针对产品间同质化严重的问题,尤其是同型号同批次的产品数量庞大且存在产品标识因磨损、污染等因素不可识读而造成产品之间特征差异小、无法辨识的问题,提出一种防止追踪失效的同质化产品标识特征设计方法。分析了特征强化的零件直接标识,提出基于标刻工艺方法和仿射变换的数据矩阵码特征设计,从源头增强了个体间的特征差异性,同时提出基于灰度共生矩阵的数据矩阵码纹理特征设计,建立了产品制造过程数据矩阵码纹理库。当标识发生失效时,采用汉明距方法和欧式距离法级联匹配目标特征和数据矩阵码标刻特征矩阵、制造过程纹理库的相似度。实例结果表明,该方法能够较好地防止同质化产品追踪失效。

针对离散制造企业生产环境和工艺的复杂性容易引起Data Matrix二维符号标记的磨损、污染和腐蚀而发生标识失效的问题,提出一种基于D-S证据理论的产品多信息融合标识失效补救方法。分析了产品物理与制造过程中多源信息之间的关联和数据结构,建立了离散制造产品零散与不完整多源信息的数学模型;设计了改进的变异系数加权法,并采用基于类中心的变权欧式距离法对失效标识产品特征和历史数据库进行相似性测度计算;通过D-S证据理论对失效标识的产品特征层进行融合辨识。实验结果表明,该方法能够较好地恢复补救产品失效的标识。

In this paper we present a method for extracting the best candidate edge combination based on multi-features fusion, aiming at the challenges of accurately locating the Data Matrix (DM) code (hereinafter referred to as DM code) with pollution and perspective deformation. Firstly, DM code edges are transformed from image into Hough domain in which linear feature is more prominent. We are able to obtain the valid combinations of candidate marginal points after prior rules-based filtering. Then, we design and extract four boundary features of the finder pattern in image domain. Meanwhile, we establish the model of distorted DM code edge distribution in Hough domain and extract the corresponding features. Finally, we merge the multi-features according to the D-S theory and make the final locating based on the fusion result. Compared with traditional methods, the experiments demonstrate the greater robustness and flexibility of our proposed approach to accurately detecting the contaminated Data Matrix coexisted with perspective deformation.

To resolve the problem of the distortion of the 2-D barcode on the cylindrical surface,surface distortion model is setted up to correct the barcodes based on the automatic reading system of the two-dimensional barcode in the surface of tools.Moreover,considering some barcodes cannot display in one image,the missing barcode image based on image mosaic is recovered.First,the overlapped areas with related phase as the range of the feature collecting is estimated.Second,the SIFT points of related areas are collectted and the SIFT features with the algorithm of approximate nearest neighbor are matched.Third,the original images are revovered by using the step-in-step-out method.The experiments show that the algorithm improves the efficiency of the 2-D barcode reading.

Inertial navigation system has many advantages such as strong independence,high update rate,good realtime performance,but the system error will accumulate with time.GPS will limit the error within a certain range,but the data update is slow and vulnerable to outside interference.Low-cost navigation system,which consists of IMU,GPS and magnetic heading meter,is becoming a research hotspot.A low-cost small AHRS is consructed.In order to apply theory into practice,taking into account the impact of time delay on the system,a 10 dimensional Kalman filter for navigation is designed.The actual measurement data are used to simulation.In a series of ground test,it is shown that the system accuracy and stability meet navigation requirements.

Fly-by-ware is the symbol of modern advanced aircraft.Redundancy is a key means to improve the reliability and safety of fly by wire control system.Some basic concepts on the monitor,the traditional four-redundant control algorithm and a modified four-redundant analog volume monitor algorithm are described in detail.This method can verify the validity of the signal more accurately,can reduce the probability of signal into the multi-fault logic to judge the situation.Simulation have shown that this modified monitor algorithm is rational,reliable and simple.

As a new intelligent algorithm,AFSA is capable of overcoming local maxima and obtaining global minimum.And AFSA also have advantages in adaptive capacity of searching space,faster searching and without objective algorithm function gradient during implementation,which make AFSA applicable to a variety of airfoil design optimization.AFSA is combined with the numerical solution of N-S equations,relying on computational fluid dynamics(CFD) calculation technique to optimal design the airfoil shape in aerodynamic fields.Linear superposition of analytic functions based on Hicks-Henne shape function is used for airfoil shape description.Airfoil NACA0012 and RAE2822 are optimal designed using the algorithm mentioned above,the results reveal that the method developed is well applicable to the optimization of a variety of airfoil design.

In the complex application environment of fuzzy sound tracking,the source direction,amplitude and phase fuzzy problems were inevitably existed in signal processing from microphone arrays,so a kind of adaptive noise cancellation algorithm based on acoustic lenses particle swarm algorithm was proposed.Speech signal was collected through the acoustic lenses beam-forming technology,particle swarm algorithm was applied in adaptive noise cancellation to solve the fuzzy problems.Matlab simulation results show that this algorithm has better denoising ability and performance than the traditional method,SNR is also greatly improved,and the fuzzy problems of speech data can be solved effectively.

Aiming to study the optimal number of spars in the aircraft wing conceptual design process,this paper offered a new layout optimization method in detail for practical aircraft engineering,the problem of layout optimization was decomposed into two subsystem problems: sizing optimization and topology optimization.The matured criteria method was used to solve the first problem and the latter was transfered to the 0/1 program problem of N spars which was solved by ground structure approach combined an improved ant colony algorithm.With the introduction of the past ant-route database,the unnecessary repeated computation of objection can be avoided and therefore the effectiveness was improved greatly.Finally,the optimal number of wing spars and the optimal size of component of wing were achieved simultaneously when the ant colony reached convergence.The numerical example shows that the method proposed is effective and feasible for solving complex optimization and has good efficiency in the cutting of weight.

