The modeling of mission profile is studied for carrier-based electronic warfare aircraft. The definition, elements and formal description of the mission profile are presented. IDEF0 and IDEF3 are adopted to accomplish modeling of its function and technical process. Simulation is made for the mission profile based on ExtendSim, and the results show the rationality of the model.

Mixed-criticality flows are integrated in Time-Triggered Ethernet (TTE). Offline scheduling time guarantees critical temporal determinacy of Time-Triggered (TT) flows, but it can block Rate-Constrained (RC) flows. A new scheduling algorithm named MC-iSLIP for Crossbar is proposed for scheduling mixed-criticality flows. Meanwhile, the strategy for updating pointers of inputs and outputs is designed to prevent starvation. Then the complexity of MC-iSLIP algorithm is analyzed. Finally, simulation compares TTE using output-queuing switches and input-queuing crossbar switches, which demonstrates that crossbar switches using MC-iSLIP decrease block of RC flows caused by TT flows, and decrease end-to-end delays and jitters of RC flows.

In view of the characteristics of ballistic missiles, the GPS/SINS integrated navigation algorithm based on speed/location in the launch inertial coordinate system is studied. The strapdown inertial navigation error equation is derived in this coordinates. The state equations and measurement equations for GPS/SINS integrated navigation system are established. The digital simulation and vehicle experiment indicate that this GPS/SINS integrated navigation algorithm can improve navigation accuracy effectively.

The problem of robot path planning is relatively complex under dynamic environment. During the process of real-time local path planning in local environment within the global path, sudden appearance of obstacles may cause oscillations for mobile robots path planning. If seriously enough, it will result in failures of path planning, and thus the mobile robots are incapable of finishing autonomous navigation. In order to solve this problem, we proposed an algorithm for local path planning and obstacle avoiding based on improved Morphin search tree. Through a multilayer local replanning and by using the corresponding function as a basis for the property evaluation of search tree, a smooth and trackable trajectory with nonholonomic constraints of mobile robots is obtained. This algorithm overcomes the shortcomings of simplex and inflexibility of Morphin algorithm in trajectory searching. The test on a real robot Pioneer3 verifies the correctness and effectiveness of the algorithm.

An accurate method is proposed for horizon detection according to the imaging characteristics of infrared images. Unlike most previous sea-sky-line detection algorithms, the method employs linear Harr features to gain edges after infrared image de-noising, thus to fix the position of the sky and the quasi horizon. Then, the position of the horizon is detected roughly via analyzing the energy of the margin. Finally, the accurate and complete horizon is acquired by means of the numerical analysis techniques. The experiment results show that the method can detect the horizon effectively in different scenes, and it is robust even if the situation is complex when the sky is overcast with cloud and mist.

High-speed motion of vehicles and dynamic change of network topology make it difficult to design Vehicular Ad Hoc Networks (VANETs) routing protocol. The stability of routing protocol is an important guarantee for transmitting data. Therefore, a graph-based s routing strategy is proposed in this paper, which is used in Ad Hoc On-Demand Distance Vector (AODV) routing protocol. The optimal AODV routing is marked as GS-AODV. In GS-AODV, the s link model is established, and the stability of routing is computed out by speed information of vehicles. After that, the dynamic information of topology is acquired by graph theory. Finally, the most s routing is selected to transmit data. Simulation results show that the performance of proposed GS-AODV is improved in terms of packet delivery ratio, end to end relay delay, and the numbers of link failures.

Aiming at the issue of object location in 3D space, we proposed a method to realize binocular visual positioning with single camera, which is simple, convenient in operation and cost-effective. We used the SURF algorithm for image feature point extracting and matching in the process of object recognition and locating, since the algorithm has good performance in all respects. In order to reduce error matching in the matching process, improvement was made to the SURF algorithm. The experimental result indicate that, the method of monocular to binocular visual positioning based on improved SURF algorithm has fine feasibility and practicability both in accuracy of positioning and in time cost, which is of a certain practical value.

Considering that the near space hypersonic target has the moving characteristics of rapid flight speed, high maneuverability, and periodic sliding jump, we proposed a near space target tracking algorithm based on interaction of different Sine models. First, in view of the periodic sliding jump trajectory of the near space target, a sine model based on low angular rate is adopted to improve the accuracy of near space target tracking. Then, in view of the unknown parameters and moving characteristics of the sliding trajectory, Sine models with different angular rates are interacted, to further improve the matching degree of the model with periodic sliding jump trajectory of near space target. The simulation experiments show that, compared with the existing near space target tracking algorithms, this algorithm has higher tracking precision.

Aiming at the requirement of the missile terminal impact angle constraint to enhance the damage efficiency, a sliding mode guidance law with impact angle constraint is proposed based on finite-time control and terminal sliding mode control theories. This guidance law chooses terminal sliding mode that contains relative velocity deflection angle and impact angle constraints, and selects the fast power reaching law to ensure that the states of the guidance system are converged in finite time and satisfy the requirement of hit precision and impact angle constraint. The law is analyzed by utilizing the finite-time control theory, thus the finite-time convergent feature of the guidance system states is proved, and the mathematical expression of convergent time is given. Finally, a contrast simulation is made and the simulation results verify the effectiveness, robustness and superiority of the proposed guidance law.

