The helmet-mounted sight/display system (HMSDS) is a typical man-machine interaction system that has significant advantages in utilization. Since the HMSDS is a complex head-borne vision equipment, it may make the users feel uncomfortable or even cause danger to them if it is not designed properly. In this paper, the operational tasks of HMSDS are analyzed, the existed problems of human/system performance are pointed out, and a man-machine interaction model is proposed. The methods for man/machine perfomance design and key factors that should be taken into consideration are presented in the end.

With the development of researches on out-of-sequence measurement problem, attentions have been given to the out-of-sequence track (OOST) fusion problem existed in distributed system.Aiming at the out-of-sequence track fusion problem in distributed system with feedback, we put forward a fusion algorithm based on recursive fusion NALE mechanism.In fusion center, the local estimation arrived out-of-sequence was processed recursively.And at the end of global fusion period, the global estimation was fed back to the local processor.Theoretical and simulation results indicate that the new algorithm can effectively deal with OOST problem, and can improve the stability and real-time performance of the system.

Target allocation is an important job in cooperative control of multiple UAVs.The mathematic model for multi-UAV cooperative target assignment was established and a multi-UAV target assignment algorithm based on the satisficing decision-making theory was given.A satisficing set was proposed according to the estimated benefits and costs when each UAV complete the task.A satisfied allocation result was obtained by establishing a reject function and a selection function. Numerical simulations were made under the Matlab environment.The simulation results show that the developed satisficing allocation decision-making algorithm is effective for the cooperative task allocation of the UAVs.

Throughout the last decade, more and more attentions have been focused on the reliability of flight system in the aircraft control.In this paper, a high-reliability attitude stability control system was designed for a novel VTOL unmanned aerial vehicle (UAV), a quad-rotor aircraft.In order to compensate for the influence of the actuator fault to the aircraft control, an active fault-tolerant control system was introduced into the attitude control system.This scheme was composed of two components:A robust fault detection module using the model-based observation approach and a reconfigurable controller.The robustness and stability of the fault-tolerant control scheme were also analyzed theoretically.The availability of the proposed scheme was verified through numerical simulation.

To solve the problems of nonlinearity and obviously changed manipulating efficiency in flight of UAV, a longitudinal control law is designed for a Flying-wing UAV, which is the integrating of Robustness Servomechanism Linear Quadratic Regulator(RSLQR) and L1 adaptive control method.The controlled variable is chosen as C*, which is a combination of longitudinal acceleration and pitch rate.The baseline controller is based on RSLQR method to fit the control requirement of the UAV.The controller is augmented by L1 adaptive output feedback structure to maintain the desired close-loop system characteristics in the presence of the aerodynamic uncertainties and the significant change of the elevator coefficient caused by the transformation of flight state.This paper summarizes the theory, the design, simulation testing and flight test results using a RSLQR-L1 method, which validates the performance and the robustness of the designed control system.

Selecting optimized action strategy can make the task coalition evolve towards the expected operation effect.Considering that the influence strength of events/actions is not consistent in different time horizons, a time-varying Dynamic Influence Nets (DINs) was utilized to model the action strategy optimization in the process of task coalition evolution.Based on causal strength logic, the consistent condition of probability propagation was given and the influence constant was calculated out.Simulation was made to an aerial attack campaign case.The result shows that the action strategy optimization considering the variation of influence constants can improve the capability of cause and effect modeling.

The radar with high sampling rate always fails to track a slow moving target when using nearest neighbor data association under the clutter background, since its measuring error is much greater than the real moving distance of the target.To improve tracking precision to the slow moving target, an adaptive range nearest neighbor data association algorithm is proposed.This method uses the location information of the state vector to calculate the real range instead of calculating the statistical range of prediction center and measurements, the tracking precision is improved by reducing the missing association probability.The real range gate size relates to measuring error and the distance of radar and target.Simulation results show that the algorithm can enable the radar with high sampling rate track the low-moving target effectively with relatively high precision.

Considering that the path planning research generally focused on theoretical study and the plan efficiency is not high, we analyzed the multiple restrictions for path planning from the point of engineering application, and proposed a rapid path planning method under multiple restrictions.An engineering search strategy was designed based on the limited discrete changing idea of course angle.The flow path of A* algorithm was improved.The minimum binary heap in structure list way was applied to manage the OPEN list and CLOSED list, which improved the search efficiency of the algorithm notably.An optimization method deleting some path nodes was proposed.Simulations were carried out respectively on traditional algorithm and the improved algorithm.The results indicate that the plan efficiency of the later can be improved considerably under the condition of multiple restrictions.

