飞机起落架着陆撞击动力分析

根据现有沿－气式缓冲器结构形式,针对模拟起落架着陆撞击过程的落 震试验模型,考虑起落架航向刚度和阻尼的影响,依据撞击过程中各变量间的运动关系,建立了描述着陆过程中的运动微分方程组,并采用龙格库塔法对运动微分方程组进行求解。最后采用该方法对Ｋ８飞机主起落架（单腔）和某机起落架（双腔）落震试验过程进行了模拟,并与试验结果进行了比较,发现计算结果与试验结果吻合较好。     

考虑温度效应的起落架落震缓冲性能研究

为了研究环境温度对起落架缓冲性能的影响，以某型飞机起落架为研究对象，考虑温度对起落架动力学模型中空气弹簧力和油液阻尼力的影响，提出了一个包含温度效应的起落架动力学分析模型，并通过试验在一定温度范围内(-35℃～60℃)进行了验证。结合试验数据和仿真模型给出了空气多变指数、油液阻尼系数的设计指导值，并研究了温度对起落架缓冲性能的影响规律。结果表明：环境温度对起落架缓冲性能影响显著，表现为起落架落震动载荷的变化；同时发现缓冲器腔内气体较油液受温度影响更为敏感，低温状态时气压的变化以及油液物理状态的改变会使得缓冲器性能明显恶化，缓冲支柱行程变化率达到25%;对于可能工作在复杂环境下的起落架，设计阶段需要充分考虑温度对缓冲器内气压和油液的影响，确保飞机着陆安全。     

起落架落震试验中缓冲系统投放功量修正方法研究

起落架落震试验中,投放功量与测试功量的比对用于验证测试系统是否正常,传统的投放功量的计算忽略了起落架弹性支撑质量与非弹性支撑质量重心位移不一致,导致投放功量的计算有一定的误差。建立起落架二质量模型,指出传统计算方法的不足,改进了投放功量的计算方法,并对比了落震试验中几种不同重量级的起落架在改进算法前后测试误差的区别。结果表明:测试误差修正前后的差值约0.15%~1.28%,在小型起落架落震试验中差异较大。同时,考虑了投放锁开锁延迟以及导轮与立柱摩擦带来的下沉速度损耗,对某型起落架落震试验中的下沉速度实时监测,提出了一种试验中适用的监测、修正下沉速度的试验方法,对比了下沉速度修正前后测试误差的变化,试验证明这种方法有效减少了测试误差,误差计算精度提高了约4%。     

一种自适应双腔缓冲器动力特性研究

建立了一种基于弹簧自适应控制油孔面积的双气腔双油腔缓冲器动力学模型和分析方法,同时也建立了一种三维摇臂式起落架着陆动力学模型.对某型号飞机起落架着陆缓冲性能进行了计算分析,并进行了落震试验验证,结果证明了本文建立的动力学模型和分析方法是正确的,并已成功地应用于工程.     

飞机起落架着陆与滑跑性能分析

阐述了一个能准确模拟飞机着陆与滑跑冲击特性的起落架分析模型,并通过落震试验的真实载荷-行程与该模型模拟计算结果的对比,显示了这种模型的有效性.为起落架设计与改进设计提供了一个实用的工程方法.     

飞机起落架舱内轮胎爆破压力场测试研究

飞机轮胎爆破压力场分布模型对于飞机轮胎强度计算和起落架舱内防护设计至关重要。本文开展某型飞机起落架舱内轮胎爆破试验研究,利用高频动压传感器测试防护罩上关键点处的压力值,建立了轮胎爆破气流场压力分布模型,最后采用有限元方法对防护罩结构进行数值模拟并与试验结果对比分析。结果发现,航空轮胎爆破时间短暂但威力巨大,起落架舱内轮胎爆破最大压力值随初始压力和爆破距离呈指数关系衰减。根据试验结果分别提出了斜交胎、子午胎的爆破压力场分布模型并对防护罩进行了数值计算,所得应变值与数值结果误差在12%以内,说明所提出的压力场分布模型可用于起落架舱内防护罩设计。本文所提出的试验方法及爆破压力场分布模型为起落架舱内防护设计提供了参考依据。     

舰载机缩比落震动载荷预计及试验技术

舰载飞机全机落震试验是考核机体结构、起落架以及机载设备承受舰动态冲击载荷能力的整机级试验,但作为大型动态试验,其试验规模大、准备周期长,一般承制单位难以实施。本文提出了一种舰载机缩比落震动载荷预计及试验方法,该方法在保证动力学相似的前提下,将原型机按照等比原则进行缩放;同时,设计了一套全机落震试验方法,经过动力学相似理论的推导,可将缩比模型落震试验结果还原到原型机载荷。该方法以较低成本预测了原型机全机落震试验结果,经过原型机试验验证,满足试验预计精度,在一定程度上可对舰面动载荷进行提前预计与分析。     

