Editing SMART-1

{{short description|European Space Agency satellite that orbited the Moon}}
{{for|the electric crossover SUV|Smart 1}}
{{Use dmy dates|date=May 2020}}
{{Infobox spaceflight
| name                  = SMART-1
| image                 = File:Artist's impression of the SMART-1 mission ESA199399.jpg
| image_caption         = Artist's impression of SMART-1

| mission_type          = Technology<br/>Lunar orbiter
| operator              = [[European Space Agency|ESA]]
| COSPAR_ID             = 2003-043C 
| SATCAT                = 27949 
| website               = [http://www.esa.int/SPECIALS/SMART-1/index.html SMART-1]
| mission_duration      = 2 years, 11 months, 6 days, 6 hours, 27 minutes, 36 seconds

| spacecraft_bus        = 
| manufacturer          = [[Swedish Space Corporation]]
| dry_mass              = {{convert|287|kg|lb}}
| launch_mass           = {{convert|367|kg|lb}}<ref name="SMART-1">{{cite web |url=https://solarsystem.nasa.gov/missions/smart-1/in-depth/ |title=SMART-1 |publisher=NASA's Solar System Exploration website |access-date=December 2, 2022}}</ref>
| power                 =

| launch_date           = {{start-date|27 September 2003, 23:14:46|timezone=yes}}&nbsp;UTC <ref name="SMART-1"></ref>
| launch_rocket         = [[Ariane 5|Ariane 5G]]
| launch_site           = [[Guiana Space Centre|Kourou]] [[ELA-3]]
| launch_contractor     = [[Arianespace]]
| decay_date            = {{end-date|3 September 2006, 05:42:22|timezone=yes}}&nbsp;UTC

| orbit_epoch           = 18 July 2005, 11:14:28&nbsp;UTC
| orbit_reference       = [[selenocentric orbit|Selenocentric]]
| orbit_periapsis       = {{convert|2205|km|mi}} 
| orbit_apoapsis        = {{convert|4600|km|mi}}
| orbit_inclination     = 90.26&nbsp;degrees
| orbit_eccentricity    = 0.352054
| orbit_period          = 4.95&nbsp;hours
| apsis                 = selene

|interplanetary         = 
 {{Infobox spaceflight/IP
   |type                = orbiter
   |object              = [[Moon|Lunar]]
   |orbits              = 
   |arrival_date        = 15 November 2004
   |location            = {{Lunar coords and quad cat|34.262|S|46.193|W}}<ref name="astromag">{{cite web |url=http://astronomy.com/news/2017/09/a-lunar-orbiters-final-resting-place |title=New observations reveal a lunar orbiter's final resting place |last=Klesman|first=Alison |date=22 September 2017 |website=[[Astronomy (magazine)|Astronomy Magazine]] |access-date=27 September 2017}}</ref>

 }}

| instruments_list       = <!-- start collapsible list of instruments -->
{{Infobox spaceflight/Instruments
 | acronym1  = AMIE   | name1  = Advanced Moon micro-Imager Experiment
 | acronym2  = D-CIXS | name2  = Demonstration of a Compact X-ray Spectrometer
 | acronym3  = EPDP   | name3  = Electric Propulsion Diagnostic Package
 | acronym4  = KATE   | name4  = Ka band TT&C Experiment
 | acronym5  = SIR    | name5  = Smart-1 Infrared Spectrometer
 | acronym6  = SPEDE  | name6  = Spacecraft Potential, Electron and Dust Experiment
 | acronym7  = XSM    | name7  = X-ray Solar Monitor
}}

| insignia              = File:SMART-1 insignia.png
| insignia_caption      = Legacy ESA insignia for the ''SMART-1'' mission
| insignia_alt          = ISO legacy mission insignia
| insignia_size         = 180x180px
}}

'''SMART-1''' was a [[European Space Agency]] [[satellite]] that [[orbit]]ed the [[Moon]]. It was launched on 27 September 2003 at 23:14 [[Coordinated Universal Time|UTC]] from the [[Guiana Space Centre]] in [[Kourou]], [[French Guiana]]. "SMART-1" stands for '''Small Missions for Advanced Research in Technology-1'''. On 3 September 2006 (05:42 UTC), SMART-1 was deliberately crashed into the Moon's surface, ending its mission.<ref>{{cite news | url=http://news.bbc.co.uk/1/hi/sci/tech/5309656.stm | work=BBC News | title=Probe crashes into Moon's surface | date=3 September 2006 | access-date=23 May 2010}}</ref>

==Spacecraft design==
SMART-1 was about one meter across (3.3&nbsp;ft), and lightweight in comparison to other probes. Its launch mass was 367&nbsp;kg or 809 pounds, of which 287&nbsp;kg (633&nbsp;lb) was non-propellant.

