A few metrological aspects of the Gaia mission

The ESA space astrometry mission Gaia is designed to measure the positions, parallaxes and proper motions of more than one billion stars of our Galaxy brighter than 20 magnitude. The expected astrometric accuracies are in the range 7–25 μas for the point-like sources down to 15 mag. To achieve this staggering performance, several issues of highly accurate metrology must be solved and implemented on the spacecraft. In this paper, I discuss first some constraining principles to perform global astrometry in space, and then a couple of examples of the metrological issues currently faced by the design or to be encountered during the operations. One concerns the optimisation of the sky coverage with a scanning instrument like Gaia, and the other deals with the instrument stability and how the stringent requirements are met in practice.     

The search for extra-solar planetary systems.

I review the observational evidence for planetary systems around nearby stars and, using our own solar system as a guide, assess the stringent requirements that new searches need to meet in order to unambiguously establish the presence of another planetary system. Basically, these requirements are: 1 milliarcsecond or better positional accuracy for astrometric techniques, 9 orders of magnitude or better star to planet luminosity ratio discrimination at 0.5 to 1" separation in the optical for direct imaging techniques, 10 meters sec-1 or better radial velocity accuracy for reflex motion techniques and +/-1% or better brightness fluctuation accuracy for planet/star occultation measurements. The astrometric accuracy is in reach of HST, direct imaging will require much larger telescopes and/or a 50 times smoother mirror than HST while the reflex motion and occultation techniques best performed on the ground are just becoming viable and promise exciting new discoveries. On the other band, new indirect evidence on the existence of other planetary systems also comes from the observation of large dusty disks around nearby main sequence stars not too dissimilar from our sun. In one particular case, that of Beta Pictoris, a flattened disk seen nearly edge-on has been imaged in the optical and near IR down to almost 70 AU of the star. It probably represents a young planetary system in its clearing out phase as planetesimals collide, erode and are swept out of the inner system by radiation pressure. The hypothesized Kuiper belt around our solar system may be the analogous structure in a later evolutionary stage. Features of this type have been detected in the far IR and sub-millimeter wavelength regions around 50-100 nearby main sequence and pre-main sequence stars. I discuss a battery of new accurate observations planned in the near future of these objects some of which may actually harbour planets or planetesimals that will certainly dramatically improve our knowledge of planetary system formation processes and our peculiar position in this scheme.     

A concept mission for the Stellar Population and Evolution with Cubesats (SPEC)

Binary or multiple stellar systems, constituting almost a third of the content of the Milky Way, represent a high priority astronomical target due to their repercussions on the stellar dynamical and evolutionary parameters. Moreover the spectral study of such class of stars allows to better constrain the evolutionary theories of the Galactic stellar populations. By resolving the members of stellar systems through photometric observations we are able to perform more detailed measurements to infer their mass. In this paper we investigate the feasibility of a cubesat based mission including an optical payload to directly optically discriminate the members of a selected sample of binary systems. The scientific targets, consisting 11?M class dwarf stars binary systems, have been extracted from the already studied Riaz catalogue. These subset has been selected considering the star distance, the members angular separation, and the distance from the Galactic plane (due to limit the background and foreground contamination). The satellite concept is based on a 6 unit Cubesat embedding some commercial off the shelf components and an ad hoc designed optical payload occupying almost 4 units. The optical configuration has been chosen in order to fit the angular resolution requirements, as derived from the target characteristics. Moreover, according to the optical analysis and the computed field of view some requirements on the attitude control system have been inferred and fulfilled by the component selection. The paper is organized as in the following: a brief scientific introduction is made; consequently the project is described with particular attention to the optical design and the standard sub-systems; finally the conclusions are drawn and the future perspectives are investigated.     

EUVITA — An extreme UV imaging telescope array with spectral capability

EUVITA is a set of 8 extreme UV normal incidence imaging telescopes, each of them sensitive in a narrow band (λ/Δλ = 15 to 80), centered at wavelengths between 50 and 175 Å. Each telescope has an effective area of a few cm²; a field of view of 1.2° and a spatial resolution of 10 arcsec.

