An experimental study on the effects of friction modifiers on wheel-rail dynamic interactions with various angles of attack

By modifying friction to the desired level,the application of friction modifiers(FMs)has been considered as a promising emerging tool in the railway engineering for increasing braking/traction force in poor adhesion conditions and mitigating wheel/rail interface deterioration,energy consumption,vibration and noise.Understanding the effectiveness of FMs in wheel–rail dynamic interactions is crucial to their proper applications in practice,which has,however,not been well explained.This study experimentally investigates the effects of two types of top-of-rail FM,i.e.FM-A and FM-B,and their application dosages on wheel–rail dynamic interactions with a range of angles of attack(AoAs)using an innovative well-controlled V-track test rig.The tested FMs have been used to provide intermediate friction for wear and noise reduction.The effectiveness of the FMs is assessed in terms of the wheel–rail adhesion characteristics and friction rolling induced axle box acceleration(ABA).This study provides the following new insights into the study of FM:the applications of the tested FMs can both reduce the wheel–rail adhesion level and change the negative friction characteristic to positive;stick–slip can be generated in the V-Track and eliminated by FM-A but intensified by FM-B,depending on the dosage of the FMs applied;the negative friction characteristic is not a must for stick–slip;the increase in ABA with AoA is insignificant until stick–slip occurs and the ABA can thus be influenced by the applications of FM.

Rock burst mechanism analysis in an advanced segment of gob-side entry under different dip angles of the seam and prevention technology

In order to investigate the frequent occurrences of rock burst in gob-side entry during the mining process of the mining zone No. 7, the mechanical model of main roof of fully-mechanized caving mining before breaking was established by the Winkler foundation beam theory, and the stress evolution law of surrounding rock with different dip angles of the seam during the mining process was analyzed by using FLAC3 D. The results show that: with the dip angle changing from 45° to 0°, the solid-coal side of gobside entry begins to form an L-shaped stress concentration zone at a dip angle of 30°, and the stress concentration degree goes to higher and higher levels. However, the stress concentration degree of the coalpillar side goes to lower and lower levels; the influence range and peak stress of the abutment at the lateral strata of adjacent gob increase with dip angle decreasing and reach a maximum value at a dip angle of 0°, but the tailgate is not affected; the abutment pressure superposition of two adjacent gobs leads to stress concentration further enhancing in both sides of gob-side entry. With the influence of strong mining disturbance, rock burst is easily induced by dynamic and static combined load in the advanced segment of gob-side entry. To achieve stability control similar to that in the roadway, the key control strategy is to reinforce surrounding rock and unload both sides. Accordingly, the large-diameter drilling and high-pressure water injection combined unloading and reinforced support cooperative control technology was proposed and applied in field test. The results of Electromagnetic Emission(EME) and field observation showed that unloading and surrounding rock control effect was obvious.

Unsteady aerodynamics modeling for flight dynamics application

In view of engineering application, it is practicable to decompose the aerodynamics into three components： the static aerodynamics, the aerodynamic increment due to steady rotations, and the aerodynamic increment due to unsteady separated and vortical flow. The first and the second components can be presented in conventional forms, while the third is described using a one-order differential equation and a radial-basis-function （RBF） network. For an aircraft configuration, the mathematical models of 6- component aerodynamic coefficients are set up from the wind tunnel test data of pitch, yaw, roll, and coupled yawroll large-amplitude oscillations. The flight dynamics of an aircraft is studied by the bifurcation analysis technique in the case of quasi-steady aerodynamics and unsteady aerodynam- ics, respectively. The results show that： （1） unsteady aerodynamics has no effect upon the existence of trim points, but affects their stability; （2） unsteady aerodynamics has great effects upon the existence, stability, and amplitudes of periodic solutions; and （3） unsteady aerodynamics changes the stable regions of trim points obviously. Furthermore, the dynamic responses of the aircraft to elevator deflections are inspected. It is shown that the unsteady aerodynamics is beneficial to dynamic stability for the present aircraft. Finally, the effects of unsteady aerodynamics on the post-stall maneuverability

