共查询到10条相似文献,搜索用时 578 毫秒
1.
L. Colangeli J. J. Lopez-Moreno P. Palumbo J. Rodriguez M. Cosi V. Della Corte F. Esposito M. Fulle M. Herranz J. M. Jeronimo A. Lopez-Jimenez E. Mazzotta Epifani R. Morales F. Moreno E. Palomba A. Rotundi 《Space Science Reviews》2007,128(1-4):803-821
The Grain Impact Analyser and Dust Accumulator (GIADA) onboard the ROSETTA mission to comet 67P/Churyumov–Gerasimenko is devoted
to study the cometary dust environment. Thanks to the rendezvous configuration of the mission, GIADA will be plunged in the
dust environment of the coma and will be able to explore dust flux evolution and grain dynamic properties with position and
time. This will represent a unique opportunity to perform measurements on key parameters that no ground-based observation
or fly-by mission is able to obtain and that no tail or coma model elaborated so far has been able to properly simulate. The
coma and nucleus properties shall be, then, clarified with consequent improvement of models describing inner and outer coma
evolution, but also of models about nucleus emission during different phases of its evolution. GIADA shall be capable to measure
mass/size of single particles larger than about 15 μm together with momentum in the range 6.5 × 10−10 ÷ 4.0 × 10−4 kg m s−1 for velocities up to about 300 m s−1. For micron/submicron particles the cumulative mass shall be detected with sensitivity 10−10 g. These performances are suitable to provide a statistically relevant set of data about dust physical and dynamic properties
in the dust environment expected for the target comet 67P/Churyumov–Gerasimenko. Pre-flight measurements and post-launch checkouts
demonstrate that GIADA is behaving as expected according to the design specifications.
The International GIADA Consortium (I, E, UK, F, D, USA). 相似文献
2.
Jessica M. Sunshine Michael F. A’Hearn Olivier Groussin Lucy A. McFadden Kenneth P. Klaasen Peter H. Schultz Carey M. Lisse 《Space Science Reviews》2005,117(1-2):269-295
The science payload on the Deep Impact mission includes a 1.05–4.8 μm infrared spectrometer with a spectral resolution ranging
from R∼200–900. The Deep Impact IR spectrometer was designed to optimize, within engineering and cost constraints, observations
of the dust, gas, and nucleus of 9P/Tempel 1. The wavelength range includes absorption and emission features from ices, silicates,
organics, and many gases that are known to be, or anticipated to be, present on comets. The expected data will provide measurements
at previously unseen spatial resolution before, during, and after our cratering experiment at the comet 9P/Tempel 1. This
article explores the unique aspects of the Deep Impact IR spectrometer experiment, presents a range of expectations for spectral
data of 9P/Tempel 1, and summarizes the specific science objectives at each phase of the mission. 相似文献
3.
F. -X. Désert 《Space Science Reviews》1995,74(1-2):157-162
The visible extragalactic background (though as yet undetected) is insufficient to explain the abundance of heavy elements in galaxies: either there should be some diffuse extragalactic light in the near infrared (from 1 to 10 m) and/or in the far infrared (100 m) if dust has reprocessed the star light. We propose a new space mission to be dedicated to the search and mapping of primordial stellar light from the visible to the mid-infrared (20 m). In this spectrum range, detectors have reached such a sensitivity that the mission should aim at being (source) photon noise limited, and not any longer background photon noise limited. For that purpose, a small passively cooled telescope with large format CCDs and CIDs could be sent beyond the zodiacal dust cloud (which is absent beyond a solar distance of about 3 AU). In that case, the only remaining foregrounds before reaching the extragalactic background, is due to the Milky Way integrated emission from stars and the diffuse galactic light due to scattering and emission by interstellar dust, which are all unavoidable. Maps of the extragalactic light could be obtained at the arcminute resolution with high signal to noise ratio. This mission is the next logical step after IRAS, COBE and ISO for the study of extragalactic IR backgrounds. It has been proposed as a possible medium-sized mission for the post-horizon 2000 ESA program that could be a piggy back of a planetary mission. 相似文献
4.
《Space Science Reviews》2007,128(1-4):433-506
The Optical, Spectroscopic, and Infrared Remote Imaging System OSIRIS is the scientific camera system onboard the Rosetta
spacecraft (Figure 1). The advanced high performance imaging system will be pivotal for the success of the Rosetta mission.
