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telemetry information that will help determine each satellite's status. During this phase the ground station will attempt to establish first contact with the satellites and perform a check out procedure to make sure all the subsystems on board are working correctly. It is expected that this checkout procedure will take several hours or even a few days depending on the duration of the communication passes with the ground station. Once the operators are satisfied with the status of the satellites, the satellites will be commanded from the ground to separate, finalizing the third phase of the mission.
477:, a grant-based competition that included 12 other participating universities. As a winner, FASTRAC was given the opportunity to launch its satellites into space. The student-led team received $ 100,000 from AFRL for the competition portion of the project, and another $ 100,000 for the implementation phase. FASTRAC is the first student-developed satellite mission incorporating on-orbit real-time relative navigation, on-orbit real-time attitude determination using a single GPS antenna, and a micro-discharge plasma thruster.
576:. The FASTRAC implementation consists of two receivers, one transmitter, a terminal node controller (TNC), a transmitter relay board, and a receiver relay board. On FASTRAC 1 "Sara Lily", two R-100 VHF receivers and one TA-451 UHF transmitter from Hamtronics are used. On FASTRAC 2 "Emma", two R-451 UHF receivers and one TA-51 VHF transmitter from Hamtronics are used. The TNC used is a KPC-9612+ from Kantronics. Both the transmitter and receiver relay boards were designed and manufactured in house.
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540:(APRS) network. This will make the satellites available to amateur radio users all around the world. Once the ground station loses all communication with the satellites, the mission will be terminated and the satellites will passively de-orbit, burning up in the atmosphere. The FASTRAC team has estimated that it will take six months to successfully achieve its mission objectives.
466:(AFRL), whose goal is to lead the development of affordable space technology. The FASTRAC mission will specifically investigate technologies that facilitate the operation of multiple satellites in formation. These enabling technologies include relative navigation, cross-link communications, attitude determination, and thrust. Due to the high cost of lifting mass into
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measurements provided by the GPS attitude determination system. After enabling the operation of the thruster from the ground, it will be only be active when one of the two nozzles is within a 15 degree cone of the anti-velocity vector. The thruster subsystem is only present on FASTRAC 1 "Sara Lily".
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The main mission sequence is composed of six distinct phases: Launch, Launch
Vehicle Separation, Initial Acquisition, GPS Onboard Relative Navigation, Onboard Single Antenna GPS Attitude Determination and Micro-discharge Plasma Thruster Operation, and Amateur Radio Operations. In the first phase, the
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was designed and built at UT-Austin. The thruster channels and superheats an inert gas through a micro-channel nozzle producing a micro-Newton level of thrust. It uses a custom made composite tank from CTD. The operation of the thruster will be automated by the spacecraft C&DH using the attitude
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Mission from Kodiak Launch
Complex (KLC) in Kodiak, Alaska. They will be transported to a 72 degree inclination circular low Earth orbit with an altitude of 650 km by a Minotaur IV rocket. Initially, the two nanosatellites will be in a stacked configuration. Once the rocket reaches the desired
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There are two separation systems for the FASTRAC satellites, both designed and manufactured by
Planetary Systems Corporation (PSC), which will be used to separate the satellites in their stacked configuration from the Launch Vehicle and then to separate the two satellites while they are in orbit.
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The third phase will begin once the two nanosatellites are ejected from the rocket. During this phase, there will be a 30-minute period where the satellites will go through a check out and initialization process. After this period, the satellites will begin transmitting beacon messages containing
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The structure of the FASTRAC satellites is a hexagonal iso-grid design that is composed of two titanium adapter plates, aluminum 6061 T-6 side panels, six hollow outer columns with inserts and six inner columns. The mass of the two nanosatellites is approximately 127 lbs with all of the
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The fifth phase will activate a micro-discharge plasma thruster with a command from the ground that will autonomously operate when the thrusting vector is within a 15 degree cone of the anti-velocity vector. The thruster operation will be dependent on the on-orbit real-time single antenna GPS
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provided to the team by AFRL. Both the solar panels and the VREG board were designed and made in-house. On each satellite, the VREG board distributes power from three VICOR VI-J00 voltage regulators, and also charges the batteries with the power collected from the solar panels.
470:, there is a strong initiative to miniaturize the overall weight of spacecraft. The utilization of formations of satellites, in place of large single satellites, reduces the risk of single point failure and allows for the use of low-cost hardware.
