超高速高空低动压柔性罩体脱落天地相关性研究

柔性罩体包裹于飞行器外表面,在飞行中段起到保护作用.再入过程中在气动力/热共同作用下,从飞行器表面拉开、脱落,脱落过程产生的附加干扰力/力矩,对飞行器再入姿态产生影响,造成惯性落点偏差.采用地面风洞模拟超高速高空低动压环境,考核不同再入动压条件下,罩体连接绳在气动力作用下的脱开过程,以及脱落过程对飞行器产生的干扰力/力...     

离心泵导叶流道进口处压力脉动研究

为研究离心泵导叶流道进口处压力脉动的分布及传播规律,深入探究导叶式离心泵内动静干涉作用机理。试验采集某核级离心泵相邻两个导叶流道进口处压力脉动信号,并对其进行分析。结果表明:模态节径模式分析方法可以用来分析预测压力脉动主要特征频率成分,导叶流道进口处压力脉动主要为叶片通过频率及其倍频,并以此形式沿叶轮旋转方向向下传播。相同导叶流道进口处流体流动具有不均匀性,各测点压力脉动主要特征频率及最大幅值对应频率不同。压力脉动在叶片通过频率及其倍频处相关性强,随着流量增大至设计工况,压力脉动能量逐渐集中到叶片通过频率及其倍频处。研究可为降低泵内压力脉动提供一定参考。     

基于高斯伪谱法的高超声速飞行器再入制导研究

针对高超声速飞行器再入标准轨迹制导方法中存在的制导准备周期长、弹上需存储标准轨迹参数、制导鲁棒性较差等缺点,本文提出了一种基于高斯伪谱法与滚动时域控制技术相结合的高超声速飞行器再入预测-校正制导方案。其中,在线高斯伪谱法采用纵/侧向、全程一体化的制导算法思路,从而实现了对高超声速飞行器再入弹道的全程预测-校正。同时结合滚动时域控制技术从工程上实现了高超声速飞行器再入制导中对开环制导信息的闭环应用,完成了飞行器预测-校正制导方案。通过对高超声速飞行器再入制导过程进行仿真分析,其结果表明应用本文设计的基于高斯伪谱法与滚动时域控制技术相结合的高超声速飞行器再入预测-校正制导方案,飞行器再入过程中具有良好的制导性能。     

基于PANDA平台的光机部件随机振动响应分析

基于PANDA自主并行计算平台,采用模态叠加法开展了多点基础激励作用下的随机振动响应分析算法设计和并行实现研究,构建了相应的并行求解模块。针对光机装置打靶样机中的六自由度平台结构,基于自主研发的软件模块,分析了该结构的模态特性及结构在地脉动载荷下的微振动响应,并与试验结果及商业软件分析结果进行了比对,在模态频率、振型和位移响应方面,都具有较好的一致性,验证了相关软件模块的正确性和PANDA平台在实际工程结构分析中的可用性。     

强耦合面对称飞行器横航向模态控制效能

面对称飞行器具有强耦合、弱阻尼的特点,为实现其横航向模态的高效控制,对控制策略效能及高效控制策略选择判据进行了研究.通过建立稳定轴系下横航向耦合动力学模型,得到了模态特征简化表达式;分析了有效的模态控制策略,并推导了各控制策略的效能公式;通过对各控制策略效能的对比分析得到了耦合特征下的高效模态控制策略选择判据;最后通过根轨迹分析、模态特性评估与6自由度仿真进行验证,结果表明理论公式与分析仿真结果一致.高效模态控制策略选择判据能够准确表征不同控制策略的效能关系,可用于指导强耦合面对称飞行器横航向模态控制方案设计.      

湍流边界层激励下腔体内水动力自噪声预报与测量

循环水槽中试验测量了腔体内水动力自噪声,并与模态法建立的湍流脉动压力引起腔体自噪声预报进行比较验证。透声窗振动以简支边界为条件,腔体内部声波以刚性边界为条件模态展开,通过辐射边界条件建立模态耦合振动方程。在随机湍流脉动压力作用下,推导了模态振动方程在随机力激励下的自噪声功率谱响应。对循环水槽中5 m/s和8 m/s两种流速工况下的腔体水动力自噪声和湍流脉动压力进行了测试,结合测量的脉动压力预报方法可以计算腔体水动力自噪声量值,理论预报与试验测量结果大致吻合,趋势一致,为声呐罩材料选取及声学环境控制提供了一种分析方法。     

湍流边界层激励下腔体内水动力自噪声预报与测量

循环水槽中试验测量了腔体内水动力自噪声,并与模态法建立的湍流脉动压力引起腔体自噪声预报进行比较验证。透声窗振动以简支边界为条件,腔体内部声波以刚性边界为条件模态展开,通过辐射边界条件建立模态耦合振动方程。在随机湍流脉动压力作用下,推导了模态振动方程在随机力激励下的自噪声功率谱响应。对循环水槽中5 m/s和8 m/s两种流速工况下的腔体水动力自噪声和湍流脉动压力进行了测试,结合测量的脉动压力预报方法可以计算腔体水动力自噪声量值,理论预报与试验测量结果大致吻合,趋势一致,为声呐罩材料选取及声学环境控制提供了一种分析方法。      

