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.     

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.     

An Introduction to Magnetosphere-Ionosphere-Thermosphere Coupling Small Satellite Constellation

A future Chinese mission is introduced to study the coupling between magnetosphere, ionosphere and thermosphere, i.e. the Magnetosphere-Ionosphere-Thermosphere Coupling Small Satellite Constellation (MIT). The scientific objective of the mission is to focus on the outflow ions from the ionosphere to the magnetosphere. The constellation is planning to be composed of four small satellites; each small satellite has its own orbit and crosses the polar region at nearly the same time but at different altitude. The payloads onboard include particle detectors, electromagnetic payloads, auroral imagers and neutral atom imagers. With these payloads, the mission will be able to investigate acceleration mechanism of the upflow ions at different altitudes. Currently the orbits have been determined and prototypes of some have also been completed. Competition for next phase selection is scheduled in late 2015.      

Design and construction of the ROSAT 5 arcsec mirror assembly

The ROSAT mission, which is currently being prepared in W.-Germany, will perform the first soft X-ray all-sky survey by means of a large imaging X-ray telescope. Detailed calculations under the cost, volume and mass constraint of the satellite being a Shuttle payload have led to a design of the imaging optics with optimized geometry. The mirror system is of the Wolter type I configuration and includes four nested shells with a maximum aperture of 835 mm and a focal length of 2400 mm. The on-axis angular resolution of the mirror assembly has been specified to 5 arcsec with a scattering level as low as 3% for single reflection at 1.5 keV photon energy. Construction and technology studies have been completed by now and manufacturing of the first mirror shell has begun.     

超大型光学镜面面形的纳米定位技术

电容式传感器在纳米级测试中得到了广泛的应用，但是对环境条件要求较高，检测中温、湿度的变化、传感器本身结构乃至其电路性能等因素，将直接影响测量的准确度和灵敏度。介绍了大型天体望远镜光学镜面面形的控制方法和工作原理。该大型天体望远镜Φ１０ｍ的主镜由３６块对角线长１．８ｍ的六角形子镜拼接而成，应用电容测微技术使此超大型镜面的共面性达到纳米量级的定位控制。通过检测原理的分析，阐述了电容式传感器在使用中提高其准确度和长期稳定性的理论分析和具体技术措施，并针对国内正在研制的ＬＡＭＯＳＴ超大型天体望远镜实际应用环境和技术指标要求，提出新的差动式传感器，并采用新材料和高集成度的进口新器件，以满足传感器在温、湿度变化大的条件下实时监测的要求。     

嫦娥三号着陆器有效载荷

嫦娥三号着陆器配置了地形地貌相机、月基光学望远镜、极紫外相机、降落相机等四种科学探测有效载荷.介绍了有效载荷的科学探测任务、系统设计方案和系统组成,描述了各有效载荷的方案设计和主要技术指标等.      

YingHuo-1——Martian Space Environment Exploration Orbiter

This paper gives a brief introduction of YingHuo-1 (YH-1), a Chinese Martian Space Environment Exploration Orbiter. YH-1 is a micro-satellite developed by Chinese Aerospace Industry,and will be launched together with Russian spacecraft, Phobos-Grunt, to orbit Mars in September,2009. Four payloads are selected for the mission, plasma package, including of electron analyzer, ion energy and mass analyzer; sat-sat occultation receiver; flux-gate magnetometer; and optical monitor.YH-1 mission focus on the investigation of the characteristics and its evolution of the Martian space Environment, and identifying major plasma processes, which provide channels for Martian volatiles escaping.      

YingHuo-1——Martian Space Environment Exploration Orbiter

This paper gives a brief introduction of YingHuo-1 (YH-1), a Chinese Martian Space Environment Exploration Orbiter. YH-1 is a micro-satellite developed by Chinese Aerospace Industry,and will be launched together with Russian spacecraft, Phobos-Grunt, to orbit Mars in September,2009. Four payloads are selected for the mission, plasma package, including of electron analyzer, ion energy and mass analyzer; sat-sat occultation receiver; flux-gate magnetometer; and optical monitor.YH-1 mission focus on the investigation of the characteristics and its evolution of the Martian space Environment, and identifying major plasma processes, which provide channels for Martian volatiles escaping.     

