民用飞机发动机反推力装置作动系统的应用研究

首先对民用飞机发动机反推力装置的出现、作用、工作原理以及最新的发展趋势进行了简要而系统的阐述。对液压反推力装置作动系统和电反推力装置作动系统的构架和控制原理进行权衡分析,阐述了其在研制中应该注意的问题和考虑的因素,并对今后工作的开展提出了意见。     

民用飞机燃油箱系统热模型分析研究

飞机燃油箱系统热分析是飞机燃油系统设计和适航取证的关键技术之一。首先对燃油箱热模型分析方法进行了阐明,然后在典型热天环境中(地面温度为327K)对一种典型民用飞机燃油箱结构的热参数进行了工程计算研究。研究表明,外翼油箱、机身油箱以及集油箱内燃油温度分布不均匀;各油箱燃油温度在地面状态均高于巡航状态;燃油的最高温度时刻出现在地面终了状态,而且最高点位置出现在集油箱内。研究结果既可以指导飞机燃油箱设计,也可以为飞机燃油系统的适航取证提供一定技术支持。     

基于时频分析的裂纹转子碰摩故障特征研究

为研究转子系统耦合故障特性,采用有限元方法建立了含有横向裂纹、转静碰摩的非线性转子动力学模型。首先研究了不同转速下裂纹、碰摩单一故障下转子系统的振动响应,其次研究了两种故障耦合情况下系统的振动响应特征。采用波形图、FFT谱图、瞬时频率和Hilbert-Huang时频谱(HHS)相结合的方法对故障转子振动信号进行了分析。分析结果表明:运用多种时频分析相结合的方法可以较为全面地了解转子的故障特征,裂纹转子在1/5、1/3临界转速时会发生较为明显的5X、3X谐波,且裂纹的产生会导致响应幅值增大,从而引起更为严重的碰摩。     

基于ERSM涡轮盘径向变形的非线性动态概率分析

为了准确设计高压涡轮盘和叶尖间隙,从概率的角度进行了涡轮盘径向变形的分析。介绍了高精度高效率的非线性动态概率分析的极值响应面方法 (Extremum Response Surface Method,ERSM),并建立了其数学模型。考虑材料属性和边界条件的非线性,以及热载荷和离心载荷的动态性,基于ERSM对涡轮盘径向变形进行了非线性动态概率分析,得到了输入输出参数的分布特征和影响涡轮盘径向动态变形的主要因素。最后,通过方法比较,验证了ERSM在保证计算精度的前提下能大大提高计算速度,节约计算时间,改善计算效率。为进行更有效的涡轮盘设计和优化,改善叶尖间隙设计和控制的合理性提供了有效依据。     

科学实验卫星高速上行链路设计

为保障在卫星与地面之间开展空间量子科学实验的条件,必须为科学实验载荷建立一条星—地高速数据双向传输链路.通过跟踪CCSDS-SLS-NGU（空间数据系统咨询委员会-空间链路业务-下一代上行链路）工作组对NGU的研究进展,结合科学实验卫星有效载荷建立高速上行链路的需求,采用高带宽利用率调制技术、高效信道编码方式及适用的链路数据传输协议,设计了一种传输速率为1Mbit/s、误码率优于1×10-9的高速上行链路方案,并给出星载设备实现方案和地面初步测试结果.该方案在技术体制上兼容已有CCSDS规范,便于地面站及星载接收机实现,完全满足开展空间量子科学实验的需要.     

FGM板三维层合模型及热-噪声载荷下的动态响应研究

 为了有效地分析热-噪声联合载荷作用下的飞行器功能梯度壁板结构的非线性动态响应,提出了运用复合材料多层壳单元建立功能梯度材料(FGM)板的层合有限元建模新方法,研究了FGM板在热曲屈前、后状态下复杂的非线性时域动态响应特性,并探讨了梯度指数、热曲屈系数及声压级(SPL)等参数对FGM板非线性动态跳变响应的影响规律。FGM板三维层合建模新方法避免了采用常规有限元法(FEM)建模时需要在厚度方向划分大量单元的缺点;求解FGM板非线性动态响应时采用的隐式积分方案避免了模态叠加法对参与模态选择的经验性要求及模态截断造成的信息丢失等缺陷。仿真结果表明:FGM板层合有限元建模新方法合理可行、过程简便、计算精度高;研究发现:陶瓷-金属FGM板在热屈曲后的抗声振性能并不像热屈曲前那样介于金属板和陶瓷板之间,而是表现最差;热屈曲系数及声压级的组合形式是导致FGM板发生非线性跳变响应的主要影响因素。     