BTT autopilot design for agile missiles with aerodynamic uncertainty

The approach to the synthesis of autopilot with aerody- namic uncertainty is investigated in order to achieve large maneu- verability of agile missiles. The dynamics of the agile missile with reaction-jet control system （RCS） are presented. Subsequently, the cascade control scheme based on the bank-to-turn （B-I-T） steering technique is described. To address the aerodynamic un- certainties encountered by the control system, the active distur- bance rejection control （ADRC） method is introduced in the autopi- lot design. Furthermore, a compound controller, using extended state observer （ESO） to online estimate system uncertainties and calculate derivative of command signals, is designed based on dynamic surface control （DSC）. Nonlinear simulation results show the feasibility of the proposed approach and validate the robust- ness of the controller with severe unmodeled dynamics.

Aerodynamic, Kinematic and Control Coupling Simulation of Aircraft Maneuvering Flight

Aiming at the high angle of attack pull-up and multi-channel roll pull-up coupling problems of high maneuvering aircraft, this paper establishes the flight attitude control rate by means of unsteady flow numerical solution, dynamic unstructured nested mesh assembly method and numerical solution method of flight mechanics equation. On this basis, a virtual flight simulation platform integrating pneumatics, motion and control is established. Based on this virtual flight simulation platform, F-16 aircraft is simulated by high angle of attack pull-up flight mode and multi-channel roll pull-up coupling flight mode. Finally, the influence of rudder on the yaw control channel is investigated. The results show that the numerical virtual flight simulation platform established in this paper has the ability to simulate maneuvering flight of aircraft.

采用方位变化率的导弹纯方位攻击优化方法

利用目标累积方位序列提升反舰导弹作战效果,在计算目标方位变化率的基础上,采用几何分析方法,建立导弹发射提前转向角的解析模型,优化纯方位攻击发射方向。仿真结果表明,将导弹发射方向优化为方位加提前转向角之后,典型态势下,百分之百捕获目标区域半径扩大3倍以上,显著提高导弹末制导雷达目标捕获概率,有助于提升反舰导弹纯方位攻击的作战效能。

考虑弹头滚转姿态变化影响的防热层厚度优化

基于气动热/结构温度响应耦合计算方法,研究了弹头固定攻角再入条件下锥身典型子午面结构温度响应特性,以及滚转姿态变化时刻对各子午面结构温度响应的影响,建立了考虑弹头滚转姿态变化影响的防热层厚度优化方法,并基于该方法开展了弹头防热层厚度优化。最后,研究了滚转姿态变化次数对优化效果的影响。结果表明:在再入弹道前段进行滚转姿态变化可使外壁面气动加热量更为合理,有效降低弹体锥身壳体内壁面温升。当迎、背风面壳体内壁面最大温升约束为25 K时,与无滚转姿态变化状态下相比,滚转姿态变化设计可使防热层厚度减小0.725 mm,减小幅度为5.4%。通过与滚转姿态变化时刻的联合设计可有效降低锥身防热层厚度。与单次滚转姿态变化时相比,两次滚转姿态变化时防热层厚度减小量仅增大1.9%,增加滚转姿态变化次数对优化效果影响较小。

迎风角对跳台滑雪运动员飞行气动性能影响的研究

以探究迎风角对跳台滑雪运动员与滑雪板组成的多体系统的飞行气动性能的影响为目的,采用CFD数值模拟方法,在风速为29 m/s情况下,研究了多体系统迎风角为15°、20°、25°、30°、35°、40°六种情况下的气动性能变化情况。并在保证跳台滑雪运动员姿态以及飞行速度不变的情况下,以多体系统的升阻比作为衡量标准,对迎风角对多体系统气动性能的影响情况进行了评估。研究得出:多体系统升阻比随迎风角的增大呈递减趋势,且不同迎风角之间多体系统升阻比差异较大。在多体系统迎风角取为15°时,整个多体系统的升阻比取得最大值,有利于运动员取得良好的气动性能。此外,迎风角对跳台滑雪运动员气动性能影响的研究可为运动员比赛技巧相关的训练提供一定的指导作用。