CALCULATION OF AIRCRAFT DYNAMIC LOADS ON SHIP-DECK AND TEST VERIFICATION

舰载飞机的舰面动载荷是结构的临界设计载荷。针对常规方法下载荷计算的设计已不能满足舰载飞机非常规工况(例如弹射拦阻、自由飞钩住、偏心着舰等)载荷计算的设计要求的问题,研究和建立了一套完整的全机动载荷计算的设计方法和流程,并以某型飞机全机落震试验为例,通过与试验数据的对比分析,验证了该设计方法和流程的合理性和可行性。     

飞机舰面动载荷计算方法研究及试验验证

舰载飞机的舰面动载荷是结构的临界设计载荷。针对常规方法下载荷计算的设计已不能满足舰载飞机非常规工况(例如弹射拦阻、自由飞钩住、偏心着舰等)载荷计算的设计要求的问题,研究和建立了一套完整的全机动载荷计算的设计方法和流程,并以某型飞机全机落震试验为例,通过与试验数据的对比分析,验证了该设计方法和流程的合理性和可行性。     

某新型直升机“地面共振”初步分析

对某新型直升机垂直起落状态“地面共振”初步分析,采用经典的空间动力模型进行计算.文中给出了该机“地面共振”初步计算的计算方法和计算结果,并得出初步计算结论.根据现有条件,该机暂时无法做起落架刚度、阻尼试验,在初步计算中,起落架的全部动力学参数都是根据理论计算或经验公式得出的,包括起落架传递系数,缓冲器和机轮的静压曲线、刚度阻尼特性等.本文推导了这些参数的计算方法以及全机平衡状态计算的计算方法.     

Applications of the group of equations of motion of a polytropic gas

The machinery of Lie theory (groups and algebras) is applied to the system of equations governing the unsteady flow of a polytropic gas. The action on solutions of transformation groups which leave the equations invariant is considered. Using the invariants of the transformation groups, various symmetry reductions are achieved in both the steady state and the unsteady cases. These reduce the system of partial differential equations to systems of ordinary differential equations for which some closed-form solutions are obtained. It is then illustrated how each solution in the steady case gives rise to time-dependent solutions.     

Hydro-gas suspension system for a tracked vehicle: Modeling and analysis

Tracked vehicles fitted with torsion bar suspensions are limited in their ability to achieve high mobility. This limitation is due to the linear characteristics and the consequent poorer ride performance. Hydro-gas suspensions due to their inherent non-linear behavior can provide higher mobility and better ride comfort performance. The hydro-gas suspension model has usually been developed from experimental force-displacement characteristics, which requires availability of suspension hardware.In this paper, a hydro-gas suspension system is modeled using polytropic gas compression model to represent the spring characteristics, while the damper orifices are modeled using hydraulic conductance. The analytical model is then validated with experiments individually for spring and damper flow characteristics and then as a suspension-wheel assembly in a test rig. The validated suspension model is incorporated in an in-plane model. Using this model, simulation is carried out for sinusoidal inputs of different wavelengths, amplitudes and vehicle speeds. The simulation model is validated with data measured on a vehicle traversing an APG course. The proposed model agrees very well with the measured data. Based on the validated model, studies on the influence of suspension parameters on the ride comfort of a tracked vehicle are carried out.     

Numerical simulation of minimum B‐jumps at abrupt drops

A numerical simulation of minimum B‐jumps in horizontal rectangular channels having an abrupt drop is given. Gradually varied, steady, supercritical flow is assumed as the initial condition. An unsteady flow is created by increasing the downstream depth. One‐dimensional, unsteady Saint‐Venant equations are solved by using the MacCormack and the dissipative two–four explicit finite difference schemes. The steady flow solution is obtained by treating the time variable as an iteration parameter and letting the solution converge to the steady state. The abrupt drop is treated as an interior boundary and solved by the method of characteristics. The results are compared with experimental and analytical studies. Copyright © 2007 John Wiley & Sons, Ltd.     

