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2013 Vol. 39, No. 7

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Predictive reentry guidance with aerodynamic parameter online correction
Liang Zixuan, Ren Zhang
2013, 39(7): 853-857.
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A new predictive reentry guidance algorithm based on aerodynamic parameter online correction for hypersonic gliding vehicles was presented. The constraints of reentry flight were studied, and a basic program for controller design was given. The aerodynamic parameters’ errors in the process of traditional target prediction were analyzed. With the new composite parameters for lift and drag, the method for aerodynamic parameter online correction was established. Online estimation and online correction were used to improve the adaptivity of the predictive reentry guidance. The longitudinal guidance law and lateral guidance law were then designed, and proved to work well with large aerodynamic disturbance. To test the capacity of the guidance method, the Monte Carlo simulation was used. The results indicate that the predictive guidance method with parameter online correction has high guidance precision and good robustness for the aerodynamic disturbance.
Two methods for vibration analysis of variable-mass systems
Xing Yufeng, Xie Ke, Pan Zhongwen
2013, 39(7): 858-862.
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The vibration analysis of variable-mass systems is of great importance in astronautics and aeronautics. The dynamical governing equation of a general variable-mass system was obtained by using the virtual displacement principle in conjunction with the conservation law of momentum, and the effects of mass variation on the dynamic properties of system were also investigated. A modified Euler symplectic midpoint difference method and a modified mode superposition method were proposed and used to solve the equation of variable-mass systems. Regarded as typical variable-mass systems, the variable-mass single particle system, the variable-mass rod and the variable-mass Euler-Bernoulli beam were studied, the numerical results of the proposed two methods agree well. This validates the correctness and feasibility of the developed two methods.
Fast reliability evaluation for SRAM-based spaceborne FPGAs
Zhao Lei, Wang Zulin, Zhou Lina, Yang Lan
2013, 39(7): 863-868.
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Static random access memory(SRAM)-based field programmable gate arrays (FPGAs) reliability is seriously affected by space radiation. A new method for fast reliability evaluation of SRAM-based FPGAs was proposed. Based on traditional fault injection technique, a pre-evaluation was introduced to analyze the effect of single event upsets (SEU) in logic gate-level and SEU sensitive bits in triple modular redundancy (TMR). Then, the fault sequences of different sensitive level were formed. Finally, different fault sequences were selected depending on the application needs and injected into system for evaluating reliability. The method can not only reduce the experiment times and improve the experiment efficiency but also ensure the fault coverage.
Optimal attitude estimation algorithm based on mulitiple star-sensor observations
Ma Hongliang, Chen Tong, Xu Shijie
2013, 39(7): 869-874.
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In most of attitude determinations with methods by using the combination of star-sensors and gyros, the accuracy of attitude determination is high due to the high accuracy of star sensors. However, because of the improper processing of observation model and error, the observation correction ability of attitude filter decreases and the gyro drift error can't be estimated efficiently. Error modeling was proposed based on attitude angle observations, and the optimum installation configurations and observation syncretizing methods were investigated. By making use of the weighted least squares(WLS) preprocessing of observation data, the observation equation changed to be constant. Then, the spacecraft attitude and gyro drift were estimated by using extended Kalman filtering(EKF) with the combination of star-sensors and gyros. The simulation results show the attitude and gyro drift can be estimated accurately by using the presented filter. This method is with less the amount of calculation and of advantage to autonomous on-orbit operation of actual attitude determination system.
TSEP positioning accuracy evaluation approach applied in 4D guidance
Wang Yanyong, Yang Gongliu, Yuan Erkai, Zhang Lu
2013, 39(7): 875-879.