嫦娥四号任务科学目标和有效载荷配置

嫦娥四号探测器由中继星、着陆器和巡视器组成.其科学目标为:月基低频射电天文观测研究,月球背面巡视区浅层结构探测研究以及月球背面巡视区形貌与矿物组分探测研究.共配置6台有效载荷设备,其中3台载荷设备配置在着陆器上,分别为降落相机、地形地貌相机和低频射电谱仪,其余3台配置在巡视器上,分别为全景相机、测月雷达和红外成像光谱仪.本文主要论述了嫦娥四号任务的科学目标、着陆区概况、有效载荷配置及系统设计、各有效载荷任务和主要技术指标等.      

Achievements of Space Scientific Experiments Aboard SJ-8 Satellite

As scientific experiment payloads, microgravity experiments of fluid physics, life science,combustion science, physics and accelerator measurement were conducted on board the Chinese recoverable satellite SJ-8 during 18-day orbital flight. The experimental payloads and an experiment support system constituted the microgravity experiment system of the flight mission. This article has presented the briefs of the scientific achievements of these space experiments, the composition and performance of the Microgravity Experimental System (MES) and the general picture of the overall flight mission, respectively.      

A future Japanese program in far-ultraviolet astronomy and solar physics

A design study of an ultraviolet-telescope satellite (UVSAT) has been carried out by the Japanese astronomical community. The main purpose of this satellite mission would be to investigate (i) the distribution and nature of ultraviolet sources in star clusters, galaxies, and clusters of galaxies, (ii) the physical structures of galactic nebulae, and (iii) the dynamics of stellar and galactic activity. A 60 cm, f/4 Cassegrain telescope will be launched into a semi-circular orbit of ～500 km altitude and of ～30° inclination, by an ISAS/Japan M3S-III rocket. An intensified CCD camera and/or a concave-grating spectrograph will be operated for the wavelength range λ?1200 Å. Various possible auxiliary instruments and sub-telescopes are considered.     

中国月球与深空探测有效载荷技术的成就与展望

有效载荷是实现科学目标最直接的工具,其技术手段和水平影响科学目标的可实现程度。简要回顾了中国月球与深空探测的科学目标与有效载荷配置。介绍了"嫦娥1号"和"嫦娥2号"月球环绕探测器中采用的CCD立体相机、干涉式成像光谱仪、激光高度计、微波探测仪、伽马射线谱仪、X射线谱仪、太阳风粒子探测仪、高能粒子探测仪等遥感探测类有效载荷的技术实现、探测结果和取得的成就。同时,也介绍了"嫦娥3号"月球着陆器和巡视器中采用的地形地貌相机、月基光学望远镜、极紫外相机、红外成像光谱仪、粒子激发X射线谱仪、测月雷达等就位和巡视探测类有效载荷的技术实现、探测结果和取得的成就。分析了有效载荷技术的发展趋势,展望了我国未来有效载荷技术的发展。     

An introduction to the lunar and planetary science activities in Korea

Korea is planning a series of lunar space programs in 2020 starting with a lunar orbiter and a lander with a rover. Compared to other countries, Korea has a relatively brief history in space and planetary sciences. With the expected Korean missions on the near-term horizon and the relatively few Korean planetary scientists, Korea Institute of Geoscience and Mineral Resources (KIGAM) has established a new planetary research group focusing on development of prospective lunar instruments, analysis of the publicly available planetary data of the Moon, organizing nationwide planetary workshops, and initiating planetary educational programs with academic institutions. Korea has also initiated its own rocket development program, which could acquire a rocket-launch capability toward the Korean lunar mission. For the prospective Korea’s lunar science program, feasibility studies for some candidate science payloads have been started since 2010 for an orbiter and a lander. The concept design of each candidate instrument has been accomplished in 2012. It is expected that the development of science payloads may start by 2014 as Phase A. Not only developing hardware required for the lunar mission but also educational activities for young students are high priorities for Korea. The new plan of the Korean lunar mission can be successfully accomplished with international cooperative outreach programs in conjunction with internationally accessible planetary data system (PDS). This paper introduces the KIGAM’s international cooperative planetary research and educational programs and also summarizes other nationwide new developments for Korean lunar research projects at Kyung Hee University and Hanyang University.     

