Last updated: August 7th, 2009
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Michael's List of Cubesat Satellite Missions
(University and private, and other student satellite missions)
[No longer being updated (last update medio 2009)]
Note: This list was created back in late 2005 because I needed to know how other cubesats had been performing at the time. I have since then attempted to update the list fairly regularly, but have come to the conclusion that I no longer have the time nor the interest in doing so.
If you feel like taking over, please contact me (see below), and we'll figure something out.
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This list is meant to give an overview over the success rate, mission and payloads, communication, attitude
and orbit determination and control systems along with links to the various projects.
Only missions already launched, scheduled for launch, or being actively worked on are included on this page.
The list was created because I couldn't find any other page with this kind of information, and browsing
the various cubesat mission websites begin to take quite some time as the number of missions increases.
In fact it took quite a bit of time to compile the information found there. I therefore hope you will find this page useful,
please leave a thank you in the guest book if you do, or contact me
if you know of a mission that is not on this list, find a mistake or have information that could be added.
List Nomenclature
Single cubesat | = 10x10x10 cm3, | 1 kg |
Double cubesat | = 10x10x20 cm3, | 2 kg |
Triple cubesat | = 10x10x30 cm3, | 3 kg |
P-POD |
(Poly-Picosatellite Orbital Deployer by Standford University and California Polytechnic Institute) holds three single
cubesats stacked on top on each other
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T-POD |
(Tokyo Pico-satellite Orbital Deployer) holds one single cubesat. If you know Japaneese you can find more information
here (there is also a number of pictures)
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X-POD |
(eXperimental Push Out Deployer) is a custom, independent separation system that was designed and built at University of Toronto Institute for Aerospace Studies/Space Flight Laboratory for each satellite and may be tailored to satellites of different sizes ranging from single cubesat to larger nanosatellites of arbitrary dimensions.
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SPL |
(Single Pico-Satellite Launcher) holds one single cubesat. The deployment velocity can be defined by the customer, it is 1 m/s default. It is manufactured by Astrofein. Details about the SPL can be found here.
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P-POD numbers (eg #1) indicate the satellite location in the P-POD. #1 is the one being released first.
The list is sorted by launch date, then deployment mechanism (earlier deployed listed first), then location in
deployment mechanism (outermost (first deployed) listed first). Alphabetical after mission name if information is missing.
Note that uplink information is generally not available, but most cubesats are using the 144 MHz band.
Table of cubesat successrate:
Batch # | LV Failure | No contact | Some contact | Full contact | | Total |
1 (June 2003) | 0 | 2 | 1 | 2 + 1 triple | | 5+1 triple |
2 (October 2005) | 0 | 1 | 0 | 2 | | 3 |
Solo (February 2006) | 0 | 0 | 0 | 1 double | | 1 double |
3 (July 2006) | 13 + 1 double | 0 | 0 | 0 | | 13 + 1 double |
Solo (December 2006) | 0 | 0 | 0 | 1 triple | | 1 triple |
4 (April 2007) | 0 | 1 | 3 + 1 triple | 2 | | 6 + 1 triple |
5 (April 2008) | 0 | 0 | 0 | 3 + 1 double + 2 triple | | 3 + 1 double + 2 triple |
6 (May 2009) | 0 | ? | ? | ? | | 3+1 triple |
7 (July 2009) | 0 | ? | ? | ? | | 2 (1U?) |
| | | | | | |
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Total | 13 + 1 double | 4 | 4+1 triple | 9 + 2 double + 4 triple | | 33 + 3 double + 6 triple |
Link to cubesat operational status information: http://www.amsat.org/amsat-new/satellites/cubesats.php
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Cubesat Missions
First batch launched June 30, 2003 at 14:15:25 UTC on a Eurockot LV from Plesetsk, Russia into a 818x832, sun synchronous orbit with a local time of 18:00
T-PODs deployed at t0 + 5551 sec
NLS-1 deployed at t0 + 5626 sec
NLS-2 deployed at t0 + 5626 sec
CUTE-I by Tokyo Institute of Technology, Japan
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Deployment Mechanism: |
Tokyo Pico-satellite Orbital Deployers (T-POD)
| Type: |
Single cubesat
| Mission: |
Test platform based on COTS components.
Deployable solar cells, piezoelectric vibrating gyroscope (4 pcs), dual axis accelerometers (4 pcs) and CMOS camera used as sun sensor.
The camera pictures could not be transmitted to the ground.
| AODC: |
Piezoelectric vibrating gyroscope to measure angular velocity, dual axis acelerometer (used to compare to gyros),
and CMOS sun sensor
| Communication: |
Callsign: JQ1YCY
Beacon: 436.8375 MHz (100 mW, CW)
Downlink: 437.470 MHz (350 mW, 1200 bps FM AFSK AX.25, only active near Japan)
| Status: |
Nominal operations.
The satellite is still operating nominally in early December 2008 (5 years, 5 months after launch)
| Link: |
http://lss.mes.titech.ac.jp/ssp/cubesat/index_e.html
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XI-IV by University of Tokyo, Japan
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Deployment Mechanism: |
Tokyo Pico-satellite Orbital Deployer (T-POD)
| Type: |
Single cubesat
| Mission: |
Test platform based on COTS components.
Included a camera to take pictures of the earth.
| AODC: |
Permanent magnet and hysteresis rods
| Communication: |
Callsign: JQ1YCW
Beacon: 436.8475 MHz (100 mW, CW)
Downlink: 437.490 MHz (600 mW, 1200 bps FM AFSK AX.25, only active near Japan)
| Status: |
Nominal operations.
Latest telemetry analysis dated September 20th, 2007.
The satellite beacon was last heard in early December 2008 (5 years, 5 months after launch).
| Links: |
http://www.space.t.u-tokyo.ac.jp/cubesat/index-e.html
http://www.space.t.u-tokyo.ac.jp/gs/en/index.aspx
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CanX-1 by University of Toronto, Canada
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Deployment Mechanism: |
P-POD NLS-1 #1
| Type: |
Single cubesat
| Mission: |
Space-testing key technologies for future missions: Low-cost CMOS horizon sensor and star-tracker, GPS receiver.
| AODC: |
CMOS horizon sensor and star-tracker, GPS receiver, magnetometer, and magnetorquers
| Communication: |
Callsign: VA3SFL
437.880 MHz (500 mW, 1200 bps FM MSK)
| Status: |
Radio contact never established
| Link: |
http://www.utias-sfl.net/nanosatellites/CanX1/
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DTUsat by Technical University of Denmark
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Deployment Mechanism: |
P-POD NLS-1 #2
| Type: |
Single cubesat
| Mission: |
MEMS sun sensors and a 600 m tether used to change the orbit.
A color CCD camera and electron emitter were not ready on time for launch
| AODC: |
MEMS sun sensors, magnetometer, and magnetorquers
| Communication: |
Callsign: OZ2DTU
437.475 MHz (400 mW, 2400 bps FM AFSK AX.25 / CW beacon)
| Status: |
Radio contact never established
| Link: |
http://dtusat1.dtusat.dtu.dk
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AAU Cubesat by Ålborg University, Denmark
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Deployment Mechanism: |
P-POD NLS-1 #3
| Type: |
Single cubesat
| Mission: |
Color CMOS camera
| AODC: |
Sun sensors, magnetometer, and magnetorquers
| Communication: |
Callsign: Unknown
437.450 MHz (500 mW, 9600 bps GMSK / CW beacon w/safemode telemetry)
| Status: |
The antennas short-circuited resulting in poor communication performance so only weak beacon signals were received. Also simple two-way
communication was established (pinging).