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As humans exploration activities increase in deep space and identification needs of space navigation equipment, traditional probability indicators and evaluation approach cannot meet the system requirements. Three sphere error probabilitiy (SEP) calculation methods were deduced and induced: triple integral equation algorithm, χ2 distribution approximation algorithm, and maximum likelihood estimation (MLE) optimization algorithm. Combined with the two statistical test schemes, time SEP (TSEP) accuracy evaluation method was raised. Simulation and test verification shows that: TSEP method of positioning accuracy of space equipment gives a relative comprehensive evaluation, the scheme is viable, compatible with traditional method of calculating indicators and takes full advantage of single test data, test simple. Three SEP algorithms can all compute SEP, maximum relative error of no more than 7%; slightly conservative the χ2 distribution approximation is recommended; MLE calculation values can be used as initial values of the integral operator in order to reduce the number of integral operation, in quickly gets the true value.
Modeling and simulation of aircraft fuel system under the framework of electromechanical integrated management
Yang Bo, Zheng Jie
2013, 39(7): 880-884,889.
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A fuel system simulation platform for a certain aircraft was built by Simulink under the framework of electromechanical integrated management. The principle and realization of each subsystem of simulation platform were expounded. This platform has achieved the basic functions of fuel system including pressure fuelling, engines oil supply and cross oil supply. The fuel oil temperature of different flight stages was simulated by adopting the thermal time constant calculation method. Electrical fault characteristics of the oil pump were simulated and analyzed by modeling method. Test results show that fuel system simulation platform can effectively achieve the actual fuel system features and provide favorable support for optimization of aircraft fuel system in the electromechanical integrated management and for the designs of fault diagnosis and fault tolerance as well.
Pressure losses in gas flow through sudden contractive sharp bends in micro channels
Cao Jiaokun, Ding Shuiting, Du Farong
2013, 39(7): 885-889.
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Flows through sudden-contractive sharp bends in rectangular cross-section micro channels were studied by using finite volume method. Specifically, the effects of Reynolds number and cross-section area ratio on local flow patterns and bend pressure losses were investigated. Reynolds number ranges from 1 to 200 and the characteristic length is 500 μm. Skin frictions mainly contribute to the pressure losses at low Reynolds numbers while flow separation and vortices dominate the losses at high Reynolds numbers. For low Reynolds numbers, the variation of bend pressure loss coefficient with Reynolds number is similar to the loss of a straight channel with the same center-line length, but the bend loss has a smaller value. The sudden-contractive cross section inhibits the flow separation at high Reynolds number and reduces the pressure loss. The velocity profiles at the cross section of the bend were affected by the contraction. Correlations of pressure loss coefficient as a function of Reynolds number and cross-section area ratio were fitted.
Simulation and application on aviators’ lung injury during rapid decompression of cabin
Li Jingwen, Xiao Huajun, Ding Li, Shi Haiwen
2013, 39(7): 890-896.
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Based on the mechanism of aviators' lung injury during rapid decompression of cabin, a non-rigid lung model for rapid decompression by considering the effect of aviator's breath state and clearness of the respiratory tract was established. The calculation and results display were accomplished through C++ program. The change of pressure in lung and the discipline of peak value of pressure in lung were studied using the model built. Verification of the non-rigid lung model was done by comparing it to the experimental data and instances in literature. The zone representing the injuring level was divided according to the peak value of pressure in lung predicted under different decompression conditions. Rapid decompression feature in three typical types of plane (fighter, bomb plane, airline) were discussed. The results provide scientific data for aviator and passengers' protection as well as design for the protective equipment.
Visual features of pilot based on Markov chain under flight simulator
Sun Ruishan, Wang Ning
2013, 39(7): 897-901.
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In order to study the visual features of pilot in difference flight phases, an integrated flight simulator was used to built an experimental platform, and a kind of non-contact eye tracker named FaceLAB4.0 was used to track the data of the tester. The tester was asked to complete the takeoff task. Based on the visual information sources, the visual interested areas of pilot were divided into three parts including instrument panel, outside and others. The data of the tester were recorded and the method of Markov chain was used to analyze state transition probability of the visual gaze data in various visual areas. The study indicates that the pilot is generally need to gaze for a long time, because there are more information clues in cockpit instrument panel and outside areas. This method could be used to analyze pilot's visual attention and its transfer pattern in operation.
