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1.
针对液体火箭发动机离心轮、涡轮静子等厚度变化大的复杂激光选区熔化成形(SLM)钢构件在常规X射线胶片照相检测(RT)时,由于胶片的宽容度低造成的检测覆盖率低,存在漏检质量隐患的问题,采用射线计算机成像技术(CR)对该类变截面厚度差在5~20 mm内的钢构件进行检测。结果表明,CR检测图像宽容度是胶片照相检测的3倍,检测覆盖率高;以离心轮线状缺陷CR检测为例,且通过CT和理化检测验证证明,CR检测具有与胶片照相检测基本一致的缺陷检测灵敏度、可靠性。 相似文献
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GE检测技术公司于2004年8月9日在上海成立中国应用中心,这是GE检测技术公司在全球成立的第8家应用中心,其服务将面向整个亚洲。 中国应用中心拥有完全数字化的X射线技术,胶片X射线技术,超声以及涡流等专业检测技术,并具有设计和生产超声波转换器的能力。GE检测技术可服务于不同领域的多个行业,包括航空、能源、化学/石化以及汽车行业,即能为不同行业客户送来的不同零件进行检测。检测的产品包括从检测航空发动机涡轮叶片 相似文献
4.
杨宝刚%金虎%任华友%吴东流 《宇航材料工艺》2004,34(2):26-28
简述了复合材料无损检测方面一些通用的射线检测方法,并通过对胶片射线照相技术、射线实时成像技术、计算机断层扫描成像技术、康普顿背散射成像技术等射线检测技术的系统介绍,展望了未来复合材料射线检测技术的发展趋势。 相似文献
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刘峻峰 《燃气涡轮试验与研究》2005,(2)
最近,G E/罗·罗战斗机发动机小组的F136项目在完成了常规起降(CTO L)和短距起飞/垂直着陆(STO V L)型发动机的所有性能、操纵性和空气动力学试验后,正向系统设计与验证(SD D)阶段迈进。目前,这两种发动机都比原计划提前交付,并按时完成了F-35项目办公室规定的所有试验要求。虽然这两种发动机的性能还不能完全令人满意,但这是完成第三阶段预先SD D合同的一个重要里程碑。预计,该小组将在8月获得F136发动机项目为期7年的第4阶段SD D合同。CTO L型发动机进行的试验包括性能评估、风扇失速风险降低和达到中间额定功率试验,同时还进… 相似文献
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衬层与药柱脱粘严重影响固体火箭发动机的结构完整性和工作安全性,该缺陷的可靠检测至关重要。文章综述了固体火箭发动机高能X射线检测技术现状。基于射线照相检测和工业CT检测手段,评述了固体火箭发动机衬层与药柱脱粘的图像分析和缺陷评判技术。针对该类缺陷,提出了综合应用射线照相技术和工业CT技术进行印证检测的方法,评判结果表明能够满足缺陷检测的可靠性与准确性要求。 相似文献
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通过铸造模拟软件ProCAST实现高Nb-TiAl合金叶轮熔模铸造充型凝固过程的模拟仿真,研究浇注充型工艺对合金熔体充型、缩孔缩松等充型凝固特性的影响,优化相应工艺;进行浇注实验与铸件的无损检测分析,并进行铸件的解剖分析验证缩孔缩松分布;使用附注试棒研究叶轮在室温和高温下的力学性能。结果表明:ProCAST软件对高Nb-TiAl铸件缩孔缩松预测较为准确,通过模拟仿真预测结果优化了工艺方案从而避免了铸件中大尺寸缩孔缩松的形成,在最终的铸件中只存在尺寸小于22μm的显微缩孔;所有铸件均实现完整充型,铸件室温抗拉强度约580 MPa,850℃高温抗拉强度约450 MPa。 相似文献
9.
