Optimal sub-millimeter bands for passive limb observations of stratospheric HBr, BrO, HOCl, and HO2 from space

Present and near future limb-sounding heterodyne instruments operating at millimeter or sub-millimeter wavelengths will be capable to gather profile information on a variety of stratospheric trace gases with relatively strong spectral features such as O₃, H₂O, O₂ (temperature), N₂O, HCl, ClO, HNO₃, CH₃Cl, and CO. Some species however, which are of particular interest for the understanding of stratospheric ozone chemistry, have only very weak spectral signatures, either due to their very small abundances and/or spectroscopic properties. These are amongst others the radical BrO, the potential bromine reservoir HBr, HOCl as a member of the chlorine family, and the hydroperoxyl radical HO₂. Often, these target species are very difficult to detect and profiles have not yet been measured by space-borne sensors at all, even considering other spectral ranges and observation techniques. A study was therefore dedicated to the investigation of the retrieval of species with spectral features close to the detection limit of a typical state-of-the-art space-borne heterodyne receiver. A survey of the millimeter- and sub-millimeter spectral range was performed in order to identify appropriate spectral bands, followed by retrieval simulations for a representative atmospheric and instrumental scenario in order to explore the relative merits of the pre-selected bands and to derive associated parameters as measurement precision, altitude range and resolution. The feasibility of retrieving profile information from limb observations at sub-millimeter wavelengths of the “weak line” species under investigation is demonstrated. Optimal dedicated bands are recommended for HBr , BrO , and HOCl . For HO₂ five more or less equivalent bands between 585 and are identified.     

基于低空成像高光谱系统探测植被日光诱导叶绿素荧光

植被叶绿素荧光与光合作用关系密切,被认为是光合作用的有效探针。该研究利用成像高光谱传感器和无人飞艇构建了一套适用于低空叶绿素荧光探测的系统。针对低空叶绿素荧光探测中,太阳下行辐射光谱难以获取的情况,基于已有的aFLD方法,提出一种新的叶绿素荧光提取方法a3FLD,该方法利用了非荧光发射体,且考虑植被反射率在夫琅和费线附近的变化。通过模拟数据以及实测数据对两种提取结果进行了比较。模拟数据分析结果显示：当地物的反射率在夫琅和费线附近存在一定的变化时,a3FLD计算得到的荧光值误差小于aFLD,地物反射率变化越大,a3FLD的改进越明显。对低空高光谱影像数据的分析显示：aFLD和a3FLD提取不同植被的日光诱导叶绿素荧光相对大小关系相一致,与作物所处的生长阶段吻合。但aFLD荧光提取值比a3FLD高15%左右。aFLD的结果中有部分非荧光发射体得到较强荧光,a3FLD能改进此问题。结果显示,利用该系统和方法能够成功地提取到植被叶绿素荧光,且所提出a3FLD方法提取的结果优于aFLD方法。     

平流层双轴椭球体飞艇绕流场的数值分析

本文在CFD软件FLUENT6.3的计算平台上采用时均Navier—Stokes方程与Realizable k-ε湍流模型对平流层双轴椭球体飞艇进行了数值模拟。着重分析了与飞艇轴线垂直的截面的周向摩擦阻力系数和压力分布情况,飞艇背部的分离流动特点,物面剪切层分离流动规律,空间流态,以及它们随攻角的变化规律。结果发现,飞艇背部的分离流动是基本对称的。在小攻角下只存在闭式分离,而随着攻角的增大也出现了开式分离。分离区随着攻角的增大而增大,分离线的起始点位置随着攻角的增大向上游移动。15°攻角时没有发现二次分离,30°,40°,45°攻角下都发现了二次分离。在相同的攻角下伴随流动沿飞艇轴线向下游发展时,分离流动的区域在横向截面上增大了。     