The Radar Cross Section (RCS) model based on precession of ballistic missiles in midcourse phase is built up. A new method is proposed to extract the precession period by combining Auto Correlation (AUTOC) with Average Magnitude Difference Function (AMDF). After the precession period is obtained, match searching method is adopted to extract precession angle. Then inertial ratio can be obtained based on the extracted precession period and precession angle, which is an effective feature for making identification to the ballistic missile. From the view of parameter estimation, the Cramer-Rao Bound (CRB) of inertial ratio is analyzed, and the mean square error of inertial ratio is compared with the CRB, which verifies the validity of the inertial ratio extracting method.

Under the natural non-controlled natural environment, one of the difficult problems in the automatic target recognition of aircraft is the attitude variation and occlusion. Therefore, we proposed an aircraft recognition method based on sparse representation. Compared with the existing methods, the highlight of the proposed method is to transform the target image recognition problem into a sparse representation problem of the training samples, which can process the original target images directly, and the processes of feature extraction and selection are not needed. Thus it possesses good robustness to the attitude and occlusion variations of the aircraft targets. Experimental results on 5 kinds of aircraft image data sets show that: the proposed method is feasible, and the recognition rate is above 90%. This method supplies a way for the identification of nonlinear and complex natural air images.

To solve the trajectory tracking problem for the under actuated, strong coupled nonlinear system of the quadrotor aircraft, a sliding mode control strategy was proposed. Based on the typical Newton-Euler dynamics model, the UAV control system was divided into two subsystems: a fully actuated subsystem (ψ, z) and a under actuated subsystem(x, y, φ, θ). The variables ψ and z of the fully actuated subsystem converged to the desired value by using the terminal sliding mode controllers. Then, the second mode control was used to achieve effective position and attitude tracking of x, y, φ and θ, whose sliding mode surface parameters were obtained by using the Hurwitz theory. Simulation was made on Matlab/Simulink, and the results show that the designed trajectory controllers have high robustness and good performance for position and angle tracking.

The infrared tracking accuracy of shipboard photoelectric tracking device may be greatly affected in the capture stage by the bow wave, pitch and roll disturbance. In order to improve the tracking accuracy, the paper presents a speed loop feedforward control strategy, which can be divided into three steps. First, transform the geodetic coordinate system into the coordinate system of deck. Secondly, use CA model least square method to filter the speed when the target appears in the image field of view and satisfies the extraction threshold value. And finally, feed the filtered speed forward to the speed loop. Series correction is used in the servo control loop, and different regulators are selected according to the tracking status. A complete double-loop circuit is formed combined with infrared miss distance information. Experiment to infrared tracking performance of an shipboard photoelectric device showed that: the maximum tracking error is respectively 120″ and 78″ before and after using the feed-forward compensation. Thus the algorithm can reduce the tracking error and improve shipboard optoelectronic countermeasure ability.

Taking the proportional navigation method of missile guidance law for reference, this paper proposes an guidance law based on rate of change in altitude (H· ), which can reduce the UAV motion sensitivity to the change of recycling network parameters, and gain a relatively straight and steady decline trajectory. According to the motion feature of recycling network center along with the wave motion in net recovery process of UAV, a Robust Servomechanism LQR (RSLQR) control law is designed based on RSLQR control method by taking H· as the main control variable. This control structure has satisfactory robustness and high control accuracy, which can satisfy the performance requirements of dynamic net recovery. The results of nonlinear simulation verify the feasibility of the method, and show that the designed controller can eliminate the position error caused by wind, and increase the rapidity, accuracy and stability of the system.

In allusion to the demands to the test equipment for photoelectric tracker system and the disadvantages of the traditional test method, a creative test method is proposed, and a por test equipment is developed. The overall design scheme and the technology guidelines of the test equipment are presented. By using the optic design of off-axis aspheric surface folded light path, two-dimensional, high-accuracy moving target mechanism, and dual-band switchable light source, a dynamic target simulator is realized, which has small volume and high precision. Based on industrial control computer, driving controller of step motors and MPS-010602 data acquisition card, the trajectory control to the target simulator and the signal acquisition/processing are realized. All of the indexes are eligible, and the application of the test equipment is successful.

Turn is widely applied in the remote sensing test field, and the requirements for its control performance become increasingly high, especially for the control of low-speed, large -torque turn. To the problems that the classical state observer is unable to detect the system state precisely and it is hard to accurately describe the system model due to inaccurate estimation of rotational inertia and uncertain perturbation model, we proposed a control method based on Extended State Observer (ESO) to track the action of uncertainties, which is independent of the exact system model. Firstly, the ESO was analyzed and designed. Then, a nonlinear PID controller for speed loop was constructed, and simulation was made to the system under the Simulink. Results of the test show that the method can improve the performance of the control system of the low-speed, large-torque turn effectively. Compared with the traditional PID control, the accuracy of steady speed of the turn was improved by 8. 6%, and the tracking error was reduced by 13. 3%.