It was propelled by a solar-powered [[Hall-effect thruster]] (Snecma [[PPS-1350]]-G) using 82 kg of [[xenon]] gas contained in a 50 [[litre]]s tank at a pressure of 150 bar at launch. The [[ion engine]] thruster used an [[electrostatic field]] to ionize the xenon and accelerate the [[ion]]s achieving a [[specific impulse]] of 16.1&nbsp;kN·s/kg (1,640 seconds), more than three times the maximum for chemical rockets. One kg of propellant (1/350 to 1/300 of the total mass of the spacecraft) produced a [[delta-v]] of about 45&nbsp;m/s. The electric propulsion subsystem weighted 29&nbsp;kg with a peak power consumption of 1,200 watts.  SMART-1 was the first in the program of ESA's Small Missions for Advanced Research and Technology.

The solar arrays made capable of 1850 W at the beginning of the mission, were able to provide the maximum set of 1,190 W to the thruster, giving a nominal thrust of 68&nbsp;mN, hence an acceleration of 0.2&nbsp;mm/s<sup>2</sup> or 0.7&nbsp;m/s per hour (i.e., just under 0.00002 [[G-force|''g'']] of acceleration). As with all ion-engine powered craft, [[orbital maneuver]]s were not carried out in short bursts but very gradually. The particular trajectory taken by SMART-1 to the Moon required thrusting for about one third to one half of every orbit. When spiraling away from the Earth thrusting was done on the [[perigee]] part of the orbit. At the end of the mission, the thruster had demonstrated the following capability:

* Thruster operating time: 5000 h
* Xenon throughput: 82&nbsp;kg
* Total Impulse: 1.2 MN-s
* Total ΔV: 3.9&nbsp;km/s

As part of the European Space Agency's strategy to build very inexpensive and relatively small [[Spacecraft|spaceships]], the total cost of SMART-1 was a relatively small 110 million [[euro]]s (about 170 million [[United States dollar|U.S. dollars]]). SMART-1 was designed and developed by the [[Swedish Space Corporation]] on behalf of [[ESA]]. Assembly of the spacecraft was carried out by [[Saab Space]] in [[Linköping]]. Tests of the spacecraft were directed by Swedish Space Corporation and executed by Saab Space. The project manager at [[ESA]] was Giuseppe Racca until the spacecraft achieved the moon operational orbit. He was then replaced by [[Gerhard Schwehm]] for the Science phase. The project manager at the Swedish Space Corporation was Peter Rathsman. The Principal Project Scientist was [[Bernard Foing]]. The Ground Segment Manager during the preparation phase was Mike McKay and the Spacecraft Operations manager was  [https://www.linkedin.com/in/octavio-camino-ramos-06ab73b/ Octavio Camino].

==Instruments==

===AMIE===
The Advanced Moon micro-Imager Experiment was a miniature colour camera for lunar imaging. The CCD camera with three filters of 750, 900 and 950&nbsp;nm was able to take images with an average pixel resolution of 80 m (about 260&nbsp;ft). The camera weighed 2.1&nbsp;kg (about 4.5&nbsp;lb) and had a power consumption of 9 watts.<ref>{{cite journal | title= Science objectives and first results from the SMART-1/AMIE multicolour micro-camera|display-authors= 4|author= Josset J. L.|author2= Beauvivre S.|author3= Cerroni P.|author4= De Sanctis M. C.|author5= Pinet P.|author6= Chevrel S.|author7= Langevin Y.|author8= Barucci M. A.|author9= Plancke P.|author10= Koschny D.|author11= Almeida M.|author12= Sodnik Z.|author13= Mancuso S.|author14= Hoffmann B. A.|author15= Muinonen K.|author16= Shevchenko V.|author17= Shkuratov Y.|author18= Ehrenfreund P.|author19= Foing B. H.|journal= Advances in Space Research|volume=37|pages=14–20|date= 2006|issue= 1|bibcode = 2006AdSpR..37...14J |doi = 10.1016/j.asr.2005.06.078 }}</ref>

===D-CIXS===
The Demonstration of a Compact X-ray Spectrometer was an [[X-ray telescope]] for the identification of chemical elements on the lunar surface. It detected the [[X-ray fluorescence]] (XRF) of crystal compounds created through the interaction of the electron shell with the solar wind particles to measure the abundance of the three main components: [[magnesium]], [[silicon]] and [[aluminium]]. The detection of [[iron]], [[calcium]] and [[titanium]] depended on the solar activity. The detection range for X-rays was 0.5 to 10 keV. The spectrometer and XSM (described below) together weighed 5.2&nbsp;kg and had a power consumption of 18 watts.