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When the satellites have successfully separated, the primary mission will begin, signaling the start of fourth phase. First, the satellites will autonomously establish a cross-link, or in other words, they will communicate with each other through
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The FASTRAC satellites transmit and receive data (GPS, Health, etc.) on amateur radio frequencies. All amateur radio operators are encouraged to downlink data from either satellite and upload the data to the radio operator section on the
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The GPS position and attitude determination system was designed and built by student researchers at The
University of Texas' GPS Research Lab. The system utilizes GPS code measurements, as well as antenna
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measurements to provide estimates of position, velocity, and attitude. Each satellite will have redundant ORION GPS receivers, dual cross-strapped antennas with RF switching and splitting hardware.
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592:. Each AVR has an Atmega 128 microcontroller and controls an individual subsystem on the satellite (i.e.: COM, EPS, GPS, and THR or IMU). The AVRs communicate with each other through the
499:'s list of prioritised spacecraft experiments in 2006. The spacecraft were expected to demonstrate Global Positioning System relative navigation and micro-charge thruster performance.
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bands. The satellites will then exchange GPS data through this cross-link in order to calculate on-orbit real time relative navigation solutions.
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The final phase of the mission will start once the communication architecture of the satellites is reconfigured from the ground to work with the
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attitude determination solution. After this phase is over, a command from the ground station will disable the thruster on FASTRAC 1.
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FASTRAC was developed under the US Air Force
Research Laboratory University Nanosatellite Program, and was ranked number 32 in the
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are underlined. Launch failures are marked with the † sign. Payloads deployed from other spacecraft are (enclosed in parentheses).
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Launches are separated by dots ( • ), payloads by commas ( , ), multiple names for the same satellite by slashes ( / ).
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orbit, the satellites will be powered on by the launch vehicle before finally separating from the launch vehicle.
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The PSC Lightband
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492:. Separation of the satellites from each other and cross-link communication were successfully carried out.
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664:(IMU) MASIMU01 from Micro Aerospace Solutions is used to measure the separation of the two satellites.
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First student-developed mission in which satellites orbit and communicate led by UT students
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Please help update this article to reflect recent events or newly available information.
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Smith, A., Muñoz, S., Hagen, E., Johnson, G.P., & Lightsey, E.G. (2008, August)
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two nanosatellites will be launched on the
Department of Defense Space Test Program
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The command & data handling (C&DH) system is composed by four distributed
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813:. 25th AIAA/USU Conference on Small Satellites. 9 August 2011. Logan, Utah.
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22nd Annual USU/AIAA Small
Satellite Conference, Logan, Utah, SSC08-XII-4.
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The FASTRAC Mission: Operations
Summary and Preliminary Experiment Results
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Formation
Autonomy Spacecraft with Thrust, Relnav, Attitude, and Crosslink
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Formation Autonomy Spacecraft with Thrust, Relnav, Attitude and Crosslink
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The communications architecture is based on a system flown on
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916:"The FASTRAC Satellites: Software Implementation and Testing"
904:, University of Texas at Austin press release, 24 March 2011.
832:. Texas Spacecraft Laboratory, University of Texas at Austin
854:. University of Texas at Austin. 2010-11-02. Archived from
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The power system for each satellite is composed of eight
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https://digitalcommons.usu.edu/smallsat/2011/all2011/24/
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On FASTRAC 2 "Emma", instead of using a thruster, an
462:. The project is part of a program sponsored by the
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93:. Unsourced material may be challenged and removed.
473:In January 2005, the University of Texas won the
880:. University of Texas at Austin. Archived from
789:. University of Texas at Austin. Archived from
480:FASTRAC launched on 19 November 2010 aboard a
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153:Learn how and when to remove this message
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807:Muñoz, Sebastián; et al. (2011).
458:) developed and built by students at
7:
1594:Dragon Spacecraft Qualification Unit
91:adding citations to reliable sources
1002:(AFRL) spacecraft and air vehicles
25:
730:145.825 MHz AX.25 1200 AFSK
538:Automatic Packet Reporting System
460:The University of Texas at Austin
727:437.345 MHz AX.25 1200 AFSK
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876:Muñoz, Sebastian (2010-11-02).
