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63-717: RAISE-2 ( RApid Innovative payload demonstration SatellitE-2 ) was a smallsat for technology demonstration , part of the Japanese space agency JAXA 's Innovative Satellite Technology Demonstration Program . RAISE-2 was launched on 9 November 2021 as the main satellite of Innovative Satellite Technology Demonstration-2. RAISE-2 was developed by Mitsubishi Electric . RAISE-2 was decommissioned on 7 April 2023. RAISE-2 carried six payloads that were tested in orbit during its one year mission. The payloads were selected in December 2018. Smallsat One rationale for miniaturizing satellites

126-435: A formation . The generic term "small satellite" or "smallsat" is also sometimes used, as is "satlet". Examples: Astrid-1 and Astrid-2, as well as the set of satellites currently announced for LauncherOne (below) In 2018, the two Mars Cube One microsats—massing just 13.5 kg (30 lb) each—became the first CubeSats to leave Earth orbit for use in interplanetary space. They flew on their way to Mars alongside

189-464: A 10 kg (22 lb) payload into a 250 km (160 mi) orbit to an even-more-capable clustered "20/450 Nano/Micro Satellite Launch Vehicle" (NMSLV) capable of delivering 20 kg (44 lb) payloads into 450 km (280 mi) circular orbits . The Boeing Small Launch Vehicle is an air-launched three-stage-to-orbit launch vehicle concept aimed to launch small payloads of 45 kg (100 lb) into low Earth orbit. The program

252-435: A larger "mother" satellite for communication with ground controllers or for launching and docking with picosatellites. Picosatellites are emerging as a new alternative for do-it-yourself kitbuilders. Picosatellites are currently commercially available across the full range of 0.1–1 kg (0.22–2.2 lb). Launch opportunities are now available for $ 12,000 to $ 18,000 for sub-1 kg picosat payloads that are approximately

315-425: A market value estimated at US$ 7.4 billion . By mid-2015, many more launch options had become available for smallsats, and rides as secondary payloads had become both greater in quantity and easier to schedule on shorter notice. In a surprising turn of events, the U.S. Department of Defense , which had for decades procured heavy satellites on decade-long procurement cycles, is making a transition to smallsats in

378-433: A mass of no more than 1.33 kilograms (2.9 lb) per unit. The CubeSat concept was first developed in 1999 by a collaborative team of California Polytechnic State University and Stanford University , and the specifications, for use by anyone planning to launch a CubeSat-style nanosatellite, are maintained by this group. With continued advances in the miniaturization and capability increase of electronic technology and

441-474: A number of companies began development of launch vehicles specifically targeted at the smallsat market. In particular, with larger numbers of smallsats flying, the secondary payload paradigm does not provide the specificity required for many small satellites that have unique orbital and launch-timing requirements. Some USA-based private companies that at some point in time have launched smallsat launch vehicles commercially: The term "microsatellite" or "microsat"

504-408: A power consumption of 4.1 watts. The Electric Propulsion Diagnostic Package was to acquire data on the new propulsion system on SMART-1. The package weighed 0.8 kg and had a power consumption of 1.8 watts. The Spacecraft Potential, Electron and Dust Experiment. The experiment weighed 0.8 kg and had a power consumption of 1.8 watts. Its function was to measure the properties and density of

567-527: A power consumption of 9 watts. 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

630-506: 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 ( ESTRACK ) plus Weilheim in Germany (DLR). The components that were developed specifically for Smart-1 were: the simulator; a mix of hardware and software derived from

693-681: Is designed to form a quantum communication network as well as communicate with Earth through an optical ground station. The term "small satellite", or sometimes "minisatellite", often refers to an artificial satellite with a wet mass (including fuel) between 100 and 500 kg (220 and 1,100 lb), but in other usage has come to mean any satellite under 500 kg (1,100 lb). Small satellite examples include Demeter , Essaim , Parasol , Picard , MICROSCOPE , TARANIS , ELISA , SSOT , SMART-1 , Spirale-A and -B , and Starlink satellites. Although smallsats have traditionally been launched as secondary payloads on larger launch vehicles,

