一种适用于窄波束雷达捕获空间目标的等仰角搜索方法

点位预报作为引导雷达寻找、捕获、跟踪目标的基础, 受定轨误差及预报误差的影响, 其精度对窄波束雷达存在不足的风险. 由于沿迹误差是影响点位预报精度的主要因素, 基于沿迹误差补偿的思路, 提出了一种适用于窄波束雷达的过境目标等仰角搜索方法, 在预估的沿迹误差范围内对目标一次过境时在指定仰角上可能出现的所有位置做遍历观测, 从而提高雷达捕获空间目标的成功率. 仿真算例表明, 当点位预报失效时, 等仰角搜索方法仍然能观测到目标.     

基于单站短弧段光学观测的低轨卫星轨道预报算法

基于单站短弧段的目标跟踪预报技术是保证高精度光电经纬仪在非常规环境下正常跟踪捕获目标的重要途径.构建了基于非线性滤波器的跟踪预报算法,能够在正常情况下为闭环跟踪提供引导数据,同时构建了基于非线性变换的目标预报算法,可以在无有效观测数据情况下为经纬仪提供轨迹引导,保证目标不丢失.证明了非线性滤波在单站短弧段跟踪预报算法中比常规扩展卡尔曼滤波(Extended Kalman Filter,EKF)更有效.计算表明,本文设计的非线性滤波器可以作为光学跟踪设备的引导算法,引导精度同经纬仪的随机测量精度等量级,在设备系统误差达到50"时,预报60 s的精度可达到20",仍然满足跟踪设备的视场要求.     

基于误差发散规律的低轨卫星大气阻力系数计算方法

低轨卫星轨道预报精度受到大气模型和大气阻力系数精度的制约,给一些高精度的空间和航天任务带来不利影响.提出了一种基于沿迹方向误差发散规律的大气阻力系数计算新方法.首先通过理论推导给出低轨卫星轨道预报中沿迹误差发散的分析表达式,定量描述初值误差和模型误差对沿迹误差的综合影响;提出利用定轨段的基本信息,优选预报段所采用的阻力系数,抑制沿迹误差的发散速率,从而降低沿迹方向预报误差的最大值,提高短期预报精度.以400 km附近的GRACE-A卫星的全弧段星载GPS高精度资料为基础,检验了方法的精度和成功率.结果表明:相对于传统的定轨预报方法,新方法能提高24 h短期预报精度约45%,成功率约71%,总体有效率约86%;方法对低、中、高等3种太阳辐射水平均有效,对于中低等级的地磁扰动也有效,具备较好的应用价值.     

基于GM(1,1)和MECM组合模型的GPS卫星钟差中短期预报

针对卫星钟差呈现趋势项和随机项变化的特点,提出了基于GM(1,1)(灰色预报模型)和修正指数曲线法(Modified Exponential Curve Method,MECM)的组合预报模型.该模型首先采用GM(1,1)预报钟差的趋势项,然后利用MECM模型对GM(1,1)残差序列进行建模和预报,最后将GM(1,1)和MECM模型的预报结果相加得到钟差的最终预报值.此外,采用IGS(International Global Navigation Satellite System Service)公布的精密卫星钟差进行预报试验,通过与卫星钟差预报中常用的二次多项式和MECM模型预报结果的对比分析,结果表明:该方法可以对GPS卫星钟差进行高精度的中短期预报.使用12 h钟差建模时,预报6 h、12 h、18 h和24 h的平均预报精度分别为0.43 ns、0.63 ns、0.74 ns和0.79 ns,相比于二次多项式的平均预报精度分别提高了57.43%、69.71%、80.47%和86.74%,相比于MECM模型的平均预报精度分别提高了50.57%、64.41%、76.80%和84.20%;使用24 h钟差建模时,预报6 h、12 h、18h和24 h的平均预报精度分别为0.57 ns、0.61 ns、1.02 ns和1.48 ns,相比于二次多项式的平均预报精度分别提高了32.94%、55.47%、55.07%和53.16%,相比于MECM模型的平均预报精度分别提高了92.98%、66.30%、65.42%和63.99%.     

