丝绸之路沿线的兰州城市空间演变及其影响因素

丝绸之路沿线的城市是丝绸之路文明演变的聚焦和投影, 研究历史时期丝绸之路沿线城市空间演变及影响因素是理解丝绸之路沿线城市发展的有效视角, 对解释丝绸之路沿线人地关系规律具有科学意义。本研究以兰州市作为丝绸之路沿线典型城市, 以历史文献资料为基础, 结合空间分析技术对历史时期兰州城市空间演变及其影响因素进行分析, 得出以下结论: 丝绸之路的兴衰与兰州城市空间演变的扩张呈现正相关性, 兰州的行政建制始于秦始皇三十三年(214 BC), 隋文帝开皇元年(581 A.D.)"兰州"首次见于诸史册, 兰州城市空间由隋唐时期(907 A.D.)的0.40 km2增加到2015年的132.67 km2。历史时期兰州城市空间演变包括4个主要阶段: 城市萌芽期的"缓慢发展", 军事职能主导下的"约束性"扩张, 王朝兴盛所带动的"年轮式"增长, 国家政策推动的"跨越式"扩展。影响兰州城市空间演化的因素涵盖丝绸之路兴衰、军事政治、交通贸易及自然环境等, 各种影响因素共同驱动着兰州城市由早期的黄河渡口、军事据点向西北地区政治、经济、文化、交通中心演变。     

Contents To Volume 88

Volume Contents

Contents To Volume 88     

改进的无网格法及其在冻土区桩基温度场中的应用

采用带权正交基函数对传统的无网格法中的基函数进行了改进,避免了计算过程中可能出现的矩阵不可逆情况,而且编程容易实现且计算效率高。并将其应用到冻土区桩基包括了热传导和相变潜热的温度场中,同时考虑了混凝土水化热释放对桩周冻土的影响,将计算结果和有限元计算结果及现场实测数据进行了比较分析,从趋势和最大数值看都反映了实测曲线的趋势,又把不同深度处桩侧和不同桩径处温度随时间的变化规律计算结果和有限元计算结果做了对比,都验证了该方法的可行性和优越性。     

方向观测后方交会的点位精度

以虚拟误差方程,经严密推证,给出了以方向作为独立观测值的后方交会点位精度估算公式。以大桥施工控制网为例,介绍了３个方向与４个方向后方交会的精度状况及其应用。     

地震折射和反射波联合勘探在桥址区工程勘察中的应用

用浅层地震折射和反射联合勘探方法在京—沪高速公路沭河桥址区进行隐伏断层和层位划分探测试验。试验是在宽约300m的水面上进行的,采用ES-2401高分辨率数字地震仪和“五小二高”的工作方法,综合利用折射和反射波信息,提高地质推断解释的可靠性,探测试验取得了良好的效果。     

Development mechanism for the landslide at Xinlu Village,Chongqing, China

Due to the continuous and intense rainfall from June 26 to 28, 2016, Xinlu Village in Ganshui Town, Qijiang District, Chongqing, experienced a unitary-slip landslide at approximately UTC+8 19:30 on June 28. This landslide disrupted the Chuan-Qian railway and damaged four residential buildings. To analyze and rehabilitate the landslide, the engineering geology, hydrological conditions, and deformation instability mechanism of this landslide were investigated and comprehensively analyzed based on an in situ survey, geophysical drilling, and a laboratory quick-shearing test. The results show that the landslide is a typical gradual progressive landslide.     

虚拟天文台的技术进展

虚拟天文台是在望远镜和探测器的研制技术、计算机网络技术取得突破性进展的条件下产生的，与最新的信息技术紧密结合成为其发展最鲜明的特点。用可扩展标记语言（简称XML）技术封装天文数据，把虚拟天文台建立在网格的体系结构之上是当今虚拟天文台技术发展的主流。按照目前虚拟天文台具代表性的层次式体系结构分层介绍各个层次的相关技术，同时提出充分利用现有资源优势实施中国虚拟天文台计算的设想。     

The First Solar Seeing Profile Measurement with Two Apertures and Multiple Guide Regions

The sky brightness is a critical parameter for estimating the coronal observation conditions for a solar observatory. As part of a site-survey project in Western China, we measured the sky brightness continuously at the Lijiang Observatory in Yunnan province in 2011. A sky brightness monitor (SBM) was adopted to measure the sky brightness in a region extending from 4.5 to 7.0 apparent solar radii based on the experience of the Daniel K. Inouye Solar Telescope (DKIST) site survey. Every month, the data were collected manually for at least one week. We collected statistics of the sky brightness at four bandpasses located at 450, 530, 890, and 940 nm. The results indicate that aerosol scattering is of great importance for the diurnal variation of the sky brightness. For most of the year, the sky brightness remains under 20 millionths per airmass before local Noon. On average, the sky brightness is less than 20 millionths, which accounts for 40.41% of the total observing time on a clear day. The best observation time is from 9:00 to 13:00 (Beijing time). The Lijiang Observatory is therefore suitable for coronagraphs investigating the structures and dynamics of the corona.     

The Orbital Evolution of Two Sounding Satellites and Analysis of the Accuracy of Orbit Determination

The satellites TC-1 and TC-2 are the two Chinese satellites with great elliptical orbits which are still in orbit around the earth at present. Since the launch the orbits of the two satellites have continuously evolved, which has a certain effect on the orbit determination and prediction precision. The regularities of the orbital evolution of the two sounding satellites are qualitatively and quantitatively analyzed. Under the current tracking mode the corresponding prediction precision of orbit determination is analyzed based on the different stages of the orbital evolution, thereby providing the basis for the adjustment of planning mode by the satellite application departments and the guarantee of normal satellite payload. Finally, the orbital lifetimes of the two satellites are predicted through the trend of the orbital evolution.     

Formation flying in elliptic orbits with the J2 perturbation

Relative dynamics between the chief satellite and the deputy ones in formation flying is crucial to maintaining the formation. A good choice of the formation usually requires a lower control frequency or less control energy. For formation flying missions in highly elliptic orbits, the well-known C-W equation is not accurate enough. Instead, Lawden’s equation is often used. First, the solution to Lawden’s equation with a very simple form is deduced. Then the J2 perturbation is added. It is found that Lawden’s solution is not necessarily valid when the J2 perturbation is considered. Completely discarding Lawden’s solution and borrowing the idea of mean orbit elements, two rules to initialize the formation are proposed. The deviation speed is greatly reduced. Different from previous studies on the J2 perturbation, except for the relatively simple expression for the semi-major axis, the tedious formulae of the long period terms and the short period terms of other orbital elements are not used. In addition, the deviation speed is further reduced by compensation of the nonlinear effects. Finally, a loose control strategy of the formation is proposed. To test the robustness of this strategy, a third body perturbation is added in numerical simulations.