cosmos.wikisort.org - Spacecraft

F-1 is a CubeSat built by FSpace laboratory at FPT University, in Hanoi, Vietnam, in partnership with Angstrom Space Technology Center (ASTC), Uppsala University, Sweden and Nanoracks LLC, United States. Its mission is to train young engineers and students about aerospace engineering and evaluate an advanced three-axis magnetometer, Spin-Dependent Tunneling Magnetometer (SDTM) designed in Sweden by ASTC.[4]

F-1

Flight Model of F-1 satellite
Mission type	Technology demonstration
Operator	FPT University/Uppsala University
COSPAR ID	2012-038E (1998-067CR)[1]
SATCAT no.	38855
Mission duration	Failed to contact ground 100 days (planned)
Spacecraft properties
Spacecraft type	CubeSat
Manufacturer	FPT University
Launch mass	1 kg (2.2 lb)
Dimensions	10 cm x 10 cm x 10 cm (1U)
Start of mission
Launch date	21 July 2012, 02:06:18 UTC[2]
Rocket	H-IIB F3
Launch site	Tanegashima, Yoshinobu LC-Y2
Contractor	Mitsubishi Heavy Industries
Deployed from	ISS Kibō Delivered by Kounotori 3
Deployment date	4 October 2012, 15:44:15.297 UTC
Entered service	Failed to contact ground
End of mission
Decay date	9 May 2013[3]
Orbital parameters
Reference system	Geocentric orbit
Regime	Low Earth orbit
Inclination	51.65°
F-1 mission patch

F-1 was launched on 21 July 2012 and delivered to the International Space Station (ISS) aboard Kounotori 3 (HTV-3) along with the RAIKO, WE WISH, Niwaka and TechEdSat-1 cubesats. Then, on 4 October 2012, it was deployed into orbit from the ISS using the JEM-Small Satellite Orbital Deployer (J-SSOD) which was attached to the Kibō module's robotic arm.[5][6]

As of 2 November 2012, F-1 failed to confirm communication after the orbital deployment.[7]

Hardware

• Structure: aluminium alloy T-6061
• Power supply: body-mounted solar cells, rechargeable Li-Polymer battery
• PIC16 and PIC18 micro-controllers
• Yaesu VX-3R handheld transceivers
• C328 low-resolution camera
• Temperature sensors
• Three-axis magnetometer (ASTC)
• 2-meter band Dipole Antenna
• 70-cm band Dipole Antenna

Specifications

• Size: 10 cm x 10 cm x 10 cm (1U CubeSat)
• Mass: 1 kg
• Communication: 2 independent radios using amateur radio Very high frequency (VHF) and Ultra high frequency (UHF) bands, transmission speed 1200 bit/s; AFSK and PWM Morse code modulation, KISS protocol
• Payload: low resolution C328 camera (640 × 480 maximum resolution, 8 bit color)
• Sensors: temperature sensors and three-axis magnetometer
• Targeted orbit lifetime: at least 3 months on orbit (depend on release altitude from the ISS)

Communication subsystem and Packet format

1. Backup UHF channel (only operational in daylight):

• Frequency: 437.485 MHz
• Modulation: Narrow FM
• Power: about 0.2 watt RF output
• Antenna: half-wave dipole
• Beacon interval: 20 seconds duration, repeated every 90 seconds

Pulse-Width-Modulation Morse code telemetry beacon

No1	Data	Description	Size (bits)	Size (chars)
1	F-1's callsign	"XV1VN"		5
2	OBC1 reset count	Number of OBC1's reset since the beginning	8
3	Temperature 1	°C (temperature inside F-1, OBC board)	8	5
4	Temperature 2	°C (temperature outside F-1, Y- side)	8
5	Checksum bit	0 if summary of items #2 to #4 is even, 1 if it is odd	1
			Total	10

2. Main VHF channel (operational during night time but may be turned on in daylight later)

• Frequency: 145.980 MHz
• Modulation scheme: AFSK/FM
• Power: 1.0 watt RF output
• Antenna: half-wave dipole
• Baud rate: 1200 bit/s
• Telemetry and interval: one burst of 3 telemetry packets in KISS format every 30 seconds (interval configurable)

F-1's KISS packet format

No	Data	Description	Size (bit)
1	Date time	Date: dd/mm/y: 5/4/3=12 bits Time: hh/mm/ss: 5/6/6=17 bits	29
2	Battery voltage	Battery voltage multiplied by 100 (divide by 100 to get actual value)	11
3	Solar cells voltage	Solar cells voltage multiplied by 10 (divide by 10 to get actual value)	8
4	Temperature 1	°C (side 1, Y+)	8
5	Temperature 2	°C (side 2, Y-)	8
6	Temperature 3	°C (side 3, X-)	8
7	Temperature 4	°C (side 4, Z+)	8
8	Temperature 5	°C (side 5, Z-)	8
9	Temperature 6	°C (side 6, X+)	8
10	Temperature 7	°C (inside side 5, Z-)	8
11	Temperature 8	°C (inside, under VX-3R1)	8
		Total	112 bits = 14 bytes

Note:

• F-1 periodically sends a burst of 3 telemetry packets with the same content, to avoid packet loss
• Time in UTC, 24 hours format
• Year count starting from 2012 (2012 equals 0, 2013 equals 1 and so on...)
• Battery voltage reading is accurate to 0.01 volt, values are multiplied by 100. Divide by 100 to get actual value.
• Solar cells voltage reading is accurate to 0.10 volt, values are multiplied by 10. Divide by 10 to get actual value.
• Temperature readings from sensors, will be added with 100 before transmission to ensure a positive number so please subtract 100 to get actual value
• 112 bits, divided into 14 bytes

References

External links

• Home page
• F1: un micro satellite vietnamien dans l'espace fin 2011
• Vietnam Student CubeSat F-1 24/2/2012

На других языках

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[de] F-1 (Satellit)

F-1 war ein vietnamesischer Satellit mit Cubesat-Architektur, der an der FPT University in Hanoi gebaut wurde.

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- [en] F-1 (satellite)

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[ru] F-1 (спутник)

F-1 — это спутник на платформе CubeSat, созданный лабораторией FSpace в Университете FPT в Ханое, Вьетнам, в сотрудничестве с Центром космических технологий Angstrom (ASTC), Университетом Упсалы, Швеция, и Nanoracks LLC, США. Его миссия состояла в том, чтобы обучить молодых инженеров и студентов аэрокосмической технике и оценить усовершенствованный трёхосевой магнитометр - спин-зависимый туннельный магнитометр (SDTM), разработанный в Швеции компанией ASTC[1].

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