高空高速航空相机光学窗口的热光学分析

分析航空相机光学窗口的热光学特性,选定熔石英作为窗口玻璃的材料,将热流密度加权分配到窗口外表面各个区域,并考虑整个窗口玻璃的辐射来计算其在一个工作循环内的温度分布。高空高速飞行时,气动热使窗口外表面的温度急剧上升,由于熔石英的导热率很小,窗口产生很大的轴向温差,分别取轴向温差55℃,70℃和90℃时的工况计算窗口热变形;光学窗口内、外表面的变形规律为近似球面,计算了其近似曲率半径,计算由面形变化和折射率变化引起的光程差并转化为Zernike多项式;将Zernike多项式系数带入Code V中考核窗口玻璃的光学性能,得到波像差变化量,其像面离焦量为-0.114mm,调制传递函数的下降最大值小于0.01。结果表明,光学窗口满足光学性能的要求。     

空间相机光学窗口的热光学评价

光学窗口是空间相机光学系统中直接暴露在轨道热真空环境中的光学元件，所处的热环境非常复杂，要产生温度梯度，从而对空间相机的成像质量和分辨率产生影响，文中结合工程实际，以光学波像差的基本理论为基础对空间相机光学窗口的非轴地称温度场进行了热光学评价，编程计算了空间相机光学窗口在一个轨道周期内各典型位置处的均方波像差，并把计算结果与美国“天空实验室”光学窗口的相应数据进行比较，以验证本文热光学分析的合理性     

光学窗口形变对平行光管光学性能影响分析

由于环境工况的多变性,光学窗口设计交叉了光、机、热等多种学科。在压差、轴向温差及径向温差工况下,分析光学窗口形变对某大口径、长焦距平行光管光学性能的影响,建立了光学窗口的有限元模型,与理论结果进行对比,验证了该有限元模型的有效性。以有限元分析得出的光学窗口变形数据为输入数据,带入改进了的Zernike多项式光机分析接口程序,获得了与像差对应的Zernike系数。用得到的Zernike系数表示光学窗口面型,以波像差作为光学系统成像质量评价指标,分析光学窗口变形对大口径、长焦距平行光管系统光学性能的影响。结果表明:光学窗口变形对平行光管系统光学性能的影响可以忽略不计。     

温度对航天相机光学系统影响的研究

空间环境温度的变化对航天相机光学系统成像质量的影响很大。分析了几种不同的温度分布形式,即均匀温度变化、温度梯度变化、径向温度梯度变化、周向温度梯度变化、轴向温度梯度变化和主、次镜间轴向温差的变化对光学系统成像质量的影响,并给出了相应的分析方法。     

空间望远镜主镜的热光学特性分析

主镜是空间望远镜光学系统的重要组成元件,其热光学特性将为光学系统的热控设计提供依据。利用建立在集成分析基础上的热光学分析方法,分析了某空间望远镜主镜在三种不同的温度分布形式,即在径向温度、轴向温度、周向温度梯度的作用下对光学系统成像质量的影响,结合设计的要求,根据计算结果给出了许用温度梯度的范围。     

机载相机非球面光学系统热光学特性分析

环境温度是影响非球面光学系统成像质量的主要因素之一,采用热光学特性分析方法,对某机载相机非球面光学系统进行热光学特性分析,通过有限元法分析相机光学系统结构热变形,并去除镜面表面刚体位移,将面型数据输入光学软件程序进行Zernike多项式拟合,将拟合结果导入光学设计软件中,对非球面光学系统成像进行性能评价。分析结果表明:热光学特性分析方法可以有效地对非球面光学系统的实际工作环境进行仿真,预测环境温度对光学系统成像质量的影响,对光学系统设计具有指导意义。     

高速航空遥感器的双层光学窗口设计研究

航空遥感器在高速飞行时,由于光学窗口玻璃与大气间的摩擦会产生大量热,致使光学窗口玻璃在热载荷作用下发生变形,光束通过时会发生偏折、产生光程差等问题,导致航空遥感器的光学系统成像受到影响。为了更好地抑制这种影响,介绍了双层光学窗口的结构,并结合实例验证,对比分析了同等厚度下单、双层光学窗口的光学性能。根据窗口结构给出了在满足外界作业环境下,圆形和矩形窗口厚度的确定方法及不同窗口安装方式对厚度的影响;分析了在压力和温度的影响下,窗口玻璃的变形情况,并结合载机飞行工况对双层窗口进行了热变形分析;结合实际光学系统,验证了双层窗口的光学性能,并和同等厚度的单层窗口进行对比。分析结果表明,在航空遥感器高速飞行条件下,与同等厚度的单层窗口相比,双层窗口玻璃的径向温差和轴向温差更小;针对所研究的光学系统,双层光学窗口玻璃热变形后引起的光学系统离焦量更小,并且对光学系统调制传递函数(MTF)的影响更小,空间频率在0~65 cycle/mm范围内不低于0.3,且在65 cycle/mm时MTF的相对下降量不超过10%,即双层光学窗口的引入使光学系统在不用调焦的情况下就可以满足使用要求。对双层光学窗口的分析研究也可以为其他航空光学窗口设计提供参考。     

