非线性三维自适应模糊变结构制导规律的研究

在三维球坐标系下建立了导弹与目标的相对运动模型,针对大机动目标提出了一种 基于零化导弹与目标视线角速度的三维自适应模糊变结构末制导律。所设计的制导律通过模 糊系统对非线性模型进行逼近,克服了模型不确 定性和外界干扰对制导系统的影响,并把目标加速度视为一类有界干扰,在线对目标加速度 的界进行估计。通过计算机数字仿真验证了导弹与目标的相对视线角速度最终趋向于零,验 证了制导规律的正确性和有效性。     

存在记忆非线性效应的功率放大器自适应线性化仿真

文章对两种常用的描述功率放大器的记忆效应和非线性特征的模型——W—H模型和记忆多项式模型进行了自适应线性化仿真,采用AM／AM和AM／PM失真特性对由于功放特性不理想而引起的放大信号的振幅畸变及相位偏移进行描述,运用自适应预失真处理方法,进行记忆预失真的模拟,并用误差矢量值（EVM）衡量这种自适应预失真方法的效果。仿真结果表明,文中的自适应预失真方法对上述两种记忆功放模型具有较好的线性化效果。     

基于角速度观测器的卫星编队飞行相对姿态控制技术

建立了卫星编队飞行的相对姿态动力学和运动学模型。利用积分反步法,设计了能够保     

多级嵌套维纳滤波自适应降维STAP抗干扰方法研究

在分析多级嵌套维纳滤波（MSNWF）给出的干扰子空间和噪声子空间信息的基础上,提出了多级嵌套维纳滤波自适应降维空时自适应处理（STAP）抗干扰算法。该方法分析了MSNWF前向迭代过程中相邻级期望信号的协方差随迭代次数变化关系,结合干扰子空间和噪声子空间信息自适应地确定迭代次数,在不增加额外计算量的条件下实现了降维维数的自适应选择。仿真结果分析表明,该方法在保证抗干扰性能不受影响的前提下,进一步减小了STAP算法的计算量,提高了算法的实时性。
     

中高层大气行星波与惯性重力内波的非线性相互作用

在弱非线性理论基础上,将三维大气中行星波和惯性重力波从原始非弹性近似方程中分离出来,讨论了典型的2天行星波与惯性重力内波的非线性相互作用过程.从共振曲面和参量不稳定增长率来看,行星波倾向于与空间尺度较大的惯性重力波发生相互作用.利用潮汐波的等价重力波假设,讨论了2天行星波与半日潮及9.6h惯性重力波的相互作用,三波相互作用时能量守恒.非线性相互作用使2天波和潮汐波的波幅受到长期调制.      

Prediction of pilot workload in helicopter landing after one engine failure

This paper presents a method to predict the pilot workload in helicopter landing after one engine failure. The landing procedure is simulated numerically via applying nonlinear optimal control method in the form of performance index, path constraints and boundary conditions based on an augmented six-degree-of-freedom rigid-body flight dynamics model, solved by collocation and numerical optimization method. UH-60A helicopter is taken as the sample for the demonstration of landing after one engine failure. The numerical simulation was conducted to find the trajectory of helicopter and the controls from pilot for landing after one engine failure with different performance index considering the factor of pilot workload. The reasonable performance index and corresponding landing trajectory and controls are obtained by making a comparison with those from the flight test data. Furthermore, the pilot workload is evaluated based on wavelet transform analysis of the pilot control activities. The workloads of pilot control activities for collective control, longitudinal and lateral cyclic controls and pedal control during the helicopter landing after one engine failure are examined and compared with those of flight test. The results show that when the performance index considers the factor of pilot workload properly, the characteristics of amplitudes and constituent frequencies of pilot control inputs in the optimal solution are consistent with those of the pilot control inputs in the flight test. Therefore, the proposed method provides a tool of predicting the pilot workload in helicopter landing after one engine failure.     

Intelligent modeling and identification of aircraft nonlinear flight

In this paper, a new approach has been proposed to identify and model the dynamics of a highly maneuverable fighter aircraft through artificial neural networks（ANNs）. In general, aircraft flight dynamics is considered as a nonlinear and coupled system whose modeling through ANNs, unlike classical approaches, does not require any aerodynamic or propulsion information and a few flight test data seem sufficient. In this study, for identification and modeling of the aircraft dynamics, two known structures of internal and external recurrent neural networks（RNNs） and a proposed structure called hybrid combined recurrent neural network have been used and compared.In order to improve the training process, an appropriate evolutionary method has been applied to simultaneously train and optimize the parameters of ANNs. In this research, it has been shown that six ANNs each with three inputs and one output, trained by flight test data, can model the dynamic behavior of the highly maneuverable aircraft with acceptable accuracy and without any priori knowledge about the system.     

Recent advance in nonlinear aeroelastic analysis and control of the aircraft

A review on the recent advance in nonlinear aeroelasticity of the aircraft is presented in this paper. The nonlinear aeroelastic problems are divided into three types based on different research objects, namely the two dimensional airfoil, the wing, and the full aircraft. Different non- linearities encountered in aeroelastic systems are discussed firstly, where the emphases is placed on new nonlinear model to describe tested nonlinear relationship. Research techniques, especially new theoretical methods and aeroelastic flutter control methods are investigated in detail. The route to chaos and the cause of chaotic motion of two-dimensional aeroelastic system are summarized. Var- ious structural modeling methods for the high-aspect-ratio wing with geometric nonlinearity are dis- cussed. Accordingly, aerodynamic modeling approaches have been developed for the aeroelastic modeling of nonlinear high-aspect-ratio wings. Nonlinear aeroelasticity about high-altitude long- endurance （HALE） and fight aircrafts are studied separately. Finally, conclusions and the chal- lenges of the development in nonlinear aeroelasticity are concluded. Nonlinear aeroelastic problems of morphing wing, energy harvesting, and flapping aircrafts are proposed as new directions in the future.     

滚弯成形解析建模与数值分析

建立了考虑材料塑性强化的滚弯成形力学分析解析模型,推导出了应力应变、残余应力以及回弹半径计算公式.基于非线性有限元软件,对滚弯成形进行了动态模拟,对应力应变状态、塑性应变分布、残余应力以及回弹等进行了分析计算,结果表明:板料滚弯成形初始效应明显,下压点附近曲率不均匀;采用足够的滚弯时间后,中间段的曲率均匀度很好;成形半径与上辊下压量呈近似幂函数关系;多道次滚弯可以减小两端的曲率波动和最大应力应变.最后通过与滚弯成形试验数据的对比,分析和验证了解析模型与数值模型的适用性和精度.     

Ion- and electron-acoustic solitons and double layers in multi-component space plasmas

A general model for the ion- and electron-acoustic solitons and double layers in a multi-component unmagnetized plasma consisting of background electrons, counter-streaming electron beams and ions is discussed. The model is based on the multi-fluid equations and the Poisson equation, and uses the Sagdeev pseudo-potential techniques. For identical counter-streaming electron beams and depending upon the plasma parameters, three types of solutions, namely, ion-acoustic, slow and fast electron-acoustic soliton/double layer, are possible. Generally, the ion acoustic solitons have positive potentials, slow-electron acoustic solitons have negative potentials and fast electron-acoustic solitons and double layers can have either positive or negative potentials depending on the core electron density. As beam speed is increased, first ion-acoustic and then slow electron-acoustic solitons disappear. At large beam speed, only fast electron-acoustic solitons/double layers survive. The results may be relevant to the observations of the electrostatic solitary waves (ESWs) observed in the Earth’s magnetosphere.