Compound control system design based on adaptive backstepping theory
Zhang Tianyu, Dong Changhong
2013, 39(7): 902-906.
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Combat environment for air-defense missile is very complex, for example, high-speed and high- maneuverability. Reaction-jet and aerodynamics compound control and guidance technology is the crucial problem of air-defense missile control and guidance system design. The control law and guidance laws for reaction-jet and aerodynamics compound guidance missile were investigated. A control method based on adaptive backstepping theory was put forward for the non-linear system. Fuzzy logic was applied to the design of compound steering law. A variable structure guidance law was proposed for 3-D terminal interception. Taking an anti-air missile as an example, simulation results show that the guidance and control system is easy to realize and has fine guidance precision for a high-speed maneuvering target, and it proves the effectiveness of the method.
Efficiency coefficient method to solve interval multi-objective linear optimization problems
Wang Chong, Qiu Zhiping
2013, 39(7): 907-911,916.
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Based on the efficiency coefficients, a new interval model and its correlative method for solving multi-objective optimization problems with uncertain parameters in the engineering field were proposed. A group of supplementary variables were introduced to transform the interval objective functions into the forms with deterministic parameters. In terms of the evaluation function deduced from efficiency coefficients, the original multi-objective optimization problem was converted into one with a single objective function. The simplified model was solved respectively under the best case and worst case of the interval constraints, and then the ranges of optimal solution and optimal values were easily obtained. Two numerical examples were given to demonstrate the effectiveness of proposed model and algorithm by comparing their results with probabilistic method.
Optimization design of synchronization mechanism for deployment of spacecraft appendages
Song Shunguang, Wang Chunjie
2013, 39(7): 912-916.
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Dimensional synthesis of the synchronization mechanism for deployment of spacecraft appendages was carried out according to the requirements of the deployment motion. A set of independent variables were selected for deduction of the mathematical model of the mechanism that satisfies the position requirements of the panels in both stowed and deployed states, and the parametric deployment dynamics simulation model was developed for prediction of deployment kinematic and dynamic performances. An optimization model with the objective to minimize the maximum driving torque during the entire deployment process and the constraint to meet the stowed volume envelope requirements was then built. With the nonlinearity characteristic and discontinuous design space, the optimization problem was solved by using the simulated annealing algorithm. The optimal mechanism was finally obtained, which could reduce the maximum driving torque and improves the dynamic performance of the mechanism.
Modeling and control of giant magnetostrictive actuators based on Hammerstein-like model
Liu Ping, Mao Jianqin, Zhang Wei, Zhou Kemin
2013, 39(7): 917-921,926.
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The rate-dependent hysteresis in giant magnetostrictive materials is a major impediment to the application of such material in actuators. A Hammerstein-like model based on the least square support vector machines (LS-SVM) was proposed to model the rate-dependent hysteresis system. It was possible to construct a unique dynamic model in a given frequency range for a rate-dependent hysteresis system using the sinusoidal scanning signals as the training set of signals for the linear dynamic subsystem of the Hammerstein-like model, which guaranteed an outstanding generalization ability of frequency. Subsequently, a proportional-integral-derivative (PID) feedback control scheme combined with a feed-forward compensation was implemented to a magnetostrictive smart structure for real-time precise trajectory tracking. Simulations and experiments on a giant magnetostrictive actuator (GMA) verify both the effectiveness and the practicality of the proposed modeling and control methods.
Integrated navigation method for SINS and odometer
Zhang Xiaoyue, Yang Gongliu, Zhang Chunxi
2013, 39(7): 922-926.
