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1.
Tiziano Zingales Giovanna Tinetti Ignazio Pillitteri Jérémy Leconte Giuseppina Micela Subhajit Sarkar 《Experimental Astronomy》2018,46(1):67-100
The ARIEL (Atmospheric Remote-sensing Exoplanet Large-survey) mission concept is one of the three M4 mission candidates selected by the European Space Agency (ESA) for a Phase A study, competing for a launch in 2026. ARIEL has been designed to study the physical and chemical properties of a large and diverse sample of exoplanets and, through those, understand how planets form and evolve in our galaxy. Here we describe the assumptions made to estimate an optimal sample of exoplanets – including already known exoplanets and expected ones yet to be discovered – observable by ARIEL and define a realistic mission scenario. To achieve the mission objectives, the sample should include gaseous and rocky planets with a range of temperatures around stars of different spectral type and metallicity. The current ARIEL design enables the observation of ～1000 planets, covering a broad range of planetary and stellar parameters, during its four year mission lifetime. This nominal list of planets is expected to evolve over the years depending on the new exoplanet discoveries. 相似文献
2.
TandEM: Titan and Enceladus mission 总被引：1，自引：0，他引：1
《Experimental Astronomy》2009,23(3):893-946
TandEM was proposed as an L-class (large) mission in response to ESA’s Cosmic Vision 2015–2025 Call, and accepted for further
studies, with the goal of exploring Titan and Enceladus. The mission concept is to perform in situ investigations of two worlds
tied together by location and properties, whose remarkable natures have been partly revealed by the ongoing Cassini–Huygens
mission. These bodies still hold mysteries requiring a complete exploration using a variety of vehicles and instruments. TandEM
is an ambitious mission because its targets are two of the most exciting and challenging bodies in the Solar System. It is
designed to build on but exceed the scientific and technological accomplishments of the Cassini–Huygens mission, exploring
Titan and Enceladus in ways that are not currently possible (full close-up and in situ coverage over long periods of time).
In the current mission architecture, TandEM proposes to deliver two medium-sized spacecraft to the Saturnian system. One spacecraft
would be an orbiter with a large host of instruments which would perform several Enceladus flybys and deliver penetrators
to its surface before going into a dedicated orbit around Titan alone, while the other spacecraft would carry the Titan in
situ investigation components, i.e. a hot-air balloon (Montgolfière) and possibly several landing probes to be delivered through
the atmosphere. 相似文献
3.
George A. Tsirogiannis 《Celestial Mechanics and Dynamical Astronomy》2012,114(4):353-363
A space mission design methodology is presented, where initial and final orbits are connected through segments of periodic orbits. After a discretization of the solution space, the problem of mission design is transformed into an equivalent combinatorial optimization problem. Specifically, a graph is constructed that represents periodic orbits connected by the execution of impulsive maneuvers. A low computational complexity algorithm for this transformation is introduced. An efficient combinatorial optimization algorithm that solves the shortest path problem is described. Subject to the initial discretization of the solution space, an optimal sequence of coastal arcs is determined for a low total Delta-V mission. Finally, the proposed methodology is applied to the design of a hypothetical Saturn?CTitan system mission. 相似文献
4.
A mission out of the planetary system, launched about the year 2000, could provide valuable data concerning characteristics of the heliopause, the interstellar medium, stellar distances (by parallax measurements), low-energy cosmic rays, interplanetary gas distribution, and mass of the solar system. Secondary objectives include investigation of Pluto. Candidate science measurements, instruments, and instrument development needs are discussed. The mission should extend from 400 to 1000 AU from the Sun. A heliocentric hyperbolic escape velocity of 50–100 km/sec or more is needed to attain this distance within a reasonable mission duration (20–50 years). The trajectory should be toward the incoming interstellar gas. For a year 2000 launch, a Pluto encounter and orbiter can be included. A second mission targeted parallel to the solar axis would also be worthwhile. 相似文献
5.