月面反射器观测位置的高精度预报

本文利用JPL的DE303/LE303星历表建立了一套预报月面反射器相对于地面观测站位置的计算机程序,并对预报精度作了估计,结果表明预报精度达到毫角秒级。     

基于Vondrák滤波1阶差分灰色模型的卫星钟差预报方法

为了提高卫星钟差预报的精度,提出基于Vondrák滤波1阶差分的灰色模型算法.首先,对原始钟差数据序列采用Vondrák滤波处理后,得到1组新的钟差数据序列.然后,对相邻历元的钟差数据序列作1阶差分处理.最后,基于Vondrák滤波后的1阶差分的钟差差值数据序列,建立了GPS钟差预报的灰色模型.此外,采用了IGS(International Global Navigation Satellite System Service)公布的精密卫星钟差数据进行了预报试验,通过与卫星钟差预报中常用的2次多项式模型和直接采用原始钟差数据建立灰色预报模型预报结果的对比分析,结果表明:该方法可以对GPS卫星钟差进行高精度的中短期预报.在12 h、16 h、20 h和24 h的平均预报精度分别为0.50 ns、0.85 ns、1.08 ns和1.27 ns,相比于2次多项式模型的平均预报精度分别提高了24.24%、15.84%、12.90%和11.81%;相比于直接采用原始钟差数据建立灰色预报模型的平均预报精度分别提高了56.14%、49.40%、48.82%和47.80%.     

一九八三年以来地球自转速率的变化及(UT1—UTC)预报

自1983年以来,我们承担了BPM短波时号UT1-UTC控制发播的任务。几年来,控制发播和预报UT1-UTC的精度不断提高,满足了用户的要求。在此项工作中,我们还发现这几年地球自转速率在不断加快。     

卫星轨道预报的一种分析方法

人造地球卫星的轨道预报是空间环境监测和实时跟踪测量中一个重要环节，由于监测对象众多，要求精度也不太高，通常采用分析法预报．在已有分析法得到t时刻平均根数的基础上给出一种轨道预报方法，由t时刻的平均根数给出该时刻卫星的位置和速度，在此基础上将地球非球形引力摄动的周期项直接用卫星直角坐标的位置和速度分量表示，这样可以避免在计算轨道根数变化的周期项时出现的奇点问题，从而对根数的选择无特殊要求，可适用于各种轨道，简化预报程序和相应的软件，提高预报效率。     

基于一次差的灰色模型在卫星钟差预报中的应用

根据星载原子钟钟差的特点,提出一种基于一次差的灰色GM(1,1)钟差预报方法.该方法首先对相邻历元的钟差作一次差,然后以一次差后的值建立灰色模型预报一次差的值,最后将预报的一次差还原即得到钟差预报值.以IGS(International GNSS Service)提供的采样率为5 min的精密钟差为实验数据,通过对不同长度的建模数据和不同预报步长进行对比分析.结果表明:该方法的预报精度较传统的灰色模型有了较大提高,特别是对于PRN01原子钟,其预报效果最好;采用一次差原理可有效改善和提高模型预报的精度和稳定性,应用于钟差较长时间预报是可行的,可靠性较强.     

Reticon探测器用于位置监测的信号处理方法和精度分析

利用低纬子午环上配备的Reticon探测器的输出信号 ,采用重心方法和互相关分析方法分析测定了Reticon用于位置监测的精度。结果表明 :在仪器系统保持稳定的情况下 ,Reticon监测位置变化的精度优于± 0 .0 1像素 (单次测定的标准误差 )。     

Evaluating digital elevation models for glaciologic applications: An example from Nevado Coropuna, Peruvian Andes

This paper evaluates the suitability of readily available elevation data derived from recent sensors – the Advanced Spaceborne Thermal Emission and Reflection Radiometer (ASTER) and the Shuttle Radar Topography Mission (SRTM) – for glaciological applications. The study area is Nevado Coropuna (6426 m), situated in Cordillera Ampato of Southern Peru. The glaciated area was 82.6 km² in 1962, based on aerial photography. We estimate the glacier area to be ca. 60.8 km² in 2000, based on analysis of the ASTER L1B scene.We used two 1:50,000 topographic maps constructed from 1955 aerial photography to create a digital elevation model with 30 m resolution, which we used as a reference dataset. Of the various interpolation techniques examined, the TOPOGRID algorithm was found to be superior to other techniques, and yielded a DEM with a vertical accuracy of ± 14.7 m. The 1955 DEM was compared to the SRTM DEM (2000) and ASTER DEM (2001) on a cell-by-cell basis. Steps included: validating the DEM's against field GPS survey points on rock areas; visualization techniques such as shaded relief and contour maps; quantifying errors (bias) in each DEM; correlating vertical differences between various DEM's with topographic characteristics (elevation, slope and aspect) and subtracting DEM elevations on a cell-by-cell basis.The RMS error of the SRTM DEM with respect to GPS points on non-glaciated areas was 23 m. The ASTER DEM had a RMS error of 61 m with respect to GPS points and displayed 200–300 m horizontal offsets and elevation ‘spikes’ on the glaciated area when compared to the DEM from topographic data.Cell-by-cell comparison of SRTM and ASTER-derived elevations with topographic data showed ablation at the toes of the glaciers (− 25 m to − 75 m surface lowering) and an apparent thickening at the summits. The mean altitude difference on glaciated area (SRTM minus topographic DEM) was − 5 m, pointing towards a lowering of the glacier surface during the period 1955–2000. Spurious values on the glacier surface in the ASTER DEM affected the analysis and thus prevented us from quantifying the glacier changes based on the ASTER data.     