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756-517: Is proposed to drive down launch costs for U.S. military small satellites to as low as US$ 300,000 per launch ($ 7,000/kg) and, if the development program was funded, as of 2012 could be operational by 2020. The Swiss company Swiss Space Systems (S3) has announced plans in 2013 to develop a suborbital spaceplane named SOAR that would launch a microsat launch vehicle capable of putting a payload of up to 250 kg (550 lb) into low Earth orbit. The Spanish company PLD Space born in 2011 with

819-695: Is the opportunity to enable missions that a larger satellite could not accomplish, such as: The nanosatellite and microsatellite segments of the satellite launch industry have been growing rapidly in the 2010s. Development activity in the 1–50 kg (2.2–110.2 lb) range has been significantly exceeding that in the 50–100 kg (110–220 lb) range. In the 1–50 kg range alone, fewer than 15 satellites were launched annually in 2000 to 2005, 34 in 2006, then fewer than 30 launches annually during 2007 to 2011. This rose to 34 launched in 2012 and 92 launched in 2013. European analyst Euroconsult projects more than 500 smallsats being launched in 2015–2019 with

882-478: Is to reduce the cost; heavier satellites require larger rockets with greater thrust that also have greater cost to finance. In contrast, smaller and lighter satellites require smaller and cheaper launch vehicles and can sometimes be launched in multiples. They can also be launched 'piggyback', using excess capacity on larger launch vehicles. Miniaturized satellites allow for cheaper designs and ease of mass production. Another major reason for developing small satellites

945-422: Is usually applied to the name of an artificial satellite with a wet mass between 10 and 100 kg (22 and 220 lb). However, this is not an official convention and sometimes those terms can refer to satellites larger than that, or smaller than that (e.g., 1–50 kg (2.2–110.2 lb)). Sometimes, designs or proposed designs from some satellites of these types have microsatellites working together or in

1008-510: The Earth-Moon L 1 Lagrangian Point and into the area dominated by the Moon's gravitational influence, and at 1748 UT on 15 November passed the first periselene of its lunar orbit. The osculating orbit on that date was 6,704 × 53,208 km, with an orbital period of 129 hours, although the actual orbit was accomplished in only 89 hours. This illustrates the significant impact that

1071-481: The PicoSAT series of microsatellites) is usually applied to artificial satellites with a wet mass between 0.1 and 1 kg (0.22 and 2.2 lb), although it is sometimes used to refer to any satellite that is under 1 kg in launch mass. Again, designs and proposed designs of these types usually have multiple picosatellites working together or in formation (sometimes the term "swarm" is applied). Some designs require

1134-583: 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

1197-595: The 2020s. The office of space acquisition and integration said in January 2023 that "the era of massive satellites needs to be in the rear view mirror for the Department of Defense" with small satellites being procured for DoD needs in all orbital regimes, regardless of "whether it's LEO MEO or GEO " while aiming for procurements in under three years. The smaller satellites are deemed to be harder for an enemy to target, as well as providing more resilience through redundancy in

1260-466: The DARPA SeeMe program that intended to release a " constellation of 24 micro-satellites (~20 kg (44 lb) range) each with 1-m imaging resolution ." The program was cancelled in December 2015. In April 2013, Garvey Spacecraft was awarded a US$ 200,000 contract to evolve their Prospector 18 suborbital launch vehicle technology into an orbital nanosat launch vehicle capable of delivering

1323-756: The ESA's BepiColombo mission to Mercury . Smart-1 operations were conducted from the ESA European Space Operations Center ESOC in Darmstadt Germany led by the Spacecraft Operations Manager 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 Rosetta , Mars Express and Venus Express . The generic mission control system software SCOS 2000 , and