656:Inertial Measurement Unit (IMU)
643:Micro-Discharge Plasma Thruster
278:Total: 58 kg (127 lb)
78:needs additional citations for
497:Space Experiments Review Board
243:
1:
1000:Air Force Research Laboratory
548:FASTRAC Concept of Operations
464:Air Force Research Laboratory
270:University of Texas at Austin
215:University of Texas at Austin
475:University Nanosat-3 Program
668:Amateur Radio Participation
580:Command & Data Handling
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1205:Tactical Satellite Program
1065:University Nanosat Program
852:"FASTRAC Project Overview"
568:Communication Architecture
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2016:SpaceX COTS Demo Flight 1
784:"FASTRAC: Press Kit 2010"
662:Inertial Measurement Unit
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40:This article needs to be
1142:Technology demonstrators
1106:Space weather satellites
588:which were developed by
190:FASTRAC 1 ("Sara-Lily")
1008:Launch/orbital vehicles
299:20 November 2010, 01:21
1047:Space Maneuver Vehicle
878:"FASTRAC News Archive"
590:Santa Clara University
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697:FASTRAC 1 "Sara Lily"
688:Operation Frequencies
607:signal-to-noise ratio
564:components included.
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486:Kodiak Launch Complex
380:Reference system
330:Kodiak Launch Complex
262:Spacecraft properties
1283:Orbital launches in
1039:Orbital Test Vehicle
763:437.345 MHz FM
750:435.025 MHz FM
715:145.825 MHz FM
647:The micro-discharge
450:(respectively named
165:For other uses, see
87:improve this article
1950:USA-222 / FASTRAC-2
1946:USA-222 / FASTRAC-1
941:"FASTRAC Media Kit"
760:145.825 MHz FM
747:145.980 MHz FM
712:437.345 MHz FM
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2107:Student satellites
756:Uplink (9600 Baud)
680:2010-11-23 at the
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375:Orbital parameters
303:2010-11-20UTC01:21
192:FASTRAC 2 ("Emma")
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1961:USA-219 / O/OREOS
1928:USA-220 / FASTSAT
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796:on 14 March 2012.
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700:FASTRAC 2 "Emma"
634:Separation System
609:(SNR) and 3-axis
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953:on 2011-07-20
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143:November 2010
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104: –
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98:Find sources:
92:
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76:This article
74:
70:
65:
64:
55:
43:
38:
29:
28:
19:
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2054:Soyuz TMA-20
2052:
2000:
1976:Chinasat 20A
1949:
1945:
1879:Eutelsat W3B
1836:
1625:Soyuz TMA-19
1623:
1598:
1504:
1461:
1444:
1439:Soyuz TMA-18
1437:
1422:EchoStar XIV
1332:
1081:
1054:
1046:
1038:
1027:
1017:Venture Star
1016:
955:. Retrieved
948:the original
935:
923:the original
909:
897:
886:. Retrieved
882:the original
871:
860:. Retrieved
856:the original
846:
834:. Retrieved
824:
809:
802:
791:the original
778:
755:
735:
720:
705:
671:
659:
646:
637:
623:solar panels
620:
617:Power System
611:magnetometer
603:
583:
571:
562:
547:
535:
531:
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506:
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267:Manufacturer
201:Mission type
149:
140:
130:
123:
116:
109:
97:
85:Please help
80:verification
77:
49:
41:
2048:Perseus 003
2044:Perseus 002
2040:Perseus 001
2036:Perseus 000
1981:Intelsat 17
1942:FalconSat-5
1933:NanoSail-D2
1807:Kosmos 2469
1769:Kosmos 2468
