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2013 Vol. 39, No. 11

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Flight test of high sink speed symmetric landing used in land-based aircraft strength verification
Jiang Qideng
2013, 39(11): 1421-1425.
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High sink speed landing was discussed which was used to verify the strength and rigidity and shock-absorbing ability of landing gear in land-based airplane flight test. Sink speed was one of the key factors in landing gear design and verification. In fact, aircraft landing was effected by many factors, so it is very difficult and full of high risk for pilot to manipulate an aircraft to land at sink speed regulated by specifications. Landing and touchdown methods,such as floating-drop and direct-gliding and landing training were put forward and used in flight tests. According to this, the sink rate of a land-based airplane flight test in domestic reached 2.47m/s, which is the maximum up to now.So the landing gears of this type aircraft satisfy relevant specifications.
Pressure multi-sensor data fusion and estimation of poor information based on bootstrap-fuzzy method
Wang Zhongyu, Wang Qian, Fu Jihua
2013, 39(11): 1426-1430.
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Pressure multi-sensor data fusion and estimation of poor information is a common problem in the field of pressure measurement. Small measurement data obtained from multi-sensor for the data fusion and estimation makes the data processing much difficult. Different from the statistical methods, a novel model based on bootstrap-fuzzy method for pressure multi-sensor data fusion and estimation of poor information was presented. The pressure multi-sensor measurement data was processed by the bootstrap sampling. The bootstrap fusion sequence was derived from the bootstrap distribution. The true value and the interval of the pressure multi-sensor measurement data were estimated. Experimental results show the model has high accuracy and the data fusion sequence is in a good agreement with the original measurement data. The validity of the proposed method is examined.
Bird strike risk assessment with airport avian radar data
Chen Weishi, Wan Jian, Li Jing
2013, 39(11): 1431-1436.
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A method that uses the real-time bird information collected by the airport-based avian radar system to assess the bird strike risk with the estimation of bird strike probability and severity was proposed. The strike probability was calculated by the prediction equation with the independent variables of the relative positions of the bird and the runway. The strike severity was estimated by the combination of the Delphi method and the analytic hierarchy process (AHP), called DAHP, which take full advantage of the expert knowledge and quantitative calculation. To reduce the number of parameters on the same level of the DAHP model, the influencing factors of the evaluation results were arranged in a two-level model, which could avoid the problem of inconsistency of the comparison matrix due to the high number of parameters on the same level. The assessment method was tested on the simulated data at Beijing capital international airport with three runways and the real data at Beihai Fucheng airport with one runway.
Experiment on influence of the communication signals transmission in plasma sheath
Wu Runhui, Liu Hongyan, Liu Jiaqi, Chang Qin
2013, 39(11): 1437-1442.
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A vehicle flying in the atmosphere at transsonic velocity creates plasma sheath, and the communication signal is defiladed or its energy is attenuated by the plasma sheath, thus the communication system is discontinued between the vehicle and the signal station. The phase changed and the energy absorbed of the communication signal in plasma sheath which is made by the shock tube was studied, and the experiment of different plasma parameter was finished. Two measuring systems were built, one is the signals generator and data sampler, and its modulation is quaternary phase shift keying (QPSK), and its carrier frequency is 7.5GHz; the other is the E8362B test system. The contrastive results of the signal phase changed and the signal energy attenuated at the plasma and no plasma were obtained. The experimental results show that not only is affected the communication by the plasma sheath absorbing, but also the phase changed of QPSK signals is achieved, the signals demodulated/decoded are badly aberrant, and the Pe of communication system is increased, and the receiver is unable to offer the original information sent by transmitter.
Quantum adaptive median filtering based on dual qubits state measurement
Yuan Suzhen, Mao Xia, Chen Lijang, Xue Yuli
2013, 39(11): 1443-1448.
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To further enhance the image detail protection ability, improve the algorithm real-time in the de-noising process, a quantum adaptive median filtering algorithm based on dual qubits state measurement was proposed. The algorithm firstly transformed the image pixel to quantum superposition state form; secondly, the quantum superposition state was measured based on quantum measurement theory; finally, output image was designed based on the measurement collapsing state. Expanding the traditional correspondence relationship between single pixel and single qubit state, the algorithm used dual qubits state to represent a single pixel. Dual qubits state has four superposition states so that it contains more information on the represented pixels and processes these pixels more accurately. Probability density of the dual qubits state was designed based on the noise characteristics, and the collapse states will adaptively increase the filtering window's size. Experiments show that the quantum adaptive median filtering algorithm has a better integrated filtering capability compared with median filtering and classical adaptive median filtering. The algorithm can remove the noise effectively, protect the detail well and has good real-time.
