旋挖钻机设备油液智能分析与健康监测

为了对直升机盒段件入水载荷进行分析，开展了模型垂直入水冲击试验，同时采用有限元-光滑粒子流体动力学（finite element method-smooth particle hydrodynamics，简称FEM-SPH）耦合数值方法进行仿真分析，计算了不同材料构型和速度下的过载、压力及应变结果。与试验结果进行对比表明，仿真结果与试验值吻合较好，预测的结构失效破坏模式与试验结果基本一致，可为真实直升机入水冲击的结构设计提供参考。     

Cryptanalysis of nonlinear confusion component based encryption algorithm

Recently many substitution box based encryption algorithms ensuring privacy have been proposed. Many, chaotic map based S-boxes have been generated posing high nonlinearity and strong cryptographic properties. Encryption schemes depending on the substitution box (S-box) only are weak and easily breakable with the help of chosen plaintext and ciphertext attacks. In this work, we have completely cryptanalyzed S-box based encryption scheme successfully by two types of attacks. Cryptanalysis in both types of attacks is performed by only one selected image. Moreover, we have suggested some improvements in the algorithm to defeat attacks.     

Dynamic load-altering attack detection based on adaptive fading Kalman filter in power systems

This paper presents an effective and feasible method for detecting dynamic load-altering attacks (D-LAAs) in a smart grid. First, a smart grid discrete system model is established in view of D-LAAs. Second, an adaptive fading Kalman filter (AFKF) is designed for estimating the state of the smart grid. The AFKF can completely filter out the Gaussian noise of the power system, and obtain a more accurate state change curve (including consideration of the attack). A Euclidean distance ratio detection algorithm based on the AFKF is proposed for detecting D-LAAs. Amplifying imperceptible D-LAAs through the new Euclidean distance ratio improves the D-LAA detection sensitivity, especially for very weak D-LAA attacks. Finally, the feasibility and effectiveness of the Euclidean distance ratio detection algorithm are verified based on simulations.     

悬臂式多级离心风机气动力计算

对一种悬臂式多级离心风机进行研究,通过改变回流器出口角和叶轮叶片进口角等参数,分析叶轮进口气流角的变化,以及对风机性能的影响。根据该风机气动力的计算结果和风机性能测试实验结果及对比分析,拟合得到了本文风机的压力—流量关系计算经验公式和流量—功率关系计算经验公式。计算结果表明:增大叶轮叶片进口角,会使压力变化曲线更平缓,减小回流器叶片出口角可以降低能耗,为悬臂式多级离心风机的设计和改进提供参考。     

直升机航空瞬变电磁Occam反演及软件实现

直升机航空瞬变电磁系统对于地形复杂、环境恶劣地区的资源勘探具有十分重要的意义.由于航空瞬变电磁系统空间采样密集,数据量很大,在工程实践中普遍采用一维反演进行数据解释.研究了以圆形回线为模型的直升机航空瞬变电磁Occam反演算法,详细推导了圆形回线正演函数的雅克比矩阵的解析解,比用数值差分计算的雅克比矩阵有更高的反演精度.为适用于野外实验,基于直升机航空瞬变电磁系统用C++语言开发了具有自主知识产权的一维Occam反演软件,该软件能实现坐标选取、数据预处理和反演等功能.将该软件应用实测数据的反演中取得了较好的效果.     

不同导线排列下500 kV输电线路直升机带电作业平台侵入路径

基于直升机和几种不同导线排列500 kV输电线路的实际参数,建立了直升机带电作业平台(HLLWP)靠近输电线路的模型。通过有限元方法计算了在不同的直升机带电作业平台的侵入角度和直升机带电作业平台与导线的距离下,操作人员屏蔽服和直升机作业平台表面的电场强度,基于计算结果给出了不同导线排布下,直升机带电作业平台靠近不同相导线时的最优侵入路径。     

风力发电机叶片变桨距偏离方式的受力分析

通过叶素理论及贝茨理论对两种风机叶片桨距角调节方法进行了对比,系统分析叶片桨距角偏离所引起的受力、边界层分离、攻角及桨距角等参数的变化,计算出叶片升力/阻力变化;通过求解流体边界层方程,揭示出叶片偏离最优桨距角之后产生的实际变化。得到下述结论:桨距角变大时,风机效率变化稳定但变化慢,桨距角调节范围较大;桨距角变小时,风机效率变化敏感,调整范围需要精密控制;该结论可为不同应用区域风机叶片参数调整方式的确定提供参考。     

基于卡尔曼滤波的MUH姿态信号融合算法研究

利用MEMS陀螺仪和加速度计获取姿态的方法已被广泛用于低成本的民用无人直升机上,陀螺仪的漂移和加速度计中的运动加速度都会影响估计精度,设计了基于四元数的卡尔曼滤波器,根据三轴角速率陀螺和加速度计信号,融合无人直升机姿态信号,并针对陀螺仪的漂移和加速度计的测量误差,设计了自适应的量测噪声方差矩阵,补偿融合精度,得到稳定可靠且精度较高的姿态信息,用于无人直升机的内环增稳控制.实验表明,该方法估值精度较高,能有效解决小型无人直升机姿态求解问题.     

离差偏好法在舰载直升机保障能力评估中的应用

考虑到目前我国舰载直升机保障能力评估方面存在数据不完整、评估中需要考虑决策者偏好的问题,研究了基于离差偏好法的舰载直升机保障能力评估模型。在通过调研并考虑舰载直升机保障实际情况的基础上,构建了保障能力评估指标体系,并根据决策者的偏好建立了评估对象的互反判断矩阵;在保障能力评估中运用了离差偏好法,从对评估对象进行排序的角度对各个指标的权重进行了重新定义,建立了量值与偏好矩阵的偏差函数,通过实例分析表明该模型实用性较强,过程简单,适合现阶段舰载直升机保障能力评估问题的研究,具有一定的应用价值。     

Robust distributed attitude synchronization of multiple three-DOF experimental helicopters

Multiple experimental three-degrees-of-freedom (three-DOF) helicopters that are equipped with active disturbance systems constitute an attractive platform to validate robust control strategies. In this paper, a distributed synchronization controller is developed for such a platform, where each helicopter is subjected to unknown model uncertainties and external disturbances, and the desired trajectories are generated online, communicated through a network and not accessible by all helicopters. The controller is composed of a continuous tracker and a continuous uncertainty and disturbance estimator (UDE). The tracker makes the nominal closed-loop system globally asymptotically stable, and the UDE output is used to reject total uncertainties. The conditions that ensure zero-error tracking for each helicopter are identified; for the case with nonzero error, explicit relationship inequalities between the involved design parameters and the ultimate bound of error are revealed. Experimental results of four cases demonstrate improved tracking and synchronization accuracy of using the UDE with small parameters.