作为数字化射线照相检测技术的一种,计算机射线照相(Computed Radiography,CR)技术能革命性地解决目前无损检测领域广泛采用的射线照相所固有的处理时间长、重拍率高、胶片保存难、不利于环境保护等问题,显著提高了无损检测的及时性和有效性.及时了解CR技术及其发展现状,将这种新型的计算机射线照相技术有效地应用到无损检测领域,具有一定的现实意义. 相似文献
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ZL2 0 5A是一种高强度铸造铝合金。它采用了高纯度原材料,多组元合金化及合理的热处理工艺技术。该合金具有三种使用状态:T6状态,T5状态,T7状态。该合金的铸造工艺性能中等,适用于砂型铸造和熔模铸造,对于结构形状简单的零件也可用于金属型铸造;具有良好的焊接性能和切削加工性能。本成果采用传统铸造方法,可以使铸件的各个指定部位,乃至整个铸件达到高强度和高致密性,而且铸件质量一致性好,保证铸件的使用可靠性。铸件指定部位切取试样的强度最低值比普通铸件高15 %~2 0 % ,达到锻件同样的质量水平。ZL2 0 5A合金是国内自行研制的高强… 相似文献
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A. Galli P. Wurz H. Lammer H. I. M. Lichtenegger R. Lundin S. Barabash A. Grigoriev M. Holmström H. Gunell 《Space Science Reviews》2006,126(1-4):447-467
We have evaluated the Lyman-α limb emission from the exospheric hydrogen of Mars measured by the neutral particle detector of the ASPERA-3 instrument on Mars Express in 2004 at low solar activity (solar activity index = 42, F10.7=100). We derive estimates for the hydrogen exobase density, n H = 1010 m?3, and for the apparent temperature, T > 600 K. We conclude that the limb emission measurement is dominated by a hydrogen component that is considerably hotter than the bulk temperature at the exobase. The derived values for the exosphere density and temperature are compared with similar measurements done by the Mariner space probes in the 1969. The values found with Mars Express and Mariner data are brought in a broader context of exosphere models including the possibility of having two hydrogen components in the Martian exosphere. The present observation of the Martian hydrogen exosphere is the first one at high altitudes during low solar activity, and shows that for low solar activity exospheric densities are not higher than for high solar activity. 相似文献
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S. J. Bame J. R. Asbridge J. T. Gosling M. Halbig G. Paschmann N. Sckopke H. Rosenbauer 《Space Science Reviews》1979,23(1):75-92
High temporal resolution measurements of solar wind electrons at the Earth's bow shock on the dawn side have been made with the LASL/MPI fast plasma experiments on ISEE-1 and 2. One dimensional, 1-d, temperatures, T
e
, and densities, N
e
, are obtained every 0.3 s and 2-d values are obtained every 3 s. Profiles of T
e
and N
e
at the shock usually are found to be similar to one another and also to the profile of the magnetic field magnitude. The time scale of electron thermalization varies from about 0.5 s to greater than 1 min, depending importantly on the shock motion and the orientation of the magnetic field. Typical thermalization times from 05:00–12:00 LT are 10 s, considerably shorter than proton thermalization times at the shock. This time scale corresponds to a distance of 100 km, comparable to but somewhat larger than the typical ion inertial length. The electron thermalization times are significantly longer than some of the values frequently cited in the past. At the end of the electron thermalization there typically is an overshoot in electron thermal pressure followed by an undershoot which give the pressure profile of the shock the appearance of a damped wave. Ion thermalization is essentially completed by the time the electron pressure wave is damped. The most probable value of the electron temperature ratio across the shock is 1.7, and this value is relatively independent of the Sun-Earth-satellite angle,
ss
, for
ss
between 25° and 100°.The Los Alamos Scientific Laboratory requests that the publisher identify this article as work performed under the auspices of the Department of Energy.By acceptance of this article, the publisher recognizes that the U.S. Government retains a non-exclusive, royalty-free license to publish or reproduce the published form of this contribution, or to allow others to do so, for U.S. Government purposes. 相似文献
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The mutual impedance experiment on GEOS-1 provides an original diagnostic of the thermal electron population. The electron density N
e, and temperature T
e, are derived from the plasma frequency and Debye length, the values of which determine the shape of the frequency dependent mutual impedance curves. The existing limits of the method are pointed out. They may be instrumental or arise from a lack of theoretical development, for instance when the steady magnetic field or the drift velocity of the plasma cannot be neglected. Nevertheless, first geophysical results have been derived, using measurements obtained on the dayside of the equatorial magnetosphere where most of the data enter within the above limits. In particular, we have drawn a map of the dayside magnetosphere, in terms of densities, Debye lengths, temperatures, at geocentric distances of 4 to 7 Earth radii. The conventional shape of the plasmasphere is recognized, but the temperatures obtained are lower than expected (2 eV at apogee, outside the plasmasphere). The influence of the magnetic activity on apogee measurements is reported: N
e values and A
m indices are shown to be correlated, but it is not the case for T
e and A
m. Finally, detailed T
e and N
e profiles are shown, and the presence of a plasmapause boundary is discussed. 相似文献
14.