飞艇姿态跟踪系统的研究

研究了具有参数不确定和外部干扰的飞艇姿态跟踪控制问题．飞艇姿态运动的数学模型为一个多输入/多输出不确定非线性系统,根据该系统的特点,采用了一个基于不确定项上界的鲁棒输出跟踪控制器设计方法,应用输入/输出反馈线性化法和李雅普诺夫方法,设计了飞艇姿态鲁棒控制律,它可确保系统输出按指数规律跟踪期望输出．该控制器设计简单,易于实现．仿真结果表明:即使系统存在不确定性和外界干扰,仍可在闭环系统中实现精确的姿态控制．     

改变飞艇重心位置控制纵向运动

本文针对目前平流层飞艇的运动控制效率较低的问题,重点研究了改变平流层飞艇重心的轴向位置来控制飞艇的纵向运动。首先讨论了考虑飞艇重心位置的力和力矩平衡,并利用德国斯图加特大学风洞试验的数据,进行了算例分析。然后和常用的升降舵控制进行效率比较,得出了在空气密度较低的平流层采用改变重心位置比舵面控制具有优越性的结论。最后提出了改变飞艇重心位置的方法。     

Lunar eclipse theory revisited: Scattered sunlight in both the quiescent and the volcanically perturbed atmosphere

The residual brightness of the shadowed Moon during a lunar eclipse is attributed to unscattered sunlight rays refracted in the Earth's atmosphere. The classical theory of lunar eclipses is built on the premise that the sunlight scattered by the gases and particles in the atmosphere contributes negligibly to the brightness of the eclipsed Moon. The current work revisits the lunar eclipse theory, extending it to accommodate spectrally resolved observations and addressing the role of scattered sunlight. Predictions of both direct and diffuse sunlight are produced by integrating the radiative transfer equations over the Earth's disk. The investigation contemplates scenarios of normal aerosol loading as well as conditions representative of the months and years following a major volcanic eruption. It is shown that omitting scattered sunlight is an acceptable approximation for low and moderate aerosol loadings at visible and longer wavelengths. However, towards the ultraviolet, or at times when the atmosphere contains elevated aerosol amounts, the relative significance of direct and diffuse sunlight may reverse. Spectra of the sunlight that reaches the shadowed Moon during the eclipse are presented to illustrate the distinct contributions from both components. It is also shown that lunar eclipse spectra obtained up to 4-5 years after a major volcanic eruption, such as Mt. Pinatubo's in 1991, will reveal that the stratosphere remains perturbed above background aerosol levels.     

飞艇最优飞行轨迹研究

目前，各国对无人飞艇平台的研究产生了很大的兴趣，飞艇作为平台可以实现无线通信、环境监测和监视等目的。本文通过采用最优控制问题的数值计算方法得到飞艇在不同性能指标下的最优飞行轨迹。飞艇的动力学模型采用六自由度非线性模型。飞艇采用安装在飞艇轴向由直流电机带动的螺旋桨作为动力。通过螺旋桨、方向舵和升降舵对飞艇进行控制。控制消耗的能量作为控制变量的函数。采用直接配点法与由遗传算法和单纯形法构成的混合参数优化方法得到飞艇在不同条件下的最优轨迹。     

<Superscript>239, 240, 241</Superscript>Pu fingerprinting of plutonium in western US soils using ICPMS: solution and laser ablation measurements