A visco-elastoplastic constitutive model of aircraft polymethylmethacrylate related to strain rate and temperature

The visco-elastoplastic mechanical behavior related to the applied strain rate and temperature around the glass transition temperature of Polymethylmethacrylate (PMMA) has been systematically investigated. The uniaxial tensile test was performed at strain rate and temperature rangs 1.0 × 10⁻⁴–1.0 × 10⁻² s⁻¹ and 363–393 K, respectively, and the Dynamic Mechanical Analysis (DMA) test was carried out between 363 K and 413 K at various frequencies. Moreover, the robust complex constitutive model considering the temperature and strain rate effect is proposed. A nonlinear viscoelastic model is established to describe the viscoelastic response on the basis of the Zhu-Wang-Tang (ZWT) model and the time temperature equivalence principle, including the dependence of strain rate and temperature. Considering the yield stress, the cooperative model is adopted. The viscoplastic mechanical response is manifested as the competition performance of the softening deformation and hardening behavior. The predicted mechanical responses maintain good consistency with the experimental results, indicating that the visco-elastoplastic constitutive model proposed can accurately predict the mechanical behavior of PMMA materials within the imposed strain rate and near the glass transition temperature range.     

Novel attitude determination method by integration of electronic level meter,INS, and low-cost turntable for level attitude evaluation and calibration of INS

Attitude references are greatly needed for the evaluation and calibration of Inertial Navigation Systems (INSs), which are widely used in gravimeter, marine, and aeronautical navigation. High-accuracy turntable, INS, and Global Navigation Satellite System have been utilized to verify the performance of relatively low-accuracy INS. The accuracy requirement of the attitude reference continuously increases with the rapid improvement of inertial sensors and navigation algorithms. However, the cost of attitude determination system increases rapidly with the increase of attitude accuracy requirement. To solve this limitation, the integration of level meter, INS, and low-cost turntable is proposed to provide level attitude, such as roll and pitch. The turntable is utilized to rotate the INS. An integration model of the level meter and INS is built to estimate the level attitude and reduce the cost of the turntable. The proposed method successfully avoids the dependence on high-accuracy turntables. An observability degree analysis is conducted to improve the level attitude accuracy further. The simulation and turntable test results indicate that the proposed method can provide high-accuracy level attitude without high-accuracy INS or turntable and is applicable to error calibration and attitude evaluation of INS.     

Real-time modular dynamic modeling for compression system of altitude ground test facilities

Modeling of a centrifugal compressor is of great significance to surge characteristics and fluid dynamics in the Altitude Ground Test Facilities (AGTF). Real-time Modular Dynamic System Greitzer (MDSG) modeling for dynamic response and simulation of the compression system is introduced. The centrifugal compressor, pipeline network, and valve are divided into pressure output type and mass flow output type for module modeling, and the two types of components alternate when the system is established. The pressure loss and thermodynamics of the system are considered. An air supply compression system of AGTF is modeled and simulated by the MDSG model. The simulation results of mass flow, pressure, and temperature are compared with the experimental results, and the error is less than 5%, which demonstrates the reliability, practicability, and universality of the MDSG model.     

基于DCRSM的HPT叶尖径向运行间隙可靠性分析

为了有效地进行航空发动机高压涡轮(HPT)叶尖径向运行间隙(BTRRC)设计,从概率的角度进行BTRRC的可靠性分析.根据BTRRC的结构特点,提出了高精度、高效率可靠性分析的分布式协同响应面法(DCRSM),以二次响应面函数为基础建立了DCRSM数学模型,并将DCRSM应用到航空发动机HPT BTRRC的可靠性分析中加以验证.结果显示:当稳态叶尖间隙δ=1.86 mm时,BTRRC的可靠度为0.996 8,综合考虑发动机效率和可靠性,基本上满足BTRRC的设计和工程需要.通过方法比较显示了DCRSM在BTRRC可靠性分析中,不但能解决难以分析的问题,还能在保证计算精度的前提下提高计算速度和计算效率;充分验证了DCRSM在BTRRC可靠性分析中的有效性和可行性,为复杂机械可靠性分析和优化提供了有效依据.