This article uses a 2/4 functional epoxy blend system (E-54/AG-80) cured with diaminodiphenyl sulphone(DDS) as a raw material and develops a methodological procedure to establish a cure kinetic model with isothermal and dynamic differential scanning calorimeter(DSC) method and a gelation model with round-disk compression mode dynamic mechanical analyzer(DMA), thus acquiring a series of experimental data. Characteristic temperatures such as initial glass transition temperature Tg0, gelation glass transition temperature gelTg, and infinite glass transition temperature Tg∞ are determined. The cure degree at gelation is turned out to be 0.45, while gelTg is found to be 70.2 °C. The data are then used to form time-temperature-transition(TTT) diagram of the system, which serves to be a tool for process optimization of epoxy-matrix composites. A new cure processing is therefore derived from the TTT diagram. The final phase structure obtained from a controllable method is identified through scanning electron microscope(SEM) photographs to be of ‘ex-situ’ phase morphology. 相似文献
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《中国航空学报》2022,35(10):56-66
Under hypersonic flow conditions, the complicated gas-graphene interactions including surface catalysis and surface ablation would occur concurrently and intervene together with the thermodynamic response induced by spacecraft reentry. In this work, the competing effects of surface heterogeneous catalytic recombination and ablation characteristics at elevated temperatures are investigated using the Reactive Molecular Dynamics (RMD) simulation method. A Gas-Surface Interaction (GSI) model is established to simulate the collisions of hyper-enthalpy atomic oxygen on graphene films in the temperature range of 500–2500 K. A critical temperature Tc around 900 K is identified to distinguish the graphene responses into two parts: at T < Tc, the heterogeneous surface catalysis dominates, while the surface ablation plays a leading role at T > Tc. Contradicting to the traditional Arrhenius expression that the recombination coefficient increases with the increase of surface temperature, the value is found to be relatively uniform at T < Tc but declines sharply as the surface temperature increases further due to the competing ablation effect. The occurrence of surface ablation decreases the amounts of active sites on the graphene surface for oxygen adsorption, leading to reduced recombination coefficient from both Langmuir-Hinshelwood (L-H) and Eley-Rideal (E-R) mechanisms. It suggests that the traditional Computational Fluid Dynamics (CFD) simulation method, which relies on the Arrhenius-type catalysis model, would result in large discrepancies in predicting aerodynamic heat for carbon-based materials during reentry into strong aerodynamic thermal environment. 相似文献
17.
《中国航空学报》2023,36(4):237-251
Owing to the lack of physical knowledge of boundary layer transition, the γ-Reθ transition model introduces closure parameters, which increase the uncertainty of transition prediction. The objective of this work is to quantify the uncertainties of closure parameters in the quantities of interests and identify the key parameters. The six closure parameters in the uncertainty intervals are used as input variables, and the uncertainties of the output results are propagated by a stochastic expansion based on the point-collocation nonintrusive polynomial chaos method. The relative contribution of each parameter to uncertainty is evaluated by the Sobol index. The computational cases include natural and bypass transitional flows on zero-pressure-gradient flat plates, and subsonic and transonic flows around airfoils. For most cases, ce2, ca2, and ca1 dominate the uncertainty, and the influence of σθt is also significant when the history effects of flow are evident. The contribution of parameters in airfoils is more complex than that in flat plates. The transonic airfoil case shows that flow separation dramatically changes the distribution of Sobol indices, which poses a challenge to the accurate prediction of transition. Generally, ce2 and ca2 are the key parameters of the γ-Reθ model. 相似文献
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Observations of ion acoustic waves in the solar wind during the first and second orbit of the Ulysses spacecraft are presented. The observations show variations of the wave activity with the heliolatitude and with the phase
of the solar cycle. The interrelationships between the wave intensity and the electron heat flux and the ratio of electron
to proton temperature, T
e/T
p, are examined.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献
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John C. Raymond 《Space Science Reviews》2001,99(1-4):209-218
The relatively faint optical and UV emission from non-radiative shock waves provides diagnostics for processes related to cosmic ray acceleration in collisionless shocks. Emission line profiles and intensities can be used to determine the efficiencies of electron-ion and ion-ion thermal equilibration, which influence the population of fast particles injected into the acceleration process. It is found that T
e/T
p declines with shock speed and that T
i is roughly proportional to mass in fast shocks. Important information about cosmic ray precursors may be available, but the interpretation is still somewhat ambiguous. The compression ratios in shocks which efficiently accelerate cosmic rays are predicted to be substantially larger than the factor of 4 expected for a strong shock in a = 5/3 perfect gas, and some limits may be available from observations. 相似文献
20.
Alain Abergel Laurent Verstraete Christine Joblin René Laureijs Marc-Antoine Miville-Deschênes 《Space Science Reviews》2005,119(1-4):247-271
Infrared spectroscopy and photometry with ISO covering most of the emission range of the interstellar medium has led to important
progress in the understanding of the physics and chemistry of the gas, the nature and evolution of the dust grains and also
the coupling between the gas and the grains. We review here the ISO results on the cool and low-excitation regions of the
interstellar medium, where T
gas≲ 500 K, n
H∼ 100–105 cm−3 and the electron density is a few 10−4.
JEL codes: D24, L60, 047
Based on observations with ISO, an ESA project with instruments funded by ESA Member States (especially the PI countries:
France, Germany, The Netherlands, and the United Kingdom), and with the participation of ISAS and NASA. 相似文献