A certain type of missileborne accelerometer is the vulnerable spot that affects the storage life of the rocket control cabin.Considering that the statistical data of accelerometer is binomial and incompletewe used isotonic regressionvariable sample Pearson χ2 test of goodness of fit together with minimum χ2 estimationto solve the “reversal” problem of failure frequency.The distribution parameters were givenand Pearson test of goodness of fit was made to the distribution function.The result showed that:both I maximum distribution and Weibull distribution were suiand Weibull distribution was selected as the life distribution because the former one had no accelerating ability.In the endthe natural storage life under confidence level of 0.90 and reliability of 0.95 was obtained.The acceleration factor under 90 ℃ is 7.2695.Thus the Accelerated Life Time (ALT) of certain batches of accelerometer was obtained.The study is of engineering significance for ALT plan of and budget.

A certain type of missile-borne accelerometer is the vulnerable spot that affects the storage life of the rocket control cabin. Considering that the statistical data of accelerometer is binomial and incomplete, we used isotonic regression, variable sample Pearson χ2 test of goodness of fit together with minimum χ2 estimation, to solve the “reversal” problem of failure frequency. The distribution parameters were given, and Pearson test of goodness of fit was made to the distribution function. The result showed that: both I maximum distribution and Weibull distribution were sui, and Weibull distribution was selected as the life distribution because the former one had no accelerating ability. In the end, the natural storage life under confidence level of 0. 90 and reliability of 0. 95 was obtained. The acceleration factor under 90 ℃ is 7. 2695. Thus the Accelerated Life Time (ALT) of certain batches of accelerometer was obtained. The study is of engineering significance for ALT plan of and budget.

Silver-zinc battery is an important energy equipment in aviation and aerospace field. It is an urgent problem to use the test data to assess battery reliability after the battery is activated. A degradation model of voltage of the standby silver-zinc battery was established based on Wiener process. The reliability function of the battery was given. The maximum likelihood estimation method was used to estimate the unknown parameters of presented model. By using the discharge data of the standby battery which was activated, the reliability of the batch of the battery was evaluated out, with the conclusion that the standby life of activated battery is 51. 95 hours on the condition that the reliability is 0. 95.

Based on the method of integrated neural networks and particle filter, a new method is proposed for predicting the residual useful life based on the particle filter with unknown measurement noise under the condition of partially observable information. Firstly, a status-observation data set is generated based on the equipment performance degradation data, and multiple data sets are constructed by using bootstrap technique. The integrated neural network is used to train the status-observation data sets, and the optimal range of measurement noise standard deviation is obtained through derivation. Then, by embedding the measurement noise standard deviation into the framework of particle filter lifetime prediction as the unknown parameter, the residual life prediction and probability density distribution of the nonlinear system are realized. Finally, the validity and feasibility of the proposed method is verified by the simulation to the life of the lithium ion battery.

Aiming at the product whose performance degradation process obeys to Wiener process, a residual lifetime prediction method is proposed by combining online measured performance degradation data of a product with normal degradation data of like products. Assume that distribution parameters obey to union conjugate prior normal-inverse gamma distribution, a Bayesian estimation model of distribution parameters is built up under individual online measured degradation data. Posterior estimation formula of hyper parameter is obtained. The complete likelihood function of degradation test data is built up. Prior estimation model of hyper parameter is established based on Expectation Maximization (EM) method. Accuracy of the method is verified by an example.

Airplane system configuration management must run through the whole life cycle of model development. Through the research on the intent of airplane system configuration management,and based on the situation and the problems existed in current configuration management,a practical and effective 4D model is established for whole-life-cycle airplane system configuration management. The standardized,systematized and information-based management of airplane system in the whole life cycle is realized by using the integrated management platform.

Aiming at the maintenance decision based on insufficient monitored degeneration informationand considering the actual situation of missileswe made study on missile components by using Wiener model to describe their degeneration process.Bayes method was used to establish a renewable remaining life prediction model on the basis of historical life data and online monitored degeneration information.Particle swarm arithmetic was used to solve the maximum likelihood functionand a priori estimate of lifetime distribution parameter was obtained.The posteriori estimate was obtained by using recursive method.Thereforethe remaining life distribution was updated.Thenthe maintenance decision models were built up based on usability and economic objectives respectively.And a multiobjective model was established by using interaction method with integration of the two objectives.The model was used in a laser gyroscopethe critical component of the missile inertial navigation systemand realized the optimized multiobjective maintenance decision.

Calibration TV measurement technology based on CCD camera is mainly used for calibration and measurement of miss distance in telemetry system. In order to improve the calibration accuracy and the measurement precision of miss distance, two continuous zoom lenses are used in the TV camera, and high-speed Digital Signal Processor (DSP), hyper-scale Field Programmable Gate Array (FPGA) and other devices are adopted. An integrated portable industrial computer is used as the main control computer, equipped with image capture card and large capacity hard disk. There are two modes of rough adjustment and fine adjustment for miss distance. After analysis and practice verificaton, it is proved that the technology can accomplish the telemetry receiving system of far and near field calibration and accurate measurement of miss distance.