空间相机热光学分析与试验验证

为了对空间高分辨率相机热设计提出准确的技术要求,基于光学波像差的基本理论,对某高分辨率空间相机的温度场进行热光学分析.在此基础上确定了热控指标,并在真空罐中进行热真空成像试验,验证了热光学分析的正确性和热控指标的合理性.结果表明:最佳焦面位置与相机温度水平的关系近似成线性关系,最佳焦面位置变化量约0.08～0.1 mm·℃-1|当温度水平在(20±1 )℃之间变化时,像面处在系统焦深范围内,系统传递函数变化量在0.02左右|当径向温差和轴向温差会大于2 ℃引起最佳焦面位置发生移动,若不调焦,传函会明显下降.     

空间相机热光学分析与试验验证

为了对空间高分辨率相机热设计提出准确的技术要求,基于光学波像差的基本理论,对某高分辨率空间相机的温度场进行热光学分析.在此基础上确定了热控指标,并在真空罐中进行热真空成像试验,验证了热光学分析的正确性和热控指标的合理性.结果表明:最佳焦面位置与相机温度水平的关系近似成线性关系,最佳焦面位置变化量约0.08～0.1mm.℃-1;当温度水平在(20±1)℃之间变化时,像面处在系统焦深范围内,系统传递函数变化量在0.02左右;当径向温差和轴向温差会大于2℃引起最佳焦面位置发生移动,若不调焦,传函会明显下降.     

热光效应对星敏感器测量准确度的影响

运用"热-结构-光"耦合分析方法,计算典型星敏感器光学系统(6透镜光具组,f=56 mm,相对孔径1/1.3)恒星像斑理想质心位移和亚像元内插质心偏移量,研究温度分布对星敏感器测量准确度的影响.以20℃为光学系统标定温度,计算光学系统均匀温度分布、轴向温差分布和上下侧温差分布三种条件下,星敏感器测量误差.均匀分布温度变化20℃时,星敏感器测量误差约0.07″;轴向温差10℃和20℃时,测量误差分别约为0.17″和0.31″;上下侧温差仅2℃时,测量误差就高达1.46″.计算结果表明,上下侧温差分布对星敏感器准确度影响最大,均匀温度分布影响最小.     

带轴向温控仪的金属蒸气激光管径向温度场分析

对带轴向温控仪的金属蒸气激光放电管,建立了描述放电管径向温度场的简单数学模型.给出了由热辐射和热传导引起的径向温度变化的解析表达式,计算分析了轴向温控仪对激光管管壁温度和径向温度分布的作用机制.结果表明轴向温控仪可在一定范围内独立调节放电管管壁温度和减小激光管的径向温度梯度,可有效提高激光器运转效率和稳定性.     

脉冲激光辐照TiO2/SiO2薄膜热效应研究

 采用1.06 μm单脉冲激光在不同能量密度下辐照特殊光电系统中典型薄膜光学元件，理论分析了激光辐照薄膜元件产生的温度场和热应力场，在此基础上建立了激光辐照多层薄膜的物理模型，计算软件使用ANSYS软件的热分析模块对激光辐照薄膜元件产生的温度场和热应力场进行了模拟，分别给出不同激光能量密度下薄膜表面光斑中心的温度场、径向温度场和轴向温度场分布；同时给出不同能量密度下薄膜的轴向、径向和环向热应力分布。并对激光辐照薄膜元件产生的温度场、热应力场进行了分析，阐明了原因。     

共轴球面光学系统的热象差分析

本文系统分析了径向均匀温度场中,热对共轴球面光学系统的影响,得到了初级位置热象差与初级倍率热象差的一般表达式.在此基础上得到了均匀温度场中薄透镜系统的热象差表示式,该热象差表示可以用来指导无热象差光学系统的设计.最后根据上述分析,讨论了几种简单系统的热效应与无热象差设计途径.     

平面光学镜低温温度场和热变形分析方法

在综合分析了温度场和热变形理论分析方法的基础上,提出了对空间光学系统中平面光学反射镜进行有限元分析具体方法;介绍了温度场特性经典理论,并对径向温度分布遵循二次规律的表达式作了简单推导;同时介绍了温度变化引起光学表面的Zern ike多项式法和用热力矩分析平面圆形板面形的方法;最后给出了用ANSYS和I-DEAS软件对联合光学元件热变形的计算流程。     

Weak temperature gradient effect on the stability of the circular Couette flow

We have investigated the influence of a weak radial temperature gradient in a wide gap and large aspect ratio Couette-Taylor system. The inner cylinder is rotating and can be heated or cooled, the outer cylinder is at rest and immersed in a large thermal bath. We found that a radial temperature gradient destabilizes the Couette flow leading to a pattern of traveling helicoidal vortices occurring only near the bottom of the system. The size of the pattern increases as the rotation frequency of the cylinder is increased. We have characterized the spatiotemporal properties of the pattern and we have shown that it behaves as a wall mode found in the simulation of the complex Ginzburg-Landau equation with homogeneous boundary conditions.     

