基于改进的蚁群算法的亚轨道再入飞行器弹道优化

基于阻力与能量再入导引律,用改进的蚁群算法优化SLV再入阻力-能量关系剖面,其优化的性能指标为总吸热量最小,并采用LQR法跟踪参考弹道.仿真结果表明,优化方法简便易行,跟踪器性能良好.     

月球详查探测的载荷配置分析

在对地外天体进行着陆/巡视探测前,一般都需要进行环绕详查探测,对期望的着陆区域进行详细的地形、地貌勘察,为后续着陆探测器的安全着陆提高安全系数,同时也可以帮助选择具有较高科学考察价值的着陆点。文章对月球详查探测器的载荷配置特点进行了分析,提出了我国月球详查探测器载荷配置方式的建议。     

月球表面太空风化作用及其效应

太空风化作用普遍发生在月球、小行星等一些无大气层的天体表面, 主要包括太阳风离子辐射和微陨石撞击等作用. 通过对真实月球样品太空风化作用的研究成果以及低能离子和激光照射等地面模拟实验结果的系统综述和分析, 重点分析了月壤颗粒中非晶质层和纳米铁的成因, 指出太空风化研究中存在的太阳风离子辐射和微陨石撞击贡献难以区分及模拟实验模拟效果尚不充分的问题.进而提出月球太空风化研究不能简单套用其他天体的模型, 并建议未来开展更多月球和陨石样品的精细化学分析.      

The Radio Observatory on the Lunar Surface for Solar studies

The Radio Observatory on the Lunar Surface for Solar studies (ROLSS) is a concept for a near-side low radio frequency imaging interferometric array designed to study particle acceleration at the Sun and in the inner heliosphere. The prime science mission is to image the radio emission generated by Type II and III solar radio burst processes with the aim of determining the sites at and mechanisms by which the radiating particles are accelerated. Specific questions to be addressed include the following: (1) Isolating the sites of electron acceleration responsible for Type II and III solar radio bursts during coronal mass ejections (CMEs); and (2) Determining if and the mechanism(s) by which multiple, successive CMEs produce unusually efficient particle acceleration and intense radio emission. Secondary science goals include constraining the density of the lunar ionosphere by searching for a low radio frequency cutoff to solar radio emission and constraining the low energy electron population in astrophysical sources. Key design requirements on ROLSS include the operational frequency and angular resolution. The electron densities in the solar corona and inner heliosphere are such that the relevant emission occurs at frequencies below 10 MHz. Second, resolving the potential sites of particle acceleration requires an instrument with an angular resolution of at least 2°, equivalent to a linear array size of approximately 1000 m. Operations would consist of data acquisition during the lunar day, with regular data downlinks. No operations would occur during lunar night.     

改进蚁群算法求解时变网络中最短路径问题

给出一种时变网络中蚁群算法的信息素更新策略,使边上残留信息素能够正确反映时变网络中边上权值的变化情况;改进了传统蚁群算法的相邻节点选择策略,使蚂蚁只需计算与当前节点存在直接路径的节点的转移概率,降低算法的计算量;将蚁群算法和遗传算法结合,将蚁群算法每次遍历后形成的解作为初始群种进行单点交叉计算,避免陷入局部最优解,提高算法收敛速度.仿真结果表明,改进的蚁群算法能够有效求解时变网络中最短路径问题,比传统蚁群算法得到全局最优解的概率更大,算法的收敛速度更高.     

Lunar apex–antapex cratering asymmetry as an impactor recorder in the Earth–Moon system

The degree of apex–antapex cratering asymmetry of a synchronously rotating satellite primarily depends on the mean encounter velocity of impactors with respect to the planetary system and the orbital velocity of the satellite. This means that we can estimate the mean encounter velocity of impactors by observing the apex–antapex cratering asymmetry, if the relationship between these is known. To apply this technique to the Moon, we attempt to derive the relationship between the mean encounter velocity of impactors and the degree of the lunar cratering asymmetry as a function of time, considering the temporal variation in the lunar orbital velocity during the last 4.0 Gyr. We used the cratering asymmetry of Zahnle et al. [Zahnle, K., Schenk, P., Sobieszczyk, S. et al. Differential cratering of synchronously rotating satellites by ecliptic comets. Icarus 153, 111–129, 2001] to obtain the relationship. Applying this relationship enables us to estimate the impactor’s velocity of the Earth–Moon system from an investigation of the spatial distribution of lunar craters. Furthermore, we re-evaluate the cratering asymmetry’s influence on lunar cratering chronology.     

