一种新颖的直升机舵回路故障诊断方法

研究了基于案例推理的直升机舵回路在线故障诊断方法。针对传统的CBR方法一般采用离散数据和符号向量来建立案例的不足,提出了动态系统多源异类信息的案例表达方法,利用系统特性集、征兆集和特征集混合模型作为案例的条件属性。在此基础上,研究了案例检索的综合相似性度量方法。最后,将上述方法在某型直升机的俯仰舵回路进行了试验验证,结果表明,该方法可以诊断出舵回路的控制参数漂移故障,为复杂动态系统的故障诊断提供了一种有效的新途径。     

一种基于波形弹簧的空间驱动机构轴承预紧力研究

基于波形弹簧提出了一种针对空间驱动机构角接触轴承的预紧力方法；文中对波形弹簧进行了设计，对波形弹簧进行了常温、耐压后、高低温刚度试验，验证了波形弹簧刚度的稳定性；然后将波形弹簧安装在驱动机构中，使用压力传感器监测波形弹簧施加在轴承上的预紧力；最后将驱动机构连同波形弹簧、压力传感器进行了高低温试验。试验表明，该种方式对轴承施加的预紧力，在高低温条件下性能稳定，具备一定的工程可行性。     

在主减速器斜撑杆上安装压电叠层作动器的直升机主动隔振

采用安装在主减斜撑杆上的压电叠层作动器建立了直升机主动隔振系统。基于压电材料本构关系推导了压电叠层作动器的驱动方程,建立了压电叠层作动器驱动的主减主动隔振系统动力学模型。采用了自适应滤波控制方法,通过最小均方算法实现了自适应控制。直升机主动隔振仿真实验表明了该系统具有高效的隔振效果。     

空间失稳目标线阵雷达成像机理及三维重建

利用线阵激光雷达载荷小、抗干扰能力强等优势，研究空间失稳目标动态测量技术。探究线阵激光雷达成像机理，建立空间失稳目标运动模型，提出基于双切片法的目标可测区域提取机制，实现线阵激光雷达对空间失稳目标的驻留观测扫描；以ICP(Iterative closest point)配准结果为先验信息，提出逆序重建方案，建立重建点云精度以及平均密度评价机制，分析数据冗余对重建精度的影响，采用采样降维的方法进行配准重建计算，提高重建结果精度；最后进行仿真实验检验分析，实验结果表明空间目标可测部位数据提取合理准确，数据输出频率可达 1 Hz ，重建结果满足任务指标要求，重建点云平均密度达到19 mm，重建点云精度达到90 mm，为地面验证及在轨应用提供数据支撑和参考。     

Integrated design of topology and material for composite morphing trailing edge based compliant mechanism

The morphing trailing edge based compliant mechanism is a developing technology which can increase lift-drag ratio for variable flight modes by bending down the trailing edge. Composite material design is integrated into topology optimization for the morphing trailing edge based compliant mechanism in the paper. A two-step optimization strategy is established to solve the integrated design problem. Initially, lamination parameters are introduced and viewed as a bridge between structure stiffness and fiber angles for composite material. Design variables include the lamination parameters and element density. The least-squares between actual and desired displacements at output points along trailing edge is adopted to evaluate the deformed capability of the trailing edge. An integrated optimization model for the composite morphing trailing edge is established with the volume constraints. The optimal topologic shape and lamination parameters are initially obtained. Subsequently, a least-squares optimization between fiber angles and the optimal lamination parameters is implemented to obtain optimal fiber angles. Finally, morphing capability of composites trailing edge based compliant mechanism is investigated by simulation and experiments. The results indicate the composites trailing edge based compliant mechanism can approximately bend down 8 degrees and satisfies the design requirement.     

Strong interactions of incident shock wave with boundary layer along compression corner

The coherent structure and instability of the interaction of incident shock wave with boundary layer developing on a compression corner are experimentally studied. The experiments are carried out in a supersonic wind tunnel of Mach number 2. Particular attention is paid to shock patterns and unsteady shock motions induced by the separation bubble. The high-speed schlieren is used to visualize the flowfield evolution and to characterize the instability. The snapshot proper orthogonal decomposition of schlieren sequences is applied to investigate the primary coherent structure in the flowfield. Fast Fourier transform and continuous wavelet transformation are applied to characterize the instability. The results show that there are large-scale low-frequency oscillations of the shock waves and small-scale high-frequency pulsations in the separation region. The peak frequency of shock oscillation is mainly concentrated in the range of 100–1000 Hz. The pulsation of the small flow structure in the separation bubble is mainly concentrated above 12.5 kHz. Based on the results of experimental analysis, the preliminary mechanism of the large-scale instability of such interaction is obtained.     