MarcoPolo-R near earth asteroid sample return mission 总被引：3，自引：0，他引：3
Maria Antonietta Barucci A. F. Cheng P. Michel L. A. M. Benner R. P. Binzel P. A. Bland H. B?hnhardt J. R. Brucato A. Campo Bagatin P. Cerroni E. Dotto A. Fitzsimmons I. A. Franchi S. F. Green L.-M. Lara J. Licandro B. Marty K. Muinonen A. Nathues J. Oberst A. S. Rivkin F. Robert R. Saladino J. M. Trigo-Rodriguez S. Ulamec M. Zolensky 《Experimental Astronomy》2012,33(2-3):645-684
MarcoPolo-R is a sample return mission to a primitive Near-Earth Asteroid (NEA) proposed in collaboration with NASA. It will rendezvous with a primitive NEA, scientifically characterize it at multiple scales, and return a unique sample to Earth unaltered by the atmospheric entry process or terrestrial weathering. MarcoPolo-R will return bulk samples (up to 2?kg) from an organic-rich binary asteroid to Earth for laboratory analyses, allowing us to: explore the origin of planetary materials and initial stages of habitable planet formation; identify and characterize the organics and volatiles in a primitive asteroid; understand the unique geomorphology, dynamics and evolution of a binary NEA. This project is based on the previous Marco Polo mission study, which was selected for the Assessment Phase of the first round of Cosmic Vision. Its scientific rationale was highly ranked by ESA committees and it was not selected only because the estimated cost was higher than the allotted amount for an M class mission. The cost of MarcoPolo-R will be reduced to within the ESA medium mission budget by collaboration with APL (John Hopkins University) and JPL in the NASA program for coordination with ESA’s Cosmic Vision Call. The baseline target is a binary asteroid (175706) 1996 FG3, which offers a very efficient operational and technical mission profile. A binary target also provides enhanced science return. The choice of this target will allow new investigations to be performed more easily than at a single object, and also enables investigations of the fascinating geology and geophysics of asteroids that are impossible at a single object. Several launch windows have been identified in the time-span 2020–2024. A number of other possible primitive single targets of high scientific interest have been identified covering a wide range of possible launch dates. The baseline mission scenario of MarcoPolo-R to 1996 FG3 is as follows: a single primary spacecraft provided by ESA, carrying the Earth Re-entry Capsule, sample acquisition and transfer system provided by NASA, will be launched by a Soyuz-Fregat rocket from Kourou into GTO and using two space segment stages. Two similar missions with two launch windows, in 2021 and 2022 and for both sample return in 2029 (with mission duration of 7 and 8?years), have been defined. Earlier or later launches, in 2020 or 2024, also offer good opportunities. All manoeuvres are carried out by a chemical propulsion system. MarcoPolo-R takes advantage of three industrial studies completed as part of the previous Marco Polo mission (see ESA/SRE (2009)3, Marco Polo Yellow Book) and of the expertise of the consortium led by Dr. A.F. Cheng (PI of the NASA NEAR Shoemaker mission) of the JHU-APL, including JPL, NASA ARC, NASA LaRC, and MIT. 相似文献
6.
M. V. Podzolko I. V. Getselev Yu. I. Gubar’ I. S. Veselovsky 《Solar System Research》2009,43(2):116-120
Radiation conditions in Jupiter’s environment and the plasma environment in interplanetary space during a Jupiter-Europa mission are estimated. The numerical modeling results can be used when planning the mission. 相似文献
7.
B. Christophe P. H. Andersen J. D. Anderson S. Asmar Ph. Bério O. Bertolami R. Bingham F. Bondu Ph. Bouyer S. Bremer J.-M. Courty H. Dittus B. Foulon P. Gil U. Johann J. F. Jordan B. Kent C. Lämmerzahl A. Lévy G. Métris O. Olsen J. Pàramos J. D. Prestage S. V. Progrebenko E. Rasel A. Rathke S. Reynaud B. Rievers E. Samain T. J. Sumner S. Theil P. Touboul S. Turyshev P. Vrancken P. Wolf N. Yu 《Experimental Astronomy》2009,23(2):529-547
The Solar System Odyssey mission uses modern-day high-precision experimental techniques to test the laws of fundamental physics
which determine dynamics in the solar system. It could lead to major discoveries by using demonstrated technologies and could
be flown within the Cosmic Vision time frame. The mission proposes to perform a set of precision gravitation experiments from
the vicinity of Earth to the outer Solar System. Its scientific objectives can be summarized as follows: (1) test of the gravity
force law in the Solar System up to and beyond the orbit of Saturn; (2) precise investigation of navigation anomalies at the
fly-bys; (3) measurement of Eddington’s parameter at occultations; (4) mapping of gravity field in the outer solar system
and study of the Kuiper belt. To this aim, the Odyssey mission is built up on a main spacecraft, designed to fly up to 13
AU, with the following components: (a) a high-precision accelerometer, with bias-rejection system, measuring the deviation
of the trajectory from the geodesics, that is also giving gravitational forces; (b) Ka-band transponders, as for Cassini,
for a precise range and Doppler measurement up to 13 AU, with additional VLBI equipment; (c) optional laser equipment, which
would allow one to improve the range and Doppler measurement, resulting in particular in an improved measurement (with respect
to Cassini) of the Eddington’s parameter. In this baseline concept, the main spacecraft is designed to operate beyond the
Saturn orbit, up to 13 AU. It experiences multiple planetary fly-bys at Earth, Mars or Venus, and Jupiter. The cruise and
fly-by phases allow the mission to achieve its baseline scientific objectives [(1) to (3) in the above list]. In addition
to this baseline concept, the Odyssey mission proposes the release of the Enigma radio-beacon at Saturn, allowing one to extend
the deep space gravity test up to at least 50 AU, while achieving the scientific objective of a mapping of gravity field in
the outer Solar System [(4) in the above list].
