某型先进发动机燃油喷嘴雾化特性的试验研究及火焰筒头部数值模拟

使用相位多普勒粒子分析仪和激光多普勒粒子测速仪系统(PDPA/LDV)等设备测量了某型航空发动机喷嘴的雾化特性,主要包括:喷嘴流量特性,雾化粒度(SMD)和喷雾锥角。应用Fluent软件,对装用该喷嘴的燃烧室火焰筒进行了数值模拟。试验和计算结果得出了一些有价值的结论,对该发动机的燃油喷嘴和火焰筒头部温度场、速度场有深入了解,对其改进提供了重要依据。     

RTM成型聚酰亚胺复合材料研究

以苯乙炔封端聚酰亚胺树脂为基体,采用高温R1M工艺复合成型了T300碳布增强聚酰亚胺层合板,复合材料的Tg达351℃(DMA),材料在300℃弯曲强度保持率达90%以上,模量保持率达85%以上,层间剪切强度保持率达60%以上.     

RFI工艺成型两种环氧树脂基复合材料性能比较

采用RFI工艺分别成型了648和5228A环氧树脂基复合材料层合板,其增强材料为碳纤维无屈曲织物,铺层方式为[(0,90)/( 45)]s;测试了两组层舍板的拉伸性能、弯曲性能和层间剪切性能并做了比较分析;对破坏形式和机理进行了探讨.结果表明:5228A相对于648环氧树脂膜有较宽的低黏度区域,较长的凝胶时间;5228A与648层合板相比,拉伸强度高106%,拉伸模量、泊松比接近;弯曲强度高58%,弯曲模量高16%;层间剪切强度高62%.     

Track-before-detect for Infrared Maneuvering Dim Multi-target via MM-PHD

In this paper, we present a novel and efficient track-before-detect (TBD) algorithm based on multiple-model probability hypothesis density (MM-PHD) for tracking infrared maneuvering dim multi-target. Firstly, the standard sequential Monte Carlo probability hypothesis density (SMC-PHD) TBD-based algorithm is introduced and sequentially improved by the adaptive process noise and the importance re-sampling on particle likelihood, which result in the improvement in the algorithm robustness and convergence speed. Secondly, backward recursion of SMC-PHD is derived in order to ameliorate the tracking performance especially at the time of the multi-target arising. Finally, SMC-PHD is extended with multiple-model to track maneuvering dim multi-target. Extensive experiments have proved the efficiency of the presented algorithm in tracking infrared maneuvering dim multi-target, which produces better performance in track detection and tracking than other TBD-based algorithms including SMC-PHD, multiple-model particle filter (MM-PF), histogram probability multi-hypothesis tracking (H-PMHT) and Viterbi-like.     

A Twin-CME Scenario for Ground Level Enhancement Events

Ground Level Enhancement (GLEs) events are extreme Solar Energetic Particle (SEP) events. Protons in these events often reach ～GeV/nucleon. Understanding the underlying particle acceleration mechanism in these events is a major goal for Space Weather studies. In Solar Cycle 23, a total of 16 GLEs have been identified. Most of them have preceding CMEs and in-situ energetic particle observations show some of them are enhanced in ICME or flare-like material. Motivated by this observation, we discuss here a scenario in which two CMEs erupt in sequence during a short period of time from the same Active Region (AR) with a pseudo-streamer-like pre-eruption magnetic field configuration. The first CME is narrower and slower and the second CME is wider and faster. We show that the magnetic field configuration in our proposed scenario can lead to magnetic reconnection between the open and closed field lines that drape and enclose the first CME and its driven shock. The combined effect of the presence of the first shock and the existence of the open close reconnection is that when the second CME erupts and drives a second shock, one finds both an excess of seed population and an enhanced turbulence level at the front of the second shock than the case of a single CME-driven shock. Therefore, a more efficient particle acceleration will occur. The implications of our proposed scenario are discussed.     

Study on Conceptual Selection for Provision of Trainers in Primary and Intermediate Training Stage

为了在初/中级教练机装备方案决策中体现出训练需求,选用质量功能展开的方法对其进行了分析.先利用比较矩阵确定训练需求重要度,建立训练需求与能力属性之间的QFD关系矩阵,得到不同能力属性的重要度,最后计算出个方案的能力属性值,通过线性加权计算将属性值反映到不同方案对于训练需求的满足程度上来,得出了量化分析的结果,为教练机装备决策方法研究提供了一个新思路.     

温度梯度环境中潜艇尾流热特征的试验研究

改进了用于实验室热尾流测量的温度测量系统,提高了系统的集成度和抗干扰能力。在水槽中实验研究了螺旋桨推进潜艇模型在有、无温度分层流体中尾流的热特征,得到两种条件下尾流的温度分布和信号衰减规律,分析了两种尾流信号的形成机理及其影响因素,表明在温度分层环境中＂冷尾流＂信号对探测和识别水下航行的潜艇更为有利,所得结果可为红外反潜和潜艇红外隐身提供更加切合实际的理论支撑。     

高速风洞试验中运输机支撑形式的选择

合理选择模型的支撑形式和解决支架干扰问题是准确获取气动力数据的关键因素。为了寻找一种合适的运输类飞机在高速风洞试验中的支撑形式,首先通过计算分析和试验验证,给出了运输类飞机高速风洞试验中30°尾支撑支架干扰问题存在的原因,然后根据0°、5°、15°以及30°不同尾支撑形式的计算分析和专项试验论证结果,提出并验证了小角度尾支撑是现阶段运输类飞机高速风洞试验中最合理、最有效的支撑形式。     

细长旋成体大迎角俯仰振荡的数值研究

为研究俯仰振荡对细长旋成体流场与气动特性的影响,利用雷诺平均方法与大涡模拟的混合方法相结合的脱体涡模拟方法对大迎角下细长旋成体俯仰运动进行了数值模拟研究。通过对背风面分离涡的强度和位置、细长体绕流形态、截面压强系数和侧向力系数的观察和分析,发现施加小振幅、特定频率的俯仰振荡对大迎角细长旋成体背风面流场有明显的控制能力,...     

Integration of high-fidelity model of forward variable area bypass injector into zero-dimensional variable cycle engine model

Forward Variable Area Bypass Injector (FVABI) is one of key components which contributes to modulate the cycle parameters of Variable Cycle Engine (VCE) under various operation conditions. The modeling method of zero-dimensional FVABI was reviewed and its deficiency was analyzed based on FVABI flow characteristic. In order to improve the accuracy of VCE performance simulation, the high-fidelity modeling method of FVABI was developed based on its working characteristics. Then it was coupled with the zero-dimensional VCE model and the multi-level VCE model was built. The results indicate that the geometric and aerodynamic parameters can affect the interaction between the two airflows and the zero-dimensional FVABI model is too simple to predict the component performance accurately, especially when the FVABI inner bypass is chocked. Based on the performance curves for single bypass mode and the regression model of multi-scale support vector regression for double bypass mode, the high-fidelity model can predict FVABI performance accurately and rapidly. The integration of high-fidelity FVABI model into zero-dimensional VCE model can be done by adjusting iterative variables and balance equations. The multi-level model has good convergence and it can predict VCE performance when the FVABI inner bypass is chocked.