不同后掠角三角翼的静态地面效应数值模拟

采用数值模拟的方法研究了不同后掠角三角翼的静态地面效应,通过对气动力和流场特性的分析发现,随着后掠角的减小,地面对迎风面下流动的阻滞作用增强,地效导致的迎风面气动力增量也随之增大。地效导致的背风面气动力增量同样随着后掠角的减小而增大,但在不同的后掠角范围内,地效诱导背风面气动力增量的机理不同:中大后掠角下,其主要通过增强前缘涡强度诱导更大的吸力,而小后掠角下,其主要通过促进前缘涡向内扩散增大吸力范围。      

调频引信谐波时序检测抗干扰方法及实现

针对调频（FM）引信抗干扰能力差的问题,提出了调频引信谐波时序检测抗干扰方法,利用弹目交会过程中谐波时序特征,提高了调频引信抗调幅（AM）、调频和扫频干扰能力;设计了基于快速傅里叶变换（FFT）的调频引信谐波提取方案,通过对差频信号进行FFT获得谐波幅值,与现有谐波定距调频引信通过带通滤波器（BPF）获得谐波幅值相比,在保证同等定距精度的前提下,可以灵活选取谐波次数和谐波通道,利用谐波时序性提高调频引信抗干扰能力,同时易于实现炸高分挡。仿真及实测结果验证了本文方案的可行性,调频引信抗干扰成功率由16.7%提高到90%以上。      

不同转速下跨声速轴流压气机内部流动失稳的机理

以跨声速轴流压气机转子NASA Rotor 67为研究对象,采用数值模拟方法,开展100%、80%及60%转速下跨声速轴流压气机内部流动失稳触发机制的机理研究。数值结果与实验数据的对比分析表明:在3个转速下,数值总性能曲线的变化趋势与实验数据符合一致。通过压气机内部流场的详细分析,得出其基本流动机理。在3个转速下,随着压气机节流,叶顶泄漏涡(TLV)的起始位置逐渐向叶片前缘移动,叶顶泄漏涡也逐渐向相邻叶片压力面偏转,相比近峰值效率点,近失速点时在100%、80%以及60%转速下叶顶泄漏涡的偏转角度分别为3°、6°和9°。在100%和80%转速下,叶顶泄漏涡与激波相互作用所导致的堵塞是触发压气机内部流动失稳的机制,并且在80%转速下,叶顶泄漏涡发生破碎;而在60%转速下,泄漏涡在相邻叶片出现的叶顶前缘溢流(LESF)是触发压气机内部流动失稳的主要机制,叶片吸力面尾缘出现的小尺度附面层气流分离(BLFS)不是主要机制。      

Application of shear-sensitive liquid crystal coating to visualization of transition and reattachment in compressor cascade

The present paper aims at introducing Shear-Sensitive Liquid Crystal Coating (SSLCC) technology into compressor cascade measurement for the first time and serves as a basis for better understanding of the influence from the boundary layers. Optical path layout, which is the most significant difficulty in internal flow field measurement, will be solved in this paper by self-designed image acquisition device. Massive experiments with different Mach number and incidence are conducted at a continuous subsonic cascade wind tunnel to capture the boundary layer phenomenon. Image processing methods, such as Three-Dimensional (3-D) reconstruction and Hue conversion, are used to improve the accuracy for transition position detection. The analysis of the color-images indicates that complex flow phenomena including transition, flow separation, and reattachment are captured successfully, and the effect of Mach number and incidence on the boundary layer flow is also discussed. The results show that: the Mach number has a significant effect on transition position; the incidence has little effect on transition position, but it has a great impact on the transition distance and leading-edge separation; influenced by the end-walls, the reattachment occurs in advance under positive angle of attack conditions.     

航天器可展开薄膜遮光罩的构型设计与优化

针对当前航天器遮光罩轻量化的需求，在保证薄膜遮光罩有效面积不变的前提下，根据质量和有效面积占比设计了一款柔性平面薄膜遮光罩。以提高薄膜边缘应力的同时尽量避免有效圆面积占比减少为优化目标，对薄膜遮光罩的边缘做弧边优化设计。结果表明，当薄膜遮光罩为正六边形时，既能保证结构对称性，又能获得较低的单位有效面积占比对应质量。通过应力叠加法建立了薄膜遮光罩的应力分布模型，求出薄膜边缘应力的理论计算值。探究了弧边拱高的增加对薄膜边缘应力和有效圆面积占比的影响规律，当二者的函数曲线相交于一点时，可取为薄膜弧边的最优拱高。根据设计的薄膜遮光罩参数，搭建薄膜遮光罩的试验样机并进行展开试验。薄膜遮光罩可完全展开，薄膜边缘张紧度高，证明了薄膜遮光罩系统方案设计的可靠性，弧边设计可有效提高薄膜边缘的应力水平。     