相似文献
8.
The paper presents the results of the definition studies performed for the European Space Agency (ESA) on system architectures and enabling technologies for “BepiColombo”, a Cornerstone class mission to be launched in the 2007–2009 time frame. The scientific mission comprises 1-year observations by a Mercury Planetary Orbiter (MPO), dedicated to remote sensing, and a Mercury Magnetospheric Orbiter (MMO), dedicated to particles and fields, plus short-duration in situ analysis by a Mercury surface element (MSE). A flexible approach to the programme has been developed, comprising two alternative launch scenarios. In the first option (2009), the 2500-kg class satellite composite, including two propulsion modules and three scientific modules, is launched by an Ariane-5. The trajectory design is based on Venus and Mercury gravity assists plus the thrust provided by a Solar Electric Propulsion Module (SEPM), that is jettisoned before being captured into Mercury orbit. Capture and orbit insertion, executed by successive manoeuvres of a Chemical Propulsion Module (CPM), occur less than 2.5 yr after launch. In the second scenario, the mission is split into two launches of a small launch vehicle. Two 1200-kg class composites are launched either in the same one-month window or at an interval of 1.6 yr. One composite comprises the SEPM, CPM, MMO and MSE and the other comprises duplicate SEPM+CPM and the MPO. The trajectory design follows the same principles as the Ariane-5 mission, with the SEPM thrust reduced by half and cruise duration ranging between 2.3 and 3.5 yr. Whatever be the implementation, the mission is expected to return about 1700 Gbit of scientific data during the one-year observation phase. The crucial aspects of the spacecraft design are associated with, and constrained by, the high-temperature and high-radiation environment. Basic feasibility has been demonstrated by an extensive design and analysis exercise, and the focus of the programme has now moved to a 3-year preparatory programme dedicated for developing the enabling technologies. 相似文献
9.
Mariner 9 was inserted into orbit about Mars on November 14, 1971, to study that planet for a period of 90 days. Observations and measurements made by Mariner 9 continued beyond the planned 90 days, providing data to meet all science objectives. The new knowledge of Mars gained from this mission has made obsolete all previous concepts of Mars.A general background of the Mariner Mars 1971 Project and the significant events of the Mariner 9 mission are presented. 相似文献
10.
Bruce A. Conway Christian M. Chilan Bradley J. Wall 《Celestial Mechanics and Dynamical Astronomy》2007,97(2):73-86
The space mission planning process is considered as a hybrid optimal control problem. Hybrid optimal control problems are
problems that include categorical variables in the problem formulation. For example, an interplanetary trajectory may consist
of a sequence of low thrust arcs, impulses and planetary flybys. However, for each choice of the structure of the mission,
for example, for a particular choice of the number of planetary flybys to be used, there is a corresponding optimal trajectory.
It is not a priori clear which structure will yield the most efficient mission. In this work we present a mathematical framework
for describing such problems and solution methods for the hybrid optimal control problem based on evolutionary principles
that have the potential for being a robust solver of such problems. As an example, the methods are used to find the optimal
choice of three asteroids to visit in sequence, out of a set of eight candidate asteroids, in order to minimize the fuel required. 相似文献
11.
《Planetary and Space Science》2007,55(12):1831-1842
The Venus Climate Orbiter mission (PLANET-C), one of the future planetary missions of Japan, aims at understanding the atmospheric circulation of Venus. Meteorological information will be obtained by globally mapping clouds and minor constituents successively with four cameras at ultraviolet and infrared wavelengths, detecting lightning with a high-speed imager, and observing the vertical structure of the atmosphere with radio science technique. The equatorial elongated orbit with westward revolution fits the observation of the movement and temporal variation of the atmosphere which as a whole rotates westward. The systematic, continuous imaging observations will provide us with an unprecedented large data set of the Venusian atmospheric dynamics. Additional targets of the mission are the exploration of the ground surface and the observation of zodiacal light. The mission will complement the ESA's Venus Express, which also explores the Venusian environment with different approaches. 相似文献
12.