OSIRIS will detect 67P/Churyumov-Gerasimenko from a distance of more than 106 km, characterise the comet shape and volume, its rotational state and find a suitable landing spot for Philae, the Rosetta
lander. OSIRIS will observe the nucleus, its activity and surroundings down to a scale of ~2 cm px−1. The observations will begin well before the onset of cometary activity and will extend over months until the comet reaches
perihelion. During the rendezvous episode of the Rosetta mission, OSIRIS will provide key information about the nature of
cometary nuclei and reveal the physics of cometary activity that leads to the gas and dust coma.
OSIRIS comprises a high resolution Narrow Angle Camera (NAC) unit and a Wide Angle Camera (WAC) unit accompanied by three
electronics boxes. The NAC is designed to obtain high resolution images of the surface of comet 67P/Churyumov-Gerasimenko
through 12 discrete filters over the wavelength range 250–1000 nm at an angular resolution of 18.6 μrad px−1. The WAC is optimised to provide images of the near-nucleus environment in 14 discrete filters at an angular resolution of
101 μrad px−1. The two units use identical shutter, filter wheel, front door, and detector systems. They are operated by a common Data
Processing Unit. The OSIRIS instrument has a total mass of 35 kg and is provided by institutes from six European countries. 相似文献
5.
Michael F. A’Hearn Michael J. S. Belton Alan Delamere William H. Blume 《Space Science Reviews》2005,117(1-2):1-21
The Deep Impact mission will provide the first data on the interior of a cometary nucleus and a comparison of those data with
data on the surface. Two spacecraft, an impactor and a flyby spacecraft, will arrive at comet 9P/Tempel 1 on 4 July 2005 to
create and observe the formation and final properties of a large crater that is predicted to be approximately 30-m deep with
the dimensions of a football stadium. The flyby and impactor instruments will yield images and near infrared spectra (1–5
μm) of the surface at unprecedented spatial resolutions both before and after the impact of a 350-kg spacecraft at 10.2 km/s.
These data will provide unique information on the structure of the nucleus near the surface and its chemical composition.
They will also used to interpret the evolutionary effects on remote sensing data and will indicate how those data can be used
to better constrain conditions in the early solar system. 相似文献
6.
J.-P. Bibring P. Lamy Y. Langevin A. Soufflot M. Berthé J. Borg F. Poulet S. Mottola 《Space Science Reviews》2007,128(1-4):397-412
CIVA (Comet Infrared and Visible Analyser) is an integrated set of imaging instruments, designed to characterize the 360∘ panorama (CIVA-P) as seen from the Rosetta Lander Philae, and to study surface and subsurface samples (CIVA-M). CIVA-P is
a panoramic stereo camera, while CIVA-M is an optical microscope coupled to a near infrared microscopic hyperspectral imager.
CIVA shares a common Imaging Main Electronics (IME) with ROLIS. CIVA-P will characterize the landing site, with an angular
sampling (IFOV) of 1.1 mrad: each pixel will image a 1 mm size feature at the distance of the landing legs, and a few metres
at the local horizon. The panorama will be mapped by 6 identical miniaturized micro-cameras covering contiguous FOV, with
their optical axis 60∘ apart. Stereoscopic capability will be provided by an additional micro-camera, identical to and co-aligned with one of the
panoramic micro-camera, with its optical axis displaced by 10 cm. CIVA-M combines two ultra-compact and miniaturised microscopes,
one operating in the visible and one constituting an IR hyperspectral imaging spectrometer: they will characterize, by non-destructive
analyses, the texture, the albedo, the molecular and the mineralogical composition of each of the samples provided by the
Sample Drill and Distribution (SD2) system. For the optical microscope, the spatial sampling is 7 μm; for the IR, the spectral range (1–4 μm) and the spectral sampling (5 nm) have been chosen to allow identification of most minerals, ices and organics, on each
pixel, 40 μm in size. After being studied by CIVA, the sample could be analysed by a subsequent experiment (PTOLEMY and/or COSAC). The
process would be repeated for each sample obtained at different depths and/or locations. 相似文献
7.
