10kW固体推进剂燃烧驱动CO2气动激光数据采集系统

 介绍了10kW固体推进剂燃烧驱动CO₂气动激光的实验装置及数据采集系统,简要描述其结构组成及工作过程,对被测参数测量的方法和数据采集系统的硬件配置、性能及软件的编制原则、方法作了重点说明,并给出典型实验结果。     

固体推进剂燃烧驱动CO2气动激光小信号增益测量

 介绍了固体推进剂燃烧驱动CO₂气动激光小信号增益测量的原理、方法及实验系统,重点说明小信号增益测量光路设计、热敏电阻红外探测器工作原理、增益输出信号滤波和放大电路设计及数据采集系统的硬件配置和软件编制原则,给出典型实验测量结果。实验证明,采用放大法可较为准确的测量固体推进剂燃烧驱动CO₂气动激光小信号增益。     

Ne原子与H2分子碰撞的同位素替代效应研究

使用密耦近似（Close-Coupling）方法、采用Tang-Toennies势模型计算了惰性气体原子Ne与H₂分子及同位素D₂分子在碰撞能量为83.8 meV时的微分散射截面及分波截面, 并与实验值和文献值进行比较.计算得到的微分散射截面值与实验值符合得较好,分波截面值与文献值也相符合.使用同样的方法和模型,文中对Ne-H₂(D₂,T₂)三个体系的微分截面和分波截面进行了系统计算和比较分析,得出对称同位素替代碰撞体系的散射截面规律.     

Ba0.98Ce0.8Tm0.2O3-α的离子导电性及其燃料电池性能

用高温固相反应法制备了Ba_0.98Ce_0.8Tm_0.2O_3-α钙钛矿型氧化物固溶体,粉末X射线衍射表明该固溶体为单相. 用交流阻抗谱技术和气体浓差电池方法研究了样品在500～900 oC、不同气体气氛中的导电性,以及该样品为固体电解质的氢-空气燃料电池性能. 该电池能稳定地工作,在900 oC时,电池的最大功率密度为110.2 mW/cm²,高于以Ba_xCe_0.8RE_0.2O₃^- (x≤1, RE=Y, Eu, Ho)为固体电解质的氢-空气燃料电池的功率密度     

一种印刷型薄膜太阳能电池p-n结调制技术

能带值为0.5~0.85 eV材料的稀缺是多结太阳能电池面临的一个主要挑战,本文使用非真空的机械化学法合成了能带值为0.83 eV的Cu₂SnS₃化合物,使用印刷技术将其制备成吸收层薄膜,并采用superstrate太阳能电池结构(Mo/Cu₂SnS₃/In₂S₃/TiO₂/FTO glass)对其光伏特性进行了研究.实验表明所制备的太阳能电池短路电流密度、开路电压、填充因子和转换效率分别为12.38 mA/cm²、320 mV、0.28和1.10%.此外,为更好地满足多结太阳能电池对电流匹配的需求,本文对所制备太阳能电池的Cu₂SnS₃/In₂S₃ p-n结进行了分析.通过在p-n结界面植入一层薄的疏松缓冲层,使调制后的太阳能电池短路电流密度从最初的12.38 mA/cm²增加到了23.15 mA/cm²,相应太阳能电池转换效率从1.1%增加到了1.92%.该p-n调制技术对印刷型薄膜太阳能电池具有重要借鉴意义.     

第2系列ZrO2(Y2O3)薄膜的慢正电子研究

用慢正电子技术研究了在溅射时不加偏压,衬底加热300℃,纯Ar气氛下制备的用Y_{2O3稳定的ZrO2薄膜材料(简称YSZ薄膜),发现了YSZ薄膜在不同 深度处的缺陷分布情况,退火温度对YSZ薄膜缺陷有影响.简要讨论了致密、优质YSZ薄膜的 制备方法.}     