Batteries slowly died beginning after slightly more than one month in orbit due to poor packaging (punch-pack).
| Link: |
http://www.cubesat.auc.dk
| Lessons Learned: |
http://www.studentspace.aau.dk/publications/AAUCubesatProject.pdf
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QuakeSat by Stanford University and Quakesat LLC, USA
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Deployment Mechanism: |
P-POD NLS-2
| Type: |
Triple Cubesat
| Mission: |
Detect ELF radio emission of seismic activity during earthquakes.
Had deployable solar panels, and a magnetometer mounted on a 60 cm boom.
The s/c was designed using COTS components.
| AODC: |
Permanent magnet and hysteresis rods
| Communication: |
Callsign: KD7OVB
436.675 MHz (1.2 W, 9600 bps FM FSK AX.25, telemetry every 10 s, data only when near USA)
| Status: |
Designed for 6 months, it worked flawlessly until at least June 6th, 2004 (more than 11 months).
Other source (http://showcase.netins.net/web/wallio/CubeSat.htm) states nominal operations in ultimo December 2006 (3 years, 6 months after launch), and beacon heard on October 7th, 2007
| Links: |
http://www.quakefinder.com/services/spaceproducts.php
| Lessons Learned: |
http://www.quakefinder.com/services/pdf/SSC_PAPER_SSC02-IX-6.pdf
| Additional information: |
Total cost to build and launch: USD 1 million
Operation cost: USD 170,000 per month
| Second batch deployed from SSETI Express, launched October 27, 2005 at 08:52 CEST on a Kosmos-3M LV from Plesetsk, Russia into
a 686 x 686 km sun synchronous orbit (inclination 98°) with a local time of 10:30
NCube2 by Norwegian University of Science and Technology
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Deployment Mechanism: |
Tokyo Pico-satellite Orbital Deployer (T-POD) (deployment time not known)
| Type: |
Single cubesat
| Mission: |
Similar to NCube1, the payload consists of an Automatic Identification System. AIS is a mandatory system on all larger
ships, which transmits identification and position data messages. The satellite will redirect these messages along with
messages from Norwegean reindeer collars.
| AODC: |
Magnetometer and magnetorquers
| Communication: |
Callsign: LA1CUB
CW ID: "LA1CUB Ncube2 Norwegian"
437.305 MHz (1 W, 9600 bps FSK AX.25)
| Status: |
Radio contact never established
May have been deployed around December 20th, 2005, when NORAD began tracking a new small object moving away from SSETI-Express.
It is believed that outgassing could have allowed the late deployment, however contact has still not been established
| Link: |
http://www.ncube.no/
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UWE-1 by University of Würzburg, Germany
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Deployment Mechanism: |
Tokyo Pico-satellite Orbital Deployer (T-POD) (deployment time not known)
| Type: |
Single cubesat
| Mission: |
Testing a communication protocol, test of GaAs cells in space, running micro Linux
| AODC: |
Information not available
| Communication: |
Callsign: DPØUWE
437.505 MHz (1 W, 9600 bps FSK AX.25 (KISS))
| Status: |
Nominal operations until November 17th, 2005, when it was last heard. Since then contact has been lost completely.
| Link: |
http://www7.informatik.uni-wuerzburg.de/cubesat
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XI-V by University of Tokyo, Japan
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Deployment Mechanism: |
Tokyo Pico-satellite Orbital Deployer (T-POD) (deployment time not known)
| Type: |
Single cubesat
| Mission: |
Original a backup for XI-IV. The following changes have been added: Test of CIGS and GaAs solar cells,
increased resolution of camera and an introduction of rapid shooting mode for estimating attitude motion.
A morse message transmission service for radio amateurs has been added
| AODC: |
Permanent magnet, libration damper
| Communication: |
Callsign: JQ1YGW
Beacon: 437.465 MHz (80 mW, CW)
Downlink: 437.345 MHz (800 mW, 1200 bps FM AFSK AX.25, only active near Japan)
| Status: |
Nominal operations, first image received November 22nd, 2005.
From December 2005, the images are showing some problems.
The satellite is still operating nominally early December 2008 (3 years, 2 months after launch)
| Links: |
http://www.space.t.u-tokyo.ac.jp/cubesat/index-e.html
http://www.space.t.u-tokyo.ac.jp/gs/en/index.aspx
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Single cubesat launched February 22nd, 2006 on a M-V LV from Uchinoura, Japan into a sun-synchronous orbit
(inclination 98°)
CUTE 1.7 + APD by Tokyo Institute of Technology, Japan
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Deployment Mechanism: |
New version of the T-POD that supports a double cubesat
| Type: |
Double cubesat
| Mission: |
Test of charged particle detector (Avalance Photo Diode sensor module), made by Tokyo Institute of Technology.
Due to low perigee (about 300 km at launch) expected lifetime is significantly less than one year
Experimental 10m tether and electron emitter to change orbit
| AODC: |
Gyrosensor (ADXRS150), magnetometer (HMR2300), sun sensor (S6560 photo diode array), earth sensor (CMOS camera), and magnetorquers
| Data handling: |
Two redundant PDAs are used for datahandling. Apparently they're running Windows CE.NET!
Communication to the subsystems is done using USB
| Communication: |
Callsign: JQ1YCC
Beacon: 437.385 MHz (CW),
Downlink: 437.505 MHz (1200 bps FM AFSK AX.25, 9600 bps GMSK AX.25/SRLL)
Digipeater uplink: 1268.5 MHz (9600 bps GMSK AX.25/SRLL)
| Status: |
Nominal operations until early March 2006, it was since fully recovered, but since April 2006 no longer responds to commands from the ground.
| Link: |
http://lss.mes.titech.ac.jp/ssp/cute1.7/cute1.7-1/index_e.html
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Third batch attempted launched July 26th, 2006 on a DNEPR LV (Belka) from Baikonur, Kazakhstan into a sun-synchronous orbit (inclination 97.43°) with a local time of 11:25 UTC
NOTE: Launch vehicle disintegrated during launch.
More info here: http://www.spaceflightnow.com/news/n0607/26dnepr/,
here: http://www.space.com/missionlaunches/060726_dnepr_failure.html
and here: http://www.russianspaceweb.com/dnepr_007_belka.html
P-POD A: 772.1 x 660.6, deployed at t0 + 929.230 sec
P-POD B: 779.7 x 660.0, deployed at t0 + 930.230 sec
P-POD C: 787.5 x 659.5, deployed at t0 + 931.230 sec
P-POD D: 795.2 x 659.6, deployed at t0 + 932.230 sec
P-POD E: 803.0 x 658.5, deployed at t0 + 933.230 sec
ION by University of Illionis, USA
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Deployment Mechanism: |
P-POD A#1+2
| Type: |
Double cubesat
| Mission: |
Features a Photomultiplier Tube (PMT) to observe airglow phenomenon in the earth's upper atmosphere (mesosphere).
