A dataset provided by the European Space Agency

DOI https://doi.org/10.5270/esa-0s2dphw
Abstract This dataset contains the RAW data of the SIR instrument from the EARTH ESCAPE PHASE of the SMART-1 mission. The principle science data are spectra. All spectra of each orbit are collected in one data product. No processing beyond unpacking has been applied to the telemetry data.
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 quality 2.4 Pointing accuracy 1. Data set description 1.1. Data set overview The data set contains spectra acquired with the SIR instrument aboard the SMART-1 spacecraft. SIR is a point spectrometer with 256 spectral channels. For details on the SIR instrument see the EAICD in the `DOCUMENT' directory. 1.2. Parameters The measured parameter is spectral intensity. The unit is data number which has a value between 0 and 65535. 1.3. Processing No processing beyond unpacking has been applied to the telemetry data. 1.4. Data Each data product contains all data from one orbit. The data product may either contain only housekeeping data or housekeeping and science data, i.e., spectra, which is reflected in the filenames, cf. the file `AAREADME.TXT' in the root directory. Each data product consists of an ASCII PDS label file and a FITS data file, which is plain ASCII for housekeeping data only or binary if science data is included. The actual data resides in the FITS file, while the label files provides a PDS compliant description of the data structure. The data is arranged in a PDS table object, where each line represents one measurement instance and the different columns represent different measured parameters. If a spectrum was taken, the complete 256 channel spectrum resides in one line-column cell of the table. For the details of the file format and a comprehensive description of the PDS labels, see the EAICD in the `DOCUMENT' directory. 1.5. Ancillary data No particular ancillary data is needed to interpret the data. 1.6. Coordinate system Lunar latitudes and longitudes are given in the lunar `mean Earth' reference frame. 1.7. Software No software is provided. As the data format is lega...
Instrument SIR
Temporal Coverage 2003-10-04T12:17:15Z/2004-11-11T14:01:25Z
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 Horst Uwe Keller
Date Published 2010-04-20
Publisher And Registrant European Space Agency
Credit Guidelines European Space Agency, 2010-04-20, S1-L-X-SIR-2-EDR-EEP, V1.0. https://doi.org/10.5270/esa-0s2dphw