短光纤延时自外差法测量窄线宽激光器线宽

从理论上分析推导了移频延时自外差法测量激光器线宽的基本原理,并采用延时自外差法数学模型,编写了仿真程序.借助此分析结果,通过对两台已知线宽的窄线宽激光器的实际测量数据,与仿真结果对比,验证了模型的正确性.在此基础上,提出了短光纤延时自外差法,采用该方法可以在延时光纤长度远小于6倍的激光器相干长度时,消除延时自外差法因为延时时间不够导致测量精度的大幅度下降这一缺陷,为工程上实现精确测量窄线宽激光器线宽提供了行之有效的方法.      

基于CCD激光经纬仪测量的舰载雷达标校方法

介绍了一种利用激光测距仪测距、CCD光学经纬仪测角对动态的舰载雷达天线进行定位的雷达标校方法。探讨了对动态目标的定位原理,给出了真值测量的数学模型,论证了方位标的设计原则,分析了雷达标校的精度。     

Prospects in the orbital and rotational dynamics of the Moon with the advent of sub-centimeter lunar laser ranging

Lunar laser ranging (LLR) measurements are crucial for advanced exploration of the laws of fundamental gravitational physics and geophysics as well as for future human and robotic missions to the Moon. The corner-cube reflectors (CCR) currently on the Moon require no power and still work perfectly since their installation during the project Apollo era. Current LLR technology allows us to measure distances to the Moon with a precision approaching 1 mm. As NASA pursues the vision of taking humans back to the Moon, new, more precise laser ranging applications will be demanded, including continuous tracking from more sites on Earth, placing new CCR arrays on the Moon, and possibly installing other devices such as transponders, etc. for multiple scientific and technical purposes. Since this effort involves humans in space, then in all situations the accuracy, fidelity, and robustness of the measurements, their adequate interpretation, and any products based on them, are of utmost importance. Successful achievement of this goal strongly demands further significant improvement of the theoretical model of the orbital and rotational dynamics of the Earth–Moon system. This model should inevitably be based on the theory of general relativity, fully incorporate the relevant geophysical processes, lunar librations, tides, and should rely upon the most recent standards and recommendations of the IAU for data analysis. This paper discusses methods and problems in developing such a mathematical model. The model will take into account all the classical and relativistic effects in the orbital and rotational motion of the Moon and Earth at the sub-centimeter level. The model is supposed to be implemented as a part of the computer code underlying NASA Goddard’s orbital analysis and geophysical parameter estimation package GEODYN and the ephemeris package PMOE 2003 of the Purple Mountain Observatory. The new model will allow us to navigate a spacecraft precisely to a location on the Moon. It will also greatly improve our understanding of the structure of the lunar interior and the nature of the physical interaction at the core–mantle interface layer. The new theory and upcoming millimeter LLR will give us the means to perform one of the most precise fundamental tests of general relativity in the solar system.     

航天器用热控薄膜材料激光打孔机的设计

文章介绍了航天器用热控镀铝薄膜材料的激光打孔设备研制,设备调试及应用,并介绍了镀铝薄膜材料打孔后的存放方法.     

小直径超薄壁管纵缝的激光焊接

小直径超薄壁管纵缝焊接的主要问题是烧穿,解决这个问题的关键是严格控制焊接接头的装配质量及焊接工艺。本文介绍了采用激光焊接小直径超薄壁管纵缝的焊接经验,对整个生产过程中的关键问题进行了分析。     

基于神经网络的激光陀螺误差测试与建模

用人工神经网络中的反向误差传播网络(BP网络)来建立温度补偿模型,通过训练后的BP网络对刻度因子误差以及随机漂移进行温度补偿。     

激光辐照充压柱壳温度场和应力场数值模拟

考虑了材料参数随温度的变化,用有限元法计算了充压柱壳在不同预应力载荷、光强分别为均匀分布和高斯分布的激光辐照下的瞬态热力学耦合过程,计算出温度场和应力场。分析了热力学耦合规律,给出了破坏的危险部位。计算得到,应力峰值出现在激光加热的高温区和常温区的交界处;对于光强高斯分布,破坏首先发生在光斑中心附近;而对光强均匀分布,破坏首先会发生在边缘处。     

KrF激光对高速飞片的驱动特性研究

利用诱导空间非相干技术平滑的KrF准分子（248nm）激光驱动带有烧蚀层的平面靶，研究激光空间均匀性对产生完整飞片的影响，结果表明激光不均匀性在2％以下，能够产生完整的高速飞片，且完整飞片能够维持20ns以上不破裂；当激光不均匀性达到5％，激光引入流体力学不稳定性种子应很强，冲击波在靶内输运过程中不稳定性不断发展增强，到靶背时强到足以使飞片解体甚至气化，不能产生完整的飞片。为了获得尽可能高的飞片速度，采用激光与烧蚀层参数不匹配方法，使冲击波对飞片作多次加速。利用功率密度为1012 W/cm2的KrF激光与含50μm Kapton烧蚀层的5μm铝飞片作用，得到速度约10km/s的高速飞片，与模拟结果吻合得很好。     

Mission feasibility analysis on deflecting Earth-crossing objects using a power limited laser ablating spacecraft

This paper analyzes several mission capabilities to deflect Earth-crossing objects (ECOs) using a conceptual future spacecraft with a power limited laser ablating tool. A constrained optimization problem is formulated based on nonlinear programming with a three-dimensional patched conic method. System dynamics are also established, considering the target ECO’s orbit as being continuously perturbed by limited laser power. The required optimal operating duration and operating angle history of the laser ablating tool are computed for various types of ECOs to avoid an Earth impact. The available final warning time is also determined with a given limited laser power. As a result, detailed laser operating behaviors are presented and discussed, which include characteristics of operating duration and angle variation histories in relation to the operation’s start time and target object’s properties. The calculated durations of the optimal laser operation are also compared to those estimated with first-order approximations previous studies. It is discovered that the duration of the laser operation estimated with first-order approximations could result in up to about 50% error if the operation is started at the final warning time. The laser operation should be started as early as possible because an early start requires a short operating duration with a small operating angle variation. The mission feasibility demonstrated in the present study will give various insights into preparing future deflection missions using power limited spacecraft with a laser ablation tool.     

粒子拖尾长度对高频DPIV测量误差的影响

基于连续激光源的高采样频率DPIV系统在进行曝光时可能会产生粒子拖尾现象。明渠湍流试验和数值模拟试验结果显示，粒子拖尾长度的增加会导致平均流速减小和湍流强度增大。分析表明，导致平均流速误差的原因之一是诊断窗口边缘局部粒子图像的缺失，且图像缺失程度会随着粒子拖尾长度增加而增大，从而使平均速度随粒子拖尾长度增加而减小；粒子拖尾的另一个直接后果是增大了粒子图像的有效粒径，从而导致湍流强度增大。通过增大第二个诊断窗口的尺寸，进行相关函数标准化和相关系数补偿等方法，可以消除粒子拖尾长度引起的误差。