Also has a low-thrust, electric propulsion system and a CMOS camera for Earth imaging.
| AODC: |
Sun sensors, magnetometer, magnetorquers, and micro-vacuum arc thrusters
| Communication: |
Callsign: TBA
437.505 MHz (2 W, 1200 bps FM AFSK AX.25, ~5 min beacon interval)
| Status: |
Destroyed due to launch failure (see above)
| Link: |
http://courses.ece.uiuc.edu/cubesat/
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Sacred by University of Arizona, USA
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Deployment Mechanism: |
P-POD A#3
| Type: |
Single cubesat
| Mission: |
This is the third cubesat by University of Arizona (the second to be launched)
Produced by Montpelier University and Alcatel the payload will measure the total amount of high-energy radiation over a two-year
span and will test the radiation properties of four commercial integrated circuits
| AODC: |
Information not available
| Communication: |
Callsign: WA4CEW
436.870 MHz (400 mW, 1200 bps FM AFSK AX.25)
| Status: |
Destroyed due to launch failure (see above)
| Link: |
http://cubesat.arizona.edu/sacred_sat/ (link does not seem to work anymore)
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KUTEsat Pathfinder by University of Kansas, USA
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Deployment Mechanism: |
P-POD B#1
| Type: |
Single cubesat
| Mission: |
Measure the radiation in LEO and take photographs with an onboard camera
| AODC: |
Magnetometer, magnetorquers, and sun sensors
| Communication: |
Callsign: KCØRMW
437.385 MHz (500 mW, 1200 bps FM AFSK AX.25)
| Status: |
Destroyed due to launch failure (see above)
| Link: |
http://www.engr.ku.edu/ae/kutesat.htm (link does not seem to work anymore)
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ICE Cube 1 by Cornell University (New York state), USA
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Deployment Mechanism: |
P-POD B#2
| Type: |
Single cubesat
| Mission: |
Perform GPS scintillation science by measuring fluctuations in the signals that the GPS satellites emit when the signals
pass through the ionosphere. Identical to ICE Cube 2
| AODC: |
Magnetometer, magnetoquers, Gravity gradient boom, GPS receiver
| Communication: |
Callsign: W2CXM
437.305 MHz (600 mW, 9600 bps FM FSK AX.25)
| Status: |
Destroyed due to launch failure (see above)
| Link: |
http://www.mae.cornell.edu/cubesat/
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RINCON 1 by University of Arizona, USA
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Deployment Mechanism: |
P-POD B#3
| Type: |
Single cubesat
| Mission: |
This is the second cubesat by University of Arizona (the first, which was just a s/c bus, is not scheduled for launch)
The payload is a low-power beacon system, which provides a redundant means of relaying sensor data in analog form if
the primary (digital) transmitter fails.
| AODC: |
Information not available
| Communication: |
Callsign: WA4CEW
Beacon: 437.345 MHz (?) (10 mW, 1200 bps PSK AX.25)
Downlink: 436.870 MHz (400 mW, 1200 bps AFSK AX.25)
| Status: |
Destroyed due to launch failure (see above)
| Link: |
http://bach.as.arizona.edu/azstarwiki/index.php/Rincon_1/ (link does not seem to work anymore)
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SEEDS by Nihon University, Japan
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Deployment Mechanism: |
P-POD C#1
| Type: |
Single cubesat
| Mission: |
Contains a gyro sensor for accurate determination of attitude motion
| AODC: |
Gyro sensor, and magnetometer. Information about control system not available
| Communication: |
Callsign: JQ1YGU
437.485 MHz (450 mW, 1200 bps FM AFSK AX.25 / 90 mW CW)
| Status: |
Destroyed due to launch failure (see above)
| Link: |
http://cubesat.aero.cst.nihon-u.ac.jp/english/main_e.html
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HAUSAT 1 by Hankuk Aviation University, South Korea
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Deployment Mechanism: |
P-POD C#2
| Type: |
Single cubesat
| Mission: |
GPS receiver, experiment on deployment mechanism of solar cell panel and space verification of homemade sun sensor
| AODC: |
Sun sensor, gps receiver
| Communication: |
Callsign: D9OHP
437.465 MHz (500 mW, 1200 bps FM AFSK AX.25 / CW ID Beacon)
| Status: |
Destroyed due to launch failure (see above)
| Link: |
http://134.75.55.85/new_version/english/hausat_1/index.php (link does not seem to work anymore)
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NCube1 by Norwegian University of Science and Technology
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Deployment Mechanism: |
P-POD C#3
| Type: |
Single cubesat
| Mission: |
Similar to NCube2, the payload consists of an Automatic Identification System. AIS is a mandatory system on all larger
ships, which transmits identification and position data messages. The satellite will collect these messages along with
messages from Norwegean reindeer collars.
| AODC: |
Magnetometer and magnetorquers
| Communication: |
Callsign: LA1CUB
CW ID: "LA1CUB Ncube1 Norwegian"
437.305 MHz (1 W EIRP, 9600 bps GMSK AX.25)
| Status: |
Destroyed due to launch failure (see above)
| Link: |
http://www.ncube.no/
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MEROPE by Montana State University, USA
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Deployment Mechanism: |
P-POD D#1
| Type: |
Single cubesat
| Mission: |
Radiation experiment (no further information is available on their website)
| AODC: |
Information not available
| Communication: |
Callsign: K7MSU-01
145.980 MHz (500 mW, 1200 bps FM AFSK)
| Status: |
Destroyed due to launch failure (see above)
| Link: |
http://www.ssel.montana.edu/merope/
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AeroCube-1 by the Aerospace Corporation, USA
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Deployment Mechanism: |
P-POD D#2
| Type: |
Single cubesat
| Mission: |
Short life satellite (10 days), using Lithium batteries as primary batteries (no recharging).
Mission is to test a communication system and the system bus plus a suite of CMOS cameras done by Harvey Mudd College.
The satellite has no deployables. Instead an omnidirectional patch antenna is used.
| AODC: |
None
| Communication: |
902-928 MHz (2 W, 9600 bps GFSK)
| Status: |
Destroyed due to launch failure (see above)
| Link: |
http://www.aero.org (this is just a link to the company. No mission information available)
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CP2 by California Polytechnic Institute, USA
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Deployment Mechanism: |
P-POD D#3
| Type: |
Single cubesat
| Mission: |
Energy Dissipation Experiment
First mission based on what is supposed to be a "standarized" bus (though CP3 features an updated bus)
| AODC: |
Probably magnetometer and magnetorquers
| Communication: |
Callsign: Unknown
437.325 MHz (1 W, 1200 bps FM AFSK AX.25 / CW beacon)
| Status: |
Destroyed due to launch failure (see above)
| Link: |
http://polysat.calpoly.edu/
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CP1 by California Polytechnic Institute, USA
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Deployment Mechanism: |
P-POD E#1
| Type: |
Single cubesat
| Mission: |
Test of sun sensor developed by Optical Energy Technologies
| AODC: |
Sun sensor, magnetorquers
| Communication: |
Callsign: N6CP
436.845 MHz (500 mW, 15 bps DTMF & CW, both FM)
| Status: |
Destroyed due to launch failure (see above)
| Link: |
http://polysat.calpoly.edu/
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ICE Cube 2 by Cornell University (New York state), USA
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Deployment Mechanism: |
P-POD E#2
| Type: |
Single cubesat
| Mission: |
Perform GPS scintillation science by measuring fluctuations in the signals that the GPS satellites emit when the signals
pass through the ionosphere. Identical to ICE Cube 1
| AODC: |
Magnetometer, magnetoquers, Gravity gradient boom, GPS receiver
| Communication: |
Callsign: N2VR
437.425 MHz (600 mW, 9600 bps FM FSK AX.25)
| Status: |
Destroyed due to launch failure (see above)
| Link: |
http://www.mae.cornell.edu/cubesat/
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Mea Huaka (Voyager) by University of Hawaii, USA
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Deployment Mechanism: |
P-POD E#3
| Type: |
Single cubesat
| Mission: |
To test a 5.8-GHz active antenna (grid oscillator) for high bandwidth communication (does not require deployment of antenna)
| AODC: |
Permanent magnet and hysteresis rod
| Communication: |
Callsign: Unknown
437.405 MHz (500 mW, 1200 bps FM AFSK AX.25)
5.84 GHz (1 mW)
| Status: |
Destroyed due to launch failure (see above)
| Link: |
http://www-ee.eng.hawaii.edu/~cubesat/ (link does not seem to work anymore)
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Single cubesat launched December 16th, 2006 on a Minotaur from MARS at
NASA Wallops Flight Facility, VA, USA into a circular LEO orbit with an inclination of 40° and an altitude of 415 km.