基于新型ICP脉动压力传感器的信号调理电路设计与实现

在飞行器地面试验中,新型ICP脉动压力传感器常用来测量飞行器与发射筒之间的关键位置表面由于空气脉动产生的脉动压力参数;ICP脉动压力传感器工作时需要恒流源供电,同时其输出信号不能满足大多数模数转换芯片对于输入电压的要求,针对以上问题,提出了一种基于新型ICP脉动压力传感器的信号调理电路,并详细介绍了电源电路、脉动压力信号调理电路等模块的设计原理和方法;测试结果表明该设计能够满足新型ICP脉动压力传感器3.4 mA恒流源供电需求,并且能准确地将其输出电压信号调理为0.366~2.13 V,符合AD7667转换范围要求,同时能有效地滤除信号中混入的9.6 kHz以上的高频噪声以及椭圆型高阶低通滤波器自身引入的开关噪声;该信号调理电路可靠性高,已经成功应用于飞行器地面发射试验中。     

基于正交试验的RLV再入轨迹参数灵敏度分析

为分析RLV再入过程中参数对再入动态性能的影响,基于正交试验设计理论,运用极差分析法对影响RLV再入过程的7项重点参数开展灵敏度研究,仿真试验结果表明峰值热流、峰值动压、峰值过载和总加热量对初始速度和质量最为敏感,质量、初始航迹偏角、常值升力系数和初始高度之间的耦合灵敏度较大。提高初始速度和质量的精度,其它灵敏度较低的参数可适当放宽精度,从而提高飞行器性能,降低飞行器研制成本,确保再入飞行的安全性和可靠性。该方法不受系统模型限制,能减少试验运算和数据处理工作量,可有效应用于非线性、不连续的RLV动态再入过程制导算法鲁棒性评估和参数灵敏度分析,为再入任务规划提供理论支撑。     

基于遗传算法的升力体外形优化设计

升力体由于低热流率再入物理特性和高效的内部容积利用率，是高超声速飞行器气动外形的一种典型布局.文章对升力体飞行器进行参数化数值建模，并提取其表征外形的参数作为设计变量，综合考虑飞行器再入过程中的气动力、气动热、容积利用率及稳定性等性能指标.运用多目标混合遗传算法对升力体进行了多变量、多约束下的气动外形优化设计，获得了再入飞行器外形的最优Pareto解.数值模拟结果表明，典型状态下最优Pareto解与CFD结果相差12%，验证了优化结果的准确性.      

Measurement and analysis of rolling tire vibrations

This paper presents the measurement and analysis of rolling tire vibrations due to road impact excitations, such as from cobbled roads, junctions between concrete road surface plates, railroad crossings. Vibrations of the tire surface due to road impact excitations cause noise radiation in the frequency band typically below 500 Hz. Tire vibration measurements with a laser Doppler vibrometer are performed on a test set-up based on a tire-on-tire principle which allows highly repetitive and controllable impact excitation tests under various realistic operating conditions. The influence on the measured velocity of random noise, cross sensitivity and alignment errors is discussed. An operational modal analysis technique is applied on sequential vibration measurements to characterise the dynamic behaviour of the rolling tire. Comparison between the operational modal parameters of the rolling tire and the modal parameters of the non-rolling tire allows an assessment of the changes in dynamic behaviour due to rolling.     

数控裁剪机切割刀壳体振动噪声预测分析

高频往复式切割刀是柔性材料数控裁剪机的核心部件.该文对切割刀壳体的振动噪声改进措施进行研究.首先对切割刀进行刚体动力学分析,获取其所受动载荷情况,并通过数值计算验证了切割刀刚体动力学模型的可靠性.其次,基于有限元法获取切割刀壳体模态特性,并通过锤击激振实验验证了有限元模型的准确性.然后基于模态仿真结果进行谐响应分析,将...     

Time domain identification of standing wave parameters in gas piping systems

A method for experimentally determining the natural frequencies and modal pressures of an air or gas piping system is presented. Such information is of interest in installations where pressure pulsations caused by pumps or compressors are of importance. In the method a time domain based technique is used which was originally developed as an alternative to frequency response methods for determining the vibration parameters (natural frequencies, modes, damping factors) of structures, to avoid difficulties often encountered in interpreting complex and non-conclusive frequency response data such as arises from systems having numerous modes, some of which may be highly damped or closely spaced in frequency. In this application, a straight steel pipe with a sound source at one end and closed at the other end was used. Two microphones were used to measure the pressure at two locations in the pipe. The free pressure response following a rapidly swept sinewave input was recorded, digitized and then used in a computational procedure based on a lumped parameter representation of the system. The natural frequencies and the corresponding modal pressure ratios at the two stations, thus obtained, are compared with mention here that although in the experiment reported here an external frequency sweep excitation was used, the technique works as well with free decay response after a system shut-off, impulse response or random responses from normal system operation.     

