Simulation study of the performance of the Very Large Area gamma-ray Space Telescope

The Very Large Area gamma-ray Space Telescope(VLAST)is a mission concept proposed to detect gamma-ray photons through both Compton scattering and electron–positron pair production mechanisms,thus enabling the detection of photons with energies ranging from MeV to TeV.This project aims to conduct a comprehensive survey of the gamma-ray sky from a low-Earth orbit using an anti-coincidence detector,a tracker detector that also serves as a low-energy calorimeter,and a high-energy imaging calorimeter.We developed a Monte Carlo simulation application of the detector using the GEANT4 toolkit to evaluate the instrument performance,including the effective area,angular resolution,and energy resolution,and explored specific optimizations of the detector configuration.Our simulation-based analysis indicates that the current design of the VLAST is physically feasible,with an acceptance above 10 m^(2)sr which is four times larger than that of the Fermi-LAT,an energy resolution better than 2%at 10 GeV,and an angular resolution better than 0.2◦at 10 GeV.The VLAST project promises to make significant contributions to the field of gamma-ray astronomy and enhance our understanding of the cosmos.

Are James Webb Space Telescope Observations Consistent with Warm Dark Matter?

We compare observed with predicted distributions of galaxy stellar masses M* and galaxy rest-frame ultra-violet luminosities per unit bandwidth LUV, in the redshift range z=2 to 13. The comparison is presented as a function of the comoving warm dark matter free-streaming cut-off wavenumber kfs. For this comparison the theory is a minimal extension of the Press-Schechter formalism with only two parameters: the star formation efficiency, and a proportionality factor between the star formation rate per galaxy and LUV. These two parameters are fixed to their values obtained prior to the James Webb Space Telescope (JWST) data. The purpose of this comparison is to identify if, and where, detailed astrophysical evolution is needed to account for the new JWST observations.

Progress on Space Solar Telescope in 2004 - 2006

The progress on Chinese Space Solar Telescope (SST) in 2004-2006 is introduced. The scientific objectives are further clarified and the ground operation system has been planned. The 7 key technical problems of SST satellite platform and payloads have been tackled, which lay solid scientific and technological foundations for engineering prototype phase of the SST project. At present the SST project undergoes evaluation by CNSA and CAS so as to enter the engineering prototype phase of the SST project if it is finally approved.

Design and Cryogenic Performance of a Hexapod Platform for a Large Ground-based Wide Field Survey Telescope

The thermal gradient is an important factor that causes degradation to the image quality of telescopes. In order to ensure the accurate alignment of the primary focus unit and the primary mirror, the hexapod platform(as a corrector) is investigated in this paper. First, a ground-based telescope with 2.5 m aperture and 3.5 deg field of view is described. The telescope is under construction, and it is expected to be finished in 2023. Second, the hexapod platform with flexure hinges utilized to adjust the primary focus unit is proposed, which is applied as a corrector.Then, the inverse kinematics of the platform is established and an open-loop control system is built based on it.Finally, the cryogenic performance test for the hexapod platform is performed. The experimental results show that the resolution and repeatability of the translation for the hexapod platform can be achieved at the micrometer level.The resolution and repeatability of the rotation can be achieved at the arc-second level. Therefore, the cryogenic performance of the hexapod platform can meet the optical imaging requirements of the wide-field ground-based telescope. The kinematic analysis and cryogenic performance tests in the paper provide a technical reference for the precise alignment of the primary focus unit and the primary mirror, which can improve the imaging quality of the telescope.

Two suggested configurations for the Chinese space telescope

China will establish a 2-meter space-based astronomical telescope. Its main science goals are performing a sky survey for research about dark matter and dark energy, and high resolution observations. Some experts suggest that this space telescope should be installed inside the Chinese space station. In accord with this suggestion we put forward our first configuration, i.e., to adopt a coude system for this telescope. This coude system comes from the Chinese 2.16 m telescope＇s coude system, which includes a relay mirror so that excellent image quality can be obtained. In our second configuration, we suggest that the whole space telescope fly freely as an independent satellite outside the space station. When it needs servicing, for example, changing in- struments, refilling refrigerant or propellant, etc., this space telescope can fly near or even dock with the core space station. Although some space stations have had accom- panying satellites, the one we propose is a space telescope that will be much larger than other accompanying satellites in terms of weight and volume. On the basis of the second configuration, we also put forward the following idea： the space station can be composed of several large independent modules if necessary.

