整流罩声振试验蜂窝夹层板建模方法

针对整流罩主体结构由蜂窝板结构构成的特点,在使用统计能量分析法进行整流罩结构高频振动噪声环境预示研究时,重点对蜂窝夹层板建模的三明治夹芯板理论、等效板理论和蜂窝板理论三种等效方法进行比较分析。采用蜂窝夹层板的三种不同等效理论对整流罩整尺度结构进行统计能量分析建模,并将预示结果与在混响室内进行的该整流罩声振实验结果进行对比,分析表明三明治夹芯板理论更适用于研究蜂窝板的高频振动特性。     

蜂窝夹层复合材料压缩损伤声发射特征研究

应用声发射技术对蜂窝夹层复合材料压缩损伤过程进行了实验研究。分析载荷与声发射信号经历图,依据其损伤过程和声发射特征,发现随着加载载荷的增加,复合材料的损伤逐步增大。在加载初始阶段,仅有少量声发射信号,各种表征信号量小幅度增加;在加载中期,声发射信号增多,各种表征信号量不断增大;在加载后期,声发射信号明显突增,各种表征信号量急剧增加。复合材料压缩损伤破坏与声发射的幅值、能量、撞击、上升时间、持续时间和计数等参量相关。蜂窝夹层复合材料试件的应力-应变曲线近似为直线,应变速率与声发射信号特征相互对应。     

微纳卫星火工冲击载荷缓冲装置设计及验证EI北大核心CSCD

火工冲击环境是卫星等航天器经历的最恶劣的力学环境之一,尤其是航天器与运载火箭分离时的冲击最为恶劣。星箭分离冲击会影响有冲击敏感元件的设备甚至航天器的正常工作,严重时甚至能导致发射任务的失败。因此,有必要研究火工冲击环境的抑制措施。针对某金属框架微纳卫星在研制阶段星箭分离实验过程中冲击响应过大的问题,结合火工冲击载荷来源、火工冲击传递机理以及火工冲击抑制方法,对整星进行了冲击载荷缓冲装置设计并进行了冲击及振动实验验证。实验结果表明,该火工冲击缓冲装置能够将冲击载荷降低70%以上,对航天产品的抗冲击分析及合理的结构设计具有重要意义。     

运载火箭前端测控设备减振隔噪技术研究

为适应新一代运载火箭"三垂"的测发模式,前端测控设备被置于发射平台台体内部房间。在火箭起飞阶段,发射平台内部的这些测控设备需要承受严酷的振动、噪声环境。为保证测控设备在发射过程中能够正常工作,提出一种减振、隔噪的设计思路,通过型号飞行任务证明这种设计方法减振、隔噪效果的有效性。     

运载火箭前端测控设备减振隔噪技术研究

为适应新一代运载火箭“三垂”的测发模式，前端测控设备被置于发射平台台体内部房间。在火箭起飞阶段，发射平台内部的这些测控设备需要承受严酷的振动、噪声环境。为保证测控设备在发射过程中能够正常工作，本文提出了一种减振、隔噪的设计思路，通过型号飞行任务证明了这种设计方法减振、隔噪效果的有效性。     

结构星噪声与振动组合环境激励试验及效应研究

受地面试验技术条件的限制,目前对卫星发射及飞行过程所经历的复合环境采用单项环境模拟试验来实现,通常是进行随机振动试验或者噪声试验。实际上,无论单独的随机振动试验还是单独的噪声试验都难以准确模拟卫星在发射飞行状态所经历的复合环境,在不同频段会存在"过"或"欠"试验的问题。以某型号结构星为对象,开展噪声与振动组合试验技术研究,对声振组合试验、随机振动试验、噪声试验的有效性及耦合效应进行分析与总结,为后续卫星产品开展相关试验提供参考。     

芳纶纤维/环氧树脂复合材料损伤与断裂过程的声发射特性

研究了芳纶/环氧复合材料在承受拉伸载荷时的损伤与断裂行为.发现不同损伤类型表现出不同的声发射特性,从声发射信号的某几种关联图中可以较好地判断损伤发生的类型,并可根据某些声发射特征参量值对临界承载值进行合理的确定.     

玻璃纤维复合材料静载荷声发射试验研究

通过对玻璃纤维复合材料试件静力载荷条件下的声发射试验,研究了该种材料在静力试验条件下的损伤破坏过程的声发射特性,分析了该材料损伤各阶段的声发射特性和对应的载荷比,系统而完整地得到了该材料损伤类型特征及声传播特性。试验证明:对玻璃纤维复合材料进行静力载荷条件下的声发射试验研究,可有效并清晰地揭示该材料在静力试验条件下损伤破坏过程中的声发射特性及材料损伤类型特征,为该材料的寿命健康监测、缺陷判定提供评价依据。     