EUVITA will be flown on the Russian mission SPECTRUM X-G. This satellite will be launched in a highly eccentric orbit with a period of 4 days, allowing long, uninterrupted observations (e.g. 10⁵ seconds). EUVITA's narrow spectral bands allow the measurement of source parameters such as temperature or power law index as well as interstellar absorption, and will resolve groups of strong lines emitted by optically thin hot plasmas.     

The HRS GTO program to study the neutral hydrogen column density and D/H ratio in the local interstellar medium

Early in the HST mission the HRS Team will observe the Lyman alpha line at 100,000 spectral resolution toward 7 late-type local stars. The purpose is to derive the hydrogen and deuterium column densities and D/H ratios along lines of sight toward nearby stars. Here we present theoretical line profiles that demonstrate why 10⁵ spectral resolution and high signal-to-noise are needed to derive accurate column densities from spectral lines that lie close to the flat part of the curve of growth and may contain multiple velocity components. The aim of the HRS program is to obtain column densities in the hydrogen and deuterium Lyman alpha lines along a variety of lines of sight within and extending beyond the local cloudlet in which the Sun is located near an edge. The broad chromospheric Lyman alpha emission lines of late-type stars are used as background sources against which to measure the interstellar absorption features. We will also obtain profiles of interstellar absorption features in Mg II and Fe II lines to derive the broadening parameter and/or identify possible multiple velocity components in the lines of sight.     

KuaFu Mission

The KuaFu mission-Space Storms, Aurora and Space Weather Explorer-is an "L1+Polar" triple satellite project composed of three spacecraft: KuaFu-A will be located at L1 and have instruments to observe solar EUV and FUV emissions, and white-light Coronal Mass Ejections (CMEs), and to measure radio waves, the local plasma and magnetic field,and high-energy particles. KuaFuB1 and KuaFu- B2 will bein polar orbits chosen to facilitate continuous 24 hours a day observation of the north polar Aurora Oval. The KuaFu mission is designed to observe the complete chain of disturbances from the solar atmosphere to geospace, including solar flares, CMEs, interplanetary clouds, shock waves, and their geo-effects, such as magnetospheric sub-storms and magnetic storms, and auroral activities. The mission may start at the next solar maximum (launch in about 2012), and with an initial mission lifetime of two to three years. KuaFu data will be used for the scientific study of space weather phenomena, and will be used for space weather monitoring and forecast purposes. The overall mission design, instrument complement, and incorporation of recent technologies will target new fundamental science, advance our understanding of the physical processes underlying space weather, and raise the standard of end-to-end monitoring of the Sun-Earth system.     

Gamma astrometric measurement experiment (GAME) – Science case

We report here on the science case of a concept for a satellite orbiting at 1 AU from the Sun and using a baffled Fizeau interferometer to look as close as possible to its limb. This configuration, and the need for looking nearby the Sun, is required for the main scientific driver of the mission, namely the measure of the γ parameter of the Parameterized Post-Newtonian formulation to the 10⁻⁶–10⁻⁷ level at least. This would lead to an accurate test of the General Theory of Relativity against other alternative theories of gravity, and set stringent constraints on some of the most significant issues of Astrophysics like those involving exotic forms of dark matter and dark energy. Exploiting the possibilities offered by the observation strategy, it is also possible to target other interesting scientific goals. One is, again, in the realm of General Relativity and aims at measuring the light deflection nearby the Giant Planets to detect asymmetric effects induced by their quadrupoles, predicted by GR but never measured so far. Others can be found in the observation of selected extrasolar systems where, e.g., the astrometric and photometric capabilities of GAME will help to improve on the knowledge of the brown-dwarf regime and on the search for exo-planets with the transit method, respectively.     