快收敛高可靠PPP-RTK大气改正模型生成方法

生成快收敛、高可靠的大气改正模型是PPP-RTK（precise point positioning-real-time kinematic）应用的关键和瓶颈问题。对顾及快收敛和可靠性的PPP-RTK大气改正模型生成方法进行了研究，通过迭代约束和时域约束保证其快收敛与可靠性，利用武汉CORS（continuously operating reference stations，连续运行参考站）进行试验，45s能够实现水平10cm（95%）的定位精度。在此基础上利用香港CORS进一步验证与分析得出：增加格网密度能够提升定位精度但会增加信息量，需要综合考虑定位效果和播发的信息量，面向普通用户的格网大小经纬度建议设置为0.5°~0.8°；生成大气改正模型的参考站空间分布必须合理且均匀，同时提出可以在合理范围内加入虚拟参考站约束大气改正模型的生成从而保证其收敛性与可靠性。     

边缘网络下多无人机协同计算和资源分配联合优化策略

针对边缘网络环境下多人机之间存在计算负载不均，造成卸载任务失败的问题，提出了一种多无人机间协作的智能任务卸载方案。通过联合考虑多无人机任务分配、计算资源分配和无人机飞行轨迹，引入公平性指数建立了无人机公平负载最大化和能量消耗最小化问题。基于多智能体深度强化学习框架，提出了融合轨迹规划和任务卸载的分布式算法。仿真结果表明，所提出的多无人机协作方案可以显著提高任务完成率和负载公平度，并且有效适用于大规模用户设备场景。     

基于高轨导航接收机的自动化地面测试系统

高轨卫星导航接收机是实现高轨航天器自主定轨的核心设备。为在地面测试阶段对高轨卫星导航接收机进行充分高效的验证，亟需设计基于高轨卫星导航接收机的地面测试系统。设计了一种基于高轨卫星导航接收机的自动化地面测试系统，主要创新点如下：第一，本系统可对高轨卫星导航接收机实际在轨状态下接收到的导航星座信号进行仿真；第二，具有模拟包含北斗三号等多导航卫星星座信号的功能；第三，本系统充分考虑自动化、通用化与一体化设计。提出的基于高轨卫星导航接收机的自动化地面测试系统能够在地面测试阶段对高轨卫星导航接收机进行充分验证，并充分考虑测试实施，从自动化、通用化、一体化方面提升测试效率，减少人为操作失误导致的质量问题，解决人工判读带来的误判漏判问题。     

Method for utilizing PIV to investigate high curvature and acceleration boundary layer flows around the compressor blade leading edge

Particle Image Velocimetry (PIV) is a well-developed and contactless technique in experimental fluid mechanics, but the strong velocity gradient and streamline curvature near the wall substantially limits its accuracy improvement. This paper presents a data processing procedure combining conventional PIV and newly developed Mirror Interchange (MI) based Interface-PIV for the measurement of the boundary layer parameter development in the blade leading edge region. The synthetic particle images are used to analyze the measurement errors in the entire procedure. Overall, three types of errors, namely the errors caused by the Window Deformation Iterative Multigrid (WIDIM) algorithm, the discrete data interpolation and integration, and the wall offset uncertainty, comprise the main measurement error. Specifically, the errors due to the discrete data interpolation and integration and the WIDIM algorithm comprise the mean bias, which can be corrected through the error analysis method proposed in the present work. Meanwhile, the errors due to the WIDIM algorithm and the wall offset uncertainty contribute to the measurement uncertainty. Computational fluid dynamics-based synthetic particle flows were generated to verify the newly developed PIV data processing procedure and the corresponding error analysis method. Results showed that the data processing method could improve the accuracy of PIV measurements for boundary layer flows with high curvature and acceleration and even with significant flow separation bubbles. Finally, the data processing method is also applied in a PIV experiment to investigate the boundary layer flows around a compressor blade leading edge, and several credible boundary flow parameters were obtained.     

A physically-based representative stress methodology for predicting stress rupture life of Ni-based DS superalloy

Smooth and three types of U-shape single-edge notched plate specimens adopted to experimentally investigate stress rupture behavior of Ni-based Directionally Solidified (DS) superalloy at 850 °C exhibit notch weakening effect and multi-source cracking initiation near the notch root. However, stress rupture behavior of smooth and V-shape notched round bars at 1040 °C revealed by Li et al indicates notch strengthening effect and creep micro-holes originating mostly from the central portion. A combined creep-viscoplastic constitutive model is employed to analyze the distribution of stress, strain and stress Triaxial Factor (TF) near the notch root. The different stress distribution and creep restraint between asymmetric notched plate specimens and symmetric notched round bars are the main reasons for the corresponding failure mechanism. Meanwhile, a good qualitative relationship exists between TF value and stress rupture life of notched specimen. Especially, the area with maximum TF value (TF_max) is highly consistent with creep damage initiation region. Hence, based on the distribution characteristics of the initial tensile loading, a representative stress method independent of time -changing creep load at the location of TF_max is conducted for life prediction. The predicted results of both smooth and notched plate specimens and round bars agrees well with the experimental results.