A modal control method based on discrete identification model was proposed in order to resolve interior uncertainty of actual control plant. The modal control method for linear discrete plant of complete state vector information was studied by using discrete standard binominal as system standard eigenequation. A methodology constructing modal control system of linear plant based on discrete identification model was proposed. Analysis results which eigenroot parameters influenced on system performance were given. The method characters are that it is easy to constructing and engineering implementing.

In order to ensure that the second differential matrix of Newton-Raphson algorithm used in every iterative step is always positive to improve convergence rate and iterative precision,two points are developed for improving Newton-Raphson algorithm: on the one hand,the second differential matrix is modified to become a positive matrix,which enhances its convergence rate;on the other hand,a revising factor is adopted to revise the iterative result,which advances its iterative precision.The simulation results dicided by using improved Newton-Raphson algorithm indicates that the precision of results is better and its convergence rate is faster.Therefor,the simulation results verify that the improved method is correct and effective.

Before the flight control computer is used in UAV,it is necessary to make a comprehensive test.In this paper,a hardware-in-the-loop simulation system was developed,the main simulation system based on embedded operation system RTLinux and simulation tool software Matlab was developed and debugged.The Simulink toolbox of matlab was used to establish a plane simulation system model.The code generation toolbox was used to translate it to C code.The simulation models were constructed rapidly and model parameters were adjusted on-line.The hardware-in-the-loop simulation results can satisfy flight quality standards and really and reliably display flight process of UAV.

Proposes an image super-resolution algorithm that takes into account inaccurate estimates of the registration parameters and the point spread function.There inaccurate estimates result in different noise level for each Low-Resolution(LR) frames.In the proposed algorithm,the LR frames are adaptively weighted according to their reliability.Using gradient descent optimization procedure,the weights are iteratively updated along with the high-resolution image.Experiment results indicate that this method is better than the conventional MAP methods on objective statistical analysis.

As a new technology of network measurement,network tomography refers to the inference of internal network characteristics using external end-to-end measurement.Thus it overcomes traditional network measurement's shortcomings.Inference analysis theory plays a central role in studies of network tomography and influences directly network measurement's computation complexity and inference veracity.This paper introduces network tomography's basic conceptions and discusses recent inference analysis theory in detail.Finally,it presents some topics to be further studied in this field.

Taking the aerofoil structure as the object of study,a kind of hybridization algorithm that could settle synchronistically the optimizations of element's position and of dimensions was put forward.Using MSC.NASTRAN to carrying out dimensional optimization,utilizing genetic algorithm to carrying through optimization on variables of positional design,and take the result of dimensional optimization as the foundation of genetic operation thus finally realized the synchronized optimizations of dimension and position.In order to enhance the efficiency of algorithm,the nonlinear mapping function of neural network was used to carrying out mapping on the result of dimensional optimization of MSC.NASTRAN so as to replace its optimization processes.The result of calculating example showed that the being mentioned method is highly active,accurate and possesses good application value of popularization.

The paper introduces an improved terrain-entropy navigation algorithm. The primary bug of this algorithm is that it discards the relative position information of terrain data and the normalized processing. Based on this, a sandia inertial terrain aided navigation method for Kalman filter is offered and the maximization of mutual information is synthesized, the performance of terrain-entropy algorithm is improved. Lastly the simulated digital maps are produced by computer on topography of Weierstrass-Mandelbrot function on matlab for simulation. Better results are obtained by simulation.

It is quite important for saving and communicating the flying control data in aviation.The data integrating of flying data depends on uniform format and powerful expressing means.XML(extensible markup language) is competent for the requirement for its agility and opening.Firstly,the study on the resolution method of XML is shown,then the flying data integrating and accessing saving by use of XML are explained.The method enables the promptness and extensibility for the flying control information.

A project of semi-physical simulation for TF/TA is brought forward.This simulation system includes three parts:two computers and one target system.Host computer manages running status of target system and scape sys- tem,at same time run digital map and configure simulation parameters.Algorithm of TF/TA run on VxWorks opera- tion system based on target system.Another computer accomplishes simulation for scape.By this platform,we can val- idate algorithm of track layout and terrain matching.

The terrain following/terrain avoidance flight trajectory planning is a key technology of low altitude penetration system.The planning track that is gotten from dynamic programming algorithm sometimes can not achieve the aimed target.Aiming at this problem,an advanced dynamic programming of optimal flight trajectory planning is presented,and through gridding digital map and establishing directed graph to improves the dynamic programming algorithm,which makes the optimal track effectively avoid these obstacles and threats.The result of simulation implies that the algorithm of flight trajectory planning mentioned is very effective.

The parameterized model of aircraft wing was achieved under Patran environment by the use of PCL(Patran Command Language).The optimization model contains two kinds of designing variables: geometric position variable and geometric dimension variable.On the bases of adopting Nastran software to realize optimization of geometric dimension and combining with the designing method of even experiment and utilizing the high degreed nonlinear mapping function of neural network this paper established the mapping relationship between objective function and positional designing variables.The optimization program was compiled by using the modified feasible directional method under Matlab environment,and completed the optimization on the position of wing beam,and finally achieved the layout optimization design of the entire aircraft wing.It can be seen through this paper that let the parameterized modeling be combined with the function of neural network to carry out structural optimization could give the reins to the mapping function of neural network nicely and let the result of optimization be more precise and effective.The method provided in this paper could be able to solve the optimization problem of complicated structural positional variables under the Patran environment,thus counteracted the deficiency point of this software and let it possesses pretty good applicable popularization value.