The science process for selecting the landing site for the 2011 Mars Science Laboratory

The process of identifying the landing site for NASA’s 2011 Mars Science Laboratory (MSL) began in 2005 by defining science objectives, related to evaluating the potential habitability of a location on Mars, and engineering parameters, such as elevation, latitude, winds, and rock abundance, to determine acceptable surface and atmospheric characteristics. Nearly 60 candidate sites were considered at a series of open workshops in the years leading up to the launch. During that period, iteration between evolving engineering constraints and the relative science potential of candidate sites led to consensus on four final sites. The final site will be selected in the Spring of 2011 by NASA’s Associate Administrator for the Science Mission Directorate. This paper serves as a record of landing site selection activities related primarily to science, an inventory of the number and variety of sites proposed, and a summary of the science potential of the highest ranking sites.     

Remote sensing of terrestrial impact craters: The TanDEM‐X digital elevation model

With the TanDEM‐X digital elevation model (DEM), the terrestrial solid surface is globally mapped with unprecedented accuracy. TanDEM‐X is a German X‐band radar mission whose two identical satellites have been operated in single‐pass interferometer configuration over several years. The acquired data are processed to yield a global DEM with 12 m independent posting and relative vertical accuracies of better than 2 m and 4 m in moderate and mountainous terrain, respectively. This DEM provides new opportunities for space‐borne remote‐sensing studies of the entire sample of terrestrial impact craters. In addition, it represents an interesting repository to aid in the search for new impact crater candidates. We have used the TanDEM‐X DEM to investigate the current set of confirmed impact structures. For a subsample of the craters, including small, midsized, and large structures, we compared the results with those from other DEMs. This quantitative analysis demonstrates the excellent quality of the TanDEM‐X elevation data. Our findings help to estimate what can be gained by using the TanDEM‐X DEM in impact crater studies. They may also be beneficial in identifying the regions and morphologies where the search for currently unknown impact structures might be most promising.     

A new segmentation algorithm for lunar surface terrain based on CCD images

Terrain classification is one of the critical steps used in lunar geomorphologic analysis and landing site selection. Most of the published works have focused on a Digital Elevation Model(DEM) to distinguish different regions of lunar terrain.This paper presents an algorithm that can be applied to lunar CCD images by blocking and clustering according to image features, which can accurately distinguish between lunar highland and lunar mare. The new algorithm, compared with the traditional algorithm, can improve classification accuracy. The new algorithm incorporates two new features and one Tamura texture feature. The new features are generating an enhanced image histogram and modeling the properties of light reflection, which can represent the geological characteristics based on CCD gray level images. These features are applied to identify texture in order to perform image clustering and segmentation by a weighted Euclidean distance to distinguish between lunar mare and lunar highlands.The new algorithm has been tested on Chang'e-1 CCD data and the testing result has been compared with geological data published by the U.S. Geological Survey. The result has shown that the algorithm can effectively distinguish the lunar mare from highlands in CCD images. The overall accuracy of the proposed algorithm is satisfactory, and the Kappa coefficient is 0.802, which is higher than the result of combining the DEM with CCD images.     

A new lunar absolute control point: established by images from the landing camera on Chang'e-3

The establishment of a lunar control network is one of the core tasks in selenodesy, in which defining an absolute control point on the Moon is the most important step. However, up to now, the number of absolute control points has been very sparse. These absolute control points have mainly been lunar laser ranging retroreflectors, whose geographical location can be observed by observations on Earth and also identified in high resolution lunar satellite images. The Chang'e-3(CE-3) probe successfully landed on the Moon, and its geographical location has been monitored by an observing station on Earth. Since its positional accuracy is expected to reach the meter level, the CE-3 landing site can become a new high precision absolute control point. We use a sequence of images taken from the landing camera, as well as satellite images taken by CE-1 and CE-2, to identify the location of the CE-3 lander. With its geographical location known, the CE-3 landing site can be established as a new absolute control point, which will effectively expand the current area of the lunar absolute control network by 22%, and can greatly facilitate future research in the field of lunar surveying and mapping, as well as selenodesy.     