1765:Kosmos 2467
1756:Chinasat-6A
1751:Kosmos 2466
1747:Kosmos 2465
1743:Kosmos 2464
1708:Nilesat 201
1671:Cartosat-2B
1666:EchoStar XV
1606:Shijian XII
1541:Waseda-SAT2
1484:Kosmos 2463
1469:Kosmos 2462
1392:Kosmos 2461
1381:Kosmos 2460
1370:Kosmos 2459
1354:Intelsat 16
1339:Tranquility
1159:MightySat-2
1154:MightySat-1
482:Minotaur IV
421:Inclination
415:652 km
405:641 km
326:Launch site
319:Minotaur IV
296:Launch date
275:Launch mass
2024:SMDC-ONE 1
1919:SkyTerra-1
1909:Fengyun 3B
1904:Meridian 3
1888:Compass-G4
1832:Shijian 6H
1828:Shijian 6G
1727:Tian Hui 1
1641:Arabsat-5A
1584:Compass-G3
1558:COMSATBw-2
1307:Compass-G1
1207:satellites
1190:(canceled)
1172:(canceled)
1169:TechSat-21
1032:(canceled)
1028:Blackswift
1021:(canceled)
957:2010-11-08
888:2010-11-08
862:2010-11-08
836:24 October
770:References
554:Subsystems
503:Operations
384:Geocentric
336:Contractor
113:newspapers
52:April 2016
2020:Mayflower
1823:Chang'e 2
1789:Yaogan 11
1779:Michibiki
1736:September
1717:Yaogan 10
1549:Negai ☆''
1457:CryoSat-2
1417:Yaogan 9C
1413:Yaogan 9B
1409:Yaogan 9A
1396:GLONASS-M
1385:GLONASS-M
1374:GLONASS-M
1055:WaveRider
815:See also
559:Structure
452:Sara-Lily
394:Low Earth
234:2010-062M
228:2010-062F
222:COSPAR ID
102:"FASTRAC"
2101:Category
1994:December
1924:STPSat-2
1897:November
1761:Gonets-M
1683:AISSat-1
1675:AlSat-2A
1645:Chollian
1631:TanDEM-X
1600:STSAT-2B
1579:SERVIS-2
1554:Astra 3B
1521:Akatsuki
1321:February
1234:TacSat-5
1229:TacSat-4
1224:TacSat-3
1219:TacSat-2
1214:TacSat-1
1187:PnPSat-1
1123:Coriolis
707:Downlink
678:Archived
359:Disposal
321:Flight 3
211:Operator
2066:GSAT-5P
1985:HYLAS-1
1971:Orion 7
1967:USA-223
1938:USA-221
1914:COSMO-4
1883:BSat 3B
1816:October
1802:USA-216
1784:USA-215
1722:USA-214
1687:TIsat-1
1679:StudSat
1563:USA-213
1537:Shin'en
1515:ICC-VLD
1511:Rassvet
1506:STS-132
1474:USA-212
1446:STS-131
1334:STS-130
1300:January
1082:FASTRAC
1072:Program
1026:HTV-3X
627:D-cells
594:I2C bus
510:STP-S26
444:FASTRAC
301: (
242:SATCAT
173:FASTRAC
167:Fastrac
127:scholar
42:updated
2072:KA-SAT
1763:No.2,
1701:August
1636:Ofek-9
1615:Picard
1611:Prisma
1589:Badr-5
1545:Hayato
1533:DCAM-2
1529:DCAM-1
1525:IKAROS
1463:GSAT-4
1343:Cupola
1292:2011 →
1277:← 2009
1195:ANGELS
1177:XSS-11
1164:XSS-10
1128:C/NOFS
1053:X-51A
1045:X-40A
739:(1200
737:Uplink
722:Beacon
574:PCSat2
390:Regime
315:Rocket
307:
231:&
129:
122:
115:
108:
100:
2032:QbX-2
2028:QbX-1
1619:BPA-1
1479:SES-1
1431:April
1363:March
1118:TSX-5
1113:ARGOS
1097:ELFIN
1092:DANDE
1087:CUSat
1037:X-37
1015:X-33
998:U.S.
951:(PDF)
944:(PDF)
926:(PDF)
919:(PDF)
794:(PDF)
787:(PDF)
468:orbit
187:Names
134:JSTOR
120:books
1844:XM-5
1659:July
1572:June
1285:2010
1182:ISAT
1149:TAOS
838:2019
741:Baud
586:AVRs
456:Emma
454:and
442:(or
106:news
1936:),
1535:),
1498:May
1399:735
1388:732
1377:731
1349:SDO
1133:DSX
1077:3CS
527:VHF
523:UHF
488:in
425:72°
309:UTC
244:no.
89:by
2103::
2046:,
2042:,
2038:,
2034:,
2030:,
2026:,
2022:,
2018:,
2008:,
2004:,
1983:,
1969:/
1958:,
1952:,
1948:,
1944:,
1940:/
1926:,
1881:,
1867:,
1863:,
1859:,
1855:,
1851:,
1830:,
1795:,
1791:,
1767:,
1749:,
1745:,
1710:,
1685:,
1681:,
1677:,
1673:,
1643:,
1617:,
1613:,
1556:,
1547:,
1543:,
1539:,
1531:,
1523:,
1513:,
1415:,
1411:,
1394:/
1390:,
1383:/
1379:,
1372:/
1341:,
684:.
596:.
1930:(
1527:(
1517:)
1509:(
1453:)
1449:(
1345:)
1337:(
1268:e
1261:t
1254:v
991:e
984:t
977:v
960:.
891:.
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840:.
819:.
743:)
525:/
305:)
169:.
156:)
150:(
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141:(
131:·
124:·
117:·
110:·
83:.
54:)
50:(
44:.
20:)
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