10.6μm激光辐照下光学薄膜的微弱吸收测量

 建立了表面热透镜技术测量光学薄膜微弱吸收的实验装置，对10.6μm CO₂激光辐照下镀制在Ge基底上的不同厚度的单层ZnS，YbF₃薄膜，以及镀制在Ge基底上不同膜系的（YbF₃/ZnSe）多层分光膜的弱吸收进行了测量，并对实验结果作了分析和讨论。实验结果表明，利用本实验系统已测得的待测样品的最低吸收为2.87×10^-4，测量系统的灵敏度为10^-5。     

非线性光学晶体HgGa2S4 和 Hg0.5Cd0.5Ga2S4的能带结构、化学键及光学性质研究

用密度泛函理论和非谐振子模型计算了晶体HgGa₂S₄和Hg_0.5Cd_0.5Ga₂S₄的能带结构、态密度、化学成键及线性、非线性光学性质。结果表明：HgGa₂S₄的价带顶部主要是Ga-S成键态的贡献，导带底部主要是Ga-S反键态的贡献; Hg_0.5Cd_0.5Ga₂S₄的价带顶部主要由S-3p轨道组成，导带底部主要是Ga-S反键态的贡献。布居分析表明Ga-S键主要是共价成分，而Hg-S和Cd-S键主要是离子成分。HgGa₂S₄的折射率计算值与实验值在低能量区很好吻合。另外，HgGa₂S₄的能隙计算值比Hg_0.5Cd_0.5Ga₂S₄小，而二阶非线性极化率比Hg_0.5Cd_0.5Ga₂S₄大。     

压力对纳米CoFe2O4/SiO2复合材料结构的影响

 采用溶胶-凝胶工艺和高温高压实验技术,制备了纳米CoFe₂O₄/SiO₂复合材料。利用X射线衍射仪、扫描电子显微镜和振动样品磁强计,对样品的结构、微观形貌和磁性进行了研究,并对CoFe₂O₄中阳离子的占位情况进行了讨论。结果表明,随着处理压力的升高,样品的晶粒尺寸增大,晶格常数减小,比饱和磁化强度增大。通过计算结果可以推断,压力的升高导致CoFe₂O₄中的部分Fe³⁺从A位移向了B位,而部分Co²⁺则从B位移向了A位。     

偶偶核基带的量子群Uqp(u2)模型的理论分析

通过对锕系和稀土偶偶核基带转动谱实验数据的拟合和Mallmann图的研究,系统地分析了量子群U_qp(u₂)模型对原子核转动谱的适用性.结果表明,U_qp(u₂)模型的理论值与实验值比较接近,明显优于单参数形变量子代数SU_q(2)模型.此外,还建立了U_qp(u₂)的形变参量q、p与核软度的关系.     

Improved method of measuring pressure coupled response for composite solid propellants

Pressure coupled response is one of the main causes of combustion instability in the solid rocket motor. It is also a characteristic parameter for predicting the stability. The pressure coupled response function is usually measured by different methods to evaluate the performance of new propellant. Based on T-burner and “burning surface doubled and secondary attenuation”, an improved method for measuring the pressure coupled response of composite propellant is introduced in this article. A computational fluid dynamics (CFD) study has also been conducted to validate the method and to understand the pressure oscillation phenomenon in T-burner. Three rounds of tests were carried out on the same batch of aluminized AP/HTPB composite solid propellant. The experimental results show that the sample propellant had a high response function under the conditions of high pressure (~11.5 MPa) and low frequency (~140 Hz). The numerically predicted oscillation frequency and amplitude are consistent with the experimental results. One practical solid rocket motor using this sample propellant was found to experience pressure oscillation at the end of burning. This confirms that the sample propellant is prone to combustion instability. Finally, acoustic pressure distribution and phase difference in T-burner were analyzed. Both the experimental and numerical results are found to be associated with similar acoustic pressure distribution. And the phase difference analysis showed that the pressure oscillations at the head end of the T-burner are 180° out of phase from those in the aft end of the T-burner.     