Limited By Cost: The Case Against Humans In The Scientific Exploration Of Space

Human space flight represents a heady mix of bravery and drama which can be inspirational to nations and to humankind but at huge economic cost. Due to the current high launch costs only a handful of people have ventured beyond low Earth orbit and walked on the Moon, propelled by aspirations related more to the Cold War than to science. Problems with reusable launch vehicle development mean that severe launch cost limitations will exist for some time. Meanwhile, cheaper robotic probes have visited all the planets except Pluto, flown by comets, landed on Mars, Venus and an asteroid, have probed Jupiter's atmosphere and studied the Universe beyond our own solar system with telescopes. Using these data we are determining mankind's place in the Universe. Public interest in the historic Eros landing eclipsed a simultaneous space walk at the fledgling International Space Station and the Mars Pathfinder landing generated hundreds of millions of website hits in a few days. Given the fact that hundreds of Mars missions could be flown for the still-escalating cost of the International Space Station, the unsuitability of human bodies for deep space exploration, and the advances in 3-d and virtual reality techniques, we discuss whether human exploration needs a place in a realistic, useful and inspirational space programme. This revised version was published online in July 2006 with corrections to the Cover Date.     

Transformable descent vehicles

This article presents some types of planetary descent vehicles, the shape of which varies in different flight phases. The advantages of such vehicles over those with unchangeable form (from launch to landing) are discussed. It is shown that the use of transformable descent vehicles widens the scope of possible tasks to solve.     

Correction Method of Antenna Pointing Error Caused by the Main Reflector Deformation

The pointing accuracy of a radio telescope is usually less than one-tenth of its antenna beam width. For large-aperture antennas at the short-centimeter band or millimeter-wave band, the pointing accuracy must be as high as several arc seconds. Therefore, for large-diameter and high-frequency reflector antennas, the pointing problem has become an important focal point to realize the antenna performance. Among many structural subsystem factors that affect the antenna pointing accuracy, there has been only less study on the factor of main reflector deformation. Based on the structural characteristics of the antenna, a reflector space coordinate system is established in this paper. And based on the space coordinates of the main reflector surface points after deformation, a non-linear least squares fitting method with 3 degrees of freedom is proposed to accurately predict the antenna pointing. Finally, the space geometric relationship is used to strictly derive the precise adjustments on the elevation and azimuth in order for correcting the antenna pointing error, and the indirect relationship between the main reflector deformation and the pointing error is constructed. This has certain guiding significance for improving the pointing accuracy of large radio antennas.     

The Beagle 2 stereo camera system

The stereo camera system (SCS) was designed to provide wide-angle multi-spectral stereo imaging of the Beagle 2 landing site. Based on the Space-X micro-cameras, the primary objective was to construct a digital elevation model of the area in reach of the lander's robot arm. The SCS technical specifications and scientific objectives are described; these included panoramic 3-colour imaging to characterise the landing site; multi-spectral imaging to study the mineralogy of rocks and soils beyond the reach of the arm and solar observations to measure water vapour absorption and the atmospheric dust optical density. Also envisaged were stellar observations to determine the lander location and orientation, multi-spectral observations of Phobos & Deimos and observations of the landing site to monitor temporal changes.     

Landing Area Selection Based on Closed Environment Avoidance from a Single Image During Optical Coarse Hazard Detection

The success of a landed space exploration depends largely on the final landing site, and the most important factor of landing site selection is the safety of lander, so, hazard detection and avoidance are crucial during asteroid landing. Many approaches have been proposed at present, most of them just detect hazard and select an area that is free of hazard threaten, however, in some cases, the selected site should not be the places that located in closed environment, such as the inner of crater. To tackle the issue, an approach for selecting landing site with closed environment avoidance based on a single image during optical coarse hazard detection was proposed in this paper, the approach was designed under the scheme of Chang’e-3’s landing process. The approach begins with hazard detection based on a proposed binary method. And then, for searching the candidate circular landing areas, the skeletons of areas with no hazard are taken into account, and then, control constraints are considered to select the landing areas that are accessible by the lander. Finally, the final selected circular landing area are chosen by a proposed scoring method, this method combines the factors of circular areas, including radius, the connection among circular areas, circular area’s texture and the cluster relation between circular area’s center and all the hazard. At last, serious of experiments would be conducted to test the performance of the proposed approach.