Progress on Space Solar Telescope in 2002-2004

The progress on Chinese Space Solar Telescope (SST) in 2002-2004 is introduced. The documentations on plans and outlines based on the standards of Chinese aerospace industry for SST mission has been fulfilled. The key technical problems of SST satellite platform and payloads are tackled during pre-study stage of the mission. The laboratory assembly and calibration of the main optical telescope of 1.2 m spherical mirror and 1 m plain mirror have been carried out with the accuracy of λ/40 and λ/30, respectively. The prototype at 17.1 nm for extreme ultraviolet telescope is under development and manufacture with a diameter of 13 cm. Its primary and secondary mirrors have a manufacturing error of 5nm with a roughness degree of less than 0.5 nm and a multiplayer reflection factor of better than 20%. The on-board scientific data processing unit has been developed. Prototypes for other payloads such as H and white light telescope, wide band spectroscopy in high energy and solar and interplanetary radio spectrometer have been developed accordingly.

Pose Estimation of Space Targets Based on Model Matching for Large-Aperture Ground-Based Telescopes

With the development of adaptive optics and post restore processing techniques,large aperture ground-based telescopes can obtain high-resolution images(HRIs)of targets.The pose of the space target can be estimated from HRIs by several methods.As the target features obtained from the image are unstable,it is difficult to use existing methods for pose estimation.In this paper a method based on real-time target model matching to estimate the pose of space targets is proposed.First,the physicallyconstrained iterative deconvolution algorithm is used to obtain HRIs of the space target.Second,according to the 3D model,the ephemeris data,the observation time of the target,and the optical parameters of the telescope,the simulated observation image of the target in orbit is rendered by a scene simulation program.Finally,the target model searches through yaw,pitch,and roll until the correlation between the simulated observation image and the actual observation image shows an optimal match.The simulation results show that the proposed pose estimation method can converge to the local optimal value with an estimation error of about 1.6349°.

Presentation on the Electronic Control System of Space Solar Telescope

This paper gives the brief view of the electronic control system of SPACE SOLAR TELESCOPE (SST), especially the On Board Data Handling unit (OBDH) on the SST which control the operation of the instrument, acquire data and make data analysis and storage. In OBDH, the Scientific Data Unit (SDU) is a special unit that requires high speed computer. In this paper gives a brief comparison of two possible choices and discuss selection of electronic parts in the space environment.

Korean Participation in the Galex Ultraviolet Space Telescope Project

The Center for Space Astrophysics at Yonsei university, Seoul, Korea, is actively participating in the development and operation of the Galaxy Evolution Explorer (GALEX), a NASA ultraviolet space telescope project to be launched in late 2001. As the first official case of NASA Korea cooperation on major space science program, this project will greatly expand the capability of Korean astronomy into space based operations.

文献“GLAST large area telescope calorimeter subsystem:vibration test”点评

文章点评的对象是一个执行宇宙粒子物质观测任务的高分辨率、长寿命、高可靠光学部组件.点评的中心内容是关于"大面积望远镜"地面振动试验,包括对试验任务的提出、试验的具体实施以及试验后的设计评审、合格标准、技术规范等等地面力学环境试验要素进行一一介绍与评述,以供业内人士参考或商榷.

Photometric Calibration of the Lunar-based Ultraviolet Telescope for Its First Six Months of Operation on the Lunar Surface

We describe the photometric calibration of the Lunar-based Ultraviolet Telescope（LUT）, the first robotic astronomical telescope working on the lunar surface, for its first six months of operation on the lunar surface. Two spectral datasets（set A and B） from near-ultraviolet（NUV） to the optical band were constructed with 44 International Ultraviolet Explorer（IUE） standards, because of the LUT＇s relatively wide wavelength coverage. Set A was obtained by extrapolating the IUE NUV spectra（λ 〈 3200 ） to the optical band based upon the theoretical spectra of stellar atmosphere models. Set B was composed of theoretical spectra from 2000 to 8000 extracted from the same model grid. In total, seven standards have been observed in15 observational runs until May 2014. The calibration results show that the photometric performance of LUT is highly stable in its first six months of operation. The magnitude zero points obtained from the two spectral datasets are also consistent with each other, i.e., zp = 17.54 ± 0.09 mag（set A） and zp = 17.52 ± 0.07 mag（set B）.