Vega project — Three channel spectrophotometer for the Halley''s comet investigation

A spectrometer for the Halley's Comet Investigation after the VEGA Project is described in the present work. It consists of a telescope and three spectral channels: UV (120 – 290 nm), resolution Δ λ / λ = 170; VIS (280 – 710 nm), resolution Δ λ / λ = 170; IR (950 – 1900 nm), resolution Δ λ / λ = 70.

With the help of two-coordinate scanner, the secondary mirror of the telescope allows spatial scanning of the Comet with a frame 2°×1,5° with 105 different pixels.     

Progress in China's Lunar Exploration Program

Chang'E-1 and Chang'E-2 of China's Lunar Exploration Program (CLEP) have successfully achieved their mission. At the present time, only Chang'E-3 is still in operation, which was successfully launched on December 2, 2013. Chang'E-3 probe is the third robotic lunar mission of CLEP, which consists of a lander and a rover, with eight payloads on board the spacecraft. Up to December 21, 2015, more than 2.86TB raw data were received from these instruments onboard Chang'E-3 probe. A series of research results have been achieved. This paper gives a detailed introduction to the new scientific results obtained from Chang'E-3 missions.      

“嫦娥4号”任务有效载荷系统设计与实现

"嫦娥4号"任务将首次实现人类在月球背面软着陆。通过分析任务特点,以多类型有效载荷配置为背景,介绍了以科学目标和探测任务为核心的有效载荷系统设计思路和实现方法。同时针对首次在深空探测领域搭载国际合作有效载荷项目情况进行了说明。"嫦娥4号"任务最重要的科学目标是利用月球背面洁净的电磁环境进行天文低频射电观测,因此分别在着陆器和中继星上新增配置了国内新研制的低频射电频谱仪及荷兰研制的低频探测仪。科学探测的太阳爆发产生的低频电场信号极其微弱,如何消除着陆器和中继星上其他电子设备发射的近场噪声对远场探测信号的干扰就成了本次任务的最大难点。在相关研制单位的多方努力下,通过优化接收天线设计和地面数据处理算法等多种手段,实现了低频探测信号不低于30 d B的噪声抑制性能,具备了实现科学目标的能力。     

First astrometric observations of space debris with the MéO telescope

The MéO (for Métrologie Optique) telescope is the Satellite and Lunar Laser Ranging (SLR) dedicated telescope of Observatoire de la Côte d’Azur (France) located at plateau de Calern. The telescope uses an altazimuth mount. The motorization of the mount has a capability of 6 deg/s allowing the follow up of Low Earth Orbits (LEO) satellites, as well as Medium Earth Orbits (MEO) and geostationary (GEO) satellites, and the Moon. The telescope has a primary mirror of 1.54 m. It uses a Nasmyth focus equipped with an EMCCD camera. The telescope field of view, defined by the equivalent focal length and the size of the camera, is currently 3.4 arcmin × 3.4 arcmin.     

大型天文望远镜研究

提出新建一台4.3m 光学红外新技术望远镜,并与北京天文台2.16m 望远镜用真空管道联机作CCD 照相和光干涉测量,提高集光能力达4.8m 口径,分辨率达10m 口径。     

Sensitivity analysis of test methods for aspheric off-axis mirrors

Following the Hubble Space Telescope (HST), the next generation James Webb Space Telescope (JWST) is being developed to be launched in a few years. JWST will be a segmented mirror telescope with a design much like that developed for ground-based telescopes over the past 20 years. Several segmented mirror telescopes are currently in operation, and next generation ground-based telescopes of the 30-m class are also being designed using segmented primary mirrors. Regardless of size, segmented primary mirror telescopes often require the use of aspheric segment mirrors. One of the key factors in fabrication of aspheric segment mirrors is feasibility of testing off-axis surfaces with high accuracy. A couple of test methods have been investigated for aspheric off-axis segments. As a case study, we apply these test methods to secondary segmented mirror models of the Giant Magellan Telescope. We derive required dimensions of test set-ups and assess sensitivity of optical alignment. Characteristics of the test methods are also discussed.