The interaction and the surface crack of single-crystal silicon induced by a millisecond laser

When the silicon material is irradiated by laser, it absorbs the laser energy leading to the temperature rise and the thermal stress. The damage effect includes melting, vaporation and thermal stress damage. Once the thermal stress exceeds the stress strength the crack will initiate. The silicon surface cracks induced by a millisecond laser are investigated. The experimental results show that three types of cracks are generated including cleavage crack, radial crack and circumferential crack. The cleavage crack is located within the laser spot. The radial crack and circumferential crack are located outside the laser spot. A two-dimensional spatial axisymmetric model of silicon irradiated by a 1064 nm millisecond laser is established. To assess what stresses generate and explain the generation mechanism of the different cracks, the thermal stress fields during laser irradiation and the cooling process are obtained using finite element method. The radial stress and hoop stress within the laser spot are tensile stress after the laser irradiation. The temperature in the center is the highest but the thermal stress in the center is not always highest during the laser irradiation. The cleavage cracks are induced by the tensile stress after the laser irradiation. The radial crack and the circumferential crack are generated during the laser irradiation.     

High-repetition rate measurements of temperature and thermal dissipation in a non-premixed turbulent jet flame

High-repetition rate laser Rayleigh scattering is used to study the temperature fluctuations, power spectra, gradients, and thermal dissipation rate characteristics of a non-premixed turbulent jet flame at a Reynolds number of 15,200. The radial temperature gradient is measured by a two-point technique, whereas the axial gradient is measured from the temperature time-series combined with Taylor’s hypothesis. The temperature power spectra along the jet centerline exhibit only a small inertial subrange, probably because of the low local Reynolds number (Re_δ ≈ 2000), although a larger inertial subrange is present in the spectra at off-centerline locations. Scaling the frequency by the estimated Batchelor frequency improves the collapse of the dissipation region of the spectra, but this collapse is not as good as is obtained in non-reacting jets. Probability density functions of the thermal dissipation are shown to deviate from lognormal in the low-dissipation portion of the distribution when only one component of the gradient is used. In contrast, nearly log-normal distributions are obtained along the centerline when both axial and radial components are included, even for locations where the axial gradient is not resolved. The thermal dissipation PDFs measured off the centerline deviate from log-normal owing to large-scale intermittency. At one-half the visible flame length, the radial profile of the mean thermal dissipation exhibits a peak off the centerline, whereas farther downstream the peak dissipation occurs on the centerline. The mean thermal dissipation on centerline is observed to increase linearly with downstream distance, reach a peak at the location of maximum mean centerline temperature, and then decrease for farther downstream locations. Many of these observed trends are not consistent with equivalent non-reacting turbulent jet measurements, and thus indicate the importance of understanding how heat release modifies the turbulence structure of jet flames.     

Higher-Order Structure of Poly(Ethylene 2,6-Naphthalene Dicarboxylate) Fibers Produced by Direct High-Speed Spin-Drawing

In order to efficiently produce poly(ethylene naphthalene-2,6-dicarboxylate) (PEN) fibers comprising α-phase crystallites with a high melting temperature, a direct high-speed spin-drawing (HSSD) system was implemented. The higher-order structure of the HSSD PEN fibers was investigated by focusing on the radial anisotropy of the fibers. A nucleating agent was added to the PEN fibers, and its effect on the formation of the higher-order structure was also studied. Highly crystalline PEN fibers predominantly composed of α-phase crystallites were produced by operating the HSSD system at 4?km/min. The PEN fibers exhibited a melting temperature of 288.8?°C and a storage modulus of 31.4?GPa. The excellent thermal stability of the HSSD PEN fibers was presumably brought about by the formation of a shish-kebab-like structure. The generation of the shish-kebab-like structure and radial anisotropy seemed to be more dependent on the effect of tensile stress during the drawing process rather than from the nucleating additive. The nucleating agent used in this study effectively increased both the α- and β-phase crystallite sizes. Such structural modification, however, did not appear to contribute to the thermal stability enhancement of the PEN fibers.     

激光照射有限尺寸高反射光学元件的温度*场

采用格林函数法,考虑径向边界条件和对流热损失,理论上求解了有限尺寸高反射光学元件在激光作用下的热传导方程,获得了样品内的温度场分布。为验证所求解,模拟计算了不同光斑形状和光斑尺寸激光束照射下样品的温升曲线,并与有限元数值计算结果进行了比较,获得了较好的一致性,讨论了此精确物理模型中不同热交换系数对激光束照射下光学薄膜样品温升的影响。结果表明:热交换系数越大,样品内的温度分布越趋于平衡。