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In order to complete independent navigation for land vehicle, integration of strapdown inertial navigation system (SINS) and odometer was realized based on Kalman filter. Odometer error model was proposed, which was associated with inertial measurement unit(IMU) error model and INS error model, and error model of integration system was established. SINS/odometer integration navigation observation model was established, the compensation method of error estimation was described. The integrated navigation method was validated in a simulation, the simulation results indicate that: in the process of integrated navigation, initial error of attitude could be estimated, and attitude error and position error retained in a certain range, navigation precision was improved compared with the traditional dead-reckoning algorithm, and independent high accuracy position and attitude determination was obtained.
Probabilistic analysis for turbine disc radial displacement
Zhao Heyang, Bai Guangchen, Fei Chengwei, Xing Weizhen
2013, 39(7): 927-931.
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To reasonably design and control blade-tip clearance, the nonlinear and dynamic probabilistic analysis of disk radial deformation was studied based on finite element model (FEM) and response surface method (RSM). Through deterministic analysis of disk deformation considering material nolinear and loads dynamic, the disk radial deformation change with time and the maximum value of disk deformation were gained. It was available to the distribution feature of disk deformation, the failure number and reliability degrees under different radial deformation preset value δ, the limit values of random parameters under different reliabilities and the sensitivities of random parameters influencing the disk radial deformation.
Error analysis and optimal bandwidth design for SINS-aided GPS tracking loop
Ji Xinchun, Wang Xinlong, Li Yafeng
2013, 39(7): 932-936.
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Design of the strapdown inertial navigation system (SINS) aided global positioning system (GPS) tracking loop is the primary process in the realization of the SINS/GPS ultra-tight integration system, and the loop bandwidth selection is the key to balance the performance of tracking loop under different error sources. Firstly, the error sources affecting the tracking performance of the phase lock loop (PLL) were modeled and analyzed. Then, on the principle of minimizing the tracking error of the SINS-aided PLL, an optimal adjustment method of the loop bandwidth according to the carrier-to-noise ratio detected by GPS receiver was proposed to keep PLL in optimal tracking state. Analysis results show that this method can effectively improve the anti-jamming performance as well as the tracking accuracy of the SINS-aided PLL.
Surface roughness of AerMet100 substrate and bond strength between the substrate and HVOF WC10Co4Cr coating
Wang Changliang, Gao Junguo, Tang Zhihui
2013, 39(7): 937-942.
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WC10Co4Cr coating was produced on the AerMet100 alloy by high velocity oxygen fuel srpaying(HVOF). Effect of grit blasting on surface roughness and bond strength between AerMet100 alloy and WC10Co4Cr coating was studied. Influence of fabrication process for the coating on the surface roughness of the substrate was also investigated. The results indicate that the bond strength between AerMet100 alloy and WC10Co4Cr coating made by HVOF is always above 72 MPa when the roughness (Sa) of the substrate is in the range from 0.994 to 4.983 μm. There is no obviously influence on substrate roughness by spraying coating. The slight decrease in the surface roughness of the substrate after spraying was observed when the original Sa is lower than 2 μm and the increase of roughness is also slight when the original Sa is larger than 3 μm. The physical bonding and mechanical bonding contribute to the bond strength between AerMet100 alloy and WCCo coating, and the first one is the main factor.
Stretch bending die clearance influence on forming accuracy to complex section profile
Guo Tao, Li Xiaoxing
2013, 39(7): 943-946.
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The finite element analysis(FEA) method was adopted to simulate the stretch-bending process for complex asymmetric section aluminum alloy profile, and the effect on distortion and the influence of spring back due to die clearance of symmetry and asymmetry was studied. The results show that thickness change to thinner after bending, and the minimum thickness is with little effect from clearance, but the asymmetric will result the change of distortion direction, it will also change after spring back. To improve the forming accuracy by reducing the distortion and spring back, a numerical simulation analysis method was adopted to optimize the right and left clearance on the die. It also provides theoretical evidence for stretch-wrap bending die design.