H.R. Williams J.C. Bridges R.M. Ambrosi M.-C. Perkinson J. Reed L. Peacocke N.P. Bannister S.D. Howe R.C. O'Brien A.C. Klein 《Planetary and Space Science》2011,59(13):1621-1631
There is enormous potential for more mobile planetary surface science. This is especially true in the case of Mars because the ability to cross challenge terrain, access areas of higher elevation, visit diverse geological features and perform long traverses of up to 200 km supports the search for past water and life. Vehicles capable of a ballistic ‘hop’ have been proposed on several occasions, but those proposals using in-situ acquired propellants are the most promising for significant planetary exploration. This paper considers a mission concept termed Mars Reconnaissance Lander using such a vehicle. We describe an approach where planetary science requirements that cannot be met by a conventional rover are used to derive vehicle and mission requirements.The performance of the hopper vehicle was assessed by adding estimates of gravity losses and mission mass constraints to recently developed methods. A baseline vehicle with a scientific payload of 16.5 kg and conservatively estimated sub-system masses is predicted to achieve a flight range of 0.97 km. Using a simple consideration of system reliability, the required cumulative range of 200 km could be achieved with a probability of around 80%. Such a range is sufficient to explore geologically diverse terrains. We therefore plot an illustrative traverse in Hypanis Valles/Xanthe Terra, which encounters crater wall sections, periglacial terrain, aqueous sedimentary deposits and a traverse up an ancient fluvial channel. Such a diversity of sites could not be considered with a conventional rover. The Mars Reconnaissance Lander mission and vehicle presents some very significant engineering challenges, but would represent a valuable complement to rovers, static landers and orbital observations. 相似文献
13.
Jacques Delabrouille 《Astrophysics and Space Science》2004,290(1-2):87-103
In this paper, we discuss why and how the Planck mission, originally designed and proposed for mapping intensity fluctuations, has been revised for polarisation measurement capability as well. 相似文献
14.
Riccardo Claudi 《Astrophysics and Space Science》2010,328(1-2):319-323
The satellite PLATO represents a new challenge for future investigations of exoplanets and oscillations of stars. It is one of the proposed missions of ESA COSMIC VISION 2015–2025 and it is scheduled for launch in 2017. The goal of the mission is a full characterization of the planet star systems with an asteroseismic analysis of the host stars. The PLATO Payload Consortium (PPLC) includes several European countries which are employed in the assessment study of the mission. Thanks to the high precision photometry, PLATO is thought to be able to detect planets and oscillations within a large sample of targets. 相似文献
15.
Y. Ogawara T. Takano T. Kato T. Kosugi S. Tsuneta T. Watanabe I. Kondo Y. Uchida 《Solar physics》1991,136(1):1-16
The SOLAR-A spacecraft is to be launched by the Institute of Space and Astronautical Science, Japan (ISAS) in August, 1991. As a successor of HINOTORI, this mission is dedicated principally to the study of solar flares, especially of high-energy phenomena observed in the X- and gamma-ray ranges. The SOLAR-A will be the unique space solar observatory during the current activity maximum period (1989–1992). With a coordinated set of instruments including hard X-ray and soft X-ray imaging telescopes as well as spectrometers with advanced capabilities, it will reveal many new aspects of flares and help better understand their physics, supporting international collaborations with ground-based observatories as well as theoretical investigations. An overview of this mission, including the satellite, its scientific instruments, and its operation, is given in this paper. Also the scientific objectives are briefly discussed.After the launch the name of SOLAR-A has been changed to YOHKOH. 相似文献
16.
Christoph Winkler 《Experimental Astronomy》1995,6(4):71-76
INTEGRAL, the International Gamma-Ray Astrophysics Laboratory, to be launched in 2001, is the second medium-size scientific mission (M2) of the ESA long term programme Horizon 2000. INTEGRAL addresses the fine spectroscopy and accurate positioning of celestial gamma-ray sources in the energy range 10 keV to 10 MeV. The observational requirements will be met by a payload utilising coded mask imaging in combination with detector pixel arrays (Imaging) and cooled Germanium detectors (Spectroscopy). INTEGRAL is an ESA led mission in collaboration with Russia and USA. Most of the observing time will be made available to the general scientific community.This paper is largely based on the INTEGRAL Phase A study report (ESA SCI(93)1), written by the INTEGRAL Phase A Science Working Team: S. Bergeson-Willis, T.J.-L. Courvoisier, A.J. Dean, Ph. Durouchoux, B. McBreen, N. Eismont, N. Gehrels, J.E. Grindlay, W.A. Mahoney, J.L. Matteson, O. Pace, T.A. Prince, V. Schönfelder, G.K. Skinner, R. Sunyaev, B.N. Swanenburg, B.J. Teegarden, P. Ubertini, G. Vedrenne, G.E. Villa, S. Volonté, and C. Winkler. 相似文献
17.
