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441.
内并联型TBCC进气道方案设计及验证 总被引:7,自引:4,他引:3
提出了一种带可变几何泄流腔的内并联型涡轮基组合循环(TBCC)进气道设计方案.介绍了进气道的总体设计思路,给出了进气道的设计马赫数、转级马赫数及飞行轨迹,对不同来流条件下进气道的工作方式以及全马赫数范围进气道型面调整的安排进行了论述,确定了进气道主要气动参数与型面参数的选取原则.通过数值模拟和高速风洞试验的手段,对进气道设计方案的可行性进行了验证.数值模拟结果表明:当Ma0≤2.5时,进气道的总压恢复系数均在0.8以上,当2.5<Ma0≤4.5时,进气道的总压恢复系数均在0.3以上,符合进气道总体方案的要求;冲压模态下,冲压通道的出口马赫数均小于0.4,出口静压均大于0.5个标准大气压,均能满足冲压燃烧室的燃烧需求.风洞试验结果表明:模态转换过程中,进气道涡轮通道具有良好的进/发匹配特性,且进气道涡轮/冲压通道具有良好的相容性能.研究结果可为我国开展组合动力研究提供方案参考和技术储备. 相似文献
442.
443.
N. Zolotukhina N. Polekh V. Kurkin O. Pirog S. Samsonov A. Moiseyev 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2012
We present an observational study of magnetospheric and ionospheric disturbances during the December 2006 intense magnetic storm associated with the 4В/Х3.4 class solar flare. To perform the study we utilize the ground data from North–East Asian ionospheric and magnetic observatories (60–72°N, 88–152°E) and in situ measurements from LANL, GOES, Geotail and ACE satellites. The comparative analysis of ionospheric, magnetospheric and heliospheric disturbances shows that the interaction of the magnetosphere with heavily compressed solar wind and interplanetary magnetic field caused the initial phase of the magnetic storm. It was accompanied by the intense sporadic E and F2 layers and the total black-out in the nocturnal subauroral ionosphere. During the storm main phase, LANL-97A, LANL 1994_084, LANL 1989-046 and GOES_11 satellites registered a compression of the dayside magnetosphere up to their orbits. In the morning–noon sector the compression was accompanied by an absence of reflections from ionosphere over subauroral ionospheric station Zhigansk (66.8°N, 123.3°E), and a drastic decrease in the F2 layer critical frequency (foF2) up to 54% of the quite one over subauroral Yakutsk station (62°N, 129.7°E). At the end of the main phase, these stations registered a sharp foF2 increase in the afternoon sector. At Yakutsk the peak foF2 was 1.9 time higher than the undisturbed one. The mentioned ionospheric disturbances occurred simultaneously with changes in the temperature, density and temperature anisotropy of particles at geosynchronous orbit, registered by the LANL-97A satellite nearby the meridian of ionospheric and magnetic measurements. The whole complex of disturbances may be caused by radial displacement of the main magnetospheric domains (magnetopause, cusp/cleft, plasma sheet) with respect to the observation points, caused by changes in the solar wind dynamic pressure, the field of magnetospheric convection, and rotation of the Earth. 相似文献
444.
基于粒子轨迹的结冰风洞收缩段优化设计数值模拟 总被引:1,自引:0,他引:1
为了研究收缩段型面和液滴轨迹特性对结冰风洞流场品质与结冰试验效果的重要影响,获得收缩段的优化设计参数,采用数值模拟方法,使用二维简化模型对3m×2m结冰风洞收缩段的流场特性进行了研究,对几种典型收缩曲线的流场进行了计算,对比了收缩曲线对沿轴向压力分布、出口截面速度分布、不同粒径云雾粒子的极限释放距离及试验段入口云雾粒子分布的影响,结果表明:三次曲线与xm为0.4的五次曲线不能满足流场合格指标,其他曲线流场特性差别不大,维氏曲线具有最小极限释放距离,在收缩段出口,三次曲线和五次曲线粒子包络面积最大,综合比较,xm为0.5的五次曲线能有效兼顾流场均匀性、极限释放距离和收缩段出口粒子包络面积比. 相似文献
445.