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1386-513: 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: As part of the European Space Agency's strategy to build very inexpensive and relatively small spaceships , the total cost of SMART-1 was a relatively small 110 million euros (about 170 million U.S. dollars ). SMART-1 was designed and developed by

1449-839: The Electrical Ground Support Equipment EGSE equipment, the Mission Planning System and the Automation System developed from MOIS Archived 3 August 2019 at the Wayback Machine (this last based on a prototype implemented for Envisat ) and a suite of engineering tools called 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 PDAs and receiving spacecraft alarms via SMS . The Mission Control Team

1512-454: The ISS external platform Materials International Space Station Experiment (MISSE-8) for testing. In April 2014, the nanosatellite KickSat was launched aboard a Falcon 9 rocket with the intention of releasing 104 femtosatellite-sized chipsats, or "Sprites". In the event, they were unable to complete the deployment on time due to a failure of an onboard clock and the deployment mechanism reentered

1575-555: The Moon's surface, as planned, on 3 September 2006 at 05:42:22 UTC , ending its mission. Moving at approximately 2,000 m/s (4,500 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 spectroscopic analysis . ESA originally estimated that impact occurred at 34°24′S 46°12′W  /  34.4°S 46.2°W  / -34.4; -46.2 . In 2017,

1638-524: 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, became the Smart-1 automation system. It permitted to operate 70% of the passes unmanned towards the end of the mission and allowed

1701-676: 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)

1764-570: 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. They were all resolved with several software patches. The EP showed sensitivity to radiation inducing shutdowns. This phenomenon identified as

1827-666: 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 Octavio Camino . 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 nm was able to take images with an average pixel resolution of 80 m (about 260 ft). The camera weighed 2.1 kg (about 4.5 lb) and had

1890-924: The atmosphere and burned up. Small satellites usually require innovative propulsion, attitude control , communication and computation systems. Larger satellites usually use monopropellants or bipropellant combustion systems for propulsion and attitude control; these systems are complex and require a minimal amount of volume to surface area to dissipate heat. These systems may be used on larger small satellites, while other micro/nanosats have to use electric propulsion, compressed gas, vaporizable liquids such as butane or carbon dioxide or other innovative propulsion systems that are simple, cheap and scalable. Small satellites can use conventional radio systems in UHF, VHF, S-band and X-band, although often miniaturized using more up-to-date technology as compared to larger satellites. Tiny satellites such as nanosats and small microsats may lack

1953-595: The atmosphere on 14 May 2014, without having deployed any of the 5-gram femtosats. ThumbSat is another project intending to launch femtosatellites in the late 2010s. ThumbSat announced a launch agreement with CubeCat in 2017 to launch up to 1000 of the very small satellites. In March 2019, the CubeSat KickSat-2 deployed 105 femtosats called "ChipSats" into Earth orbit. Each of the ChipSats weighed 4 grams. The satellites were tested for 3 days, and they then reentered

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2016-413: 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

2079-655: The design of LauncherOne". Virgin Orbit has been working on the LauncherOne concept since late 2008, and as of 2015 , is making it a larger part of Virgin's core business plan as the Virgin human spaceflight program has experienced multiple delays and a fatal accident in 2014. In December 2012, DARPA announced that the Airborne Launch Assist Space Access program would provide the microsatellite rocket booster for

2142-645: The design of a large distributed network of satellite assets . In 2021, the first autonomous nanosatellites , part of the Adelis-SAMSON mission, designed and developed by the Technion and Rafael in Israel were launched into space. In 2023, SpaceX launched a 20cm quantum communication nano satellite developed by the Tel Aviv University , it is the world's first quantum communication satellite. TAU's nanosatellite

