Study on eight-pass dual-frequency laser interferometer with nanometer precision

A new dual-frequency laser displacement measurement interferometer with nanometer precision has been developed. An eight-pass optical subdivision technology is proposed to improve resolution based on commercial interferometers. A static positioning error measuring method has been used to examine the precision and repeatability of the laser interferometer. An optical resolution of 1.24 nm and an accuracy of nanometer scale have been achieved.

Modelling and simulation of the second-order Doppler error of a laser dual-frequency interferometer

Only the first- order Doppler frequency shift is considered in current laser dual- frequency interferometers; however; the second- order Doppler frequency shift should be considered when the measurement corner cube ( MCC) moves at high velocity or variable velocity because it can cause considerable error. The influence of the second- order Doppler frequency shift on interferometer error is studied in this paper, and a model of the second- order Doppler error is put forward. Moreover, the model has been simulated with both high velocity and variable velocity motion. The simulated results show that the second- order Doppler error is proportional to the velocity of the MCC when it moves with uniform motion and the measured displacement is certain. When the MCC moves with variable motion, the second- order Doppler error concerns not only velocity but also acceleration. When muzzle velocity is zero the second- order Doppler error caused by an acceleration of 0.6g can be up to 2.5 nm in 0.4 s, which is not negligible in nanometric measurement. Moreover, when the muzzle velocity is nonzero, the accelerated motion may result in a greater error and decelerated motion may result in a smaller error.

双频激光干涉仪的最大可测量速度研究

现代制造业对双频激光干涉仪的最大可测量速度提出了越来越高的要求。最大可测量速度是双频激光干涉仪的一项重要指标，它主要受双频激光光源所输出的频差、干涉仪的光学结构以及电子带宽等因素的限制。本文从理论和实验两方面对干涉仪的最大可测量速度进行了研究，搭建了基于自由落体运动的实验装置。实验结果表明，实际最大可测量速度略低于其理论值。另外，文中还分析了上述三种因素对最大可测量速度的影响。实验装置和结果可供工业应用提供参考。

A novel optical subdivision method for dual-frequency interferometer

The theory of optical subdivision techniques of dual-frequency laser interferometers is stated. And a novel optical subdivision technique is proposed originally to enhance resolution of a commercial interferometer by adding some corner-cubes. Then the performance of the interferometer is tested. The interferometer resolution of 1.24 nm and the average error of below 2 nm are achieved by using the technique. The most novel of the optical subdivision technique is without lambda/4 plates. It is less sensitive to environmental changes, it has prodigious potential to improve resolution farther and it can reduce polarization mixing error. (C) 2007 Elsevier GmbH. All rights reserved.

沉积温度对LaF3薄膜性能的影响

abstract {LaF₃ single-layer coatings were prepared by thermal boat evaporation at the deposition temperatures of 189, 255, 277 and 321°C respectively. The crystal structures of the coatings were characterized by X-ray diffraction (XRD). A spectrophotometer was employed to measure its transmittance. Moreover, refractive index, extinction coefficient and cut-off wavelength were obtained from the measured transmittance spectral curve. The residual stress was evaluated by the Stoney's equation and optical interferometer. Laser induce damage threshold (LIDT) was performed by a tripled Nd:YAG laser system. The results show that the crystallization status becomes better with the deposition temperature increasing. Correspondingly, the grain size also gets larger. Meanwhile, the coatings become more compact and the refractive index increases. However, the absorption of coatings seriously rises and the cut-off wavelength drifts to the long wave. In addition, the residual stress also increases and the intrinsic stress plays a determinant role in the coating. The LIDT of the coating also enhances at high temperature.}

SOI thermo-optic modulator with fast response

Silicon-on-insulator (SOI) technology offers tremendous potential for integration of optoelectronic functionson a silicon wafer. In this letter, a 1 * 1 multimode interference (MMI) Mach-Zender interferometer(MZI) thermo-optic modulator fabricated by wet-etching method is demonstrated. The modulator has anextinction ratio of -11.0 dB, extra loss of -4.9 dB and power consumption of 420 mW. The response timeis less than 30μs.