GeneSat-1 by Center for Robotic Exploration and Space Technologies, CA, USA
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Deployment Mechanism: |
P-POD
| Type: |
Triple cubesat (4.6 kg)
| Mission: |
Perform experiment on E. Coli bacteria in space, first cubesat to carry a biological experiment.
| AODC: |
Permanent magnets, hysteresis rods
| Communication: |
Callsign: KE7EGC
Beacon: 437.067 MHz (1200 bps FM AFSK AX.25)
Downlink: 2.4 GHz (proprietary)
| Status: |
Nominal operations.
96-hour experiment completed succesfully on December 22nd, 2006
Last confirmed telemetry reception on April 11th, 2008 (2 year, 4 months after launch)
| Links: |
http://www.crestnrp.org/genesat1/ (Excellent website)
http://directory.eoportal.org/presentations/129/13064.html (Additional information)
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Fourth batch launched April 17th, 2007 on a DNEPR LV (EgyptSat) from Baikonur, Kazakhstan into
a sun-synchronous orbit (inclination 98°) with a local time of 22:30
P-POD A: 772.1 x 660.6, deployed at t0 + 929.230 sec
P-POD C: 787.5 x 659.5, deployed at t0 + 930.230 sec
P-POD B: 779.7 x 660.0, deployed at t0 + 931.230 sec
CP4 by California Polytechnic Institute, USA
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Deployment Mechanism: |
P-POD A#1
| Type: |
Single cubesat
| Mission: |
Second flight unit of CP2, which was destroyed during the previous DNEPR launch
| AODC: |
Same as CP2
| Communication: |
Callsign: Unknown
437.325 MHz (1 W, 1200 bps FM FSK AX.25)
| Status: |
CP4 has been heard from numerous ground stations, but is not responding to tele commands. To the best of my knowledge it never reached full functionality. It is no longer operational
| Link: |
http://polysat.calpoly.edu/ (General CalPoly Cubesat website)
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AeroCube-2 by the Aerospace Corporation, USA
|
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Deployment Mechanism: |
P-POD A#2
| Type: |
Single cubesat
| Mission: |
Similar to AeroCube-1, except added charging system for the Lithium batteries.
Mission is to test a communication system and the system bus plus a suite of CMOS cameras done by Harvey Mudd College.
The satellite has no deployables. Instead an omnidirectional patch antenna is used.
| AODC: |
None
| Communication: |
902-928 MHz (2 W, 9600 bps GFSK)
| Status: |
Solar upconverter failed shortly after launch. Batteries dead.
Shortly after ejection, AeroCube-2 took a picture of CP4, see bottom of this page: http://www.dk3wn.info/sat/afu/sat_cp.shtml
| Link: |
http://www.aero.org (this is just a link to the company. No mission information available)
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CSTB-1 (Cubesat Testbed 1) by The Boeing Company, USA
|
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Deployment Mechanism: |
P-POD A#3
| Type: |
Single cubesat
| Mission: |
Testbed for components for future Boeing small-sat missions.
Redundant radios, deployable antenna, various non-disclosed sensors
| AODC: |
Sun sensors, magnetometer and magnetorquers
| Communication: |
Callsign: Unknown
400.0375 MHz (1 W, 1200 bps FM AFSK AX.25)
| Status: |
Nominal operations
| Links: |
http://www.boeing.com (this is just a link to the company. No mission information available)
http://www.boeing.com/news/frontiers/archive/2006/october/i_ids02.pdf
|
MAST by Tethers Unlimited, USA
|
---|
Deployment Mechanism: |
P-POD C
| Type: |
Triple cubesat (actually 3 tethered cubesats)
| Mission: |
Tether experiment (1 km Hoytether). ~1 million USD for the entire program
| AODC: |
Unknown + GPS
| Communication: |
Callsign: Unknown
2.4 - 2.4835 GHz (1 W, FHSS)
| Status: |
Only had contact to one of the two modules. Tether may have deployed "a little", but definetly not fully.
| Links: |
http://www.tethers.com/Missions.html (Mission info)
http://www.tethers.com/MAST_Blog.html (Mission status)
|
CP3 by California Polytechnic Institute, USA
|
---|
Deployment Mechanism: |
P-POD B#1
| Type: |
Single cubesat
| Mission: |
Three-axis magnetorquing experiment
| AODC: |
Magnetometers and magnetorquers
| Communication: |
Callsign: Unknown
436.845 MHz (1 W, 1200 bps FM FSK AX.25)
Experimental license. Will only transmit on request from ground station
| Status: |
Radio never established
| Link: |
http://polysat.calpoly.edu/ (General CalPoly Cubesat website)
|
CAPE-1 by University of Louisiana, USA
|
---|
Deployment Mechanism: |
P-POD B#2
| Type: |
Single cubesat
| Mission: |
Camera(?)
| AODC: |
Permanent magnet and hysteresis rods
| Communication: |
Callsign: K5USL
435.245 MHz (1 W, 9600 bps FSK AX.25 and CW switching every 30 s)
| Status: |
Has power system problems and is semi-operational (battery appears to be dead; currently only operates in the sun).
CW has been received by several ground stations.
9600 bps TM packets have not been received by any station
| Links: |
http://cape.louisiana.edu/
http://jonathanwagner.net/ Lots of pictures
|
Fifth batch launched April 28th, 2008 on a Polar Satellite Launch Vehicle (PSLV)
from Satish Dhawan Space Centre, India into a 630 km sun-synchronous orbit (inclination 98°) with a local time of 10:30
X-POD A: Deployed at t0 + 1044.2 sec
X-POD B: Deployed at t0 + 1064.2 sec
X-POD C: Deployed at t0 + 1084.2 sec
X-POD D: Deployed at t0 + 1104.2 sec
X-POD E: Deployed at t0 + 1124.2 sec
X-POD F: Deployed at t0 + 1144.2 sec
Up-to-date communication parameters can be found here:
http://showcase.netins.net/web/wallio/CubeSat.htm
CanX-2 by University of Toronto, Canada
|
---|
Deployment Mechanism: |
X-POD A
| Type: |
Triple cubesat (3.5 kg!)
| Mission: |
Will test instrumentation for future CanX missions including a propulsion system, momentum wheel, sun sensors,
gps receiver, CMOS camera (star tracker), and a new communication protocol.
Scientific instrumentation and goals includes: Atmospheric spectrometer, GPS occultation experiment, and atomic oxygen
material degredation experiment
| AODC: |
Sun sensors, magnetometer, magnetorquers, momentum wheel, liquid-fuelled cold gas propulsion system (SF6)
| Communication: |
Callsign: VA3SFL
Downlink: 437.478 MHz and 2407.650 (GMSK AX.25)
| Status: |
TM received
| Link: |
http://www.utias-sfl.net/nanosatellites/CanX2/
|
CUTE 1.7 + APD II by Tokyo Institute of Technology, Japan
|
---|
Deployment Mechanism: |
X-POD B
| Type: |
Double cubesat
| Mission: |
Improved CUTE 1.7 + APD
| AODC: |
Probably similar to CUTE 1.7 + APD
| Communication: |
Downlink: 437.475 MHz (1200 bps AX.25 / 9600 bps GMSK SRLL)
Beacon: 437.275 MHz (CW, Morse signal of housekeeping data)
Uplink: 1267.6 MHz (9600 bps FM GMSK, AX.25/SRLL)
| Status: |
Pictures downloaded.