USING THE CROSS-CORRELATION TECHNIQUE TO EXTRACT MODAL PARAMETERS ON RESPONSE-ONLY DATA

Modal parameter identification is used to identify those parameters of the model which describe the dynamic properties of a vibration system. Classical modal parameter extractions usually require measurements of both the input force and the resulting response in laboratory conditions. However, when large-scale operational structures are subjected to random and unmeasured forces such as wind, waves, or aerodynamics, modal parameters estimation must base itself on response-only data. Over the past years, many time-domain modal parameter identification techniques from output-only have been proposed. Among them, the natural excitation technique (NExT) has been a very powerful tool for the modal analysis of structures excited in operating environment. This issue reviews the theoretical development of natural excitation technique (NExT), which uses the cross-correlation functions of measured responses coupling with conventional time-domain parameter extraction under the assumption of white-noise random inputs. Then a frequency-domain poly reference modal identification scheme by coupling the cross-correlation technique with conventional frequency-domain poly reference modal parameter extraction is presented. It uses cross-power spectral density functions instead of frequency response functions and auto- and cross-correlation functions instead of impulse response functions to estimate modal parameters from response-only data. An experiment using an airplane model is performed to investigate the effectiveness of the cross-correlation technique coupled with frequency-domain poly reference modal identification scheme.     

32级模块化Marx发生器机芯模态分析

模态分析可以获得结构的动特性参数。对32级模块化Marx发生器机芯进行了力学特性仿真分析和模态试验,用以评估Marx发生器的力学环境适应性。首先,建立了模块化Marx机芯的有限元模型,获得了初步振型;其次,在自由边界条件下分别开展了Marx机芯整体模态试验、局部模态试验和传递特性试验,得到了整体和局部结构的模态参数。研究表明,模块化Marx机芯在23.58 Hz处出现整体一阶扭转;机芯局部结构固有频率较高;机芯在x,y,z三个方向的振动传递率的范围分别为5～15,6～10和10～35,为后续工程中Marx发生器机芯的针对性设计提供了参考。     

Evolution of the vibrational behavior of a guitar soundboard along successive construction phases by means of the modal analysis technique

The crucial piece of a craft guitar is the soundboard since it determines the quality of the sound given by the instrument. From the initial phase (the gross plate with no hole) until the last construction phase (the plate with the full structure) several stages are followed to modify the dynamic behavior of the structure and hence the acoustic response of the final guitar. The aim of this work is to analyze the effect of each modification on the vibrational response of the plate. With this in mind, an experimental modal analysis of all the construction phases has been performed in the low frequency range under free conditions. The response of the plate in each stage is defined by vibration patterns, resonance frequencies, quality factors, and admittance curves.     

Response of plates with unconstrained layer damping treatment to random acoustic excitation,part I: Damping and frequency evaluations

For theoretical evaluation of the response of a structure under random acoustic excitation a complete understanding is required of the various modes of vibration and the modal damping associated with each mode. In order to evaluate these parameters for plates with unconstrained layer damping treatment, some of the theoretical approaches applicable are used. Experimentally observed modal frequencies and associated loss factors are compared with those estimated by different theories for all edges simply supported and all edges clamped boundaries, after accounting for the damping at supports. The modes of vibration used in the theoretical analysis for these boundaries are compared with those observed in the experiments. These results are made use of in Part II for the evaluation of response under random acoustic excitation.     

The impact of flow induced loads on snap-through behavior of acoustically excited, thermally buckled panels

The analysis, and ultimately the design, of air-breathing hypersonic cruise-type vehicles is hampered by the inability to accurately capture the coupled fluid-thermal-structure interactions. There are few laboratory experiments that have investigated the interactions of compliant surface panels and hypersonic flow. The vast majority of experimental studies are limited to replicating only parts of the physical mechanisms and couplings because of the difficulty in imposing the complete transient, hypersonic environment. Studies of hot-structures, thermal protection systems, or exotic material and structural configurations, typically neglect vibration induced fluctuating pressures, shock-boundary layer interaction, the effect of transition, and separated flow. Conversely, hypersonic wind-tunnel experiments purposely neglect the influence of non-rigid structure on the aforementioned high-speed flow effects in an effort to better understand the nature of the high-speed effects. The goal of this study is to implement a simple computational model that seeks to incorporate many of the fluid-thermal-structure interactions inherent in hypersonic flow. This is accomplished using simplified aerothermal and aerodynamic theories in conjunction with a simply supported von Kármán panel in cylindrical bending. Comparisons are made between the inclusion and exclusion of self-induced and forced fluctuating pressures, as well as the fidelity required in computing the temperature distributions. Results indicate that self-induced pressure fluctuations, which arise from interactions of a vibrating structure with an ambient mean flow, significantly impact the response of panels to random acoustic loadings. Additionally, the inclusion of forced fluctuating pressure loadings can significantly reduce the onset time of panel flutter. It is surmised that experimental investigations must combine thermal loads, as well as both forced and self-induced fluctuating pressures.