基于静气动弹性效应的飞机型架外形修正方法研究

民用客机主要针对巡航外形设计,这就需要通过静气动弹性修正得到型架外形,保证型架外形在设计巡航状态飞行时,气动性能能够恢复到巡航设计状态。本文基于混合网格的N-S方程和结构柔度矩阵方法的耦合求解,发展了大飞机静气动弹性计算方法。根据静气动弹性变形过程的可逆性,结合飞行器质量分布、发动机推力以及巡航飞行重量等设计参数,发展了考虑静气动弹性效应的飞机型架外形修正方法。利用所发展的修正方法,获得了某大型客机巡航飞行的型架修正外形,同时分析了其它飞行工况的弹性气动特性,并通过算例比较验证了本文发展方法的有效性。     

Enhanced ultrasonic total focusing imaging of CFRP corner with ray theory-based homogenization technique

Ultrasonic testing is effective in defect characterization and quality assurance of Carbon Fiber Reinforced Plastic (CFRP) components in the aerospace industry. Due to the coupling between complex shape and elastic anisotropy, the Phased Array Ultrasonic Testing (PAUT) and time-based Total Focusing Method (TFM) face significant challenges in the calculation of wave propagation. A wave velocity distribution model is established for a multidirectional convex corner of CFRP based on a homogenization theory and the above coupling effects are also incorporated. A ray-tracing method is proposed based on Dijkstra’s shortest path search algorithm. The predicted time of flight ensures that this technique, the homogenized TFM, could synthesize a high-quality focused image by post-processing on the full matrix capture data. Experiments on a laminate with three ?1.5 mm Side-Drilled Holes (SDHs) in different circumferential directions confirm a successful homogenized TFM imaging that all SDHs can be effectively detected. As compared to the isotropic scenario, the maximum positioning error is reduced to 0.12, 0.08, and 0.38 mm, and the Signal-to-Noise Ratios (SNRs) are increased by 2.1, 1.1, and 11.8 dB, respectively. It is suggested that the ray-tracing assisted TFM technique can effectively improve the imaging of corners in CFRP components.     

A point cloud deep neural network metamodel method for aerodynamic prediction

Aiming to reduce the high expense of 3-Dimensional (3D) aerodynamics numerical simulations and overcome the limitations of the traditional parametric learning methods, a point cloud deep learning non-parametric metamodel method is proposed in this paper. The 3D geometric data, corresponding to the object boundaries, are chosen as point clouds and a deep learning neural network metamodel fed by the point clouds is further established based on the PointNet architecture. This network can learn an end-to-end mapping between spatial positions of the object surface and CFD numerical quantities. With the proposed aerodynamic metamodel approach, the point clouds are constructed by collecting the coordinates of grid vertices on the object surface in a CFD domain, which can maintain the boundary smoothness and allow the network to detect small changes between geometries. Moreover, the point clouds are easily accessible from 3D sensors. The point cloud deep learning neural network, which employs re-sampling technique, the spatial transformer network and the fully connected layer, is developed to predict the aerodynamic characteristics of 3D geometry. The effectiveness of the proposed metamodel method is further verified by aerodynamic prediction and robust shape optimization of the ONERA M6 wing. The results show that the proposed method can achieve more satisfactory agreement with the experimental measurements compared to the parametric-learning-based deep neural network.     

航天器大尺度部件折叠展开原理分析及应用

围绕航天器向大尺度、远距离发展所涉及的大尺度部件在轨展开技术中新工艺、新材料、新结构等，对现有航天器大尺度部件的折展机构进行了统计与分析，系统梳理了在轨航天器折展机构的技术参数、结构与组成等。介绍了折纸艺术、自回弹材料与记忆合金等新工艺、新材料在航天器太阳帆板、天线等大尺度部件上的应用。重点分析并梳理了新型结构的特性及其工作原理，包括：充气展开式、单轴旋转式、径向扩展式、单元重构式、延长伸展式等。最后，结合即将开展的载人登月与月球基地建设、太阳系探测等深空探测任务，对在轨航天器大尺度部件的折展结构与机构的发展趋势进行了展望。     

基于运行模态的复合材料梁脱层损伤识别

为了实现复合材料结构损伤的定位与定量识别,利用传递率函数的运行模态分析方法探讨了复合材料梁无损检测方法,通过对加速度传递函数的最小二乘拟合,得到结构的模态频率和阻尼,对传递率函数矩阵奇异值分解,得到结构的振型.运用曲率模态(CMS)和曲率模态变化率(CMSI)作为损伤指标,对具有单损伤、多损伤和不同损伤程度的复合材料梁...     

