PROFILBARU.COM

F-1
	Flight Model of F-1 satellite
Mission type	Technology demonstration
Operator	FPT University/Uppsala University
COSPAR ID	2012-038E (1998-067CR)
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
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
Orbital parameters
Reference system	Geocentric orbit
Regime	Low Earth orbit
Inclination	51.65°
	; F-1 mission patch

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 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

^ "Display: F-1 2012-038E". NASA. 14 May 2020. Retrieved 13 January 2021. This article incorporates text from this source, which is in the public domain.
^ Bergin, Chris (20 July 2012). "Japanese H-IIB launches HTV-3 to the International Space Station". NASASpaceFlight.com. Retrieved 13 January 2021.
^ "Trajectory: F-1 2012-038E". NASA. 14 May 2020. Retrieved 13 January 2021. This article incorporates text from this source, which is in the public domain.
^ Gunter, Dirk Krebs (28 January 2020). "F-1". Gunter's Space Page. Retrieved 13 January 2021.
^ 大塚実 (25 January 2012). "JAXA、宇宙ステーションから超小型衛星を放出できる装置をプレス公開" (in Japanese). mynavi.jp. Retrieved 13 January 2021.
^ 「きぼう」日本実験棟からの小型衛星放出ミッション (in Japanese). JAXA. 5 October 2012. Archived from the original on 13 November 2012. Retrieved 13 January 2021.
^ "Attempt to recover the F-1 Amateur Radio CubeSat". 3 November 2012. Archived from the original on 24 September 2015. Retrieved 22 December 2012.