Helicopter blade tracking by laser light

A new helicopter rotor blade tracking method based on the diffuse reflection of laser light is presented. The blade tip paths are marked by bright flashes of laser light reflected on the running blades. The flashes are detected by a television camera and after appropriate digital processing displayed on a tv monitor. The method offers an exceptional accuracy of about 1 mm and very good reproducibility.     

无人直升机自主着舰的光学3D测量解析算法

推导了一种用于无人直升机自主着舰的相对位姿单目单帧视觉测量算法。设计了基于正方形主特征的着降区域平面特征图案,根据几何透视投影学理论,采用摄像机针孔模型,以特征图案主正方形四角点的物理坐标和图像坐标作为输入,并以正方形邻边的垂直特性作为束缚条件,推导出了位置和姿态6个参数的解析表达式。通过在实验室环境下对真实图像的测量表明,当特征图案主正方形边长为0.1m(等效实际甲板特征图案边长1m)和相对距离为1m(等效实际距离10m)左右时,位置参数RMS误差小于0.2cm(等效为2cm),姿态参数RMS误差小于1.2°,算法具有很好的稳定性,可用于无人直升机着舰过程中的位姿测量。     

直升机旋翼瞬态气动响应分析的一个高效方法

基于旋翼动量-叶素组合理论,计入桨叶挥舞运动和动态入流对旋翼拉力的非定常影响,建立了一个快速计算垂直飞行状态总距突增时旋翼气动响应的方法,可用于旋翼拉力、桨叶挥舞运动和诱导速度的瞬态变化的分析。为验证方法的有效性,分别对三种不同总距突增情况下的旋翼气动响应进行了计算,并与可得到的实验结果进行了对比。应用该方法,研究了铰接式旋翼桨叶的挥舞铰外伸量对动态响应的影响,对比了总距突增和突减两种情况下的不同瞬态变化。在此基础上,得出了一些结论。     

直升机气动弹性力学发展现状(续)

Ⅲ.单片桨叶气动弹性问题的求解1.桨叶离散化方法求解旋翼桨叶气动弹性力学问题的第一步是将连续桨叶离散化,即把一个具有无限多个自由度的连续参数系统离散化为具有有限个自由度的离散系统。常用方法有三种: 1)整体模态方法在直升机旋翼气动弹性力学中,以往用得多的离散方法是整体模态法,或称为整体伽辽金方法。此方法的实质是利用桨叶自由振动振型是线性独立      

直升机旋翼／机身耦合系统的气弹响应分析（二）方程的求解

在文（一）得到的直升机旋翼系统运动方程的基础上,运用动态子结构的方法对旋翼系统和机身作为相对独立的部分进行分析,通过界布的力平衡和几何协调将子系统耦合系统整体系统,用分割－迭代法求解直至旋翼系统和机身的响应同时收敛到精度要求,并研制相应的计算程序,给出了工程算例。     

BILU implicit multiblock Euler/Navier–Stokes simulation for rotor tip vortex and wake convection

In this paper, a block incomplete lower–upper (BILU) decomposition method is incorporated with a multiblock three‐dimensional Euler/Navier–Stokes solver for simulation of hovering rotor tip vortices and rotor wake convection. Results of both Euler and Navier–Stokes simulations are obtained and compared with experimental observations. The comparisons include surface pressure distributions and tip vortex trajectories. The comparisons suggest that resolution of the boundary layer is important for the accurate evaluation of the blade surface loading, but is less so for the correct prediction of the vortex trajectory. Numerical tests show that, using Courant–Friedrichs–Lewy (CFL) number of 10 or 30 with the developed BILU implicit scheme can be 6–7 times faster than an explicit scheme. The importance of solution acceleration schemes that increase the permitted time‐step is illustrated by comparing the evolving wake structures at different stages of the calculation. In contrast to fixed wing simulations, the extent of the wake structures is shown to require resolution of large physical time. This observation explains the poor performance that is obtained when employing convergence acceleration strategies originally intended for solution of equilibrium problems, such as the multigrid methods. Copyright © 2007 John Wiley & Sons, Ltd.     

直升机弹性多支点传动轴的主共振分析

传动轴主共振的最大振幅、稳定性、振幅突变性是其主要特性。在根据质心运动定理、Galer-kin法和Dirac函数求得非惯性移动系下直升机的倾斜弹性多支点传动轴的弯曲运动方程基础上,用多尺度法求得稳态下主共振的一次近似定常解,再分析了主共振的最大振幅、支点的位置及数量对主共振的影响、主共振的稳定性及振幅突变性等。弹性中间支点有提高传动轴的运动稳定性、增大相邻阶主共振之间的频率范围及限幅器的功用。提出通过减小偏心距、降低主共振的阶数、加大传动轴中及中间支点处的阻尼减小主共振的最大振幅及消除振幅突变。     

直升机机载光电吊舱的发展现状及对策

介绍了直升机机载光电吊舱的应用背景、基本组成和工作原理,主要以警用机载吊舱为对象,分析了该系统的国内外发展现状及未来的发展趋势,并有针对性地提出了进行相关研究的具体思路和方案。     

海事直升机垂直下降涡环状态实验研究

直升机涡环状态严重影响飞行安全,其气流特性非常复杂,难以准确计算。本文在旋臂机设备上开展了涡环状态的专题实验,首先介绍了旋臂机的组成以及模型子系统、控制子系统和测试及数据采集子系统的工作特点。然后说明实验过程及实验数据处理方法。进行了不同总距、不同下滑角以及不同垂直速度的直升机下降实验,并测量其气流特性。最后以实验数据为基础,分析了在悬停状态、低速下降状态、涡环状态前期、中期及后期扭矩平均值和脉动幅度、拉力平均值和脉动幅度随下降速度的变化关系,确定了涡环状态的一般规律,探讨了涡环状态的改出方法。本文结果可为保证飞行安全提供参考。     

The analysis of thin walled composite laminated helicopter rotor with hierarchical warping functions and finite element method

In the present paper, a series of hierarchical warping functions is developed to analyze the static and dynamic problems of thin walled composite laminated helicopter rotors composed of several layers with single closed cell. This method is the development and extension of the traditional constrained warping theory of thin walled metallic beams, which had been proved very successful since 1940s. The warping distribution along the perimeter of each layer is expanded into a series of successively corrective warping functions with the traditional warping function caused by free torsion or free bending as the first term, and is assumed to be piecewise linear along the thickness direction of layers. The governing equations are derived based upon the variational principle of minimum potential energy for static analysis and Rayleigh Quotient for free vibration analysis. Then the hierarchical finite element method is introduced to form a numerical algorithm. Both static and natural vibration problems of sample box beams are analyzed with the present method to show the main mechanical behavior of the thin walled composite laminated helicopter rotor. The project supported by the National Natural Science Foundation of China (19932030)