An automatic navigation and aspect sensing system for X-ray astronomy

An automatic navigation and aspect sensing system is being developed for use in trans-Australia and possible globe circling balloon flights by the University of Tasmania stabilised platform for X-ray astronomy. This system comprises an Omega receiver, three axis magnetometer, alt-az. mounted CID camera and an on-board computer. The computer uses the Omega receiver output or other dead reckoning information together with the magnetometer data to calculate the approximate position of selected bright stars. It then drives the camera to each of these positions in turn and determines from the camera output the precise coordinates relative to the platform of each of these stars. From this information it will fix the geographic coordinates of the platform to within a few nautical miles and will determine the true platform azimuth with a precision of approximately 0.1°. These data will be passed to the platform aspect control computer via a serial link.     

HiPeG: A high performance balloon gondola for fine angular resolution X-ray telescopes

A platform for balloon-borne hard X-ray experiments capable of tens of arcsec pointing accuracy is a necessary condition for the new generation of high angular resolution X-ray telescopes. We have designed a new multi-mission platform in which the attitude determination system is based upon a high performance GPS and a star sensor equipped with a high-dynamic range CCD detector. The device is an autonomous and flexible system which, by means of efficient star identification and tracking algorithms, permits a fine dynamical pointing and reconstruction of the pointing trajectory down to the arcsec level. This paper presents specifications of the gondola and summarizes its characteristics which will be tested in a balloon flight scheduled in near future.     

Mars Sample Return: Do Australians trust NASA?

Mars Sample Return (MSR) represents an important scientific goal in space exploration. Any sample return mission will be extremely challenging from a scientific, economic and technical standpoint. But equally testing, will be communicating with a public that may have a very different perception of the mission. A MSR mission will generate international publicity and it is vital that NASA acknowledge the nature and extent of public concern about the mission risks and, perhaps equally importantly, the public’s confidence in NASA’s ability to prepare for and manage these risks. This study investigated the level of trust in NASA in an Australian population sample, and whether this trust was dependent on demographic variables. Participants completed an online survey that explored their attitudes towards NASA and a MSR mission. The results suggested that people believe NASA will complete the mission successfully but have doubts as to whether NASA will be honest when communicating with the public. The most significant finding to emerge from this study was that confidence in NASA was significantly (p < 0.05) related to the respondent’s level of knowledge regarding the risks and benefits of MSR. These results have important implications for risk management and communication.     

Distinguishing features of CCD astrometry of faint GEO objects

The problem of initial reduction of CCD observations of faint GEO objects is studied. Several difficulties and questions arising in connection with image processing for this kind of observations are mentioned. A natural way to apply the PSF fitting technique to line-shaped trails of stars or GEO objects is described and illustrated by its implementation in the Apex II astronomical image processing package. Logical filtering technique to improve the automatic object detection is proposed. These rather convenient and versatile methods can increase astrometric and, to a lesser degree, photometric accuracy of faint GEO object observations.     

Gamma Astrometric Measurement Experiment (GAME) – Implementation and performance

The GAME mission concept is aimed at testing the General Relativity, through precise measurement of the gravitational deflection of light by the Sun, by means of an optimised telescope operating in the visible and launched in orbit on a small class satellite. We describe the proposed mission profile, the preliminary payload design and the expected performance. The targeted precision on the γ parameter of the PPN formulation of General Relativity is in the range 10⁻⁶ to 10⁻⁷. The measurement principle relies on the differential astrometric signature on the stellar positions. The instrument concept is based on a dual field, multiple aperture Fizeau interferometer, observing simultaneously two sky regions close to the solar limb. A beam combiner folds the telescope line of sight on two different directions on the sky, separated by a base angle of 4°. The diluted optics approach achieves an efficient rejection of the scattered solar radiation, while retaining an acceptable angular resolution on the science targets.     