446.
《中国航空学报》2021,34(9):133-142
The low-speed wind tunnel experiment is carried out on a simplified aircraft model to explore the influence of wing flexibility on the aircraft aerodynamic performance. The investigation involves the measurements of force, membrane deformation and velocity field at Reynolds number of 5.4 × 104–1.1 × 105. In the lift curves, two peaks are observed. The first peak, corresponding to the stall, is sensitive to the wing flexibility much more than the second peak, which nearly keeps constant. For the optimal case, in comparison with the rigid wing model, the delayed stall of nearly 5° is achieved, and the relative lift increment is about 90%. It is revealed that the lift enhanced region corresponds to the larger deformation and stronger vibration, which leads to stronger flow mixing near the flexible wing surface. Thereby, the leading-edge separation is suppressed, and the aerodynamic performance is improved significantly. Furthermore, the effects of sweep angle and Reynolds number on the aerodynamic characteristics of flexible wing are also presented. 相似文献
447.
448.
飞翼布局飞行器等离子体激励滚转操控试验 总被引:2,自引:0,他引:2
飞翼布局飞行器采用多个气动舵面共同作用来控制飞行,常规气动舵面的结构复杂,在大迎角时由于流动分离,舵面操纵效率显著降低。等离子体激励器具有结构简单、重量轻和响应快等优势,常被用在流动控制上。本文利用激励器抑制单侧翼面流动分离产生不对称的气动力,对飞翼布局飞行器滚转通道的控制进行了试验研究,得出了激励器在飞行器上的最优布置位置和最佳控制参数,并和常规副翼舵面滚转操控效果进行了对比。结果表明:布置于内翼、中翼前缘的等离子体激励器能够获得最佳的滚转控制效果;激励器调制频率对飞行器滚转控制效果的影响较大,而激励电压对滚转控制效果的影响较小;与常规副翼相比,等离子体激励器在大迎角时对滚转通道的操控效果优于副翼。 相似文献
449.
针对舰载直升机小速度、大侧滑的飞行状态,采用了旋翼非均匀入流模型,导出了直升机在风场中的运动方程。以某型机为例,对不同风速条件下直升机悬停时的平衡特性进行了计算分析。计算结果表明:左侧风对该机悬停性能影响最大,而尾桨操纵裕度要求左侧风速不能超过30m/s,与同类直升机的飞行数据吻合。分析模型为制订舰载直升机的风险图提供了理论依据。 相似文献
450.
Vladimir Pines Marianna ZlatkowskiArnon Chait 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2010
In this paper we study the charging process of small grain particles by anisotropic multi-component solar wind plasmas (electrons, protons and heavy ions), versus two-component (electron/proton) plasmas. We are focusing attention on the important characteristics of the charging process, namely the charging time, floating potential and current content as functions of plasma parameters such as He++/H+ (α/p) number density and Tα/Tp temperature ratios of alpha particles to protons, as well as plasma streaming velocity v0. Measured statistical properties of solar wind plasma parameters at 1 AU show considerable variations in α/p-temperature ratios from 1 to 10, in α/p-number density ratio from 0.01 to 0.35, as well as in values of streaming velocity v0 from 200 km/s to 1000 km/s and more. Periods of these variations could last for several days each, leading to significant variability in the charging process, according to newly derived general analytical expressions. Numerical calculations performed for protons/alphas plasmas showed large disparity in the charging characteristics. For example, in anisotropic plasma, grain charging time varies up to 90% depending on α/p-particles temperature and number density ratios, whereas changes in floating potential are up to 40%. In contrast, in isotropic plasma, charging characteristic for grains do not change very much for the same plasma parameters variations, with charging time varying about 12% and floating potential only varying about 4%. It is also shown that in highly anisotropic plasma, with all ballistic electrons and ions, dust grains could not hold their charges, and characteristic discharged time is calculated. We note that the analysis is equally applicable to any sized body immersed in solar wind plasma. 相似文献