2205-428: The emergence of the technological advances of miniaturization and increased capital to support private spaceflight initiatives in the 2010s, several startups have been formed to pursue opportunities with developing a variety of small-payload Nanosatellite Launch Vehicle (NLV) technologies. NLVs proposed or under development include: Actual NS launches: The term "picosatellite" or "picosat" (not to be confused with

2268-441: 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. 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. SMART-1 impacted

2331-526: The impact site was identified from Lunar Reconnaissance Orbiter data at 34°15′43″S 46°11′35″W  /  34.262°S 46.193°W  / -34.262; -46.193 . 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

2394-412: 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 m/s. The electric propulsion subsystem weighted 29 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

2457-493: The mission, were able to provide the maximum set of 1,190 W to the thruster, giving a nominal thrust of 68 mN, hence an acceleration of 0.2 mm/s or 0.7 m/s per hour (i.e., just under 0.00002 g of acceleration). As with all ion-engine powered craft, orbital maneuvers 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

2520-482: The objective of developing low cost launch vehicles called Miura 1 and Miura 5 with the capacity to place up to 150 kg (330 lb) into orbit. The term "nanosatellite" or "nanosat" is applied to an artificial satellite with a wet mass between 1 and 10 kg (2.2 and 22.0 lb). Designs and proposed designs of these types may be launched individually, or they may have multiple nanosatellites working together or in formation, in which case, sometimes

2583-653: The opportunity to test new hardware with reduced expense in testing. Furthermore, since the overall cost risk in the mission is much lower, more up-to-date but less space-proven technology can be incorporated into micro and nanosats than can be used in much larger, more expensive missions with less appetite for risk. Small satellites are difficult to track with ground-based radar, so it is difficult to predict if they will collide with other satellites or human-occupied spacecraft. The U.S. Federal Communications Commission has rejected at least one small satellite launch request on these safety grounds. SMART-1 SMART-1

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2646-447: The orbit was 179,718 × 305,214 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 kg of xenon and produced a delta-v of 2,737 m/s (46.5 m/s per kg xenon, 0.75 m/s per hour on-time). It

2709-508: 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 2003 solar storms . It was built by Finnish Meteorological Institute and its name

2772-514: The power supply or mass for large conventional radio transponders , and various miniaturized or innovative communications systems have been proposed, such as laser receivers, antenna arrays and satellite-to-satellite communication networks. Few of these have been demonstrated in practice. Electronics need to be rigorously tested and modified to be "space hardened" or resistant to the outer space environment (vacuum, microgravity, thermal extremes, and radiation exposure). Miniaturized satellites allow for

2835-518: 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. Other anomalies during this period were a combination of environmental problems: high radiation doses, especially in the star trackers and onboard software anomalies:

2898-929: The same mission cost, with significantly increased revisit times: every area of the globe can be imaged every 3.5 hours rather than the once per 24 hours with the RapidEye constellation. More rapid revisit times are a significant improvement for nations performing disaster response, which was the purpose of the RapidEye constellation. Additionally, the nanosat option would allow more nations to own their own satellite for off-peak (non-disaster) imaging data collection. As costs lower and production times shorten, nanosatellites are becoming increasingly feasible ventures for companies. Example nanosatellites: ExoCube (CP-10) , ArduSat , SPROUT Nanosatellite developers and manufacturers include EnduroSat , GomSpace , NanoAvionics , NanoSpace, Spire , Surrey Satellite Technology , NovaWurks , Dauria Aerospace , Planet Labs and Reaktor . In

2961-690: The secondary payload paradigm does not provide the specificity required for many increasingly sophisticated small satellites that have unique orbital and launch-timing requirements. In July 2012, Virgin Orbit announced LauncherOne , an orbital launch vehicle designed to launch "smallsat" primary payloads of 100 kg (220 lb) into low Earth orbit , with launches projected to begin in 2016. Several commercial customers have already contracted for launches, including GeoOptics , Skybox Imaging , Spaceflight Industries , and Planetary Resources . Both Surrey Satellite Technology and Sierra Nevada Space Systems are developing satellite buses "optimized to

