A dataset provided by the European Space Agency

Name S1-X-SPEDE-2-EDR-LEOP-CALIBRATION
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-2-EDR-LEOP-CALIBRATION-V1.0
DOI 10.5270/esa-qooyw38
Abstract N/A
Description Data Set Overview = This data set contains level 1b processed data for the SPEDE instrument on SMART-1. The set covers the time period from SPEDE pre-commissioning during orbit 3 on 29 September 2003 to the end of the pre-commissioning campaign after orbit 14 on 3 October 2003. A general description of activities during this time period is given in 'SMART-1 SPEDE Pre-Commissioning Report', S1-SPE-RP-3007. For SPEDE instrument description see INST.CAT. The activities performed during the period start with the instrument pre-commissioning during orbit 3 on 29 September 2003. The pre-commissioning consisted of the power-on sequence, health check measurements, configuration table dumps and first test measurements with science modes. The science mode measurements started with calibration measurements in eclipse, performed using a coordinated instrument timeline with the EPDP instrument. These measurements were performed at low altitudes (below 1000 km) during eclipses around perigees 5 to 12. The measurements consist of three consecutive Langmuir mode sweeps in mode 5, with varying overlap with the EPDP Langmuir probe sweeps, followed by monitoring of SPEDE response to EPDP RPA operation, with SPEDE mode 3. With coordinated data analysis, cross calibration of the two instruments will be checked. A second category of measurements is monitoring of Electric Propulsion (EP) operation. The first pulse was monitored during orbit 5, after which all EP operations during the pre-commissioning campaign were monitored. The operation of the instrument was controlled by Direct Operation Request (DOR) sequences, following pre-defined timelines. During orbits 8 and 9 there is a data gap due to error in mode configuration updates, which resulted in SPEDE making only one measurement in mode 3, instead of continuous monitoring. This error was corrected during orbit 9. During orbits 9 and 10, a special timeline for Joint cal...
Instrument SPEDE
Temporal Coverage 2003-09-29T16:50:51Z/2003-10-04T16:08:16Z
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 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-2-EDR-LEOP-CALIBRATION, V1.0. https://doi.org/10.5270/esa-qooyw38