===XSM===
The X-ray solar monitor studied the [[solar variation|solar variability]] to complement D-CIXS measurements.

===SIR===
The Smart-1 Infrared Spectrometer was an [[Infrared spectroscopy|infrared spectrometer]] for the identification of mineral spectra of [[olivine]] and [[pyroxene]]. It detected wavelengths from 0.93 to 2.4&nbsp;μm with 256 channels. The package weighed 2.3&nbsp;kg and had a power consumption of 4.1 watts.<ref>{{cite journal| title= Scientific objectives and selection of targets for the SMART-1 Infrared Spectrometer (SIR)|display-authors= 4|author= Basilevsky A. T.|author2= Keller H. U.|author3= Nathues A.|author4= Mall J.|author5= Hiesinger H.|author6= Rosiek M.|journal= Planetary and Space Science|volume= 52|pages= 1261–1285|date= 2004|doi=10.1016/j.pss.2004.09.002|bibcode=2004P&SS...52.1261B| issue= 14}}</ref>

===EPDP===
The Electric Propulsion Diagnostic Package was to acquire data on the new propulsion system on SMART-1. The package weighed 0.8&nbsp;kg and had a power consumption of 1.8 watts.<ref>{{cite journal| author=  Di Cara D. M.| author2=  Estublier D.|title=Smart-1: An analysis of flight data  |journal= Acta Astronautica| volume= 57 |issue= 2–8 |date= 2005| pages= 250–256|doi= 10.1016/j.actaastro.2005.03.036 |bibcode = 2005AcAau..57..250D }}</ref>

===SPEDE===
The Spacecraft Potential, Electron and Dust Experiment. The experiment weighed 0.8&nbsp;kg and had a power consumption of 1.8 watts. Its function was to measure the properties and density of the plasma around the spacecraft, either as a Langmuir probe or as an electric field probe. SPEDE observed the emission of the spacecraft's ion engine and the "wake" the Moon leaves to the [[solar wind]]. Unlike most other instruments that have to be shut down to prevent damage, SPEDE could keep measuring inside radiation belts and in solar storms, such as the [[Halloween solar storms, 2003|Halloween 2003 solar storms]].<ref>{{Cite web |url=http://sci.esa.int/smart-1/31415-instruments/ |website=sci.esa.int |title=ESA Science & Technology - Instruments}}</ref><ref name="Schmidt2014">{{cite journal | bibcode = 2014EGUGA..1613174S | title=SMART-1 SPEDE: Results and Legacy after 10 Years | volume=16 | year=2014 |author1=Schmidt, Walter |author2=Mälkki, Anssi | journal=EGU General Assembly Conference Abstracts | pages=13174 }}</ref> It was built by [[Finnish Meteorological Institute]] and its name was intentionally chosen so that its acronym is the same as the nickname of [[Spede Pasanen]], a famous Finnish movie actor, movie producer, and inventor. The algorithms developed for SPEDE were later used in the [[ESA]] lander [[Philae_(spacecraft)|Philae]].<ref name="Schmidt2014" />

===KATE===
[[Ka band|K<sub>a</sub> band]] TT&C (telemetry, tracking and control) Experiment. The experiment weighed 6.2&nbsp;kg and had a power consumption of 26 watts. The Ka-band transponder was designed as precursor for [[BepiColombo]] to perform radio science investigations and to monitor the dynamical performance of the electric propulsion system.

==Flight==

SMART-1 was launched 27 September 2003 together with [[INSAT-3E|Insat 3E]] and [[Eurobird 3|eBird 1]], by an [[Ariane 5]] rocket from the [[Guiana Space Centre]] in [[French Guiana]]. After 42 minutes it was released into a [[geostationary transfer orbit]] of 7,035&nbsp;×&nbsp;42,223&nbsp;km<!--- 654 × 35,885 km altitude --->. From there it used its Solar Electric Primary Propulsion (SEPP) to gradually spiral out during thirteen months.