Fast analytical model of cruise missiles penetration ship-based anti-missile system
Du Zheng, Wang Chaozhi, Chen Wanchun
2013, 39(11): 1449-1454.
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Aim at the characteristics of frequent human-computer dialogue of cruise missile in the initial design phase, the interceptor performance correction factor was introduced, a fast analytical model of cruise missiles penetration ship-based anti-missile system with penetration efficiency as evaluation index was established with new ideas by the integrated use of estimation method and simulation method of missile analytical methods, which provided fast and reliable mathematical tools for the improvement of cruise missile operational performance in the initial design phase. Based on the establishment of fast analytical model, sensitivity analysis of the main factors that affect cruise missiles penetration typical ship-based anti-missile system were conducted. Results can set the direction for cruise missile design.
Variance-based uncertainty analysis methods of logistic support time
Wu Yong, Pan Xing, Kang Rui, Ma Lin
2013, 39(11): 1455-1459.
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Uncertainty in logistics support process is present under the influence of support activities parameters. In this work, global sensitivity indicator was introduced which looks at the influence of input uncertainty on the entire output distribution without reference to a specific moment of the output and which can be defined also in the presence of correlations among the parameters. Variance-based uncertainty analysis method with the graphic evaluation and review technique(GERT) model of logistic support process duration was designed. And then, an analytic algorithm to calculate the uncertainty analysis was designed with GERT. At last, the analytic algorithm was used to analysis the aircraft support activities uncertainty analysis. Given the limited support resources, the uncertainty analytic algorithm is helpful for a decision maker to identify the most important input parameters that control the uncertainty in the model output.
Structural reliability analysis based on polynomial basis function neural network
Meng Guangwei, Li Guangbo, Li Feng, Zhou Liming
2013, 39(11): 1460-1463.
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The polynomial basis function neural network method for structural reliability calculation was adopted. When the limit state function of the structure is highly complex or with nonlinearity, sometimes, limit state function is implicit, the traditional method of structure reliability analysis calculation is time-consuming. The polynomial basis function neural network method provides an effective means for the reliability analysis of large scale structures. Based on the polynomial approximation theory, a pseudo-inverse of random variable input matrix was used to be incentive function to determine the weights between the hidden layer and output layer with the approximation of neural network. The failure probability was calculated by first-order reliability method (FORM). The numerical example results show the proposed method has ability of solving the structural reliability analysis problems. The test results show that the formula of the proposed method is simple and easy to program. A new method for solving the structural reliability analysis was displayed.
Three-dimensional finite element analysis for non-synchronized cure of thick composite laminates
Zhang Jikui, Zhang Jiang, Ma Zhiyang, Cheng Xiaoquan
2013, 39(11): 1464-1469.
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A three-dimensional finite element model was established and verified for the description of curing process of thick composite laminates. Temperature, degree of cure, viscosity, resin volume fraction and thickness reduction ratio during the curing process were calculated for a 400-ply AS4/3501-6 laminate. Numerical results manifest that the peak temperature which is 49K higher than the dwell temperature appears at the laminate's central ply; the changes of the temperature and degree of cure are not synchronized along the z-direction; the overshoot and quick-curing area is found evidently in the central part of the laminate; the viscosity varies greatly and the curing time is curtailed in this area, which prevent the spare resin in this area and under-part of the laminate flowing into the bleeder; the fact that the non-average distribution of the resin volume in the laminate stems from the existing of this area in the cure cycle, and the resin volume fraction is about 41% in the surface and 46.5% in the bottom which contact with the bleeder and the tool respectively; the approximate value of thickness reduction ratio is 15.7%.
Anti-saturation robust adaptive switching control scheme of a hypersonic flight vehicle
Wang Qing, Wu Zhendong, Dong Chaoyang, Bai Bin
2013, 39(11): 1470-1474.
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A robust adaptive switching control scheme with a multi-loop control structure was proposed for hypersonic flight vehicles in the presence of actuator constraints. State variables was designed with the multi-time-scale property of hypersonic vehicle motion, and the switched system was established to describe the state variables related to actuator constraints, thus cutting down the design effort for switched reference system and the corresponding controllers. The events that potentially induce actuator saturation were regarded as switching signals that specify the active subsystem and corresponding robust adaptive controller, which ensure control input restricted. Utilizing the multiple Lyapunov functions method and model reference adaptive control methodology, a detailed stability analysis for such control scheme was designed which guarantees the closed-loop switched system globally asymptotically stable with linear matrix inequation (LMI). Simulation demonstrates the effectiveness of the switching control scheme, and the system has well tracking performance and the amplitude of control input satisfies the actuator limit.