Article

Planning for extraterrestrial sample returns--whether from Mars or other solar system bodies--must be done in a way that integrates planetary protection concerns with the usual mission technical and scientific considerations. Understanding and addressing legitimate societal concerns about the possible risks of sample return will be a critical part of the public decision making process ahead. This paper presents the results of two studies, one with lay audiences, the other with expert microbiologists designed to gather information on attitudes and concerns about sample return risks and planetary protection. Focus group interviews with lay subjects, using generic information about Mars sample return and a preliminary environmental impact assessment, were designed to obtain an indication of how the factual content is perceived and understood by the public. A research survey of microbiologists gathered information on experts' views and attitudes about sample return, risk management approaches and space exploration risks. These findings, combined with earlier research results on risk perception, will be useful in identifying levels of concern and potential conflicts in understanding between experts and the public about sample return risks. The information will be helpful in guiding development of the environmental impact statement and also has applicability to proposals for sample return from other solar system bodies where scientific uncertainty about extraterrestrial life may persist at the time of mission planning.     

Generic procedure for designing and implementing plan management systems for space science missions operations

This paper is one of the components of a larger framework of activities whose purpose is to improve the performance and productivity of space mission systems, i.e. to increase both what can be achieved and the cost effectiveness of this achievement. Some of these activities introduced the concept of Functional Architecture Module (FAM); FAMs are basic blocks used to build the functional architecture of Plan Management Systems (PMS). They also highlighted the need to involve Science Operations Planning Expertise (SOPE) during the Mission Design Phase (MDP) in order to design and implement efficiently operation planning systems. We define SOPE as the expertise held by people who have both theoretical and practical experience in operations planning, in general, and in space science operations planning in particular. Using ESA’s methodology for studying and selecting science missions we also define the MDP as the combination of the Mission Assessment and Mission Definition Phases. However, there is no generic procedure on how to use FAMs efficiently and systematically, for each new mission, in order to analyse the cost and feasibility of new missions as well as to optimise the functional design of new PMS; the purpose of such a procedure is to build more rapidly and cheaply such PMS as well as to make the latter more reliable and cheaper to run. This is why the purpose of this paper is to provide an embryo of such a generic procedure and to show that the latter needs to be applied by people with SOPE during the MDP. The procedure described here proposes some initial guidelines to identify both the various possible high level functional scenarii, for a given set of possible requirements, and the information that needs to be associated with each scenario. It also introduces the concept of catalogue of generic functional scenarii of PMS for space science missions. The information associated with each catalogued scenarii will have been identified by the above procedure and will be relevant only for some specific mission requirements. In other words, each mission that shares the same type of requirements that lead to a list of specific catalogued scenarii can use this latter list of scenarii (regardless of whether the mission is a plasma, planetary, astronomy, etc. mission). The main advantages of such a catalogue are that it speeds-up the execution of the procedure and makes the latter more reliable. Ultimately, the information associated to each relevant scenario (from the catalogue or freshly generated by the procedure) will then be used by mission designers to make informed decisions, including the modification of the mission requirements, for any missions. In addition, to illustrate the use of such a procedure, the latter is applied to a case study, i.e. the Cross-Scale mission. One of the outcomes of this study is an initial set of generic functional scenarii. Finally, although border line with the above purpose of this paper, we also discuss multi-spacecraft specific issues and issues related to the on-board execution of the plan update system (PUS). In particular, we show that the operation planning cost of N spacecraft is not equal to N times the cost of 1 spacecraft and that on-board non-synchronised operation will not require inter-spacecraft communication. We also believe that on-board PUS should be made possible for all missions as a standard.     

