Zadeh模糊推理算法的直觉化扩展

对Zadeh模糊推理算法进行了直觉化扩展.将Zadeh定义的模糊关系Rm进行直觉化扩展,推出了其对应的直觉模糊取式推理算法和直觉模糊拒式推理算法.以具体算例叙述了推理计算过程中的细节,验证了方法的正确性和有效性,并依据直觉准则,对其性能进行了评价.     

Aircraft robust multidisciplinary design optimization methodology based on fuzzy preference function

This paper presents a Fuzzy Preference Function-based Robust Multidisciplinary Design Optimization (FPF-RMDO) methodology. This method is an effective approach to multidisciplinary systems, which can be used to designer experiences during the design optimization process by fuzzy preference functions. In this study, two optimizations are done for Predator MQ-1 Unmanned Aerial Vehicle (UAV): (A) deterministic optimization and (B) robust optimization. In both problems, minimization of takeoff weight and drag is considered as objective functions, which have been optimized using Non-dominated Sorting Genetic Algorithm (NSGA). In the robust design optimization, cruise altitude and velocity are considered as uncertainties that are modeled by the Monte Carlo Simulation (MCS) method. Aerodynamics, stability and control, mass properties, performance, and center of gravity are used for multidisciplinary analysis. Robust design optimization results show 46% and 42% robustness improvement for takeoff weight and cruise drag relative to optimal design respectively.     

Prediction of aerodynamic characteristics of an aircraft model with and without winglet using fuzzy logic technique

This paper describes the potentials of an aircraft model without and with winglet attached with NACA wing No. 65-3-218. Based on the longitudinal aerodynamic characteristics analyzing for the aircraft model tested in low subsonic wind tunnel, the lift coefficient (CL) and drag coefficient (CD) were investigated respectively. Wind tunnel test results were obtained for CL and CD versus the angle of attack α for three Reynolds numbers Re (1.7×¹⁰⁵, 2.1×¹⁰⁵, and 2.5×¹⁰⁵) and three configurations (configuration 1: without winglet, configuration 2: winglet at 0° and configuration 3: winglet at 60°). Compared with conventional technique, fuzzy logic technique is more efficient for the representation, manipulation and utilization. Therefore, the primary purpose of this work was to investigate the relationship between lift coefficients and drag coefficients with free-stream velocities and angle of attacks, and to illustrate how fuzzy expert system (FES) might play an important role in prediction of aerodynamic characteristics of an aircraft model with the addition of winglet. In this paper, an FES model was developed to predict the lift and drag coefficients of the aircraft model with winglet at 60°. The mean relative error of measured and predicted values (from FES model) were 6.52% for lift coefficient and 4.74% for drag coefficient. For all parameters, the relative error of predicted values was found to be less than the acceptable limits (10%). The goodness of fit of prediction (from FES model) values were found as 0.94 for lift coefficient and 0.98 for drag coefficient which were close to 1.0 as expected.     

飞控系统故障检测的参数模糊自适应调节

提出通过模型参数的模糊比例积分自适应调节，以校正基于模型的飞控系统故障检测中的系统数学模型偏差。针对模型中误差差较大的迎角导数值，将俯仰角加速度的测量值与教学模型估计值之差作为比例积分调节的反馈量，动态实时校正数学模型参数。     

某型穿甲弹试验模态分析

本文通过试验模态分析的方法，得到了某型反坦克穿甲弹的结构参数，进而为了解该穿甲弹的动态特性以及改进弹体的结构提供了依据。     

INTERNET网检工具逻辑算符及检索表达式优化

对ＩＮＴＥＲＮＥＴ网检工具逻辑算符进行分析和比较。在此基础上，提出制定和优化检索表达式的方法。     

基于有限元方法的并联机床模态分析

并联机床的模态分析有着重要的意义。本文针对3—HSS型并联机床,利用大型有限元软件ANSYS,对此并联机床进行了模态分析,分别获得了该机床的低阶固有频率及其对应的振型图,通过振动动画,分析了六阶模态的振动规律,找到了机床的薄弱环节,为机床的结构设计和动力学分析提供了依据。     

权力制约：经典范式、内在逻辑与语境化

实质意义上的权力制约肇始于权力分化之后，历经以道德制约权力、以权力制约权力、以社会制约权力等经典范式，体现了权力制约活动从关注权力执掌者、权力本体到关注权力归属者不断演变的内在逻辑。植根于我国国情的权力制约实践在伦理学、社会学途径方面与西方存有共性，但于政治学途径却存有个性。实现我国权力制约的语境化既需要体现权力制约的普遍性规律，更需要把握马克思主义政治观视域下权力制约的特殊性。     

多值逻辑函数最小化的McCluskey—Quine方法改进及程序实现

多值逻辑电路的发展，使得以往的化简方式已不能适应电路取值的增高和函数项的增加。本文以三变量三值函数为例，讨论了多值逻辑电路化简的物理背景，采用改进的McCluskey-Quine方法进行最小化的算法，以及质蕴含项覆盖问题的求解，并给出了程序流程。由于该程序采用的面向对象技术，经过适当扩展可以应用于多变量多值函数。