带有槽缺陷游乐设施用Q235圆管构件弯曲破坏声发射特性

为研究带有槽缺陷游乐设施用Q235圆管构件破坏时声发射特性,利用声发射技术监测其三点弯曲破坏过程。通过对载荷时间曲线与声发射相对能量、幅度、振铃计数特征参数历程图的综合分析,可将其破坏过程划分为3个阶段。该过程声发射信号幅值主要集中在40～70 dB之间,且随缺陷长度增加,超过70 dB信号振铃计数明显增多,典型阶段特征参数峰值增大。相对能量—持续时间历程图中高持续时间、低能量信号来自于加载过程中的噪声干扰。声发射特征参数将缺陷微小变化对构件整体性能的影响量化,历程图变化与力学行为一一对应,建立声发射特征信号与弯曲力学性能和缺陷长度的联系,为声发射监测游乐设施损伤的判定提供依据。     

基于声振传递的飞行器噪声振动环境预示方法研究

针对高速飞行器飞行条件下的噪声、振动环境恶劣、复杂、难预示的问题,提出了基于声振传递的飞行器飞行条件下的噪声、振动环境预示方法。采用数值仿真、脉动压力风洞试验或工程分析等方法,获取飞行器在典型工况下的舱外脉动压力场;通过噪声试验或声振耦合仿真分析的方法,得到飞行器声振传递特性;根据获得的舱外脉动压力和声振能量传递特性,结合具体飞行参数得到实际飞行条件下的飞行器声振预示环境。采用该方法对某飞行器开展了振动环境预示研究,经地面及飞行试验验证振动环境量级预示精度可达1.6 dB。提出的基于声振传递的飞行声振环境预示方法可以广泛应用在导弹、火箭等飞行器的精细化环境设计中,对于提高飞行器总体性能、环境适应性和飞行可靠性具有重要的工程意义。     

Failure Analysis of a Launch Vehicle Umbilical Shutter Mechanism During Vibration Qualification

Payload fairing (PLF) of a launch vehicle is exposed to harsh vibration environments due to jet noise during liftoff and in-flight aerodynamic noise. Accordingly, the systems mounted on the payload fairing are to be qualified for the vibration levels, predicted corresponding to the envelope of acoustic spectrums at critical instants of atmospheric flight. This paper presents a detailed study of a failure observed on the payload cooling umbilical system, mounted on the cylindrical portion of the PLF structure, during its design qualification vibration testing. The umbilical shutter inadvertently opened during the test. The vibration responses on the shutter, the dynamic behavior of the system, and the forces and moments on the mechanism are analyzed, and the physics of failure is understood. The design marginality is identified, and the shutter locking mechanism reconfigured to achieve the desired level of robustness in the system.     

Design and testing of the Minotaur advanced grid-stiffened fairing

A composite grid-stiffened structure concept was selected for the payload fairing of the Minotaur launch vehicle. Compared to sandwich structures, this concept has an advantage of smaller manufacturing costs and lighter weight. To reduce weight the skin pockets are allowed to buckle visibly up to about 0.5 cm peak displacement.

Various failure modes were examined for the composite grid-stiffened structure. The controlling criterion for this design was a joint failure in tension between the ribs and skin of the structure. The identification of this failure mechanism and the assessment of bounding strains required to control it required extensive test and analysis effort. Increasing skin thickness to control skin buckling resulted in reduced strains between the skin and ribs.

Following the identification of the relevant failure criteria, a final design for the fairing was generated. The resulting 6 m tall fairing was constructed of a tow-placed carbon fiber composite grid structure that was over-wrapped to create a laminated skin. Upon completion of curing and machining, the fairing was cut in half to create the classic “clam-shell” fairing. Static qualification testing demonstrated the structural integrity of the fairing, thereby proving the design and manufacturing process. Loads were applied incrementally in a static loading scenario. The applied load envelope exceeded worst-case dynamic flight conditions with an added safety factor of 25%. At peak load the fairing maintained structural integrity while remaining within the required displacement envelope for payload safety.

Data were collected during the test from a variety of sensors including traditional displacement transducers and strain gages. In addition, full field displacement was monitored at critically loaded fairing sections by means of digital photogrammetry. This paper summarizes the test results, presents the overall performance of the fairing under the test loads, correlates test response and analysis, and identifies lessons learned.

Work continues at the Air Force Research Laboratory (AFRL) and Boeing to identify means of further controlling tensile failure of the un-reinforced polymer bonded joint between the ribs and skin. Stiffening of skin adjacent to the joints and introduction of lightweight foam jackets at the interior of the fairing both show promise of delaying joint failure to higher loads.     

扬声器阵列辐射声压级自动控制装置设计

针对强声波设备的使用安全性的问题，设计了一种强声波扬声器阵列辐射声压级自动控制装置，该装置通过控制功放驱动功率达到自动调节扬声器阵列输出声压级目的。硬件电路基于单片机ATmega48设计，单片机中固化了自动控制软件，结合目标距离实现对扬声器阵列辐射声压级的调节控制。将该装置加装于多个型号的强声波装置进行外场测试，结果表明，各扬声器阵列前方声压级均控制在安全范围内，因此可将其应用于强声波系统中避免强声波对非目标人员造成伤害。     