空间非合作目标物柔性捕获技术进展

分类探讨了近年来出现的多种空间柔性捕获技术的原理及性能特点，给出了一些具有代表性的案例，结果表明：空间绳系捕获技术在理论及试验研究方面都相对成熟，是未来行之有效、可工程实现的柔性捕获方式之一。重点针对空间非合作目标物捕获中容易出现的翻滚问题，对比分析现有的几种常用的接触式消旋方法，分析表明能同时实现捕获+消旋的一步式消旋法更具有应用前景。以空间绳系捕获技术作为空间柔性捕获的代表，对其捕获后的空间绳系组合体动力学模型建立过程中的系绳模型进行了综述，指出了各种系绳模型的优缺点及适用条件。对系绳控制机构进行了分类综述，给出了设计系绳控制机构需重点关注的问题。最后对空间绳系捕获技术的发展方向做了展望。     

Positioning error compensation for parallel mechanism with two kinematic calibration methods

Compared with serial mechanisms, the parallel mechanism (PM) theoretically exhibited higher positioning accuracy, dynamic performance, strength-to-weight ratio, and lower manufacturing cost, but they had not been widely used in the practical application. One key issue, positioning accuracy, which directly affected their performance and was greatly influenced by the errors of kinematic structure parameters was analyzed. To effectively enhance the positioning precision of PMs, a novel modeless kinematic calibration method, namely the split calibration, was presented and its compensation effect of the positioning error was comprehensively compared with that of an integrated method on two different types of PMs. A strange phenomenon-correct and incorrect identified results were derived from two different PMs by the same integrated method, respectively-which had not been reported yet was discovered, and the origin of it was revealed utilizing numerical simulations. Finally, respective merits and drawbacks of these two methods obtained in this paper provided underlying insights to guide the practical application of the kinematic calibration for PMs.     

无人系统免疫智能技术

传统的无人系统人工智能技术重点研究人脑思维、感知和肌电反应等领域的科学发现和技术实现。免疫反应是生物体在面临病毒、细菌和天敌时保持生存和健康的独特生理机制，是智能系统技术研究领域的崭新视点。受动物应对病毒侵袭、环境剧变、天敌威胁等不利态势的免疫反应、保护自我和进化机制启发，提出无人系统在包含攻击、干扰、拒止、封锁、损伤、故障和博弈等恶劣环境和对抗模式下的生存安全问题，建立无人系统免疫智能技术的一般框架，架设无人系统和生物体之间免疫机制的桥梁。主要内容包括无人系统免疫智能技术的基本概念、反应机理、关键技术和研究框架，并分别从感知与诊断、适应与激励、学习与进化等技术层面进行了问题描述。最后，对免疫智能技术的未来研究方向和应用领域进行了展望。     

基于力位协同控制的大飞机机身壁板装配调姿方法

为校正中机身壁板由于重力和调姿内力产生的变形，提高中机身壁板装配调姿精度，提出了一种基于力位协同控制的装配调姿方法。通过将调姿机构等效为并联机构，推导了调姿机构的解析正反解模型；根据螺旋理论，建立了力传感器测量值与重力、调姿内力之间的映射关系，实现重力补偿值的动态计算，基于局部刚体-弹性连接假设，通过多元线性回归方法构建了调姿内力转化为位置补偿量的模型；根据Clamped-Free变形协调原理，简化了定位器调姿内力之间的协调关系，在此基础上提出了重力前馈补偿和调姿内力转化为位置补偿的力位协同控制策略，并对其进行了理论分析与设计。最后，对所提出的控制策略进行了仿真分析，结果表明采用力位协同控制方法，调姿定位精度提高35.3%，调姿内力降低77.8%，通过应用实验，说明了该方法的可行性和有效性。