光纤环非互易相位误差尾纤补偿方法研究CSCD

针对光纤环的热致非互易误差的补偿方法进行研究,并通过仿真分析与实验验证,证明了某种光纤环尾纤长度与光纤环热致非互易误差之间的关系。根据等效介质理论和Mohr理论,建立了光纤环热致非互易相位误差仿真分析模型,并利用该模型计算了不同温度环境条件下,某类型光纤环顺逆时针方向光纤长度发生变化时,陀螺仪输出的全温零位漂移的变化量。仿真及实验结果表明,在1℃/min温变速率条件下,总长约800m的光纤环圈顺逆时针方向光纤长度相差约0.5m时,光纤环全温零位漂移量缩小了0.4(°)/h。研究结果得出了针对此类型的光纤环,当光纤环尾纤每减少0.5m,其热致非互易相位误差减小0.4(°)/h的规律。该项研究成果为后续优化光纤环的全温精度奠定了基础。     

基于改进狼群算法的多无人机协同多目标分配CSCD

针对现代空战多无人机协同多目标任务分配问题,结合标准狼群算法,提出了一种改进狼群算法的多目标任务分配方法。根据狼群的不同分工以及搜索属性,建立了基于自主游走机制的头狼产生规则、基于多策略知识库的探狼游走机制和基于自适应步长的猛狼奔袭及围攻方式,从而对传统狼群算法的随机性进行智能化约束与控制,以解决多无人机协同多目标任务分配问题。数值仿真结果表明,该方法能够快速有效获得任务分配方案,避免陷入局部最优。     

Collaborative force and shape control for large composite fuselage panels assembly

This study proposed a force and shape collaborative control method that combined method of influence coefficients(MIC) and the elitist nondominated sorting genetic algorithm(NSGA-II) to reduce the shape deviation caused by manufacturing errors, gravity deformation,and fixturing errors and improve the shape accuracy of the assembled large composite fuselage panel. This study used a multi-point flexible assembly system driven by hexapod parallel robots. The proposed method simultaneously considers...     

Lift enhancement based on virtual aerodynamic shape using a dual synthetic jet actuator

The Dual Synthetic Jet Actuator (DSJA) is used to develop a new type of lift enhancement device based on circulation control, and to control the flow over the two-dimensional (2D) NACA0015 airfoil. The lift enhancement device is composed of a DSJA and a rounded trailing edge (Coanda surface). The two outlets of the DSJA eject two jets (Jet 1 and Jet 2). Jet 1 ejects from the upper trailing edge, which increases the circulation of airfoil with the help of the Coanda surface. Jet 2 ejects from the lower trailing edge, which acts as a virtual flap. The Reynolds number based on the airfoil chord length and free flow velocity is 250000. The results indicate that the circulation control method based on Dual Synthetic Jet (DSJ) has good performance in lift enhancement, whose control effect is closely related to momentum coefficient and reduced frequency. With the increase of the reduced frequency, the control effect of the lift enhancement is slightly reduced. As the momentum coefficient increases, the control effect becomes better. When the angle of attack is greater than 4°, the increments of lift coefficients under the control of DSJ are larger than those under the control of the steady blowing at a same momentum coefficient. The maximum lift augmentation efficiency can reach 47 when the momentum coefficient is 0.02, which is higher than the value in the case with steady blowing jet circulation control.     

Calculating the simultaneous effect of ion dynamics and oscillating electric fields on Stark profiles

We calculate hydrogen line shapes resulting from the simultaneous Stark effect of the plasma microfield and an oscillating electric field. Like laboratory plasmas, many kinds of space plasmas are affected by oscillating electric fields with a magnitude similar to that of the microfield. Here we focus on conditions where we expect that the effect of ion dynamics and oscillating electric are both significant. The combined effect of their dynamics on the quantum emitter is retained by a computer simulation coupled to a numerical integration of the Schrödinger equation. Our calculations are applied for conditions and transitions where significant changes in the line shape allow for a diagnostic of the plasma and oscillating field.