机位资源影响因素及效率优化模型研究

停机位分配方案对机场运行效率至关重要。本文分别从机场和航空公司角度考虑,分析了影响机场机位分配(AGA)的诸多因素。针对AGA问题,以旅客步行距离最短和停机位使用效率最大化为目标构建优化模型,然后运用生长竞争蚁群算法求解,最后用算例来说明优化的可行性。     

Lunar Reconnaissance Orbiter Overview: The Instrument Suite and Mission

NASA’s Lunar Precursor Robotic Program (LPRP), formulated in response to the President’s Vision for Space Exploration, will execute a series of robotic missions that will pave the way for eventual permanent human presence on the Moon. The Lunar Reconnaissance Orbiter (LRO) is first in this series of LPRP missions, and plans to launch in October of 2008 for at least one year of operation. LRO will employ six individual instruments to produce accurate maps and high-resolution images of future landing sites, to assess potential lunar resources, and to characterize the radiation environment. LRO will also test the feasibility of one advanced technology demonstration package. The LRO payload includes: Lunar Orbiter Laser Altimeter (LOLA) which will determine the global topography of the lunar surface at high resolution, measure landing site slopes, surface roughness, and search for possible polar surface ice in shadowed regions, Lunar Reconnaissance Orbiter Camera (LROC) which will acquire targeted narrow angle images of the lunar surface capable of resolving meter-scale features to support landing site selection, as well as wide-angle images to characterize polar illumination conditions and to identify potential resources, Lunar Exploration Neutron Detector (LEND) which will map the flux of neutrons from the lunar surface to search for evidence of water ice, and will provide space radiation environment measurements that may be useful for future human exploration, Diviner Lunar Radiometer Experiment (DLRE) which will chart the temperature of the entire lunar surface at approximately 300 meter horizontal resolution to identify cold-traps and potential ice deposits, Lyman-Alpha Mapping Project (LAMP) which will map the entire lunar surface in the far ultraviolet. LAMP will search for surface ice and frost in the polar regions and provide images of permanently shadowed regions illuminated only by starlight. Cosmic Ray Telescope for the Effects of Radiation (CRaTER), which will investigate the effect of galactic cosmic rays on tissue-equivalent plastics as a constraint on models of biological response to background space radiation. The technology demonstration is an advanced radar (mini-RF) that will demonstrate X- and S-band radar imaging and interferometry using light weight synthetic aperture radar. This paper will give an introduction to each of these instruments and an overview of their objectives.     

20世纪初年沈阳市近代私营工业的产生发展

沈阳市近代私营工业产生于20世纪初年,至“九一八”事变前夕初具规模。通过对历史文献资料的整理和分析,对私营工业的主要行业结构、发展规模及特点作了较为全面的阐述,指出私营工业在中国半殖民地化逐步加深的历史背景下,在外国资本和本国官僚资本的夹缝中艰难发展,不可能形成独立的工业体系,必然走上畸形的殖民地经济道路。     

Lunar ground penetrating radar: Minimizing potential data artifacts caused by signal interaction with a rover body

Ground-penetrating radar (GPR) is the leading geophysical candidate technology for future lunar missions aimed at mapping shallow stratigraphy (<5 m). The instrument’s exploration depth and resolution capabilities in lunar materials, as well as its small size and lightweight components, make it a very attractive option from both a scientific and engineering perspective. However, the interaction between a GPR signal and the rover body is poorly understood and must be investigated prior to a space mission. In doing so, engineering and survey design strategies should be developed to enhance GPR performance in the context of the scientific question being asked. This paper explores the effects of a rover (simulated with a vertical metal plate) on GPR results for a range of heights above the surface and antenna configurations at two sites: (i) a standard GPR testing site with targets of known position, size, and material properties, and; (ii) a frozen lake for surface reflectivity experiments. Our results demonstrate that the GPR antenna configuration is a key variable dictating instrument design, with the XX polarization considered optimal for minimizing data artifact generation. These findings could thus be used to help guide design requirements for an eventual flight instrument.