《Planetary and Space Science》2001,49(14-15)
The MErcury, Surface, Space ENvironment, GEochemistry, and Ranging (MESSENGER) mission will send the first spacecraft to orbit the planet Mercury. A miniaturized set of seven instruments, along with the spacecraft telecommunications system, provide the means of achieving the scientific objectives that motivate the mission. The payload includes a combined wide- and narrow-angle imaging system; γ-ray, neutron, and X-ray spectrometers for remote geochemical sensing; a vector magnetometer; a laser altimeter; a combined ultraviolet-visible and visible-infrared spectrometer to detect atmospheric species and map mineralogical absorption features; and an energetic particle and plasma spectrometer to characterize ionized species in the magnetosphere. 相似文献
18.
D. V. Titov H. Svedhem F. W. Taylor S. Barabash J. -L. Bertaux P. Drossart V. Formisano B. Häusler O. Korablev W. J. Markiewicz D. Nevejans M. Pätzold G. Piccioni J. -A. Sauvaud T. L. Zhang O. Witasse J. -C. Gerard A. Fedorov A. Sanchez-Lavega J. Helbert R. Hoofs 《Solar System Research》2009,43(3):185-209
Venus Express is the first European (ESA) mission to the planet Venus. Its main science goal is to carry out a global survey of the atmosphere, the plasma environment, and the surface of Venus from orbit. The payload consists of seven experiments. It includes a powerful suite of remote sensing imagers and spectrometers, instruments for in-situ investigation of the circumplanetary plasma and magnetic field, and a radio science experiment. The spacecraft, based on the Mars Express bus modified for the conditions at Venus, provides a versatile platform for nadir and limb observations as well as solar, stellar, and radio occultations. In April 2006 Venus Express was inserted in an elliptical polar orbit around Venus, with a pericentre height of ～250 km and apocentre distance of ～66000 km and an orbital period of 24 hours. The nominal mission lasted from June 4, 2006 till October 2, 2007, which corresponds to about two Venus sidereal days. Here we present an overview of the main results of the nominal mission, based on a set of papers recently published in Nature, Icarus, Planetary and Space Science, and Geophysical Research Letters. 相似文献
19.
Ludovic Puig Göran Pilbratt Astrid Heske Isabel Escudero Pierre-Elie Crouzet Bram de Vogeleer Kate Symonds Ralf Kohley Pierre Drossart Paul Eccleston Paul Hartogh Jeremy Leconte Giusi Micela Marc Ollivier Giovanna Tinetti Diego Turrini Bart Vandenbussche Paulina Wolkenberg 《Experimental Astronomy》2018,46(1):211-239
ARIEL, the Atmospheric Remote sensing Infrared Exoplanet Large survey, is one of the three M-class mission candidates competing for the M4 launch slot within the Cosmic Vision science programme of the European Space Agency (ESA). As such, ARIEL has been the subject of a Phase A study that involved European industry, research institutes and universities from ESA member states. This study is now completed and the M4 down-selection is expected to be concluded in November 2017. ARIEL is a concept for a dedicated mission to measure the chemical composition and structure of hundreds of exoplanet atmospheres using the technique of transit spectroscopy. ARIEL targets extend from gas giants (Jupiter or Neptune-like) to super-Earths in the very hot to warm zones of F to M-type host stars, opening up the way to large-scale, comparative planetology that would place our own Solar System in the context of other planetary systems in the Milky Way. A technical and programmatic review of the ARIEL mission was performed between February and May 2017, with the objective of assessing the readiness of the mission to progress to the Phase B1 study. No critical issues were identified and the mission was deemed technically feasible within the M4 programmatic boundary conditions. In this paper we give an overview of the final mission concept for ARIEL as of the end of the Phase A study, from scientific, technical and operational perspectives. 相似文献
20.
M. B. Martynov S. N. Alexashkin N. M. Khamidullina O. I. Orlov N. D. Novikova E. A. Deshevaya V. I. Trofimov 《Solar System Research》2011,45(7):593-596
The article presents an analysis of the Phobos-Grunt mission, a classification of its phases in terms of planetary protection,
and the main principles of activities management and definition of actions for fulfilling the planetary-protection requirements
developed by Committee on Space Research. 相似文献