μ-synthesis robust control for air-to-air missile based on dynamic acceleration constant PSO arithmetic
Lu Qidong, Chen Xin, Zhang Min
2013, 39(11): 1475-1479,1508.
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Particle swarm optimization (PSO) algorithm is prone to premature convergence in the control parameter optimization of air-to-air missile μ-synthesis controller, which makes the global optimal solution inaccessible. Aiming at this situation, dynamic acceleration constant particle swarm optimization (CPSO) algorithm was proposed. This improved algorithm, through changing the index form of the acceleration constant, expanded the searching range in the beginning phase of optimization, improved the efficiency of convergence in its latter phase, and finally the premature phenomena was avoided. The simulation results reveal that the improved version of exponential CPSO algorithm is of great significance in engineering applications. It has a better ability in global searching. μ-synthesis controller based on this algorithm maintains optimal performance, which meets the given performance indicators and automatic design specifications and saves much design time.
Suppression of aeroservoelasticity in anti-aircraft missile using thrust vector
Wu Yunjie, Song Jiayun, Liu Xiaodong, Zhang Wulong
2013, 39(11): 1480-1485.
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Anti-aircraft missile are always designed with large aspect ratio,which has low body flexible frequency. Besides, nozzle swing would increase the vibration of missile body. To eliminate this effect, the article analyzed the relationship between the vibrations and control system. Based on modeling of flexible missile, it proposed the layout of the dual sensor plan and the way of pre-integrating for signal preprocessing. Using a new adaptive notch filter basing on Steiglitz-McBride, the useful signal could be got from the rigid body motion of the missile. In this way, the control system would have more flexibility and adaptability while dealing with the aeroservoelasticity. What's more, the layout of dual sensor would increase the reliability of measure and filter at the same time.
Path planning for continuum robot based on target guided angle
Gao Qingji, Wang Lei, Niu Guochen, Wang Weijuan
2013, 39(11): 1486-1490.
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To inspect the aircraft fuel tank which has strong space constraints, path planning for continuum robot applied to this kind of convex space was studied. An algorithm based on target guided angle was presented. Strategies of dimension reduction and regional division were proposed to decrease the high time complexity of blind search. The relationship between the target and the searching range of joint variables was established by introducing the target guided angle. Then the search process was optimized and evaluation function was proposed to evaluate results of search algorithm. Feasibility and effectiveness of the algorithm are confirmed through simulative results.
Hardware-in-loop simulation platform for UAV autonomous aerial refueling based on computer vision
Duan Haibin, Zhang Qifu, Fan Yanming, Li Hao
2013, 39(11): 1491-1496.
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A hardware-in-loop simulation platform of unmanned aerial vehicle(UAV) autonomous aerial refueling based on computer vision was developed. Point feature matching and LHM pose estimation algorithms were adopted to the recognition of light emitting diodes(LEDs) on the drogue. The models of atmospheric disturbances and wake vortex had been built, and the drogue model was also presented. Subsequently, a linear quadratic regulator (LQR) control law for UAV was designed. The hardware-in-loop simulation platform with airborne monocular camera for UAV autonomous aerial refueling had been developed in lab environment. Series of hardware-in-loop experimental results demonstrate the feasibility and effectiveness of our presented approaches in this simulation platform.
Approach of UAS airspace integration based on systematic classification and level of safety assessment
Cai Zhihao, Wu Huiyao, Wang Yingxun
2013, 39(11): 1497-1502.
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UAS (Unmanned Aircraft System) airspace integration, which means UAVs entering non-segregated airspace, is the trend of next generation air transportation system,which will also bring new challenges to the air traffic management.Referring to the airspace integration project of United States, the classification of airspace should be proposed. Based on the comprehensive capacity of the UAS, the operations profile can lead to a full dynamic operation solution. Aiming at evaluating UAS, two aspects are taken into consideration: the classification of the systems and the assessment of safety level; in which the two key factors of system classification are autonomouscontrolabilityand surveillance method. The airspace integration of a certain type of UAS can be achieved by define the accessible airspace and the mode of operating through different types of airspace.
Design of integrated navigation system simulation platform based on RT-LAB
Zhang Yachong, Yue Yazhou, Liu Yushuang, Zhao Yan
2013, 39(11): 1503-1508.