Considering the various errors existed in the data from ADS-B surveillance system and the flight characteristics of low-altitude aircraft, a new algorithm for track monitoring based on ADS-B was proposed.The decision threshold was set up to achieve multi-mode switching for aircraft.The advantage of Kalman algorithm was exploited in the steady phase and the smooth and stable performance of RMIMM was used in the maneuvering phase.Comprehensive performance of the algorithm is superior to that of the conventional monitoring algorithm based on Kalman filtering.The shortcoming that the response of Kalman filter is inadequate when processing the high frequency signal is overcome while the good tracking performance of it when processing the low frequency signal is kept.Besides, the multi-mode switching based on different modes is achieved, and the future mode can be predicted rapidly.

Because of targets complicated movement, conventional ISAR imaging algorithm can not meet the demands of maneuvering target imaging.On the basis of analyzing the echo’s non-linear Doppler shifts caused by maneuvering target movements, a new ISAR imaging method based on AOK TFR is proposed.The instantaneous target images can be obtained by calculating the AOK TFR of different range bins.Compared with the classical time frequency distribution, the AOK TRF has no cross item interference from multi-component signals.Meanwhile, the instantaneous Doppler frequencies of echoes in range bins are estimated.According to the estimated Doppler frequencies, imaging time can be selected.The simulationd results demonstrate the validity of the proposed method.

In order to solve the problem that the estimation accuracy of ordinary federated filter is insufficient when processing the actual targets, especially the maneuvering targets, a new federated filter is proposed based on interacting multiple model(IMM) algorithm.The IMM algorithm is introduced in the federated filter instead of Kalman filter as a sub-filter to prevent the divergence in nonlinear situation and enhance the estimate accuracy and stability.The simulation results show that the estimation error of the federated IMM filter is continually limited to a certain bound while processing the maneuvering targets, which reveals its fine stability and fault tolerance.

In order to establish a more realistic airdrop kinematics model, the drag direction was presented and the interaction force between cargo and airplane were deduced.Many influence factors such as rigid body good, extraction parachute and the angle of cabin floor were considered in the model.The 0-1 control variables were designed for time-shared control of the cargo at different airdrop phases.The modeling process was simplified, which could simulate the different airdrop modes.A simulation platform for cargo airdrop system was designed, which integrated such functions as airdrop parameter setting, simulation, analysis and display.At last, a quantitative analysis was made to the dynamics response error of the proposed mathematical model and the tradition model through simulation.

Laser transmission in the atmosphere is influenced by the atmospheric turbulence and other factors, which may degrade the laser beam quality and the operational effect of the laser.The low spatial frequency part usually deviates significantly from theoretic value generated by power spectrum method.To solve the problem, we used H-V model to establish the model of atmospheric turbulence effects on laser at day and nigh, and the algorithm of Zernike to generate the phase screen of atmospheric turbulence.The result of simulation of atmospheric turbulence meets the Kolmogonov statistics law.The result shows that low-frequency part of atmospheric turbulence can be well reflected by the algorithm of Zernike, and the high-frequency part can also be reflected finely with the increasing of order of Zernike.The system parameters of ABL and ATL of USA were used to simulate the distorted wavefront of high-power lasers atmospheric propagation.The result shows that the maximal P-V value of turbulent phase screen of ATL is about 3.5λ, and is about 7.5λ for the ABL system, which may provide a reference to the design of the adaptive optic system for high-power lasers.

The airborne pod is a kind of airborne optical-electronic detection and countermeasure equipment, which can observably improve the airplanes operational performance in combat.The environmental control system is an important part of the pod, which design is difficult and very important for the pod design.A method for working performance analysis of the environmental control system was presented.Acoording to the method, we obtained the formula for calculating the temperature difference between inside and outside of the pod, and that for calculating the mininum and the maximum speed permissible for different altitudes.This method was certified by theoretic analysis and simulation with an example of an optical-electronic pod, which can be taken as a good reference for the design of an environmental control system.

In order to realize autostereoscopic display, a new directional optic structure was proposed, which could provide a pair of parallax images time-sequentially aided with the human eye tracking system, and a high resolution multi-user parallax 3D displayer was invented.Its backlight control system based on single chip microcomputer was elaborated, in view of the crosstalk existed in 3D displays, three methods were put forward for improvement:reducing lit time ratio of backlight, refreshing LCD at a faster speed, and using Kalman prediction interpolation.As the experimental results shows, these methods can reduce the crosstalk effectively, and finally a strong 3D visual sense is achieved without loss of resolution.