电流变夹层圆柱腔体的高频声振响应特性的实验研究

采用电流变流体(ERF)，结合工程实际中常见的隔声腔体结构，通过实验研究了高频声激励作用下含电流变材料夹层圆柱腔体的声振响应特性及其变化。结果表明：当外激励为高频信号时，电流变效应的影响仍相当明显，通过对电流变材料施加电场控制，可以对夹层壳形成的封闭腔体的结构振动进行有效的控制。所进行的声振实验结果显示，电流变效应对复合结构的振动在不同的频率段可产生抑制和放大的不同作用，说明在高频激励环境下，电流变复合结构仍具备较强的振动控制能力；同时，腔体外部的声压并未因电流变效应的作用发生明显改变，表明电流变效应对高频噪声没有明显的控制作用。     

成都市锦城绿道一期声景调查与评价

随着人们环境保护意识的提高及声景学相关研究在国内的兴起,声景对城市绿地的影响日渐加深。基于客观声压级与主观声舒适度评价两种数据的绿道声环境表现,通过解析场地声景优劣的影响因素,运用多维视角提出锦城绿道一期声景优化的策略与建议。并得出以下主要成果及结论：首先,城市道路所产生的车流噪声对绿道影响显著,绿道内部景观节点处呈现出高声压级点状聚集。其次,游客对安静的声环境期待较高,较为安静且自然声较高的区域更容易被游客接受,同时消极声的干扰程度、场地功能的协调性是产生声环境差异的主要因素。最后,全局统筹规划并在声源、传播过程及受声处实现多过程管控才能够形成协调的声环境。     

3 t 叉车驾驶室声场特性分析

建立3 t叉车驾驶室的三维有限元模型,进行结构模态分析;再建立驾驶室声学有限元模型,进行声学模态分析,初步了解驾驶室的声场。对驾驶室进行谐响应分析,得到位移响应,为后续声场提供边界条件。用有限元法进行驾驶室内部声学特性研究,对驾驶员耳旁声压进行分析,得出驾驶室内声场的声学特性。在计算出场点声压频率响应的基础上,在峰值频率处进行面板贡献量分析,找出产生峰值声压的主要来源,为降低驾驶室内噪声提供依据。     

薄壁板在随机声载荷作用下的振动响应谱估算

针对飞行器薄壁结构声疲劳问题，研究了具有多模态的薄壁板结构在声载荷作用下振动响应谱的估算方法。基于正交模态法，采用结合受纳函数描述结构模态和声场空间压力分布的耦合关系，建立动态响应计算模型。为与试验结果进行对比，选取具有固支边界的金属薄壁板作为研究对象，以试验测得的噪声载荷作输入，计算了该结构的振动响应谱，估算了均方应力，并将计算结果与试验数据进行比较和讨论。     

用小型传声器阵列测量环境噪声中简单声源声压级

常规声级计测量到的是目标声和环境噪声的总声压,不具备抑制环境噪声的功能。为此使用以球面波函数叠加逼近理论为基础的声波分离方法,用以提升环境噪声中简单声源声压级的测量精度。该方法以小型传声器阵列探头作为测量前端,近场声全息和声波分离为核心计算方法进行实施。为验证该方法的有效性,在全消声室内对关键参数进行了实验验证。实验结果表明,该方法在500 Hz~2 750 Hz频带内,且探头距目标声源5 cm~12 cm的近场区域,可以在环境噪声中得到较精确的目标声源的声压级。     

Thermo-acoustic random response of temperature-dependent functionally graded material panels

A nonlinear finite element model is provided for the nonlinear random response of functionally graded material panels subject to combined thermal and random acoustic loads. Material properties are assumed to be temperature-dependent, and graded in the thickness direction according to a simple power law distribution in terms of the volume fractions of the constituents. The governing equations are derived using the first-order shear-deformable plate theory with von Karman geometric nonlinearity and the principle of virtual work. The thermal load is assumed to be steady state constant temperature distribution, and the acoustic excitation is considered to be a stationary white-Gaussian random pressure with zero mean and uniform magnitude over the plate surface. The governing equations are transformed to modal coordinates to reduce the computational efforts. Newton–Raphson iteration method is employed to obtain the dynamic response at each time step of the Newmark implicit scheme for numerical integration. Finally, numerical results are provided to study the effects of volume fraction exponent, temperature rise, and the sound pressure level on the panel response.     

Optimality criteria-based topology optimization of a bi-material model for acoustic–structural coupled systems

This article investigates topology optimization of a bi-material model for acoustic–structural coupled systems. The design variables are volume fractions of inclusion material in a bi-material model constructed by the microstructure-based design domain method (MDDM). The design objective is the minimization of sound pressure level (SPL) in an interior acoustic medium. Sensitivities of SPL with respect to topological design variables are derived concretely by the adjoint method. A relaxed form of optimality criteria (OC) is developed for solving the acoustic–structural coupled optimization problem to find the optimum bi-material distribution. Based on OC and the adjoint method, a topology optimization method to deal with large calculations in acoustic–structural coupled problems is proposed. Numerical examples are given to illustrate the applications of topology optimization for a bi-material plate under a low single-frequency excitation and an aerospace structure under a low frequency-band excitation, and to prove the efficiency of the adjoint method and the relaxed form of OC.