Surface temperatures at the nearside of the Moon as a record of the radiation budget of Earth’s climate system

Understanding the balance between incoming radiation from the Sun and outgoing radiation from Earth is of critical importance in the study of climate change on Earth. As the only natural satellite of Earth, the Moon is a unique platform for the study of the disk-wide radiation budget of Earth. There are no complications from atmosphere, hydrosphere, or biosphere on the Moon. The nearside of the Moon allows for a focus on the solar radiation during its daytime, and on terrestrial radiation during its nighttime. Additionally, lunar regolith temperature is an amplifier of the terrestrial radiation signal because lunar temperature is proportional to the fourth square root of radiation as such is much more sensitive to the weak terrestrial radiation in nighttime than the strong solar radiation in daytime. Indeed, the long-term lunar surface temperature time series obtained inadvertently by the Heat Flow Experiment at the Apollo 15 landing site three decades ago may be the first important observation from deep space of both incoming and outgoing radiation of the terrestrial climate system. A revisit of the lunar surface temperature time series reveals distinct characteristics in lunar surface daytime and nighttime temperature variations, governed respectively by solar and terrestrial radiation.     

一种新的基于从明暗恢复形状的月球表面三维形状恢复算法

提出了一种新的基于从明暗恢复形状的月球表面三维形状恢复算法。首先 ,分析了在太阳光照条件下月球表面的成像模型,建立了基于Lunar\|Lambert反射模型的 图像辐照度方程。然后由图像辐照度方程建立相应的静态Hamilton\|Jacobi方程,使用
Lax\|Friedrichs sweeping方法逼近其粘性解,得到表面三维高度。最后通过对合成图像和 实际月球图像进行三维形状恢复,实验结果表明提出的新算法可以有效地应用于月球表面的 三维形状恢复。     

月面巡视探测器直流电机的准极限选择

针对月面巡视探测器特殊使用条件和要求,为充分利用电机的极限性能,提出了基于准极限理论的直流电机的选择准则。用准极限度表征电机极限能力的利用率,根据准极限度小于1且接近于1的准则选择月面巡视探测器的走行轮电机。所选电机在满足要求的前提下,具有较小的质量和体积。     

月球探测器软着陆机构展开过程的运动学分析

软着陆机构是月球探测器实现软着陆的关键部件。针对一种四腿式软着陆机构方案,论述了该软着陆机构展开的工作原理,分析了机构的奇异性,推导了机构不发生奇异的条件,建立了展开机构的运动学方程组,采用Newton-Raphson法求解了该非线性运动学方程组,获得了主支撑杆运动参数的变化规律。     

一种改进的巡视器惯性/视觉组合导航模型

在传统的以惯性与视觉相对运动参数差为观测量的惯性/视觉组合导航模型中,为了得到简单的观测矩阵,惯性相对旋转四元数与平台失准角之间的函数关系往往通过近似处理得到。但当航向角较大时,该近似处理的误差很大,不可忽略。为解决该问题,文章提出了一种不需该近似处理的改进的观测量误差分析方法,并建立了改进的观测模型。该方法利用含误差的惯性姿态已知的特点,得到了更精确的惯性相对旋转四元数误差表达式,减少了Kalman滤波中惯性与视觉相对旋转差的状态模型预测误差。月面仿真和地面试验表明该改进方法相比传统方法可实现更高的导航精度,其中位置精度提高达68%。     

Photon counting detector for space debris laser tracking and lunar laser ranging

We are reporting on a design, construction and performance of solid state photon counting detector package which has been designed for laser tracking of space debris. The detector has been optimized for top photon detection efficiency and detection delay stability. The active area of the commercially available avalanche photodiode manufactured on Si (SAP500 supplied by Laser Components, Inc.) is circular with a diameter of 500 μm. The newly designed control circuit enables to operate the detection sensor at a broad range of biases 5–50 V above its breakdown voltage of 125 V. This permits to select a right trade-off between photon detection efficiency, timing resolution and dark count rate. The photon detection efficiency exceeds 70% at the wavelength of 532 nm. This is the highest photon detection efficiency ever reported for such a device. The timing properties of the detector have been investigated in detail. The timing resolution is better than 80 ps r.m.s, the detection delay is stable within units of picoseconds over several hours of operation. The detection delay stability in a sense of time deviation of 800 fs has been achieved. The temperature change of the detection delay is 0.5 ps/K. The detector has been tested as an echo signal detector in laser tracking of space debris at the satellite laser station in Graz, Austria. Its application in lunar laser ranging is under consideration by several laser stations.     

羽流场与月壤颗粒相互作用的一种新计算方法

针对登月着陆器发动机下降过程中羽流场与月壤颗粒相互作用问题提出了一种新的计算方法。通过Morh\|Coulomb破坏准则确定月壤颗粒可以被羽流扬起的临界剪应力,采用动量原理计算被扬起的月壤颗粒的质量大小及形成的月坑深度;基于牛顿第二定律,采用羽流场与月壤颗粒的流固耦合相互迭代的计算方法,获得被扬起月壤颗粒随时间的质量分布等。本文通过美国Apollo 11登月过程实测数据对该新方法进行了验证,为人类探月工程提供一定数据参考。     

月面巡视器实时动力学建模与牵引控制

为实现月面巡视器GNC系统的闭环测试,研究了六轮摇臂式巡视器在月表崎岖地形、松软土壤和低重力环境下的动力学建模与控制问题。基于弹塑性轮—土力学和粘弹性运动副约束分析,建立了巡视器的牛顿—欧拉动力学模型。以跟踪期望速度、角速度为目标,采用速度协调控制和车轮滑移控制,完成了巡视器闭环牵引控制。在实时操作系统下实现了巡视器动力学模型和牵引控制系统,并建立了三维可视化平台,对该动力学模型和牵引控制方法进行验证。测试结果证实了建立的动力学模型准确、稳定,可以真实地模拟巡视器在月球表面的运动行为和轮—土作用关系,且满足运动副的约束;所设计的牵引控制方法可以较准确地实现巡视器跟踪期望的运动。     

月壤钻采进尺力形成机理及进尺力预测建模

针对月壤钻采过程中进尺力无法准确预测的问题,基于钻采过程中钻具进尺和回转运动模式下土体产生的位移和形变分析了进尺力形成机理。钻头下压使土体径向扩张从而产生的扩孔压力是决定进尺力大小的核心因素,同时,通过回转状态下有限土体柱孔扩张问题的等效解析解建立了进尺力预测模型。开展基础模拟月壤地面钻采试验,将低、中、高回转速度下的进尺力试验结果与仿真结果相对比,验证了进尺力形成机理的合理性以及进尺力预测模型的准确性,为其他地外天体钻取采样任务的技术突破提供了理论支持。     

月球表面元素含量的定量分析方法

综合了月球元素定量研究在探测手段和定量方法等方面取得的最新进展。在探测手段方面,介绍了美国最近发射的克莱门汀和月球勘探者探测器使用的多谱段成像仪、中子探测仪以及γ谱仪的主要性能,在定量方法方面,讨论Fe、Ti以及稀土元素等在定量方法上的进展。