Unified Modeling Approach of Kinematics, Dynamics and Control of a Free-Flying Space Robot Interacting with a Target Satellite

In this paper a unified control-oriented modeling approach is proposed to deal with the kinematics, linear and angular momentum, contact constraints and dynamics of a free-flying space robot interacting with a target satellite. This developed approach combines the dynamics of both systems in one structure along with holonomic and nonholonomic constraints in a single framework. Furthermore, this modeling allows consid-ering the generalized contact forces between the space robot end-effecter and the target satellite as internal forces rather than external forces. As a result of this approach, linear and angular momentum will form holonomic and nonholonomic constraints, respectively. Meanwhile, restricting the motion of the space robot end-effector on the surface of the target satellite will impose geometric constraints. The proposed momentum of the combined system under consideration is a generalization of the momentum model of a free-flying space robot. Based on this unified model, three reduced models are developed. The first reduced dynamics can be considered as a generalization of a free-flying robot without contact with a target satellite. In this re-duced model it is found that the Jacobian and inertia matrices can be considered as an extension of those of a free-flying space robot. Since control of the base attitude rather than its translation is preferred in certain cases, a second reduced model is obtained by eliminating the base linear motion dynamics. For the purpose of the controller development, a third reduced-order dynamical model is then obtained by finding a common solution of all constraints using the concept of orthogonal projection matrices. The objective of this approach is to design a controller to track motion trajectory while regulating the force interaction between the space robot and the target satellite. Many space missions can benefit from such a modeling system, for example, autonomous docking of satellites, rescuing satellites, and satellite servicing, where it is vital to limit the con-tact force during the robotic operation. Moreover, Inverse dynamics and adaptive inverse dynamics control-lers are designed to achieve the control objectives. Both controllers are found to be effective to meet the specifications and to overcome the un-actuation of the target satellite. Finally, simulation is demonstrated by to verify the analytical results.

空间天文望远镜自适应精密稳像闭环控制

针对空间天文望远镜低频段视轴扰动补偿问题,提出了一种基于主动光学技术的自适应精密稳像闭环控制方法。该方法以精细导星仪(Fine Guide Sensor,FGS)为高精度视轴扰动检测器,以四点支撑压电驱动大口径快摆镜机构(Fast Steering Mirror,FSM)为视轴扰动补偿器。首先,采用位置式PID控制器串联积分环节进行精密稳像闭环控制,得到补偿FGS检测出的二维视轴扰动所需FSM的二维摆动角度,进而根据驱动结构转换为每个支撑点的压电陶瓷执行器(Piezoelectric actuators,PZT)的伸缩量。然后,利用基于广义Bouc-Wen逆模型的压电动态迟滞前馈补偿方法进行高精度的压电陶瓷执行器定位控制。最后,根据有监督的Hebb学习规则,利用具有自学习和自适应能力单神经元对PID控制器参数进行调整,从而得到最优控制器参数。实验结果表明,所提控制方法能够有效地补偿空间天文望远镜的视轴偏差,可以将精细导星仪X方向和Y方向的星点质心位置偏差功率谱密度在0~6 Hz频段内积分值分别抑制了98.54%和98.62%。

NASA重大项目预研管理过程研究——以韦布望远镜为例

做好重大科技项目的组织管理是实现抢占科技制高点目标的重要前提条件。本文以美国国家航空航天局(National Aeronautics and Space Administration,NASA)系列管理文件为分析对象,剖析其项目组织管理模式,并以投资近百亿美元、持续数十年的詹姆斯·韦布太空望远镜项目为例,对NASA重大项目预研管理过程进行分析。NASA将项目按照成本、风险、是否属于优先事项等分为3个类别进行管理,项目生命周期可以分为从“A前”(pre-A)到A、B直至F共7个阶段。韦布望远镜从1995年进入NASA的“A前阶段”,由3家单位独立开展概念研究;1999年7月从3家单位中遴选2家开始“A阶段”研究;2002年9月正式选择1家单位牵头开展“B阶段”研究。可供我国借鉴之处包括:项目组织方应发挥好“总体”角色,凝聚多方资源、提供长期稳定支持;新项目的酝酿需充分利用前期项目的科学、技术、管理人才基础;可利用“赛马制”等分阶段推进重大项目的实施,以降低不确定性和决策风险等。

大口径空间光学望远镜桁架结构关键技术研究进展

近年来大口径空间光学望远镜以高像质、宽波段、大幅宽等特点,在开展空间科学探索、精细化对地观测等方面越来越重要。大口径望远镜的主承力结构、大型光学组件的支撑结构往往采用桁架结构,本文围绕实现桁架结构的超轻、超稳特性,从构型优化设计、新型材料、先进制造工艺、精确测量标定方法等方面,系统性梳理了其理论基础、研究方法、应用现状等,并探讨了空间桁架结构技术的发展趋势。