Lifetime evaluation method with integrated accelerated testing and field information
Wang Lizhi, Jiang Tongmin, Li Xiaoyang, Wang Xiaohong
2013, 39(7): 947-951.
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Accelerated testing is an important method in lifetime prediction. It can obtain enough lifetime information in short time. Sometimes, the lifetime information from the laboratory condition and the one from actual condition are different. To solve the problem above, a Bayesian evaluation method was proposed to integrate the accelerated life testing(ALT) data, accelerated degradation testing(ADT) data and field data together. Calibration method was introduced to calibrate the difference between the different conditions, to evaluate the product's real lifetime more accurately. The statistical inference method was carried out through Markov chain Monte Carlo methods. The proposed method was demonstrated through an example, and relevant analyses were implemented.
Fault detector of fault-tolerant distributed systems based on self-adaptive heartbeat algorithm
Wang Ming, Zhang Chunxi, Yi Xiaosu
2013, 39(7): 952-956.
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The detection of failures is one of the fundamental issues for fault tolerant distributed systems. In order to improve the performance of the fault detection, a novel failure detector called self-adaptive heartbeat detector (SA-HD) was proposed. SA-HD employed a self-adaptive heartbeat detecting algorithm based on pull mode, in which the performance of the failure detection and the network resource caused by heartbeat detecting were both considered. The algorithm could change the frequency of transmitting the heartbeat messages and enhance the adaptability for the network environment, especially in a heavy network payload. The model of SA-HD was built and simulations were carried out to compare the performance between SA-HD and the approach based on push mode. The simulation analysis and experiment results show that the performance of SA-HD is better than the latter’s.
Applying of Groebner bases method in LEO satellite networks routing optimization
Gao Zhijie, Sun Fuchun, Yang Zhian, Yang Dongfang
2013, 39(7): 957-962.
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The multi-objective quality of service(QoS) routing problem in low earth orbit (LEO) satellite networks was convinced as a non-deterministic polynomial complete (NPC) problem. Based on the regular and predictable features of topology changes in low earth orbit (LEO) satellite networks, the Groebner based method was utilized to solve the multi-objective routing problem. The algorithm is able to transform the multi-objective problem into the single-objective problem, and the corresponding single-objective problem can be resolved by shortest path first (SPF) algorithm. Thus the Groebner based method was herein used to solve the multi-objective QoS routing problem, in which the effectiveness of QoS parameters was guaranteed. The performance comparison of the algorithm with Heuristic algorithm and SPF algorithm was evaluated by simulation. The results show that the Groebner based method greatly decreases the difficulty of the calculation and provide more QoS guarantees than traditional algorithms.
Fast recursive adaptive weight stereo matching
Yang Kui, Zhao Yan, Su Qinghua, Deng Nianmao
2013, 39(7): 963-967.
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Stereo matching based on traditional adaptive weight is computational intensive. The basic idea of adaptive weight is that bigger weight should be given to those pixels with less color difference and shorter distance. A novel weight was defined to recursively implement cost aggregation. The weight between neighbor pixels was redefined as the product of distance attenuation factor and color difference function, while the weight between other pixels was redefined as the product of weights between neighbor pixels. Using the proposed weight, cost aggregation was recursively implemented with only 4 multiplications and 8 additions per pixel per disparity. A new fast dense stereo matching was designed based on recursive adaptive weight. Evaluation on the Middlebury’s benchmark proved that the proposed method is faster and more accurate than traditional adaptive weight method.
Fault diagnosis approach based on multiple model estimator with simplified CDKF
Qiu Yueheng, Zhang Weiguo, Zhao Pengxuan, Liu Xiaoxiong
2013, 39(7): 968-972.