Oscillation flow induced by underwater supersonic gas jets

This paper describes an experimental study on the oscillation flow characteristics of submerged supersonic gas jets issued from Laval nozzles. The flow pattern during the jet development and the jet expansion feedback phenomenon are studied using a high-speed camera and a pressure measurement system. The experimental results indicate that along the downstream distance, the jet has three flow regimes: (1) momentum jet; (2) buoyant jet; (3) plume. In the region near the nozzle exit a so-called bulge phenomenon is found. Bulging of the jet occurs many times before the more violent jet expansion feedback occurs. During the feedback process, the jet diameter can become several times that of the original one depending on the jet Mach number. The frequencies of the jet bulging and the jet expansion feedback are measured.

压缩折角激波-湍流边界层干扰直接数值模拟

进行了来流Mach数2.9,24°压缩折角激波-湍流边界层干扰的直接数值模拟,在上游的平板添加扰动以激发边界层转捩到湍流.计算得到的统计结果与实验吻合,验证了结果的可靠性.分析了角部分离区附近湍能的生成,耗散及分配机制.结果显示角部区域激波与湍流边界层相互作用造成大量湍动能产生,而湍动能的主要耗散区仍在近壁.湍流输运项起到了主要的平衡机制,把湍动能由外层输运到近壁区.通过对激波后及壁面瞬时压力的分析,认为激波低频振荡并非上游扰动引起,而是由于分离泡本身不稳定振荡产生的

Direct Numerical Simulation of Shock/Turbulent Boundary Layer Interaction in a Supersonic Compression Ramp

A direct numerical simulation of the shock/turbulent boundary layer interaction flow in a supersonic 24-degree compression ramp is conducted with the free stream Mach number 2.9. The blow-and-suction disturbance in the upstream wall boundary is used to trigger the transition. Both the mean wall pressure and the velocity profiles agree with those of the experimental data, which validates the simulation. The turbulent kinetic energy budget in the separation region is analyzed. Results show that the turbulent production term increases fast in the separation region, while the turbulent dissipation term reaches its peak in the near-wall region. The turbulent transport term contributes to the balance of the turbulent conduction and turbulent dissipation. Based on the analysis of instantaneous pressure in the downstream region of the mean shock and that in the separation bubble, the authors suggest that the low frequency oscillation of the shock is not caused by the upstream turbulent disturbance, but rather the instability of separation bubble.

Performance of supersonic model combustors with staged injections of supercritical aviation kerosene

Supersonic model combustors using two-stage injections of supercritical kerosene were experimentally investigated in both Mach 2.5 and 3.0 model combustors with stagnation temperatures of approximately 1,750 K. Supercritical kerosene of approximately 760 K was prepared and injected in the overall equivalence ratio range of 0.5-1.46. Two pairs of integrated injector/flameholder cavity modules in tandem were used to facilitate fuel-air mixing and stable combustion. For single-stage fuel injection at an upstream location, it was found that the boundary layer separation could propagate into the isolator with increasing fuel equivalence ratio due to excessive local heat release, which in turns changed the entry airflow conditions. Moving the fuel injection to a further downstream location could alleviate the problem, while it would result in a decrease in combustion efficiency due to shorter fuel residence time. With two-stage fuel injections the overall combustor performance was shown to be improved and kerosene injections at fuel rich conditions could be reached without the upstream propagation of the boundary layer separation into the isolator. Furthermore, effects of the entry Mach number and pilot hydrogen on combustion performance were also studied.