固体火箭发动机低空羽流场的相似研究

本文针对固体火箭发动机低空羽流场的数据外推问题进行研究。应用相似方法分析发动机低空羽流场模型,整理相似准则及相似条件。简化相似模型,根据工程计算半经验方法,拟和低空羽流温度场的计算公式,计算结果与工程计算数据基本吻合,验证了相似方法的可行性。     

Single-pulse CARS spectra in solid propellant combustion at atmosphere pressure

The unstable-resonator spatially enhanced detection (USED) coherent anti-stokes Raman spectroscopy (CARS) measurements of temperature and N2 concentration in the combustion of solid propellant at atmosphere pressure are reported. The USED CARS measurement system has a high spatial solution of ~ 0.1 mm in diameter and 3 mm in length, and permits instantaneous measurement at 10-Hz rate. The single-pulse N2 Q-branch CARS spectra have been obtained from the propellant combustion. The temperatures and N2 concentrations of the propellant flame at different height have been achieved by fitting the experimental data to theoretical spectra. The results indicate that the temperature is up to ~ 2500 K with N2 concentration in a range from 10% to 26%.     

利用辐射光谱法在线测量固体火箭推进剂燃烧温度

针对固体火箭发动机恶劣环境下的高温燃烧测量问题,提出了利用辐射光谱法来开展固体火箭推进剂燃烧温度在线测量的方法,采用200～1 100 nm光纤光谱仪测量了高压实验燃烧器下固体火箭推进剂燃烧火焰辐射光谱,总结了其光谱特性,并基于普朗克定律和光谱拟合方法获得了相应的推进剂燃烧温度,这对固体火箭推进剂燃烧诊断与燃烧机理研究具有重要的参考价值。     

Experimental observations of the dependence of impedance tube behavior upon gas phase losses and propellant self-noise

Some of the unexpected behavior observed during admittance measurement of burning solid propellants in a modified impedance tube set-up is discussed. Specifically, repeated tests conducted with the same solid propellant resulted, unexpectedly, in different standing wave structures in the impedance tube when the exhaust configuration was changed. This resulted in the calculation of different admittances at the propellant surface. It is shown in this paper that the observed experimental trends can be explained when the presence of gas phase damping and a propellant self-noise are taken into consideration in the development of a simplified analytical model describing the behavior of the impedance tube.     

Thermomechanical modeling of regressing heterogeneous solid propellants

A numerical framework based on the generalized finite element method (GFEM) is developed to capture the coupled effects of thermomechanical deformations and thermal gradients on the regression rate of a heterogeneous solid propellant. The thermomechanical formulation is based on a multiplicative split of the deformation gradient and regression of the heterogeneous solid propellant is simulated using the level set method. A spatial mesh convergence study is performed on a non-regressing solid heterogeneous propellant system to examine the consistency of the coupled thermomechanical GFEM solver. The overall accuracy (spatial and temporal) of the coupled thermomechanical solver for regressing solid propellants is obtained from a periodic sandwich propellant configuration, where the effects of thermomechanical deformations on its regression rate is investigated. Finally, the effects of thermomechanical deformations in a regressing two-dimensional heterogeneous propellant pack are studied and time-average regression rates are reported.     

固体推进剂燃烧驱动CO_2气动激光小信号增益测量

介绍了固体推进剂燃烧驱动 CO2 气动激光小信号增益测量的原理、方法及实验系统 ,重点说明小信号增益测量光路设计、热敏电阻红外探测器工作原理、增益输出信号滤波和放大电路设计及数据采集系统的硬件配置和软件编制原则 ,给出典型实验测量结果。实验证明 ,采用放大法可较为准确的测量固体推进剂燃烧驱动 CO2 气动激光小信号增益     

红外光谱遥测固体推进剂燃烧温度及有机化合物对其影响

本文用遥感FTIR光谱 ,测定了固体推进剂燃烧火焰在光谱范围为 4 5 0 0～ 70 0cm- 1 处的红外发射光谱 ,利用HCl分子转振基带 (3 4 6 μm)精细结构的P 分支光谱 ,准确测定了固体推进剂燃烧火焰温度 ,并对含有不同材料固体推进剂 ,如有机化合物对燃烧温度的影响 ,作了讨论。