Considering the gradual increasing of store stations and available types of stores, and the low transfer velocity and limited remote terminal numbers of traditional MIL-STD-1553B Multiplex Data Bus in airborne avionics system and weapon system, a new data bus named enhanced bit rate 1553(EBR-1553) data bus was introduced.This paper expatiated EBR-1553 data bus from the topology architecture, hardware configuration, transfer characteristics and bus transfer model.Then the applied field of EBR-1553 was addressed.Finally, the method of EBR-1553 data bus hardware implementation based on FPGA IP core was proposed.

The application of millimeter-wave seekers in foreign air-to-ground missiles in active service and under-development is introduced.The pitch scanning scope of the seeker and terminal overload capability of the missile are calculated and analyzed based on gliding trajectory with the constant flight path angle.The results may offer some references to the design of millimeter-wave guidance missiles.

The hypersonic vehicle has numerous control problems such as heading and Dutch roll instability, roll reverse in reentry phase due to high angle of attack.In order to ensure flight safety, its necessary to study the roll control in large angle of attack.Firstly, two kinds of roll control strategies are presented in this paper, which are improved LCDP roll control by aileron and roll control by rudder.Then, the structured singular value is applied to analyze the robustness of them.Finally, control quality and robustness of the two roll control strategies are compared with each other by simulation.The simulation results show that they are both efficient to control roll angle in the nominal state, but the latter roll control strategy is more robust than the former one considering the perturbation of aerodynamic parameters.

A high-precision driving circuit was designed and realized for semiconductor lasers, which has two parts of temperature control and current control.The temperature is controlled in the range of ±1.50×101 K at room temperature, the temperature control precision is better than 1.81 mK, and the standard deviation is less than 0.20 mK.The current adjusting range is 0 to 2.00×102 mA and the ripple is less than 1.00×102 nA.When used for driving a semiconductor laser, the system can make the output frequency of the laser diode reach 1.00×10-9 within 10 s, which can meet the requirements of atom molecule physics, laser spectroscopy, and other fields to high-precision lasers.

To improve the effectiveness and real-time performance of the wireless image transmission, tail-biting triple-branch absolute error correction coding, an efficient analog error correction coding method, and the maximum-likelihood decoding algorithm, were proposed based on the encoding theory and nonlinear theory.We applied the new coding method to the transmission of the digital images, and compared it with the tail-biting triple-branch Bakers map coding by simulation.The result shows that:1) Compared with the later, the proposed method has better correction ability in the Gaussian channel; 2) The PSNR of the restored image can get the gain of more than 2 dB; and 3) The decoding complexity of the new codes is decreased.In this way, the effectiveness and real-time performance of the wireless transmission can be improved greatly.The tail-biting triple-branch absolute error correction codes can play a better role in the image transmission for the wireless communication through the channel with severe noise or interference.

The current situation of navigation sensor flight test was briefly analyzed, a method using data fusion algorithm to obtain navigation sensor benchmark was proposed.In this scheme, the performance characteristics of different types of navigation sensors were taken into full consideration.A preliminary test flight navigation data fusion based on centralized Kalman filter was carried out.On the basis of Kalman filtering, fixed-internal smooth filtering was used to achieve global information optimization.The data fusion algorithms were verified by the flight test data.The result shows that, the method makes full advantage of different types of sensors on their characteristics and post data processing capability, and the precision of fusion output is significantly improved.The method supplies a new idea for navigation sensor flight test evaluation.

The mathematic model of deviation angle distribution of uniform thickness conical surface windshield glass was deduced based on the theory of ray-tracing, and a method for establishing the engineering model of angle of deviation was also proposed.Based on which, an approximate model with high-precision was developed by using least square method.The model is applicable for real-time compensation of the relative deviations for the onboard software, which has been applied in a certain type of airplane successfully.

Considering the random jitter of a flying aircraft, a simulation method for dynamic RCS series of aircraft was proposed.An electromagnetic calculation model of the aircraft based on scaling model size was established in FEKO, and the all-space static RCS was obtained.After the flight path was simulated and the attitude angle of the aircraft in flight was calculated out, the dynamic RCS series of the aircraft flying with random jitter were obtained.Random jitter was considered in movement modeling to make movement more realistic.The simulation results show that there are 17.5% points that have 3 dB or above difference with the initial RCS value after considering the effect of the random jitter.The presented method is beneficial to the study of dynamic characteristics of radar targets.