Imaging a black hole: MAXIM

With the general acceptance of black holes as real entities the astrophysics community has turned its attention to studying their behavior and properties. Because of the great distance and compact size of the central engine, astronomers are limited to spectroscopic analysis. But to take a picture, or better yet a movie, of the black hole in silhouette against its accretion disk would be a triumph of exploration and scientific inquiry. Probing to the event horizon is best accomplished in the X-ray band, where material primarily radiates in the last orbits before its final plunge. Not only will the signal be bright and minimally confused in the X-ray, but the size of the required interferometer drops dramatically. We describe MAXIM, the Micro-Arcsecond X-ray Imaging Mission, which is now being studied and developed by NASA. We will explain the preliminary mission concept which will use currently existing technology to achieve spatial resolution one million times higher than that of the Hubble Space Telescope and capture the image of an event horizon in a nearby Active Galactic Nucleus. We will also describe the MAXIM Pathfinder. Designed as a stepping stone at resolution of 100 micro-arcseconds, it will demonstrate the techniques of X-ray interferometry and perform groundbreaking science like resolving the coronae of the nearby stars.     

Photospheric composition and structure in white dwarfs

One of the central mysteries of white dwarf studies has been the nature and abundance of trace elements in the atmospheres of these stars. It had been thought that the dominant trace element in otherwise pure hydrogen DA white dwarf atmospheres was helium. However, some spectroscopic and theoretical evidence suggested that, at least in some stars, heavier elements may be important. Prior to the launch of ROSAT the questions regarding the atmospheric composition of DA white dwarfs in general remained unresolved. The ROSAT mission has provided EUV and X-ray data for a large sample of DA white dwarfs with which we can study their photospheric composition and structure through the effect of trace opacity sources on the emergent fluxes. Contrary to expectations little (if any) helium is found and the main sources of opacity appear to be trace heavy elements. Support for these conclusions is found in recent EUV and far-UV spectra of several stars. However, photometric data do not allow us to determine the abundance of the individual elements and observations with the EUVE spectrometers will be essential for detailed composition measurements.     

Chang'E-1 Lunar Mission:An Overview and Primary Science Results

Chang'E-1 is the first lunar mission in China, which was successfully launched on Oct. 24th, 2007. It was guided to crash on the Moon on March 1, 2009, at 52.36oE, 1.50oS, in the north of Mare Fecunditatis. The total mission lasted 495 days, exceeding the designed life-span about four months. 1.37 Terabytes raw data was received from Chang'E-1. It was then processed into 4 Terabytes science data at different levels. A series of science results have been achieved by analyzing and applicating these data, especially "global image of the Moon of China's first lunar exploration mission'. Four scientific goals of Chang'E-1 have been achieved. It provides abundant materials for the research of lunar sciences and cosmochemistry. Meanwhile these results will serve for China's future lunar missions.      

Development of the Infrared Telescope in Space: IRTS

Infrared Telescope in Space (IRTS) is a cryogenically cooled small infrared telescope aboard the small space platform, SFU (Space Flyer Unit). IRTS has a telescope of 15 cm diameter, which is rather small compared with other big space missions. IRTS, however, is optimized to observe extended diffuse sources with four focal plane instruments which have wide wavelength coverage from the near infrared to the submillimeter region.

All instruments have been calibrated with a test cryostat, and integrated into the flight cryostat. Cooling tests of the whole IRTS system have confirmed that instruments and cryostat will perform as expected. Integration of the IRTS on the SFU will soon begin and the ground tests of the SFU system will be conducted in the coming year.

The launch of the SFU will be in early 1995. The IRTS will survey the 10% of the sky during the three week mission and provide significant scientific results on cosmology, galactic structure, interstellar matter, stars, and solar system.     

高精度高动态星模拟器研究

给出了高精度高动态星模拟器系统组成和总体结构, 提出一种基于亚像素显示技术提高动态星模拟器星点位置显示精度从而减小星点几何中心与能量中心位置偏差的新方法. 针对动态星模拟器高动态性要求, 提出一种快速精确检索全天球导航星的新方法, 将已知SAO (Smithsonian Astrophysical Observatory) 星表进行分区, 计算当前姿态四元数并分析航天器视轴所在区域, 对于距离视轴较远区域停止搜索和匹配, 很大程度上缩小了导航星搜索范围, 进而缩短了全天球恒星遍历所需时间. 软件测试结果表明, 此快速检索法可使全天球导航星的选取速度提高近10倍.