3024-525: The size of a soda can. The term "femtosatellite" or "femtosat" is usually applied to artificial satellites with a wet mass below 100 g (3.5 oz). Like picosatellites, some designs require a larger "mother" satellite for communication with ground controllers. Three prototype "chip satellites" were launched to the ISS on Space Shuttle Endeavour on its final mission in May 2011. They were attached to

3087-521: 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 kg and had a power consumption of 18 watts. The X-ray solar monitor studied the solar variability to complement D-CIXS measurements. The Smart-1 Infrared Spectrometer was an infrared spectrometer for the identification of mineral spectra of olivine and pyroxene . It detected wavelengths from 0.93 to 2.4 μm with 256 channels. The package weighed 2.3 kg and had

3150-476: 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

3213-608: The successful Mars InSight lander mission. The two microsats accomplished a flyby of Mars in November 2018, and both continued communicating with ground stations on Earth through late December. Both went silent by early January 2019. A number of commercial and military-contractor companies are currently developing microsatellite launch vehicles to perform the increasingly targeted launch requirements of microsatellites. While microsatellites have been carried to space for many years as secondary payloads aboard larger launchers ,

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3276-564: The ten years of nanosat launches prior to 2014, only 75 nanosats were launched. Launch rates picked up substantially when in the three-month period from November 2013–January 2014 94 nanosats were launched. One challenge of using nanosats has been the economic delivery of such small satellites to anywhere beyond low Earth orbit . By late 2014, proposals were being developed for larger spacecraft specifically designed to deliver swarms of nanosats to trajectories that are beyond Earth orbit for applications such as exploring distant asteroids. With

3339-417: The term "satellite swarm" or " fractionated spacecraft " may be applied. Some designs require a larger "mother" satellite for communication with ground controllers or for launching and docking with nanosatellites. Over 2300 nanosatellites have been launched as of December 2023. A CubeSat is a common type of nanosatellite, built in cube form based on multiples of 10 cm × 10 cm × 10 cm, with

3402-414: The use of satellite constellations , nanosatellites are increasingly capable of performing commercial missions that previously required microsatellites. For example, a 6U CubeSat standard has been proposed to enable a satellite constellation of thirty five 8 kg (18 lb) Earth-imaging satellites to replace a constellation of five 156 kg (344 lb) RapidEye Earth-imaging satellites, at

3465-485: The validation of the first operational "spacecraft automation system" at ESA. 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. The efficient operations of

3528-456: Was 367 kg or 809 pounds, of which 287 kg (633 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 litres tank at a pressure of 150 bar at launch. The ion engine thruster used an electrostatic field to ionize the xenon and accelerate the ions achieving a specific impulse of 16.1 kN·s/kg (1,640 seconds), more than three times

3591-712: Was a Swedish-designed European Space Agency satellite that orbited the Moon . It was launched on 27 September 2003 at 23:14 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. SMART-1 was about one meter across (3.3 ft), and lightweight in comparison to other probes. Its launch mass

3654-521: 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

3717-660: Was designed as precursor for BepiColombo to perform radio science investigations and to monitor the dynamical performance of the electric propulsion system. SMART-1 was launched 27 September 2003 together with Insat 3E and 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 × 42,223 km. 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 spaceref.com , when

3780-519: 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

3843-450: 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 . K a band TT&C (telemetry, tracking and control) Experiment. The experiment weighed 6.2 kg and had a power consumption of 26 watts. The Ka-band transponder

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3906-403: 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 km above the Moon's surface. The end of mission performance demonstrated by the propulsion system is stated above. After its last perigee on 2 November, on 11 November 2004 it passed through

3969-495: Was sometimes time consuming, especially when the spacecraft was found in SAFE mode. Overall, they impeded to run the operations as originally planned having one 8 hours pass every 4 days. The mission negotiated the use the 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

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