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As the direct application of traditional Kalman filter to fault diagnosis of the nonlinear system usually results to low estimation accuracy, a new fault diagnosis approach was proposed. The method combines the multitude model adaptive estimation and the simplified central difference Kalman filter. Therefore, it achieves on-line fault detection rapidly, and makes the state estimation values converge to real values correctly benefits from the replacement of the Jacobian matrix calculation by central difference transformation. Moreover, the repeated process of solving measurement equations and variances is avoided. In the presents of various actuator faults, the simulation results indicate the effectiveness and rapidity of the proposed algorithm compared with the other filters.
Least Wilcoxon learning method based fuzzy tree model
Zhang Wei, Mao Jianqin
2013, 39(7): 973-977.
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Fuzzy tree (FT) method used the least square method to learn the consequent parameters of the fuzzy rules, so it was sensitive to the outliers. The least Wilcoxon learning method was used to replace the least square method and a robust modeling method against (or insensitive to) outliers was proposed based on the least Wilcoxon learning method, called least Wilcoxon-fuzzy tree (LW-FT). The proposed method is not only insensitive to the outliers, but also has the advantages of the FT. Finally, the simulations on Mackey-Glass chaotic time series prediction were performed. The results show that the chaotic time series are accurately predicted, which demonstrates the effectiveness and the robustness to the outliers of this method.
Analog electronic system multiple fault diagnosis based on minimizing-deviation LS-SVR
Xie Lulu, He Yuzhu, Li Jianhong
2013, 39(7): 978-982.
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Aiming at multi-duplicated samples training and excessive training models in the process of multi-classification with standard support vector machine, and insuring high integral and partial diagnosis accuracy for analog electronic system, a multiple fault diagnosis method based on minimizing-deviation least squares support vector regression (MDLS-SVR) was proposed. With the square of deviation between the dimension fitting error and the average fitting error of the sample introduced to mimize the spacing between each dimension of the output variable, a new multiple-output least squares support vector regression was finally obtained which had high resolution for prediction results. Then through multiplying the model output by pre-set multi fault modes, the corresponding multiple fault mode to which the maximum value in the result set mapped was just the final diagnosis result. The simulation results show that, the new method simplifies the training process and could keep high integral and partial diagnosis accuracy under small sample set.
Simulation method for PBIT fault detection and false alarm reduction based on stateflow
Li Haiwei, Shi Junyou, Liu Hongtao
2013, 39(7): 983-989.
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Aiming at the application requirements of built-in test (BIT) technology in equipment design for testability and prognostic and health management (PHM), a method of periodic BIT (PBIT) simulation based on stateflow was proposed. The fault detection features and fault alarms problem were analyzed, and the simulation principle of PBIT was given. Based on the simulation of power-on BIT (POBIT), the simulation elements of PBIT were analyzed, as well as the stateflow chart objects simulation mode of those elements, and the modeling of faults injection, interferences injection and false alarm reduction measures were implemented. Finally, the flow of modeling and simulation for PBIT was given, including the flow of simulation input dataset design. A typical avionic module PBIT was taken as the case, the stateflow model of power board, interferences, PBITs and false alarm reduction measures were built. The simulation results show that this method contributes to realizing the dynamic logic process simulation of PBIT in fault detection and false alarm reduction effectively.
Pruning the Volterra series for behavioral modeling of power amplifiers
Liao Yi, Su Donglin, Wu Qi, Song Xinwei
2013, 39(7): 990-994.
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General Volterra series based models are limited to weakly nonlinear systems due to their high complexity. It involves a great number of coefficients for behavioral modeling of power amplifier with strong nonlinearities and long memory effects. The behavioral modeling of radio frequency (RF) power amplifiers was studied. A pruned Volterra series based model was proposed by introducing a ‘near-diagonality’controlling factor and a ‘dynamic deviation reduction’ controlling factor simultaneously to remove the coefficients which are not sensitive to the output error. The pruning approach could effectively reduce the model complexity and save time for parameters extraction under the condition of the model fidelity required. A 10 W RF power amplifier was employed for providing input and output data which were used in model extraction and validation. The agreement obtained between the output response of simulated circuit and model validates the pruned model is flexible and effective.

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