哈勃空间望远镜运行控制及规划模式研究综述

哈勃空间望远镜(Hubble Space Telescope,HST)作为首个大型且复杂的在轨空间天文观测站,其成功运行离不开NASA的主导及多个控制中心与机构的协同努力。深入探讨了哈勃任务的多机构协同管理模式,详细分析了运控中心飞行操作人员的构成及其执行的典型操控活动。同时,针对HST的数据上下行处理及转发测控模式进行了分析,并研究了其地面软件系统的架构及其自任务实施以来的升级改造情况。全面分析了哈勃开展天文观测任务的全规划流程及周期规划模式。基于哈勃任务的成功实施经验,为我国未来开展空间望远镜任务提供了具体且有益的启示。

星冕仪模块光机热集成仿真分析与试验研究

针对巡天望远镜星冕仪模块光机系统进行集成仿真分析和试验研究,首先根据星冕仪模块热边界仿真分析光机系统热温度场分布;其次,将热温度场映射到光机系统中,利用有限元方法分析在此温度场映射下镜面形变;再次,提取各镜面节点数据拟合镜面的刚体平移量和Zernike多项式系数,分别导入Zemax光学方案,分析温度场对光学系统影响,从而实现光机热集成仿真分析的完整过程;最后,通过试验研究最终方案在主动热控方案下光学性能。集成仿真结果显示,在主动温控载荷条件下,其波前畸变RMS值变化小于千分之一;试验测试结果显示,其波前畸变RMS值为1/25波长,满足指标优于1/20波长的设计要求。

星载望远镜消光材料积分散射特性测试研究(英文)

在散射理论的基础上,介绍了一种星载望远镜消光材料积分散射特性测试装置,实现对星载望远镜消光材料散射特性更为全面的测量。对积分散射理论、系统构造、系统性能进行了阐述。对系统进行建模仿真分析,得到结论:消光材料的散射特性在不同点位和入射角下存在明显差异,系统能够测量多种条件下消光材料的散射特性,并得到消光材料全面的散射特性分布。研究结果为根据消光材料特性进行针对性设计提供了更全面、更准确的散射特性分布,为杂散光的测量与抑制、高性能光学仪器的研制与装调以及计算光学等领域的研究提供了参考。为空间引力波探测星载望远镜系统的材料选型、特性研究、杂散光分析与抑制提供了基础。

空间引力波星载望远镜测试与评估技术研究进展

在空间引力波探测任务中,星载望远镜承担太空超长干涉光路双向光束准直的重要作用。空间引力波探测对星载望远镜提出了pm级光程稳定性和低于10^(-10)级后向杂散光水平的极高要求。超高水平指标要求超过了当前测试技术的精度极限,因此,针对星载望远镜发展测试与评估技术并开展系统超高精度测试是空间引力波探测计划成功的重要前提。本文在概述国内外在研的空间引力波探测星载望远镜研制情况的基础上,重点围绕星载望远镜的核心技术指标——光程稳定性和后向杂散光,介绍了在研望远镜的测试技术发展现状和已经取得的部分测试成果,以及各研究单位进一步的测试计划,为我国的空间引力波探测的星载望远镜测试与评估技术发展提供参考。

基于光电阵列系统的空间碎片精密定轨应用研究

光电阵列系统具有视场大、单元众多、覆盖空域广、可靠性高、实时性好等优点,在空间碎片探测领域中具有重要的作用。首先,为了解决空间碎片关联匹配问题,采用TLE数据,配合SGP4/SDP4模型,实现了光电阵观测空间碎片的数据关联匹配。随后,研究了空间碎片弹道系数计算方法,为基于观测数据定轨结果的空间碎片平均弹道系数的计算奠定基础。最后,基于长春人卫站建设的光电阵列系统,验证其数据精度、定轨精度以及弹道系数计算精度,实验结果表明:空间碎片关联匹配成功率达到91.19%;观测精度可达7:65′′;对拥有高精度激光测距的空间合作目标Sentinel-6A和HY-2C进行基于激光测距数据的精密定轨,并以定轨结果为标准轨道,对光电阵列观测系统所得光学数据进行精密定轨和3 d预报的均方差做精度分析,三维位置精度分别为319.11 m、107.25 m,速度精度分别为0.26 m/s、0.09 m/s;计算所得目标36508弹道系数生成的新两行根数3 d预报均方根误差为746.84 m,比公开数据均方根误差748.68 m减小0.25%,两者精度相近。以上结果说明该系统基本满足常规任务需求。