Sector field inductively coupled plasma mass spectrometry (SF-ICPMS) has been used with analysis of solution samples and laser ablation (LA) of electrodeposited alpha sources to characterize plutonium activities and atom ratios prevalent in the western USA. A large set of surface soils and attic dusts were previously collected from many locations in the states of Nevada, Utah, Arizona, and Colorado; specific samples were analyzed herein to characterize the relative contributions of stratospheric fallout vs. Nevada Test Site (NTS) plutonium. This study illustrates two different ICPMS-based analytical strategies that are successful in fingerprinting Pu in environmental soils and dusts. Two specific datasets have been generated: (1) soils are leached with HNO₃-HCl, converted into electrodeposited alpha sources, counted by alpha spectrometry, then re-analyzed using laser ablation SF-ICPMS; (2) samples are completely dissolved by treatment with HNO₃-HF-H₃BO₃, Pu fractions are prepared by extraction chromatography, and analyzed by SF-ICPMS. Optimal laser ablation and ICPMS conditions were determined for the re-analysis of archived alpha spectrometry “planchette” sources. The best ablation results were obtained using a large spot size (200 μm), a defocused beam, full repetition rate (20 Hz) and scan rate (200 μm s⁻¹); LA-ICPMS data were collected with a rapid electrostatic sector scanning experiment. Less than 10% of the electroplated surface area is consumed in the LA-ICPMS analysis, which would allow for multiple re-analyses. Excellent agreement was found between ^239+240Pu activities determined by LA-ICPMS vs. activity results obtained by alpha spectrometry for the same samples ten years earlier. LA-ICPMS atom ratios for ²⁴⁰Pu/²³⁹Pu and ²⁴¹Pu/²³⁹Pu range from 0.038–0.132 and 0.00034–0.00168, respectively, and plot along a two-component mixing line (²⁴¹Pu/²³⁹Pu = 0.013 [²⁴⁰Pu/²³⁹Pu] – 0.0001; r ² = 0.971) with NTS and global fallout end-members. A rapid total dissolution procedure, followed by extraction chromatography and SF-ICPMS solution Pu analysis, generates excellent agreement with certified ^239+240Pu activities for standard reference materials NIST 4350b, NIST 4353, NIST 4357, and IAEA 385. ^239+240Pu activities and atom ratios determined by total dissolution reveal isotopic information in agreement with the LA-ICPMS dataset regarding the ubiquitous mixing of NTS and stratospheric fallout Pu sources in the regional environment. For several specific samples, the total dissolution method reveals that Pu is incompletely recovered by simpler HNO₃-HCl leaching procedures, since some of the Pu originating from the NTS is contained in refractory siliceous particles.     

平流层飞艇气动参数辨识

进入21世纪以来,随着科技的飞速发展,世界上掀起了研究和开发平流层平台的热潮。飞艇作为平流层平台可以实现无线通信、空间观测、大气测量以及军事侦查等目的。本文首先将飞艇所受的气动力分成由于来流速度产生的定常气动力和飞艇转动引起的非定常气动力两部分,通过理论分析建立了飞艇的气动力模型,从而得到需要辨识的气动参数。其次建立了以浮心为原点的六自由度非线性动力学模型和一种基于混合遗传算法的气动力系数辨识方法——混合遗传算法（遗传算法＋单纯型法）与极大似然法相结合的方法,并利用该方法对飞艇的气动参数进行辨识。通过仿真结果验证了该方法实用性和有效性。最后通过对气动参数的准确值与辨识值的分析比较,得出各个参数对飞艇运动性能的影响情况。     

平流层飞艇空气动力估算

本文采用有限基本解方法与工程估算方法相结合的气动力工程计算方法,用以计算平流层飞艇的气动力。将飞艇所受的气动力分成飞艇艇身和尾翼所受气动力两部分,每一部分的气动力按照无粘性流产生的线性气动力和粘性引起的非线性气动力分别进行计算。根据势流理论对飞艇艇身线性气动力进行分析计算,由于飞艇艇体是旋成体,故根据Allen的横流阻力理论对其所受的非线性气动力进行计算;尾翼的线性气动力采用有限基本解方法进行计算,非线性气动力用Polhamus-Lamar吸力比拟方法估算。该方法中考虑了由于尾翼安装在体上后,处于艇体产生的上洗流场中,尾翼气动力的变化和尾翼对艇身气动力的干扰作用。通过算例的计算与实验结果比较得出该方法可以快速、准确的计算飞艇所受的气动力。