断索工况下风攻角对曲梁单边斜拉桥动力响应影响分析

风攻角的变化可能会对桥梁的风致振动产生不利影响。基于有限元模拟和节段模型风洞试验,分析了5种风攻角工况下曲梁单边斜拉桥的风振响应。结果表明:在断索全过程中,随着风攻角的增大,桥梁跨中位移和加速度极值以及拉索张力均先增大后减小且在15°时达到最大,在抗风设计中应着重考虑最不利风攻角。动力放大系数(dynamic amplification factor, DAF)推荐值应考虑风攻角15°时拉索断裂引起的风振放大效应,有助于为同类型桥的抗风设计提供借鉴。

远程AUV微速操纵性仿真研究

建立了适合于远程AUV大攻角微速条件下运动仿真的六自由度数学模型,对AUV在定点旋转、垂直上浮下潜、水平左右横移等形式的微速运动下的操纵性进行了仿真研究。结果显示AUV在微速条件下可以稳定的运动;鱼雷形AUV在水平、垂直方向的操纵性能基本相同。并经过与湖上试验结果的对比,说明了仿真结果真实可信。

脉动风下高速铁路接触网抖振对弓网受流性能的影响

接触网系统在短周期脉动风的作用下,会发生抖振现象,从而引起弓网受流的恶化。本文考虑作用在接触网上的水平与竖直脉动风和静风载荷,推导作用在接触网系统上的抖振力模型;采用Davenport谱和Panosfsky谱,运用谐波合成法分别模拟水平和竖直方向上的脉动风时程;利用有限元分析软件MSC-MARC建立弓网耦合模型,将抖振力施加到接触网模型中,分析接触网在脉动风下的风振响应,对脉动风作用下的弓网系统进行动态仿真,研究脉动风下接触网抖振对弓网动态受流性能的影响。研究结果表明:脉动风引起的接触网抖振对弓网受流影响很大,在研究接触网风振响应和弓网动态特性时,应综合考虑静风载荷和脉动风载荷的影响;脉动风攻角的变化对弓网受流影响明显,风攻角是研究风载荷下弓网受流性能时不可忽视的因素。

某跑车尾翼外形变化对气动升力影响的仿真分析

为研究汽车行驶时,气动升力随着车速的提高,对汽车的操纵稳定性和动力性的影响,研究气动升力的附加装置.以一跑车模型的尾翼为基础,采用一种修正湍流模型的数值计算方法,探讨了外形、攻角、翼面凹坑以及支架形式对尾翼表现的影响.结果表明:后负升力翼产生的负升力与外形和支架形式有很大关系,且随着攻角的增大而增加,而翼面凹坑能起到增加负升力的作用.

飞机大攻角空间机动气动力建模研究

准确的气动力模型是大攻角机动仿真与控制等飞行动力学问题研究的基础。针对纵向运动建立的非线性非定常气动力微分方程模型扩展应用于一般空间运动形式,在分析大攻角非定常流动机理和试验数据的基础上,发展了一种多自由度非线性非定常气动力数学模型,并探讨了模型辨识和参数估计问题。用全机构形的大攻角动态风洞试验数据对模型进行的验证表明所发展的气动力模型能够描述大攻角气动力主要的非线性和非定常特性。

跨超、高超声速风洞模型动导数试验技术研究

介绍了气动中心高速所为航空航天飞行器所开展的动导数试验技术研究,主要包括高速大攻角动导数试验技术、再入体模型配平状态动导数试验技术及基于气体轴承的高超声速风洞模型滚转阻尼导数试验技术。阐述了这些试验技术的试验设备及测试系统,给出了典型的试验结果。

大攻角下有限振幅俯仰飞行的非线性动稳定性分析

本文介绍了一种关于大攻角飞行条件下，飞行器非线性动稳定性分析的数学方法。基于飞行器整体运动的低频特点（ｋ１），将动稳定性导数的概念推广到大攻角有限摆幅振荡飞行的稳定性分析，给出了逐次求取各阶动导数的摄动方法，导出了小参数形式的非线性动力学方程。结合常微分方程的定性理论，可以揭示大攻角飞行中的某些非线性特征，方法原则上可推广到多自由度问题。