Nominal operations, December 7th, 2008
| Link: |
http://lss.mes.titech.ac.jp/ssp/cute1.7/index_e.html
|
Delfi-C3 by Delft University of Technology, Holland
|
---|
Deployment Mechanism: |
X-POD C
| Type: |
Triple cubesat
| Mission: |
Test of autonomous sun sensor using a wireless link for data transfer (915 MHz),
test of new type of thin film solar cells developed by Dutch Space,
and test of a high efficiency transceiver. No on-board data storage is planned.
| AODC: |
Sun sensor and by measuring input power of solar panels, permanent magnet and hysteresis rods for control
| Communication: |
Primary telemetry downlink: 145.870 MHz (400 mW, 1200 Baud BPSK AX.25, 1 frame/s)
Backup telemetry downlink: 145.930 MHz (400 mW, 1200 Baud BPSK AX.25; DSB FSK for emergency mode)
Linear transponder passband downlink: 145.880 - 145.920 MHz (400 mW PEP, inverting)
Linear transponder passband uplink: 435.570 - 435.530 MHz
Transponder mode beacon: 145.930 MHz (10dB below transponder PEP, CW)
| Status: |
Nominal operations
| Link: |
http://www.delfic3.nl/
|
AAUsat-2 by Ålborg University, Denmark
|
---|
Deployment Mechanism: |
X-POD D
| Type: |
Single cubesat
| Mission: |
Detect gamma ray bursts by a gamma ray detector developed by the Danish National Space Center
| AODC: |
Magnetic based (coils) and momentum wheels
| Communication: |
Callsign: OZ2CUB
Downlink: 437.425 MHz (1200-9600 bps AFSK & FSK AX.25 FM CW TLM)
| Status: |
The satellite is tumbling, at one time up to 85 RPM, but using the magnetorquers the tumbling has been reduced to 35 RPM.
The tumbling is making communication a challenge, they are currently using a 1 kW (yes, kilo watt) PA on the ground station.
The satellite suffers from spontaneous reboots every 1-4 hours (typically).
The payload has been powered on briefly, but no science data has been downlinked.
They are in the process of uploading new software to the satellite.
| Link: |
http://www.aausatii.auc.dk/
|
Compass One by Fachhochschule Aachen, Germany
|
---|
Deployment Mechanism: |
X-POD E
| Type: |
Single cubesat
| Mission: |
Technology demonstration of a miniature GPS receiver, and a transceiver for fast RF communication.
A color camera is implemented for p/r purposes.
| AODC: |
Magnetometer, sunsensors, and magnetorquers
| Communication: |
Callsign: DPØCOM
Downlink: 437.405 MHz (1200 bps AFSK AX.25; also 2400/4800 bps MSK)
Beacon: 437.275 (CW 15 wpm @ 3 min intervals; 8 min for power safe)
| Status: |
Pictures (although saturated) downlinked.
High speed telemetry (4800 MSK) confirmed working
| Link: |
http://www.cubesat.de
http://www.dk3wn.info/sat/afu/sat_compass.shtml
|
SEEDS (2) by Nihon University, Japan
|
---|
Deployment Mechanism: |
X-POD F
| Type: |
Single cubesat
| Mission: |
Rebuild of the SEEDS cubesat which was destroyed during June 26th, 2006 DNEPR launch failure.
Contains a gyro sensor for accurate determination of attitude motion
| AODC: |
Gyro sensor, and magnetometer. Information about control system not available
| Communication: |
Callsign: JQ1YGU
Downlink: 437.485 MHz (450 mW, AX.25; 90 mW CW)
| Status: |
Nominal operations, December 7th, 2008
| Link: |
http://cubesat.aero.cst.nihon-u.ac.jp/english/main_e.html
| Sixth batch launched May 19th, 2009 (TacSat-III) on a Minotaur-1
from the Mid-Atlantic Regional Spaceport (Wallops Island)
AeroCube-3 by the Aerospace Corporation, USA
|
---|
Deployment Mechanism: |
P-POD
| Type: |
Single cubesat
| Mission: |
New solar power subsystem to replace the one failing on AeroCube-2.
Two foot diameter semi-spherical (8-panel) balloon that can serve as a de-orbit device as well as a tracking aid.
The change in orbit life is estimated to be from 1-3 years (depending on atmosphere assumptions) without a balloon to 2-3 months with the balloon inflated.
A VGA-resolution camera pointing in the direction of the balloon will photograph its state of inflation.
200' tether attached to the upper stage. AeroCube-3 will measure the dynamics while at the end of this tether. The tether will be cut some time into the mission
| AODC: |
Two axis sun sensor and Earth sensor, permanent magnets and hysteresis rods
| Communication: |
TBD
| Status: |
TBD
| Link: |
http://www.aero.org (this is just a link to the company. No mission information available)
|
Hawksat-1 by Hawk Institute of Space Sciences, USA
|
---|
Deployment Mechanism: |
P-POD
| Type: |
Single cubesat
| Mission: |
Cubesat platform demonstrator mission
| AODC: |
TBD
| Communication: |
Downlink: 437.345 MHz
| Status: |
TBD
| Link: |
http://www.aero.org (this is just a link to the company. No mission information available)
|
Pharmasat-1 by Santa Clara University, NASA Ames Small Spacecraft Division, USA
|
---|
Deployment Mechanism: |
P-POD
| Type: |
Triple cubesat (mass 4 kg)
| Mission: |
Follow on from GeneSat-1, will study the influence of microgravity on yeast resistance to an antifungal agent
| AODC: |
TBD
| Communication: |
Beacon: 437.465 MHz (1200 bps AX.25, 150 mW, 0.5 seconds every 5 seconds)
Up/Downlink: 2.4 GHz ISM band
| Status: |
TBD
| Link: |
http://microsatellitefreeflyer.arc.nasa.gov/pharmasat.html
|
Polysat CP6 by California Polytechnic State University, USA
|
---|
Deployment Mechanism: |
P-POD
| Type: |
Single cubesat
| Mission: |
Test attitude determination and contol using magnetometers and magnetorquers. Also has two cameras
and tether for deorbit experiment
| AODC: |
Magnetometers and magnetorquers
| Communication: |
437.365 CW and 1200 baud FSK AX25
| Status: |
TBD
| Link: |
None
|
Seventh batch deployed from space shuttle Endeavour on July 30th, 2009
Aggiesat-2 by Texas A&M University, USA
|
---|
Deployment Mechanism: |
TBD
| Type: |
Single cubesat (?)
| Mission: |
TBD
| AODC: |
TBD
| Communication: |
Downlink: 436.250 MHz
| Status: |
TBD
| Link: |
http://aggiesat.org/Home
|
BEVO 1 (Dragonsat 1) by University of Texas at Austin, USA
|
---|
Deployment Mechanism: |
TBD
| Type: |
Single cubesat(?)
| Mission: |
TBD
| AODC: |
TBD
| Communication: |
Downlink: 437.325 MHz (1 W, 1200/9600 bps, GMSK, AX.25; 200 mW CW FM beacon)
| Status: |
TBD
| Link: |
http://paradigm.ae.utexas.edu/
|
Eighth batch scheduled for launch NET October, 2010 (Glory) on Taurus Rocket from Vandenberg
Explorer1Prime by Montana State University, USA
|
---|
Deployment Mechanism: |
TBD
| Type: |
Single cubesat (?)