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A strapdown inertial navigation system/global positioning system/celestial navigation system(SINS/GPS/CNS) simulation platform based on RT-LAB was designed. Based on attitude, position and velocity, the integrated navigation system solution with federated Kalman filter has the capability of fault detection, isolation and system reconfiguration. The SINS/GPS sub-filter observations are the difference of position and velocity. And the inertial attitude information of carrier was given by CNS, therefore the attitude error measurement of SINS was obtained. Simulation results show that the solutions have the stronger fault tolerant performance and higher navigation accuracy and the stronger real-time performance. The work is valuable for the research of related techniques in integrated navigation system.
Multivariable model reference adaptive control of aircraft with asymmetric damage
Yang Lingyu, Leng Ning, Zhang Jing, Shen Gongzhang
2013, 39(11): 1509-1514.
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Some issues in adaptive control of generic aircraft with asymmetric damage and its key conditions were analyzed.A thorough study of modeling, linearized aircraft models and coupling of lateral and longitudinal dynamic was presented. And the detailed proof of the key condition for model reference adaptive control(MRAC): the invariance of the signs of principal minors of the high frequency matrix and the infinite zero structure was performed which demonstrates the theoretical feasibility of MRAC of generic aircraft with asymmetric damage. At last, simulation results were given to illustrate the design and performance of adaptive control systems for aircraft flight control.
Method of dynamic flight envelop assessment for aircraft wing damages
Liu Xiaoxiong, Sun Xun, Tang Qian, Zhang Weiguo
2013, 39(11): 1515-1519.
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It is important for flight envelop assessment in the presence of control surface damage of aircraft, which can offer information to pilot and protection control in order to improve the reliability. Considered dynamic characteristic of the wing damage, a method of dynamic flight envelop assessment was proposed. According to control surface damage could cause the aerodynamic parameter change, the damage modeling was built. Based on the least square method, the aerodynamic parameters and failure diagnosis were achieved by online. The flight envelop was assessed accurately based on identification and operating trim points. The simulation results show the effectiveness of the proposed method.
Robust fault detection for network-based system with time-varying delay
Zhang Yingxin, Wang Qing, Wu Zhendong, Dong Chaoyang
2013, 39(11): 1520-1524.
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For network-based system with time-varying delay, the fault detection filter design approach based on robust H∞ theory was proposed. The robust H∞ fault detection problem was converted into design parameter matrices of the filter which guarantees the internal stability and the robust H∞ performance index. Faults were detected based on the residual error evaluation function and the fault threshold. It was assumed that the time-varying delay was bounded and the upper and lower bounds were known. The delay-dependent Lyapunov-Krasovskii functional was chosen to derive the delay-dependent condition for the existence of the fault detection filter. The parameters of the corresponding fault detection filter were obtained by solving the delay-dependent condition. Under bounded control inputs, external disturbances and fault signals, the fault detection filter can guarantee the boundedeness of the resultant residual error. The effectiveness of the proposed approach was demonstrated by the application to the highly maneuverable technology (HiMAT) vehicle flight control system.
Simulated GPS IF and IMU signals and verification
Wang Kedong, Hu Zheng, Hou Shaodong
2013, 39(11): 1525-1528,1541.
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A software simulator to simulate GPS IF signal and inertial measurement unit(IMU) signal was developed for the research on the GPS/INS integration algorithm. The vehicle trajectory was modeled in kinematics. The method to simulate the signal was put forward. The IMU signal was modeled based on the typical vehicle motions, such as the level motion, the rolling, the pitching, and the yawing. The typical interference signals, including the spoofing signal and the blocking signal (the narrow-band noise interference, the wide-band noise interference, the continuous-wave interference, and the sawtooth frequency modulated continuous wave interference), were modeled and generated to simulate the interference scenarios. The data generated by the simulator were calculated by the GPS/INS integration algorithm. The results prove that the algorithm of the signal simulation is correct and the IF signal and IMU signal provided by the simulator are effective preliminarily.
Observer-based sensor fault detection and signal reconstruction method
Xia Jie, Xu Jingjing
2013, 39(11): 1529-1535.
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The sensor-fault detection for linear system with bounded unknown input disturbance was studied. By non-singular linear transformation, the sensor-faults were converted equivalently into actuator failures. The residual generation was proposed which is robust to disturbance and sensitive to sensor faults. A sliding mode observer was further designed to give the estimation of residuals. The sensor faults can be detected and the sensor signals can be reconstructed by using the estimation of residuals. For typical sensor failure modes (slow bias fault and step bias fault, complete invalidation and reverse fault), the simulation results on the aircraft longitudinal model show the effectiveness of the proposed methods.