The orbit can be seen up to 26 October 2004 at [http://www.spaceref.com/news/viewsr.html?pid=14345 spaceref.com], when the orbit was 179,718&nbsp;×&nbsp;305,214&nbsp;km. On that date, after the 289th engine pulse, the SEPP had accumulated a total on-time of nearly 3,648 hours out of a total flight time of 8,000 hours, hence a little less than half of its total mission. It consumed about 58.8&nbsp;kg of [[xenon]] and produced a delta-v of 2,737&nbsp;m/s (46.5&nbsp;m/s per kg xenon, 0.75&nbsp;m/s per hour on-time). It was powered on again on 15 November for a planned burn of 4.5 days to enter fully into lunar orbit. It took until February 2005 using the electric thruster to decelerate into the final orbit 300–3,000&nbsp;km above the Moon's surface.<ref>{{cite journal| display-authors = 4| author = Rathsman P.| author2 = Kugelberg J.| author3 = Bodin P.| author4 = Racca G. D.| author5 = Foing B.| author6 =Stagnaro|title= SMART-1: Development and lessons learnt|  journal= Acta Astronautica|
volume= 57 |issue= 2–8 | date= 2005| pages= 455–468| doi= 10.1016/j.actaastro.2005.03.041  |bibcode = 2005AcAau..57..455R }}</ref>  The end of mission performance demonstrated by the propulsion system is stated above.

{| class="wikitable"
|+'''Summary of [[osculating orbit|osculating]] geocentric orbital elements'''
|-
! abbr="Epoch"       | Epoch (UTC) 
! abbr="Perigee"     | Perigee (km)
! abbr="Apogee"      | Apogee (km)
!                      Eccentricity
! abbr="Inclination" | Inclination (deg)<br>(to Earth equator)
! abbr="Period"      | Period (h)
|-
! 27 September 2003
|align="right"| ~7,035 ||align="right"| ~42,223 ||align="right"| ~0.714 ||align="right"| ~6.9 ||align="right"| ~10.6833
|-
! 26 October 2003, 21:20:00.0
|align="right"| 8,687.994 ||align="right"| 44,178.401 ||align="right"| 0.671323 ||align="right"| 6.914596 ||align="right"| 11.880450
|-
! 19 November 2003, 04:29:48.4 
|align="right"| 10,843.910 ||align="right"| 46,582.165 ||align="right"| 0.622335 ||align="right"| 6.861354 ||align="right"| 13.450152
|-
! 19 December 2003, 06:41:47.6 
|align="right"| 13,390.351 ||align="right"| 49,369.049 ||align="right"| 0.573280 ||align="right"| 6.825455 ||align="right"| 15.366738
|-
! 29 December 2003, 05:21:47.8 
|align="right"| 17,235.509 ||align="right"| 54,102.642 ||align="right"| 0.516794 ||align="right"| 6.847919 ||align="right"| 18.622855
|-
! 19 February 2004, 22:46:08.6 
|align="right"| 20,690.564 ||align="right"| 65,869.222 ||align="right"| 0.521936 ||align="right"| 6.906311 ||align="right"| 24.890737
|-
! 19 March 2004, 00:40:52.7 
|align="right"| 20,683.545 ||align="right"| 66,915.919 ||align="right"| 0.527770 ||align="right"| 6.979793 ||align="right"| 25.340528
|-
! 25 August 2004, 00:00:00 
|align="right"| 37,791.261 ||align="right"| 240,824.363 ||align="right"| 0.728721 ||align="right"| 6.939815 ||align="right"| 143.738051
|-
! 19 October 2004, 21:30:45.9 
|align="right"| 69,959.278 ||align="right"| 292,632.424 ||align="right"| 0.614115 ||align="right"| 12.477919 ||align="right"| 213.397970
|-
! 24 October 2004, 06:12:40.9 
|align="right"| 179,717.894 ||align="right"| 305,214.126 ||align="right"| 0.258791 ||align="right"| 20.591807 ||align="right"| 330.053834
|}
After its last [[perigee]] on 2 November,<ref>[http://www.moontoday.net/news/viewsr.html?pid=14345 SMART-1: On Course for Lunar Capture | Moon Today – Your Daily Source of Moon News<!-- Bot generated title -->] www.moontoday.net {{webarchive|url=https://web.archive.org/web/20051102120549/http://www.moontoday.net/news/viewsr.html?pid=14345 |date=2 November 2005 }}</ref> on 11 November 2004 it passed through the [[Lagrange point#Earth–Moon|Earth-Moon]] L<sub>1</sub> [[Lagrangian Point]] and into the area dominated by the Moon's [[gravity|gravitational]] influence, and at 1748 [[Universal Time|UT]] on 15 November passed the first [[periselene]] of its lunar orbit. The [[osculating orbit]] on that date was 6,704&nbsp;×&nbsp;53,208&nbsp;km,<ref>[http://www.moontoday.net/news/viewsr.html?pid=14573 SMART-1 completes its first orbit around the Moon | Moon Today – Your Daily Source of Moon News<!-- Bot generated title -->] www.moontoday.net {{webarchive|url=https://web.archive.org/web/20041215100120/http://www.moontoday.net/news/viewsr.html?pid=14573 |date=15 December 2004 }}</ref> with an orbital period of 129 hours, although the actual orbit was accomplished in only 89 hours. This illustrates the significant impact that the engine burns have on the orbit and marks the meaning of the osculating orbit, which is the orbit that would be travelled by the spacecraft if at that instant all perturbations, including thrust, would cease.