| Mission: |
Evolved version of MEROPE, will study the Van Allen Belts using a Geiger Counter
| AODC: |
TBD
| Communication: |
Downlink: 437.505 MHz (CW, 1200 baud AFSK, Audio beacon)
| Status: |
Awaiting launch
| Link: |
http://ssel.montana.edu/explorer-1_prime/
|
Hermes by Colorado Space Grant Consortium, USA
|
---|
Deployment Mechanism: |
TBD
| Type: |
Single cubesat
| Mission: |
Verification of spacecraft bus and of high speed communication system (115 kbaud / 8 W (?))
| AODC: |
Permanent magnets and hysteresis rods, and magnetometer used for verification of the passive AODC system
| CDH |
PIC24HJ256GP610 microcontroller, using internal watchdog, and external RTC, three 64 MB SD cards, used for majority voting
| Communication: |
Downlink: 437.425 MHz and 2.4 GHz ISM band
| Status: |
Awaiting launch
| Link: |
http://spacegrant.colorado.edu/COSGC_Projects/co3sat/
|
Nineth batch scheduled for launch NET November, 2010 on VEGA Maiden Flight from French Guiana
Up-to-date communication parameters can be found here:
http://showcase.netins.net/web/wallio/CubeSat.htm
AtmoCube by University of Trieste, Italy
|
---|
Deployment Mechanism: |
TBD
| Type: |
Single cubesat
| Mission: |
Space weather monitoring.
Contains a (supposedly modified for space use(?)) GPS receiver (Trimble M-Loc MPM Module), a radiation sensor, and a
chip-based magnetometer based on magnetoresistance
| AODC: |
Magnetometer and GPS receiver
| Communication: |
70 cm amateur radio, AX.25
| Status: |
Awaiting launch
| Link: |
http://www2.units.it/~atmocube/
|
e-st@r by Politecnico di Torino, Italy
|
---|
Deployment Mechanism: |
TBD
| Type: |
Single cubesat
| Mission: |
Demonstration of active 3-axis attitude control system
| AODC: |
Inertial measurement unit and ?
| Communication: |
TBD
| Status: |
Awaiting launch
| Link: |
None
|
Goliat by University of Bucharest, Romania
|
---|
Deployment Mechanism: |
TBD
| Type: |
Single cubesat
| Mission: |
Imaging of the Earth surface using digital camera and in-situ measurements of radiation dose and micrometeoroid flux (50x37 mm piezo-film).
Part of the system is based on the Pumpkin Cubesat kit (2 pcs MSP430)
| AODC: |
Magnetometer (HMR 3400), Trimble GPS receiver, two axes momentum wheel system
| Communication: |
Beacon: 437.485 MHz (300 mW, 1200 bps, AFSK AX.25)
Downlink: 2.4 GHz band (1W, 9600 bps)
| Status: |
Awaiting launch
| Link: |
http://atl.calpoly.edu/~jfoley/SummerWorkshop08/Sun/1%20University%20of%20Bucharest.pdf
|
OUFTI-1 by University of Liège, Belgium
|
---|
Deployment Mechanism: |
TBD
| Type: |
Single cubesat
| Mission: |
Test use of D-STAR amateur radio digital communication protocol in space
| AODC: |
Permanent magnet and hysteresis rods
| Communication: |
70 cm amateur radio, D-STAR
| Status: |
Awaiting launch
| Link: |
http://www.leodium.ulg.ac.be/cmsms/
|
PW-Sat by Warsaw University of Technology, Poland
|
---|
Deployment Mechanism: |
TBD
| Type: |
Single cubesat
| Mission: |
Test deployable atmospheric drag de-orbiting device
| AODC: |
Magnetometer, MEMS gyroscope, GPS receiver (SSTL), Magnetorquers
| Communication: |
70 cm amateur radio, 1200 bps, AFSK AX.25
| Status: |
Awaiting launch
| Link: |
http://ska.meil.pw.edu.pl/pwsat_blog_pl/?page_id=75
|
Robusta by University of Montpellier 2, France
|
---|
Deployment Mechanism: |
TBD
| Type: |
Single cubesat
| Mission: |
Test radiation effects on bipolar transistors
| AODC: |
TBD
| Communication: |
Callsign: F6FAO
Downlink: 435.325(requested; 800 mW, 1200 bps, AFSK AX.25; data burst for 20 sec every 3 min)
| Status: |
Awaiting launch
| Link: |
http://robusta.ies.univ-montp2.fr/ (french)
|
SwissCube by EPFL (Polytechnical School of Lausanne), Switzerland
|
---|
Deployment Mechanism: |
TBD
| Type: |
Single cubesat
| Mission: |
Observe oxygen emission in order to characterise the airglow intensity.
Minimum science mission is 3 months, can be extended up to one year.
| AODC: |
Sun sensors, magnetometer, gyro and magnetorquers
| Communication: |
437.500 MHz (100 mW, CW beacon; 1 W, 1200 bps, AFSP AX.25)
| Status: |
Awaiting launch
| Link: |
http://swisscube.epfl.ch
|
UNICubeSAT by University of Rome, Italy
|
---|
Deployment Mechanism: |
TBD
| Type: |
Single cubesat
| Mission: |
Performing in-situ measurements of atmospheric neutral density using Broglio drag balance instrument
| AODC: |
TBD
| Communication: |
TBD
| Status: |
Awaiting launch
| Link: |
None
|
XaTcobeo by a collaboration of University of Vigo and INTA, Spain
|
---|
Deployment Mechanism: |
TBD
| Type: |
Single cubesat
| Mission: |
Demonstrate software-defined radio and solar panel deployment
| AODC: |
TBD
| Communication: |
70 cm amateur radio
| Status: |
Awaiting launch
| Link: |
http://www.xatcobeo.com/cms/index.php
|
HiNCube by Narvik University College, Norway
|
---|
Deployment Mechanism: |
TBD
| Type: |
Single cubesat
| Mission: |
Camera
| AODC: |
TBD
| Communication: |
TBD
| Status: |
Awaiting launch (backup payload for VEGA Maiden Flight
| Link: |
http://hincube.hin.no
|
UWE-3 by University of Wuertzburg, Germany
|
---|
Deployment Mechanism: |
TBD
| Type: |
Single cubesat
| Mission: |
Demonstration of active 3-axis ADCS system (magnetorquers)
| AODC: |
TBD
| Communication: |
TBD
| Status: |
Awaiting launch (backup payload for VEGA Maiden Flight
| Link: |
None
|
Other cubesats under development, not presently scheduled for launch
The list is probably not complete. If you know of a project not on the list, please contact me,
preferable with a link to a website containing mission profile etc.