Decision-making approach to UCAV based on gray interval relative theory
Dong Zhuoning, Lu Junyan, Xiao Xiao
2013, 39(11): 1536-1541.
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To solve the problems of tactical decision-making for unmanned combat air vehicle(UCAV) under the condition of incomplete information, an independent tactical decision-making approach to UCAV based on gray interval relative theory was proposed. The decision-making elements were selected and the UCAV decision-making reasoning rule base was established in accordance with the combat mission's requirements. Incomplete information was modeled, a tactical decision-making model for UCAV was established according to the theory of gray interval relative. Conflict resolution algorithm, an effective solution to reasoning failures caused by the incomplete information, was designed. Some experiments were presented to simulate the decision-making process, the feasibility in resolving the UCAV tactical decision-making problems and the validity in resolving the rule match conflicts was verified. The results show that the approach is able to deal with the uncertainties of the decision-making factors, and gives reasonable results.
Antiwindup attitude controller for maneuvering glide vehicles with guaranteed convergence rate
Dai Shicong, Ren Zhang, Li Jingjing, Qu Xin
2013, 39(11): 1542-1547.
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An attitude control law which can obtain stability and satisfactory response rate simultaneously with input saturation for a novel near space glide vehicle was presented. For nominal antiwindup, the convergence rate of control error is generally neglected and can be extremely small in some situation. In order to improve the fastness of controlled system, an existing LMI based design algorithm was modified. By utilizing the comparative principle, the asymptotically stability of the controlled close-loop system and guaranteed convergence rate for Lyapunov function was proved. Differently from previous works, this method satisfy the basic fastness need of controlled system and provide a way to trade-off between stability and fastness. The simulation of heeling angle maneuvering with nonzero slip angle shows the effectiveness of the proposed antiwindup control method. Compared with nominal Antiwindup method the proposed one performed better in fastness.
Method of UAV emergency disposition training based on fault tree analysis and snapshot
Lin Qing, Cai Zhihao, Wang Yingxun, Chen Lifang
2013, 39(11): 1548-1552.
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In order to improve UAV (unmanned aerial vehicle) operators-ability to detect and deal with emergency cases, a method based on FTA (fault tree analysis) and software snapshot technology was proposed. Taking a flying-wing UAV for example, some key technologies were researched. Then a universalized emergency disposition training system was designed and hands-on trainings were carried out by degrees. The fault tree analysis method was used to build a relatively complete model of the reasons which could cause accidental cases, and key reasons were picked out for more intense trainings. The snapshot technology was introduced to decouple different training stages. Then with the RTW (real-time workshop) method, data base technology and VR(visual reality) technology, a universalized UAV emergency disposition training system was built and applied to the training of the target UAV. Through the comparative analysis, the effectiveness and high fault coverage of the method were verified.
Black-box modeling of ship manoeuvring motion based on support vector machines
Xu Feng, Zou Zaojian, Xu Xiaoka, Yin Jianchuan
2013, 39(11): 1553-1557.
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Least square support vector machines(LS-SVM) was applied to black-box modeling of ship manoeuvring motion by using the 15°/5° zigzag test data of free-running model. To solve the problem of the uncertainty in choosing the parameters of SVM, grid search method was adopted for parameter optimization. The established model was used for predicting the 10°/1° and 25°/5° zigzag manoeuvres and 35° turning circle manoeuvre. The prediction results are in good agreement with the test data, which demonstrates the validity of LS-SVM in black-box modeling of ship maneuvering motion and the feasibility of grid search method in optimizing the parameters of SVM.
Thermal bias drift compensation of MEMS accelerometer based on relevance vector machine
Xu Zhe, Liu Yunfeng, Dong Jingxin
2013, 39(11): 1558-1562.
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Thermal bias drift prognosis and compensation model was built based on the regression algorithm of relevance vector machine. The thermal bias drift of the accelerometer experiencing different temperature load can be classified by using both the temperature and the temperature rate as the model input. The influence of training sample number, the kernel function and the parameter sigma were discussed. Experimentation with the data of the temperature cycling test was conducted. According to the experimental result, the thermal bias drift of the accelerometer can be prognosed accurately by the model, the mean square error is less than 1%, and the size of the thermal hysteresis loop is reduced from 0.06g to 0.015g.

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