{| class="wikitable"
|+'''Summary of [[osculating orbit|osculating]] selenocentric orbital elements'''
|-
! abbr="Epochea"       | Epoch (UTC)
! abbr="Periseleneaa"  | Periselene (km) 
! abbr="Aposeleneaa"   | Aposelene (km) 
!                      Eccentricity
! abbr="Inclinationaa" | Inclination (deg)<br>(to Moon equator)
! abbr="Periodic"      | Period (h)
|-
! 15 November 2004, 17:47:12.1 
|align="right"| 6,700.720 ||align="right"| 53,215.151 ||align="right"| 0.776329 ||align="right"| 81.085 ||align="right"| 129.247777
|-
! 4 December 2004 10:37:47.3 
|align="right"| 5,454.925 ||align="right"| 20,713.095 ||align="right"| 0.583085 ||align="right"| 83.035 ||align="right"| 37.304959
|-
! 9 January 2005, 15:24:55.0 
|align="right"| 2,751.511 ||align="right"| 6,941.359 ||align="right"| 0.432261 ||align="right"| 87.892 ||align="right"| 8.409861
|-
! 28 February 2005, 05:18:39.9
|align="right"| 2,208.659 ||align="right"| 4,618.220 ||align="right"| 0.352952 ||align="right"| 90.063603 ||align="right"| 4.970998
|-
! 25 April 2005, 08:19:05.4
|align="right"| 2,283.738 ||align="right"| 4,523.111 ||align="right"| 0.328988 ||align="right"| 90.141407 ||align="right"| 4.949137
|-
! 16 May 2005, 09:08:52.9
|align="right"| 2,291.250 ||align="right"| 4,515.857 ||align="right"| 0.326807 ||align="right"| 89.734929 ||align="right"| 4.949919
|-
! 20 June 2005, 10:21:37.1
|align="right"| 2,256.090 ||align="right"| 4,549.196 ||align="right"| 0.336960 ||align="right"| 90.232619 ||align="right"| 4.947432
|-
! 18 July 2005, 11:14:28.0
|align="right"| 2,204.645 ||align="right"| 4,600.376 ||align="right"| 0.352054 ||align="right"| 90.263741 ||align="right"| 4.947143
|}
ESA announced on 15 February 2005 an extension of the mission of ''SMART-1'' by one year until August 2006. This date was later shifted to 3 September 2006 to enable further scientific observations from Earth.<ref>[http://www.esa.int/esaCP/SEMQFHL8IOE_index_0.html ESA Portal – SMART-1 manoeuvres prepare for mission end<!-- Bot generated title -->] www.esa.int</ref>

===Lunar impact===

SMART-1 impacted the Moon's surface, as planned, on 3 September 2006 at 05:42:22 [[Universal Coordinated Time|UTC]], ending its mission. Moving at approximately 2,000&nbsp;m/s (4,500&nbsp;mph), SMART-1 created an impact visible with ground telescopes from Earth. It is hoped that not only will this provide some data simulating a [[meteor impact]], but also that it might expose materials in the ground, like water ice, to [[spectroscopy|spectroscopic analysis]].

ESA originally estimated that impact occurred at {{Coord|34.4|S|46.2|W|globe:Moon}}.<ref>{{cite web |url=http://www.esa.int/SPECIALS/SMART-1/SEMBY5BVLRE_0.html|title=SMART-1 impacts Moon |date=3 September 2006 |website=[[European Space Agency]] |access-date=3 September 2006 |archive-url=https://web.archive.org/web/20060905050753/http://www.esa.int/SPECIALS/SMART-1/SEMBY5BVLRE_0.html |archive-date=5 September 2006}}</ref> In 2017, the impact site was identified from [[Lunar Reconnaissance Orbiter]] data at {{coord|34.262|S|46.193|W|globe:Moon}}.<ref name="astromag" /> At the time of impact, the Moon was visible in North and South America, and places in the Pacific Ocean, but not Europe, Africa, or western Asia.

