A dataset provided by the European Space Agency

Name S1-X-SPEDE-4-REFDR-EP-MONITORING
Mission SMALL-MISSIONS-FOR-ADVANCED-RESEARCH-AND-TECHNOLOGY
URL ftp://npsa01.esac.esa.int/pub/mirror/SMALL-MISSIONS-FOR-ADVANCED-RESEARCH-AND-TECHNOLOGY/SPEDE/S1-X-SPEDE-4-REFDR-EP-MONITORING-V1.0
DOI 10.5270/esa-bh4odaz
Abstract N/A
Description Data Set Overview = This data set contains level 2 processed data for the SPEDE instrument on SMART-1. The set covers the time period from start of SPEDE nominal operations on orbit 15 (4 October 2003) to the start of commissioning activities on orbit 204 (1 February 2004). Activities during this period will be covered in more detail in later documents and reports of science analysis. For SPEDE instrument description see SPEDEPAPER in /DOCUMENT directory. The main activity performed during the period was monitoring the plasma environment of SMART-1 during operation of the EP thruster. EP was operated most of the time in order to raise the SMART-1 orbit outside of the radiation belts. Thus very little data other than EP monitoring was collected. Especially during christmas period, EP was on almost two weeks continuously. On October 20, 2004, the +X probe of SPEDE started showing anomalous behavior, resulting in non-nominal data. The event has been analysed and reported in S1-SPE-RP-3009 'SMART-1 SPEDE Anomaly Report: Probe +X Malfunction'. For this delivery, data from +X probe have not been processed to Level 2 for orbits that occur after that event. For the remainder of the orbit corresponding to the event of anomaly, data are flagged (for flags see below). The Probe +X data has not been processed for the remainder of the data set because the calibration of the probe after the malfunction is not known to an accuracy that would allow for normalising the measurements with sufficient confidence on the results. The end of October and beginning of November was a period of extremely high Solar activity. Interesting results can be expected from later analysis of SPEDE data taken during that period. The operation of the instrument was controlled by nominal Instrument Operations Timeline (ITL) sequences, developed for EP monitoring. The activities in the ITL were coordinated with the EPDP instrument. During EP...
Instrument SPEDE
Temporal Coverage 2003-10-04T21:48:03Z/2004-02-01T22:46:14Z
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 Dr. Anssi Malkki
Date Published 2005-10-18T00:00:00Z
Publisher And Registrant European Space Agency
Credit Guidelines European Space Agency, 2005-10-18T00:00:00Z, S1-X-SPEDE-4-REFDR-EP-MONITORING, V1.0. https://doi.org/10.5270/esa-bh4odaz