谐波平衡法在动导数快速预测中的应用研究

谐波平衡法以傅里叶级数展开为基础,将周期性非定常流场的非定常求解过程转化为几个定常流场的耦合求解过程,并通过重建得到整个流场的非定常过程.建立了基于谐波平衡法的动导数快速预测方法,数值模拟了超声速带翼导弹俯仰的动态流场,并通过积分法获取了俯仰动导数,与实验结果吻合很好;且在同等计算精度下,谐波平衡法的计算效率是双时间步方法的13倍.应用谐波平衡法研究了较大范围内减缩频率对俯仰动导数的影响规律.研究发现,对于本外形,当减缩频率降低到一定值后,俯仰动导数的值迅速变化,甚至发生变号;对此现象产生的原因进行了深入分析,并通过对导弹自激俯仰运动的数值模拟验证了该结果.此外,针对大攻角条件下动态流场非线性强的特点,开展了谐波平衡法在大攻角下的适用性研究.结果表明,谐波平衡法在大攻角下也能取得很好的计算结果.

典型覆冰导线碰撞系数仿真分析

覆冰碰撞系数是导线覆冰生长预测的关键参数。基于气液两相流标准湍流模型和欧拉—拉格朗日原理建立导线外部二维流场数学模型,计算水滴的运动轨迹,实现对圆形、椭圆形、翼形3种典型导线覆冰的碰撞系数仿真;并分别给出不同迎风攻角下椭圆形、翼形覆冰的碰撞系数。仿真结果表明：在相同气象条件下,圆形截面覆冰导线碰撞系数较长短轴比4：3的椭圆形高出4.79%~6.21%,较翼形高出4.04%~8.14%;相同导线覆冰形状在0°~30°迎风攻角范围内,攻角越大,碰撞系数越高。

大攻角下基于信息融合的攻角/侧滑角估计方法

攻角和侧滑角是飞控系统和导航系统的重要参数。针对高性能飞行器在大攻角飞行时攻角和侧滑角不能精确测量问题,引入飞行动力学模型,选取姿态、姿态角速率、气流角和速度等飞行参数作为状态向量,以惯性导航系统提供的姿态、姿态角速率、加速度组成观测向量,构建扩展卡尔曼滤波器,融飞行动力学模型求解和状态估计的过程为一体,实现攻角和侧滑角实时精确估计。利用X-Plane系统的飞行仿真数据对攻角/侧滑角估计方法的可行性和有效性进行了验证。仿真结果表明,该方法不仅具有较高的精度、良好的稳定性和鲁棒性,而且可提高大气数据系统的测量范围和可靠性,能够有效地适用于大攻角飞行环境下攻角和侧滑角的测量。

超机动飞机动态逆-PID控制器设计

对超机动飞机在大迎角机动下的控制律进行设计,并完成相关仿真验证。通过引入推力矢量技术,建立带推力矢量的飞机非线性数学模型;采用奇异摄动理论,将飞机状态划分为快慢变换不同的回路,分别应用动态逆设计飞行控制律;并采用PID控制补偿由于未精确建模带来的系统逆误差;最后对所设计的控制律进行了机动指令飞行仿真。仿真结果表明,设计的控制律能在大迎角机动条件下控制飞机跟踪指令飞行,并保证闭环系统的稳定性。

新型海底沉积物采样器结构设计及采样过程动态分析

针对海底沉积物采集的特点,设计了新型海底沉积物采样器,将采样和保真融为一体,利用海底触发装置实现采样,利用海水等静压原理实现采样器的封口与保真,采用FLUENT软件对采样过程进行了模拟仿真,并对采样的动态过程进行了分析,结果显示在下落高度足够时,采样器撞击海底的速度趋于稳定值,同时攻角小于5°时采样时所受的阻力最小。