Aeroelastic analysis of an idealized landing gear door in subsonic potential flow

Landing gear doors on aircraft have experienced flutter during preliminary flight testing. While designs vary widely, landing gear doors are typically plate-like structures with a relatively rigid actuator attached to their inside surface. To better understand the aeroelasticity of landing gear doors, this study investigates the aeroelastic stability of an idealized model. The model consists of a hinged plate with an interior constraint approximating the actuator attachment. The plate is subject to uniform flow, and an unsteady vortex lattice model is coupled to the structural model to predict critical flow velocities. The location and footprint area of the internal constraint, along with plate aspect and mass ratios, are varied to investigate a large parameter space. Results reveal that the critical flow speed and instability mechanism are sensitive to the postulated actuator placement. In general, flutter is the dominant mode of instability when the actuator is postulated in the leading quarter of the plate. In other postulated locations, divergence dominates. However, the exact shape and location of the boundary between flutter and divergence is configuration dependent and found to be especially sensitive to changes in aspect ratio.     

聚氨酯橡胶超弹性本构模型拟合效果评估

对聚氨酯橡胶进行了单轴拉伸、单轴压缩和平面拉伸试验,采用常用的超弹性本构模型拟合试验数据,并基于拟合优度、拟合曲线与试验曲线相似性、相对偏差三方面,对拟合效果进行评估．结果表明：采用拟合优度评估,能从总体上反映超弹性本构模型对试验数据的拟合效果,采用拟合曲线与试验数据相似性的对比进行评估,能直观反映超弹性本构模型对试验数据的拟合效果,若同时考虑相对偏差,则可以反映超弹性本构模型与试验数据之间的相对偏差量,更为准确地对超弹性本构模型的拟合效果进行评估．     

The effect of an unsteady drag force on the structure of a non-equilibrium region behind a shock wave in a gas-particle mixture

For numerical analysis of shock wave propagation in gas-particle mixtures, drag coefficients of a sphere in steady flows are generally used. However, it is shown both experimentally and numerically that a shock loaded solid sphere experiences unsteady drag forces. The paper describes a model of unsteady drag force and its effect on the structure of the non-equilibrium region behind a shock front traveling in a dusty gas. The results are compared with those obtained by using a steady drag coefficient and are discussed. It is demonstrated that the large drag force at the early stage of the interaction between shock-wave induced flow and a solid particle affects the flow structure that is obtained with a steady drag force.      

页岩气藏压裂水平井试井分析

页岩气藏资源丰富,开发潜力巨大,已成为目前研究的热点.与常规气藏相比,页岩气藏运移机制复杂,流动模式呈非线性,有必要考虑页岩气的吸附解吸,天然微裂缝的应力敏感性,人工裂缝内的非达西流等非线性因素对压裂水平井压力响应的影响. 基于双重介质和离散裂缝混合模型,分别采用Langmuir等温吸附方程描述吸附解吸,渗透率指数模型描述应力敏感,Forchheimer方程描述非达西效应,建立页岩气藏压裂水平井数值试井模型. 运用伽辽金有限元法对模型进行求解.根据试井特征曲线,划分流动阶段,着重分析非线性因素对压力响应的影响.结果表明:页岩气藏压裂水平井存在压裂裂缝线性流、压裂裂缝径向流、地层线性流、系统径向流及封闭边界影响5 种流动阶段.吸附解吸的影响发生窜流之后,Langmuir吸附体积增大,拟压力导数曲线凹槽更加明显,系统径向流出现时间与压力波传播到边界时间均延迟;天然裂缝系统的应力敏感性主要影响试井曲线的晚期段,拟压力和拟压力导数曲线均表现为上翘,应力敏感效应越强,上翘幅度越大;高速非达西效应对早期段影响较大,非达西效应越强,拟压力降幅度越大,试井曲线上翘.与解析解的对比以及矿场实例验证了模型的正确性与适用性.      

Certain hydrodynamic characteristics of the evolution of a solitary spherical bubble in the finite compression regime

The characteristics of unsteady incompressible fluid flow around a gas or vapor bubble compressed to a finite size are theoretically investigated. The velocity on the bubble boundary, the integral flow-rate and kinetic energy, and the form of the pressure distribution in the fluid are analyzed. Certain general qualitative regularities independent of viscosity, surface tension, and the intensity of the heat and mass transfer processes are revealed. The general results obtained are illustrated and specified with reference to a simplified polytropic model.     

Transverse Elastic–Friction Vibrations of a Running Aircraft

An analytical model of the plane-parallel running of an aircraft under crosswind load is proposed. The compliance of the internal constraints of the aircraft and the nonlinearity of the side force on the landing gear wheels are taken into account. The model is intended to study the transverse elastic friction vibrations of the aircraft hull and landing gears. The steady motion of the aircraft is considered. The dependence of the lateral friction force on the slip angle is assumed to have the form of a sinusoidal segment. The Routh–Hurwitz instability conditions are derived in an explicit form