This project has generated data and know-how that will be used for other missions, such as the ESA's [[BepiColombo]] mission to [[Mercury (planet)|Mercury]].

==Important events and discoveries==

{| align="right"
|- style="vertical-align: bottom;"
|
| 
|}

*27 September 2003: SMART-1 launched from the European Spaceport in Kourou by an [[Ariane 5]] launcher.
*17 June 2004: SMART-1 took a test image of Earth with the camera that would later be used for Moon closeup pictures. It shows parts of Europe and Africa. It was taken on 21 May with the AMIE camera.
*2 November 2004: Last [[perigee]] of Earth orbit.
*15 November 2004: First [[perilune]] of lunar orbit.
*15 January 2005: Calcium detected in [[Mare Crisium]].
*26 January 2005: First close up pictures of the lunar surface sent back.
*27 February 2005: Reached final orbit around the Moon with an orbital period of about five hours.
*15 April 2005: The search for [[Peak of Eternal Light|PEL]]s begins.
*3 September 2006: Mission ends with a planned crash into the Moon during orbit number 2,890.<ref>[http://www.esa.int/SPECIALS/SMART-1/SEMV386LARE_0.html ESA – SMART-1 – Intense final hours for SMART-1<!-- Bot generated title -->] www.esa.int</ref>

== Smart-1 Ground Segment and Operations ==
[[File:ESA's_SMART-1-_testing_solar_electric_propulsion_and_studying_the_Moon_ESA194476.jpg|thumb|Smart-1 spacecraft]]
[https://www.esa.int/Enabling_Support/Operations/SMART-1 Smart-1] operations were conducted from the ESA European Space Operations Center [https://www.esa.int/About_Us/ESOC ESOC] in Darmstadt Germany led by the Spacecraft Operations Manager  [https://www.linkedin.com/in/octavio-camino-ramos-06ab73b/ Octavio Camino].

The ground segment of Smart-1 was a good example of infrastructure reuse at ESA: Flight Dynamics infrastructure and Data distribution System (DDS) from [https://www.esa.int/Science_Exploration/Space_Science/Rosetta Rosetta], [https://www.esa.int/Science_Exploration/Space_Science/Mars_Express Mars Express] and [https://www.esa.int/Enabling_Support/Operations/Venus_Express Venus Express]. The generic mission control system software [https://www.esa.int/Enabling_Support/Operations/gse/SCOS-2000 SCOS 2000], and a set of generic interface elements use at ESA for the operations of their missions.

The use of CCSDS TLM and TC standards permitted a cost effective tailoring of seven different terminals of the ESA Tracking network ([https://www.esa.int/Enabling_Support/Operations/Estrack ESTRACK]) plus [https://www.dlr.de/content/en/sites/weilheim.html Weilheim] in Germany (DLR).

The components that were developed specifically for Smart-1 were: the simulator; a mix of hardware and software derived from the Electrical Ground Support Equipment EGSE equipment, the Mission Planning System and the Automation System developed from [https://www.rheagroup.com/news/new-generation-toolset-mission-operations-preparation-and-validation MOIS] {{Webarchive|url=https://web.archive.org/web/20190803032612/https://www.rheagroup.com/news/new-generation-toolset-mission-operations-preparation-and-validation |date=3 August 2019 }} (this last based on a prototype implemented for [https://earth.esa.int/web/guest/missions/esa-operational-eo-missions/envisat Envisat]) and a suite of engineering tools called [https://www.esa.int/Enabling_Support/Operations/WebMUST_br_A_web-based_client_for_MUST MUST]. This last permitted the Smart-1 engineers to do anomaly investigation through internet, pioneering at ESA monitoring of spacecraft TLM using mobile phones and [[Personal digital assistant|PDAs]] and receiving spacecraft alarms via [[SMS]].<ref>{{Citation |work=6th ICLCPM 2005 SMART-1 Lunar Mission – Reducing Mission Operations Costs.pdf (O.Camino et al) ESA |title=English: SMART-1 is the first of the European Space Agency's Small Missions for Advanced Research in Technology. |date=22 September 2005 |url=https://commons.wikimedia.org/wiki/File:6th_ICLCPM_2005_SMART-1_Lunar_Mission_-_Reducing_Mission_Operations_Costs.pdf |access-date=8 May 2020}}</ref>
<nowiki/>The Mission Control Team was composed of seven engineers in the Flight Control Team (FCT), a variable group between 2–5 Flight Dynamics engineers and 1–2 Data Systems engineers. Unlike most ESA missions, there were no Spacecraft Controllers (SPACONs), and all operations and mission-planning activities were done by the FCT. This concept originated overtime and night shifts during the first months of the mission but worked well during the cruise and the Moon phases.
The major concern during the first three months of the mission was to leave the radiation belts as soon as possible in order to minimize the degradation of the solar arrays and the star tracker CCDs.