AAUSAT-3 by Ålborg University, Denmark
|
---|
Deployment Mechanism: |
TBA
| Type: |
Single cubesat
| Mission: |
Color camera and an AIS receiver which will be used to monitor vessels around Greenland
| AODC: |
Magnetometer, gyroscopes and magnetorquers
| Communication: |
UHF and S-band (plus VHF receiver for AIS)
| Status: |
Under development
| Link: |
http://aausat3.aau.dk
|
AS-1 by Auburn University, USA
|
---|
Deployment Mechanism: |
TBA
| Type: |
Single cubesat
| Mission: |
TBD
| AODC: |
No attitude control (according to website)
| Communication: |
TBA
| Status: |
Under development
| Link: |
http://space.auburn.edu/as1/index.html
|
BeeSat by Technical University of Berlin, Germany
|
---|
Deployment Mechanism: |
SPL (Single Pico-Satellite Launcher)
| Type: |
Single cubesat
| Mission: |
Demonstrate use of coin size micro wheels for attitude control and 640x480 color camera
| AODC: |
Gyro, magnetometer, sun sensors, magnetorquers and above mentioned wheels
| Communication: |
TBA, but 435 MHz amateur frequency range envisioned, 0,5W GMSK 9600/4800 bps; uplink 4800bps
Callsign: DP0BEE
| Status: |
Under development
| Link: |
http://www.beesat.de
|
CAPE-2 by University of Louisiana, LA, USA
|
---|
Deployment Mechanism: |
TBA
| Type: |
Single cubesat
| Mission: |
TBD
| AODC: |
TBD
| Communication: |
TBA
| Status: |
Being planned
| Link: |
http://ulcape.org/wiki/Main_Page
|
DTUsat-2 by Technical University of Denmark
|
---|
Launch: |
TBA, expected 2007/8
| Deployment Mechanism: |
TBA
| Type: |
Single cubesat
| Mission: |
Tracking of migrating birds. A small 5-8 g transmitter will be mounted on a number of birds.
The signals will be received by the satellite and returned to the groundstation. Position accuracy
of the tracked birds is TBD.
The mission was chosen among these proposals
at a meeting on November 10th, 2005
| AODC: |
TBD, MEMS sun sensors, magnetometer and magnetorquers are likely.
It looks like they want to use a 1.5 m boom for gravity control!
| Communication: |
Uplink: 1268.900 MHz
Downlink: 2401.835 MHz
| Status: |
Under development
| Link: |
http://www.dtusat.dtu.dk
|
Funsat by University of Central Florida, USA
|
---|
Deployment Mechanism: |
TBA
| Type: |
Single cubesat
| Mission: |
TBD at a design competition. Winner will be announced at a workshop in May
| AODC: |
TBD
| Communication: |
TBA
| Status: |
Being planned
| Link: |
http://fsgc.engr.ucf.edu/funsat
|
GSAT by Gator Amateur Radio Club, University of Florida, USA
|
---|
Deployment Mechanism: |
TBA
| Type: |
Single cubesat
| Mission: |
Demonstrate an inflateable device to deorbit a pico-satellites after completion of its mission in order to minimize space debris
| AODC: |
TBD
| Communication: |
437.385 MHz (2 W, 1200 bps AX.25)
| Status: |
Under development
| Link: |
http://www.ufsmallsat.com
|
HEIDELSAT by Heidelberg University of Applied Sciences, Germany
|
---|
Launch: |
TBA, expected 2009
| Deployment Mechanism: |
TBA
| Type: |
Three single cubesats
| Mission: |
Study of cosmic ray air showers
| AODC: |
TBD
| Communication: |
TBA
| Status: |
Under development
| Link: |
http://www.fh-heidelberg.de/satellit (German) .
|
ITUpSAT-I by Istanbul Technical University, Turkey
|
---|
Deployment Mechanism: |
TBA
| Type: |
Single cubesat
| Mission: |
Low resolution camera
| AODC: |
Gyro, accelerometer, magnetometer (under study)
| Communication: |
TBA
| Status: |
Under development
| Link: |
http://usl.itu.edu.tr/?&dil=en
|
KatySat 1 by Stanford University, USA
|
---|
Deployment Mechanism: |
P-POD
| Type: |
Single cubesat
| Mission: |
This mission is the first cubesat mission for high school students (KatySat = Kids Aren’t Too Young for Satellites).
The mission is to implement a "technically simple, fun, flexible, and affordable satellite system that will
challenge and motivate young people’s interest in the fields of space, technology, and science".
KatySat will feature sensors for radiation, magnetic field, and optical (camera).
Editors note: And they call it simple?
| AODC: |
Permanent magnet (Editors note: and presumeably hysteresis rods)
| Communication: |
Downlink: 70 cm (1200 bps AFSK/FM AX.25)
Uplink: 2m (1200 bps AFSK/FM AX.25)
| Status: |
Under development
| Link: |
http://www.katysat.org/
|
KKS-1 by Metropolitan College of Industrial Technology, Japan
|
---|
Deployment Mechanism: |
TBA
| Type: |
Single cubesat, TBC
| Mission: |
TBD
| AODC: |
TBD
| Communication: |
Downlink: 437.445 MHz
Beacon: 437.275 MHz (CW)
Uplink: 145.980 MHz
| Status: |
Under development
| Link: |
http://www.kouku-k.ac.jp/~kks-1 (Japaneese)
|
M-Cubed by University of Michigan, USA
|
---|
Deployment Mechanism: |
TBA
| Type: |
Single cubesat
| Mission: |
Camera
| AODC: |
Permanent magnet and hysteresis rods
| Communication: |
TBA, Amateur frequencies
| Status: |
Under development
| Links: |
http://umcubed.com
|
MOVE by Technical University of München, Germany
|
---|
Deployment Mechanism: |
TBA
| Type: |
Single cubesat
| Mission: |
TBD
| AODC: |
TBD
| Communication: |
TBA
| Status: |
Being planned
| Link: |
http://www.move2space.de/home.php
|
Sallesat by La Salle University, Spain
|
---|
Deployment Mechanism: |
TBA
| Type: |
Single cubesat
| Mission: |
TBD
| AODC: |
TBD
| Communication: |
TBA
| Status: |
Being planned
| Link: |
http://www.sallesat.org (Spanish)
|
SMARTsat by Texas A&M University, USA
|
---|
Launch: |
TBA
| Deployment Mechanism: |
TBA
| Type: |
Single cubesat
| Mission: |
Demonstrate the use of shape memory alloys to deploy solar panels, camera
| AODC: |
Gravity gradient boom, sun sensor, magnetometer (Honeywell HMC2003), magnetorquers
| Communication: |
TBA
| Status: |
Under development
| Link: |
http://sei.tamu.edu/cubesat
|
UCISat 1 by University of California, Irvine, USA
|
---|
Launch: |
Target for 2008Q4 or 2009Q1 (will be decided in June 2008)
| Deployment Mechanism: |
P-POD
| Type: |
Single cubesat
| Mission: |
CMOS camera and IMU (Inertial Measurement Unit) used to determine how well the passive ACS performs
| AODC: |
Permanent magnet and hysteresis rods
| Communication: |
437.405 MHz (1 W, AFSK AX.25TBA)
| Status: |
Under development
| Link: |
http://www.ucisat.org
|
UWE-2 by University of Würzburg, Germany
|
---|
Deployment Mechanism: |
TBA
| Type: |
Single cubesat (TBC)
| Mission: |
Test a newly developed attitude determination system
| AODC: |
Information not available
| Communication: |
437.385 MHz (AX.25 and CW)
| Status: |
Under development
| Link: |
http://www7.informatik.uni-wuerzburg.de/cubesat
|
[Unnamed] by University of Leicester, England
|
---|
Deployment Mechanism: |
TBA
| Type: |
Single cubesat
| Mission: |
Nanometeroid dust detector
| AODC: |
Magnetometer, magnetorquers
| Communication: |
TBA
| Status: |
Under development
| Link: |
http://cubesat.wikidot.com
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Other Student Satellite Missions
The major part of the project must have student involvement to qualify.
The list is currently far from being complete. If you know of a project not on the list, please contact me,
preferable with a link to a website containing mission profile etc.