乘波飞行器低马赫数飞行状态下的气动性能研究

乘波飞行器在低马赫数飞行状态下的气动性能是近空间飞行器设计和研究人员关心的问题之一. 本文以M=3,设计飞行高度H=15 km为设计点,最大升阻比为优化目标,并通过满足一定的有效载荷容积,气动热防护和气动操纵的要求进行了工程化设计后得到的锥导乘波体为研究对象,借助数值模拟和风洞实验技术相结合的研究手段对乘波飞行器在跨声速和超声速飞行阶段的气动性能进行了探讨. 研究结果表明,乘波飞行器在该飞行阶段的气动性能与前缘所处的气动状态密切相关

基于直接数值模拟的超/高超声速湍流模型评估与改进

对来流Mach数2.25及6的平板边界层湍流进行了直接数值模拟，并通过与理论、实验及他人计算结果的对比对数值结果进行了验证。基于直接数值模拟得到的湍流数据库，对常用的湍流模型进行了先验评估。评估的湍流模型有k-e模型（包括标准k-e模型、可实现的k-e模型及低Reynolds数k-模型）、SA模型及BL模型。结果显示，可实现的k-e模型的具有较好的预测能力，而标准k-e模型预测的湍流粘性系数偏高。SA模型在边界层内层预测准确度较高，而在外层预测值偏高。对于高Mach数情况，原始的BL模型严重低估了内-外层交界位置，造成湍流粘性系数预测值偏低。作者通过修改模型系数及内-外层交界位置对BL模型进行了修改，修改后模型预测的湍流粘性系数与DNS给出的值吻合较好

Modeling study to compare the flow and heat transfer characteristics of low-power hydrogen, nitrogen and argon arc-heated thrusters

A modelling study is performed to compare the plasma °ow and heat transfer char- acteristics of low-power arc-heated thrusters (arcjets) for three di®erent propellants: hydrogen, nitrogen and argon. The all-speed SIMPLE algorithm is employed to solve the governing equa- tions, which take into account the e®ects of compressibility, Lorentz force and Joule heating, as well as the temperature- and pressure-dependence of the gas properties. The temperature, veloc- ity and Mach number distributions calculated within the thruster nozzle obtained with di®erent propellant gases are compared for the same thruster structure, dimensions, inlet-gas stagnant pressure and arc currents. The temperature distributions in the solid region of the anode-nozzle wall are also given. It is found that the °ow and energy conversion processes in the thruster nozzle show many similar features for all three propellants. For example, the propellant is heated mainly in the near-cathode and constrictor region, with the highest plasma temperature appear- ing near the cathode tip; the °ow transition from the subsonic to supersonic regime occurs within the constrictor region; the highest axial velocity appears inside the nozzle; and most of the input propellant °ows towards the thruster exit through the cooler gas region near the anode-nozzle wall. However, since the properties of hydrogen, nitrogen and argon, especially their molecular weights, speci¯c enthalpies and thermal conductivities, are di®erent, there are appreciable di®er- ences in arcjet performance. For example, compared to the other two propellants, the hydrogen arcjet thruster shows a higher plasma temperature in the arc region, and higher axial velocity but lower temperature at the thruster exit. Correspondingly, the hydrogen arcjet thruster has the highest speci¯c impulse and arc voltage for the same inlet stagnant pressure and arc current. The predictions of the modelling are compared favourably with available experimental results.

Numerical modeling of heat transfer and plasma flow in a low power arcjet thruster

Modeling studies are preformed to investigate the plasma and heat transfer characteristics of a low power argon arcjet thruster. Computed temperature, velocity, static pressure, and Mach number distribution in arcjet thruster under typical operating condition are presented in this paper. It shows that the performance data from numerical modeling results are basically consistent with the experimental measured values.

高超声速风洞用蓄热式加热器

本文介绍了纯净空气高超声速风洞用蓄热式加热器的结构形式、蓄热材料选择、蓄热体结构设计方案。回顾了现有文献报道的国内外蓄热式加热器的性能和特点。对多孔砖型蓄热式加热器的蓄热能力以及结构特性进行了估算，结果表明采用多孔砖型蓄热体可有效降低相同流量下蓄热体浮起危险；选用合适的蓄热材料以及蓄热体尺寸可以获得Mach 6巡航飞行的来流条件。材料和结构等工程问题是蓄热式加热器研制的主要难点。