The first and most critical problem came after the first revolution when a failure in the onboard Error Detection and Correction (EDAC) algorithm triggered an autonomous switch to the redundant computer in every orbit causing several reboots, finding the spacecraft in SAFE mode after every pericenter passage. The analysis of the spacecraft telemetry pointed directly to a radiation-triggered problem with the EDAC interrupt routine.<ref name=":1">{{Citation |last=Camino|first=Octavio |title=English: Smart-1 Operations Report (O.Camino et al) |date=10 February 2020 |via=commons.wikimedia.org |url=https://commons.wikimedia.org/wiki/File:RCSGSO_SMART-1_-_Europe%27s_Lunar_Mission_-_Octavio_Camino_(114381).pdf |access-date=8 May 2020}}</ref>

Other anomalies during this period were a combination of environmental problems: high radiation doses, especially in the star trackers and onboard software anomalies: the Reed Solomon encoding became corrupt after switching data rates and had to be disabled. It was overcome by procedures and changes on ground operations approach.
The star trackers were also subject of frequent hiccups during the earth escape and caused some of the Electric Propulsion (EP) interruptions.<ref name=":0">[[c:File:SMART-1_Lunar_Mission_Star_Tracker_Operations_Experience.pdf|SMART]]-1 Lunar Mission Star Tracker Operations Experience (M.Alonso)</ref> They were all resolved with several software patches.

The EP showed sensitivity to radiation inducing shutdowns. This phenomenon identified as the Opto-coupler Single Event Transient (OSET), initially seen in LEOP during the first firing using cathode B, was characterized by a rapid drop in Anode Current triggering the alarm 'Flame Out' bit causing the shutdown of the EP. The problem was identified to be radiation induced Opto-coupler sensitivity. The recovery of such events was to restart the thruster. This was manually done during several months until an On Board Software Patch (OBSW) was developed to detect it and initiate an autonomous thruster restart. Its impact was limited to the orbit prediction calculation used for the Ground Stations to track the spacecraft and the subsequent orbit corrections.

The different kind of anomalies and the frequent interruptions in the thrust of the Electric Propulsion led to an increase of the ground stations support and overtime of the flight operations team who had to react quickly. Their recovery was sometimes time consuming, especially when the spacecraft was found in SAFE mode.<ref>{{Citation |work=SMART-1 AOCS and its relation with electric propulsion system (M.Alonso et al) ESA |title=English: SMART-1 is the first of the European Space Agency's Small Missions for Advanced Research in Technology. |via=commons.wikimedia.org |date=16 October 2005 |url=https://commons.wikimedia.org/wiki/File:SMART-1_AOCS_and_its_relation_with_electric_propulsion_system_GNC_Alonso_Ref166673.pdf |access-date=8 May 2020}}</ref> Overall, they impeded to run the operations as originally planned having one 8 hours pass every 4 days.
[[File:Once_SMART-1_has_been_captured_by_the_Moon's_gravity,_it_begins_to_work_its_way_closer_to_the_lunar_surface_ESA234908.gif|thumb|Smart-1 Moon orbit descend]]
The mission negotiated the use the [https://www.esa.int/Enabling_Support/Operations/Estrack ESTRACK] network spare capacity. This concept permitted about eight times additional network coverage at no extra cost but originated unexpected overheads and conflicts. It ultimately permitted additional contacts with the spacecraft during the early stage of the mission and an important increase of science during the Moon phase. This phase required a major reconfiguration of the on-board stores and its operation. This change designed by the flight control team at ESOC and implemented by the Swedish Space Corporation in a short time required to re-write part of the Flight Control Procedures FOP for the operations at the Moon.