Launched Missions
SEDSAT-1 (OSCAR-33) by University of Huntsville, AL, USA
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Launch: |
October 24th, 1998 on a Delte II LV from Vandenberg, CA, USA into a 1054x543 km,
low Earth orbit (inclination = 31.44°)
| Type: |
36 kg microsatellite, 35x35x30 cm3 with several protuberances (antennas etc).
| Mission: |
Provide multi-spectral remote sensing with a resolution of 200 m from an 800 km orbit.
Data provided to the public over the internet.
Demonstrate a new ADCS.
Reprogrammability of software components.
| AODC: |
Image processing, AshTech 12-ch GPS receiver, and magnetorquers
| Communication: |
Mode V/A Linear Transponder (non-operational):
Uplink: 145.9150-145.9750 MHz (SSB/CW)
Downlink: 29.3500-29.4200 MHz (SSB/CW)
Mode L/U Packet (semi-operational):
Uplink: 1266,6870 MHz (9600 bps FSK)
Downlink: 437.9100 MHz (9600 bps FSK)
| Status: |
Problems with receivers meant that the imaging system was never used.
| Link: |
http://www.seds.org/sedsat
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SSETI Express by many European universities, supported by ESA
|
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Launch: |
October 27th, 2005 on a Kosmos 3M LV from Plesetsk, Russia into a 686x686,
sun synchronous orbit (inclination = 98°) with a local time of 10:30
| Type: |
Satellite build by students from 10 European universities, supported by ESA
| Mission: |
MEMS sun sensors (made for DTUsat), color camera (made for AAUsat), propulsion system, Cubesat deployment
| AODC: |
Sun-sensors, magnetometer, semi-passive magnetic stabilization and a cold-gas payload propulsion system (Nitrogen)
| Communication: |
Callsign: SSETI1
437.250 MHz (1 W, 9600 bps FSK AX.25) and
2401.835 MHz (3 W, 38.4 kbps FSK AX.25)
| Status: |
Contact established
Problems with the excess power dissipation system causes insufficient power for battery charging.
The cause seems to be a short-circuited MOSFET. Ground tests have shown that it will open-circuit (2nd fail)
after about 100 cycles, which should have happend in the middle of November 2005.
Contact lost within 12 hours after launch
Check http://www.express.space.aau.dk/?language=en&page=news for most up-to-date status
| Links: |
http://www.esa.int/ssetiexpress
http://sseti.gte.tuwien.ac.at/express/mop/ (follow related site links from here)
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HIT-SAT by Hokkaido Institute of Technology, Japan
|
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Launch: |
Launched September 22nd, 2006 on a M-V-7 from Uchinoura Space Center, Japan into a
600 x 250 km sun-synchronous orbit (inclination 98°)
| Type: |
2.7 kg, 12 cm cube
| Mission: |
Test of spacecraft bus
| AODC: |
Sun-sensors, magnetometer, gyro, and magnetorquers
| Communication: |
Callsign: JR8YJT
437.425 MHz (1200 bps FM AFSK) (Not AX.25!)
437.275 MHz (100mW, CW)
| Status: |
Operational, problems with the power subsystem in the end of October 2006, last telemetry received June 18th, 2008, shortly before reentry.
| Links: |
http://www.hit.ac.jp/~satori/hitsat/index-e.html
http://www.dk3wn.info/sat/afu/sat_hitsat.shtml (German)
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RAFT1 and MARScom by US Naval Academy Satellite Lab, USA
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Launch: |
The satellites were deployed from the Space Shuttle Discovery during STS-116 mission on December 21st, 2006
Initial altitude of 170 to 185 km, resulting in a lifetime of 75 to 200 days
| Type: |
Two 5" cubes, 3 (MARScom) and 4 (RAFT1) kg
| Mission: |
The satellites will be the first of their size with the ability to be tracked by the Navy Space Surveillance (NSSS) radar fence.
The satellites will also function as amateur radio transponders
| AODC: |
Permanent magnet
| Communication: |
Downlink: 27 MHz SSB (MARScom); 145.825 MHz (AX.25) (RAFT1)
Uplink: 123/148 MHz (MARScom); 28.122/145.825 MHz (RAFT1)
| Status: |
RAFT1: Nominal Operations
MARScom: No information available
| Links: |
http://web.ew.usna.edu/~raft/index.htm
http://web.usna.navy.mil/~bruninga/raft.html
http://web.usna.navy.mil/~bruninga/ande-raft-ops.html
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Missions Being Planned or Under Development
Bayernsat by Technische Universität München
|
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Launch: |
TBA
| Type: |
Micro-satellite (<50 kg; 42 x 42 x 42 cm3)
| Mission: |
Test geostationary relay link, 756 x 567 pixel, 2 fps color camera, onboard parallel processor (XPP)
| AODC: |
TBD
| Communication: |
S-band communication through a geostationary relay satellite (ARTEMIS) at 500 kbps, and
S-band TM/TC link.
| Status: |
Under development
| Link: |
http://www.bayernsat.com
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BLUEsat by University of New South Wales, Australia
|
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Launch: |
TBA
| Type: |
Micro-satellite (10-15 kg; 22 x 22 x 22 cm3)
| Mission: |
GPS unit for orbit position and timing, possibly a CMOS camera, and an experiment testing the
UV resistance and durability of a piece of specially coated Lexan.
| AODC: |
Permanent magnet and hysteresis rods
| Communication: |
TBA, but: 433-437 MHz band for downlink (9600 bps GMSK AX.25); 145 MHz Uplink (9600 bps)
| Status: |
Under development
| Link: |
http://www.bluesat.unsw.edu.au/
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HAUSAT-2 by Hankuk Aviation University, South Korea
|
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Launch: |
TBA, 2008
| Type: |
Micro-satellite (10-20 kg)
| Mission: |
Electric plasma probe, animal tracking system.
Mission lifetime: 2 years
| AODC: |
Star tracker, GPS receiver
| Communication: |
TBA, but: Downlink: 9600 bps FSK; Uplink: 2400 bps FSK
| Status: |
Under development
| Link: |
http://134.75.55.85/new_version/english/hausat_2/index.php
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Mars Gravity by Massachustts Institute of Technology, USA and University of Queensland, Australia
|
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Launch: |
Funding dependent, no earlier than mid 2009.
Launch from Cape Canaveral, Florida, USA, into a 400 km circular orbit with an inclination of 31 deg.
Recovery in Woomera, Australia. Baseline LV is Falcon 1 from SpaceX
| Type: |
About 400 kg, 1.2 m long, 1 m diameter
| Mission: |
Study 15 mice exposed to artificial Mars gravity during 5 weeks, after which
the s/c will reenter the Earth's atmosphere and land in Australia.
Budget is around 30 million USD, including launch.
| AODC: |
Spin stabilization (for artificial gravity environment) and propulsion system
| Communication: |
TBD
| Status: |
Being planned
| Link: |
http://www.marsgravity.org
|
Other Space Related Student Projects
This is a non-exhaustive list of other space related student projects, intented to be used as inspiration for future student projects.
If you know of a project which you thing should be on this list, please contact me,
preferable with a link to a website containing project information.
Penn State Sounding Rocket Projects
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Description: |
The students at Penn State have designed, build and launched a number of sounding rocket experiments.
| Link: |
http://spirit.ee.psu.edu
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Other General Cubesat / Student Satellite Links
Official Cubesat homepage
|
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Description: |
This is the official Cubesat homepage. It contains some general requirements in order for
the cubesat to fit into the P-PODs, and requirements regarding testing.
| Link: |
http://cubesat.org
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21 is only half the truth
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