A dataset provided by the European Space Agency

Name S1-L-X-AMIE-2-EDR-EP
Mission SMALL-MISSIONS-FOR-ADVANCED-RESEARCH-AND-TECHNOLOGY
URL ftp://npsa01.esac.esa.int/pub/mirror/SMALL-MISSIONS-FOR-ADVANCED-RESEARCH-AND-TECHNOLOGY/AMIE/S1-L-X-AMIE-2-EDR-EP-V1.0
DOI 10.5270/esa-wwmuhot
Abstract This dataset contains the RAW data of the AMIE instrument from the EXTENDED MISSION of the SMART-1 mission. The AMIE CCD is divided into eight regions covered by five different filters. The individual data products each contain one filter image. The telemetry data from the DDS has been unpacked and uncompressed.
Description Contents 1 Data set description 1.1 Data set overview 1.2 Parameters 1.3 Processing 1.4 Data 1.5 Ancillary data 1.6 Coordinate system 1.7 Software 1.8 Media/Format 2 Confidence level note 2.1 Confidence level overview 2.2 Review 2.3 Data coverage and quality 2.4 Limitations 2.4.1 Telemetry errors 2.4.2 Timing of image acquisition 2.4.3 Exposure time 2.4.4 Focal plane temperature 2.4.5 Calibration 2.4.6 Vertical stripes with 8 pixel spacing 2.4.7 Scattered light 1. Data set description 1.1. Data set overview The data set contains images acquired with the AMIE camera aboard the SMART-1 spacecraft. The AMIE CCD of 1024 x 1024 pixels is divided into eight regions covered by five different filters (one of them being just no filter). The size of the different regions varies from 256 x 256 to 512 x 512 pixel. The individual data products --- i.e., the image files contained in subdirectories of the `DATA' directory --- each contain one filter image. During the extended mission, a few times an instrument mode was used where only the LASER filter CCD area is read out. Files for the other filters have been padded with dummy values. For each image acquisition, files for all eight filter images are present in the dataset. Even if the CCD has been read out completely, the used exposure time may only be appropriate for some of the filters, cf. 2.3. For details on the arrangement and properties of the filters see the EAICD in the `DOCUMENT' directory. Basic geometry and illumination information is provided in the label of each image. More comprehensive information is provided in the table `GEO_MOON.LBL'/`GEO_MOON.TAB' in the `INDEX' directory. 1.2. Parameters The measured parameter is brightness. The unit is data number which has a value between 0 and 1023. 1.3. Processing The telemetry data from the DDS has been unpacked and uncompressed. 1.4. Data Each image file starts with an attached PDS label header. The label is ASCII text ma...
Instrument AMIE
Temporal Coverage 2005-10-12T07:24:19Z/2006-09-03T05:37:16Z
Version V1.0
Mission Description Mission Overview SMART-1 is the first of the Small Missions for Advanced Research and Technology (SMART), which are elements of ESA's Horizons 2000 plan for scientific projects. A brief description of the mission and its objectives can be found in the SMART-1 Archive Plan [S1_ARCH_PLAN_2003], and in papers by [MARINI_ET_AL_2002] and [RACCA_ET_AL_2002]. A detailed description of the mission analysis can be found in the Consolidated Report on Mission Analysis [CREMA_2001]. The SMART missions aim at testing key technologies for future cornerstone missions. The primary technological objective of SMART-1 is the flight demonstration of Solar-Electric-Primary-Propulsion (SEPP) for a scientific lunar orbiting spacecraft delivered from launch into a geostationary transfer orbit (GTO). The spacecraft was designed to operate with minimum ground intervention (e.g. one pass every 4 days). However, the use of ground stations throughout the mission was on availability basis with, on average, a pass once a day. SMART-1 was launched from Kourou at 23:14 UTC on 27th Sept 2003 as a co- passenger on an Ariane-5 launcher. The launch mass of the spacecraft was 367kg, including 82.5kg of Xenon propellant for the SEPP and 19kg instrument payload. After release into the geostationary transfer orbit (GTO) the spacecraft acquired initial attitude, autonomously deployed the solar arrays and entered a checkout phase. The GTO had the following parameters. A=24702.3km E=0.71578 Inc=6.999deg RAAN=250.965deg APER=178.246deg Perigee=7020.8km Apogee=42383.7km The first firing of the SEPP occurred at 12:20:21 UT on 30th September 2003. The escape from the Earth was performed by gradually expanding the orbit from the initial geostationary transfer orbit parameters. Continuous thrusting was required for a little over 80 days in order to pass the main radiation belts as quickly as possible, pushing the perigee out to 20,000km. After this ...
Creator Contact Stephane Beauvivre
Date Published 2010-04-14T00:00:00Z
Publisher And Registrant European Space Agency
Credit Guidelines European Space Agency, 2010-04-14T00:00:00Z, S1-L-X-AMIE-2-EDR-EP, V1.0. https://doi.org/10.5270/esa-wwmuhot