The Operations during the Moon phase become highly automated: the flight dynamics pointing was "menu driven" allowing more than 98% of commanding being generated by the Mission Planning System MPS. The extension of the MPS system with the so called MOIS Executor,<ref name=":1" /> became the Smart-1 automation system. It permitted to operate 70% of the passes unmanned towards the end of the mission and allowed the validation of the first operational "spacecraft automation system" at ESA.<ref>{{Citation |last=Camino|first=Octavio |title=SMART-1 – Europe's Lunar Mission (O.Camino et al) |date=10 February 2020 |url=https://commons.wikimedia.org/wiki/File:RCSGSO_SMART-1_-_Europe%27s_Lunar_Mission_-_Octavio_Camino_(114381).pdf |via=commons.wikimedia.org |access-date=8 May 2020}}</ref>

The mission achieved all its objectives: getting out of the radiation belts influence 3 months after launch, spiraling out during 11 months and being captured by the Moon using resonances, the commissioning and operations of all instruments during the cruise phase and the optimization of the navigation and operational procedures required for Electric Propulsion operation.<ref>D.Milligan [https://commons.wikimedia.org/wiki/File:SMART-1_D.Milligan_SMART-1_Electric_Propulsion_Operational_Experience.pdf Operationally Enhanced Electric Propulsion Performance on Electrically Propelled Spacecraft] via commons.wikimedia.org</ref> The efficient operations of the Electric Propulsion at the Moon allowed the reduction of the orbital radius benefiting the scientific operations and extending this mission by one extra year.

A detailed chronology of the operations events is provided in ref.<ref name=":1" />

== Smart-1 Mission Phases ==

* Launch and Early Orbit Phase: Launch on 27 September 2003, initial orbit 7,029 x 42263&nbsp;km.
* Van Allen Belt Escape: Continuous thrust strategy to raise the perigee radius. Escape phase completed by 22 December 2003, orbit 20000 x 63427&nbsp;km.
* Earth Escape Cruise: Thrust around perigee only to raise the apogee radius.
* Moon resonances and Capture: Trajectory assists by means of Moon resonances. Moon capture on 15 November 2004 at 310,000&nbsp;km from the Earth and 90,000&nbsp;km from the Moon.
* Lunar Descent: Thrust used to lower the orbit, operational orbit 2,200 x 4,600&nbsp;km.
* Lunar Science: Until the end of lifetime in September 2006, interrupted only by a one-month re-boost phase in September 2005 to optimize the lunar orbit.
* Orbit re-boost: Phase in June/July 2006 using the attitude thrusters to adjust the impact date and time.
* Moon Impact: Operations from July 2006 until the impact on 3 September 2006.

The full mission phases from the operations perspective is documented in<ref name=":12">{{Citation |last=Camino|first=Octavio |title=English: Smart-1 Operations Report (O.Camino et al) |date=10 February 2020 |url=https://commons.wikimedia.org/wiki/File:RCSGSO_SMART-1_-_Europe%27s_Lunar_Mission_-_Octavio_Camino_(114381).pdf |via=commons.wikimedia.org |access-date=8 May 2020}}</ref> including the performance of the different subsystems.

==See also==
{{Portal|Spaceflight}}
*[[List of artificial objects on the Moon]]

==References==
{{Reflist|30em}}

;General
*Kaydash V., Kreslavsky M., Shkuratov Yu., Gerasimenko S., Pinet P., Chevrel S., Josset J.-L., Beauvivre S., Almeida M., [[Bernard Foing|Foing B.]] (2007). [http://www.lpi.usra.edu/meetings/lpsc2007/pdf/1535.pdf "PHOTOMETRIC CHARACTERIZATION OF SELECTED LUNAR SITES BY SMART-1 AMIE DATA"]. ''Lunar Planetary Science, XXXVIII,'' abstract 1535.

==External links==
{{Commons}}
*{{Official website}}
*[http://sci.esa.int/science-e/www/area/index.cfm?fareaid=10 ESA SMART-1 scientific website]
*[https://web.archive.org/web/20040106163407/http://www.solarsystem.nasa.gov/missions/profile.cfm?MCode=SMART-1 SMART-1 Mission Profile] by [http://solarsystem.nasa.gov NASA's Solar System Exploration]
*[http://www.cfht.hawaii.edu/News/Smart1/ Observation of the Impact of Smart-1]
*[http://viva-fizika.org/content.php?article.21 SMART 1 on Serbian science portal Viva fizika] {{Webarchive|url=https://web.archive.org/web/20070928221629/http://viva-fizika.org/content.php?article.21 |date=28 September 2007 }}
*[http://www.lpi.usra.edu/publications/newsletters/lpib/lpib101.pdf SMART-1, Europe at the Moon]

{{Moon spacecraft}}
{{European Space Agency}}
{{Orbital launches in 2003}}

{{DEFAULTSORT:Smart-1}}
[[Category:Missions to the Moon]]
[[Category:Hall effect]]
[[Category:European Space Agency space probes]]
[[Category:Space programme of Sweden]]
[[Category:Space probes launched in 2003]]
[[Category:Spacecraft that impacted the Moon]]
[[Category:2003 establishments in South America]]
[[Category:2006 on the Moon]]