motion vectors with lost macro blocks.The method makes full use of the motion vector information of the blocks around the lost blocksand can adaptively choose different algorithms to conceal errors according to the division.Experiments show that the visual quality of corrupted video is efficiently improved with the proposed method.

The rotating platform and the antennaarray are two main parts of RadioFrequency (RF) Simulation Test System.The error of RF Simulation Test System is represented by the angle simulation precision of the antennaarraywhich may be influenced by the error of the rotating platform and the incoincidence between the rotating platform center and the spherical center of the antennaarray.The mathematic models of static and dynamic error of the rotating platform are analyzed and calculated out based on the operational principle of the antennaarray and motion performance of the rotating platform.Finallythe simulation results about rotating platforms effects on the angle simulation precision of the antennaarray angle are presented.

In multitarget trackingthe measurement noise is not an absolute Gaussian distribution because of clutter and the undulation of RCS.A model of noise was studied based on asymptotic stationary processand a confidence function was introduced.A method that could feed back the confidence degree of the measured value to the filtering process was proposed.By correcting the gain matrix and covariance matrixthe effect of measuring noise fluctuation on filtering was reduced.The method could enhance the ability of the noise compression and restrain the peak error.Simulation result verifies the validity and feasibility of the method.

To solve the problem of the stealthy object detectionthe judging inequality of radar detection based on the bistatic MIMO radar equation was utilized to make a research on the radars detection coverage to stealthy object.Taking the F117A fighter as a typical stealthy objectthe detection area was divided by the grid splitting algorithm.By calculating the bistatic radar across section of the stealthy object at each pointthe object detection coverage for bistatic MIMO radar could be obtained.The relationship among the detection coveragethe baseline lengththe number of the transmitting antenna and phase coherent accumulation was determined by experiment.The experimental result shows that the bistatic MIMO radar is superior to the conventional bistatic radar on detection range to stealthy target.