Peter H. Schultz Carolyn M. Ernst Jennifer L. B. Anderson 《Space Science Reviews》2005,117(1-2):207-239
The NASA Discovery Deep Impact mission involves a unique experiment designed to excavate pristine materials from below the
surface of comet. In July 2005, the Deep Impact (DI) spacecraft, will release a 360 kg probe that will collide with comet
9P/Tempel 1. This collision will excavate pristine materials from depth and produce a crater whose size and appearance will
provide fundamental insights into the nature and physical properties of the upper 20 to 40 m. Laboratory impact experiments
performed at the NASA Ames Vertical Gun Range at NASA Ames Research Center were designed to assess the range of possible outcomes
for a wide range of target types and impact angles. Although all experiments were performed under terrestrial gravity, key
scaling relations and processes allow first-order extrapolations to Tempel 1. If gravity-scaling relations apply (weakly bonded
particulate near-surface), the DI impact could create a crater 70 m to 140 m in diameter, depending on the scaling relation
applied. Smaller than expected craters can be attributed either to the effect of strength limiting crater growth or to collapse
of an unstable (deep) transient crater as a result of very high porosity and compressibility. Larger then expected craters
could indicate unusually low density (< 0.3 g cm−3) or backpressures from expanding vapor. Consequently, final crater size or depth may not uniquely establish the physical
nature of the upper 20 m of the comet. But the observed ejecta curtain angles and crater morphology will help resolve this
ambiguity. Moreover, the intensity and decay of the impact “flash” as observed from Earth, space probes, or the accompanying
DI flyby instruments should provide critical data that will further resolve ambiguities. 相似文献
8.
Aiming at a 1-cm Orbit for Low Earth Orbiters: Reduced-Dynamic and Kinematic Precise Orbit Determination 总被引:1,自引:0,他引:1
The computation of high-accuracy orbits is a prerequisite for the success of Low Earth Orbiter (LEO) missions such as CHAMP,
GRACE and GOCE. The mission objectives of these satellites cannot be reached without computing orbits with an accuracy at
the few cm level. Such a level of accuracy might be achieved with the techniques of reduced-dynamic and kinematic precise
orbit determination (POD) assuming continuous Satellite-to-Satellite Tracking (SST) by the Global Positioning System (GPS).
Both techniques have reached a high level of maturity and have been successfully applied to missions in the past, for example
to TOPEX/POSEIDON (T/P), leading to (sub-)decimeter orbit accuracy. New LEO gravity missions are (to be) equipped with advanced
GPS receivers promising to provide very high quality SST observations thereby opening the possibility for computing cm-level
accuracy orbits. The computation of orbits at this accuracy level does not only require high-quality GPS receivers, but also
advanced and demanding observation preprocessing and correction algorithms. Moreover, sophisticated parameter estimation schemes
need to be adapted and extended to allow the computation of such orbits. Finally, reliable methods need to be employed for
assessing the orbit quality and providing feedback to the different processing steps in the orbit computation process.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献
9.
We review some of the new results for suprathermal electrons obtained with the 3-D Plasma and Energetic Particle Instrument
on the WIND spacecraft, which provides high sensitivity electron and ion measurements from solar wind thermal plasma up to
≳MeV energies. These results include: (1) the observation of solar impulsive electron events extending down to ∼0.5 keV energy;
(2) the observation of a turnover at ∼12 keV for electrons in a gradual large solar energetic particle (LSEP) event; (3) the
detection of a quiet-time population (the ‘superhalo’) of electrons extending up to ∼100 keV energy; and (4) the probing of
the magnetic topology and source region for magnetic clouds, using electrons. These unique WIND measurements are highly complementary
to the particle composition measurements which will be made by ACE.
This revised version was published online in June 2006 with corrections to the Cover Date. 相似文献
10.
Microscope Instrument Development,Lessons for GOCE 总被引:2,自引:0,他引:2
Two space missions are presently under development with payload based on ultra-sensitive electrostatic accelerometers. The
GOCE mission takes advantage of a three axis gradiometer accommodated in a very stable thermal case on board a drag-free satellite
orbiting at a very low altitude of 250 km. This ESA mission will perform the very highly accurate mapping of the Earth gravity
field with a geographical resolution of 100 km. The MICROSCOPE mission is devoted to the test of the “Universality of free
fall” in view of the verification of the Einstein Equivalence Principle (EP) and of the search of a new interaction. The MICROSCOPE
instrument is composed of two pairs of differential electrostatic accelerometers and the accelerometer proof-masses are the
bodies of the EP test. The satellite is also a drag-free satellite exhibiting a fine attitude control and in a certain way,
each differential accelerometer is a one axis gradiometer with an arm of quite null length. The development of this instrument
much interests the definition and the evaluation of the sensor cores of the gradiometer. The in flight calibration process
of both instruments is also very similar. Lessons form these parallel developments are presented.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献