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Last updated: August 7th, 2009
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[No longer being updated (last update medio 2009)]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.

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
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)
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.
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.

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 contactSome contactFull contactTotal
1 (June 2003) 0 2 1 2 + 1 triple5+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 double0 0 0 13 + 1 double
Solo (December 2006) 0 0 0 1 triple 1 triple
4 (April 2007) 0 1 3 + 1 triple2 6 + 1 triple
5 (April 2008) 0 0 0 3 + 1 double + 2 triple3 + 1 double + 2 triple
6 (May 2009) 0 ? ? ? 3+1 triple
7 (July 2009) 0 ? ? ? 2 (1U?)
Total 13 +
1 double
44+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

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
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

XI-IV by University of Tokyo, Japan
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

CanX-1 by University of Toronto, Canada
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/

DTUsat by Technical University of Denmark
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

AAU Cubesat by Ålborg University, Denmark
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

QuakeSat by Stanford University and Quakesat LLC, USA
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
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/

UWE-1 by University of Würzburg, Germany
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

XI-V by University of Tokyo, Japan
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


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
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


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
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/

Sacred by University of Arizona, USA
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)

KUTEsat Pathfinder by University of Kansas, USA
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)

ICE Cube 1 by Cornell University (New York state), USA
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/

RINCON 1 by University of Arizona, USA
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)

SEEDS by Nihon University, Japan
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

HAUSAT 1 by Hankuk Aviation University, South Korea
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)

NCube1 by Norwegian University of Science and Technology
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/

MEROPE by Montana State University, USA
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/

AeroCube-1 by the Aerospace Corporation, USA
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)

CP2 by California Polytechnic Institute, USA
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/

CP1 by California Polytechnic Institute, USA
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/

ICE Cube 2 by Cornell University (New York state), USA
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/

Mea Huaka (Voyager) by University of Hawaii, USA
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)


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
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)


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
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)

AeroCube-2 by the Aerospace Corporation, USA
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)

CSTB-1 (Cubesat Testbed 1) by The Boeing Company, USA
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

Libertad-1 (Freedom 1) by University of Sergio Arboleda, Columbia
Deployment Mechanism: P-POD B#3
Type: Single cubesat
Mission: Camera and transmission of one stanza of the Colombian national anthem.
Note: Powered by primary batteries only. They will last for about 52 days.
This is the first Colombian satellite
AODC: GPS receiver, attitude determination/control unknown
Communication: Callsign: 5K3L
Downlink: 437.405 MHz (1200 bps FM AFSK AX.25)
Digipeater: 145.825 MHz
Status: Last confirmed telemetry on May 4th, 2007 (weak, undecoded until May 7, 2007).
Designed with a 50 day lifespan
Links: http://www.usergioarboleda.edu.co/proyecto_espacial/index.htm (mostly spanish) and
http://www.universia.net.co/galeriadecientificos/noticiasdelacienciaencolombia/libertad1,primersatelitecolombiano4.html (spanish)


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/

KySat by a consortium consisting of a number of Kentucky universities, USA
Deployment Mechanism: TBA
Type: Single cubesat
Mission: Build technological interest in students, much of the satellite is based on commercially available parts, including from the Pumpkin cubesat kit
AODC: TBD
Communication: Downlink: 436.975 MHz (APRS type packets, HAM V/U FM transponder with 145.850 MHz uplink)
Status: Awaiting launch
Links: http://www.kysat.com
http://www.engr.uky.edu/idea/wiki/doku.php?id=projects:active:kysat:public:default
http://kysat.typepad.com/


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)

SEDSAT-2 by International collaboration
Deployment Mechanism: TBA
Type: Single cubesat
Mission: Earth imaging
AODC: TBD
Communication: TBA
Status: Being planned
Links: http://wiki.seds.org/index.php/SEDSAT-2 and:
http://blogs.seds.org/sedsat2

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

SOMP by Dresden University of Technology, Germany
Deployment Mechanism: TBA
Type: Single cubesat
Mission: Insitu measurements of atomic and molecular oxygen
AODC: Magnetometer, sun sensor, and magnetorquer
Communication: TBD
Status: Under development
Links: http://www.stard-online.de/ (German)
Here is a nice poster in english:
http://atl.calpoly.edu/~bklofas/Presentations/DevelopersWorkshop2008/SOMP.pdf

TJsat by Thomas Jefferson High School for Science and Technology, VA, USA
Launch: TBA, expected 2009
Deployment Mechanism: TBA
Type: Single cubesat
Mission: Cosmic Ray Detector
AODC: TBD, GPS and gravity boom considered
Communication: TBA
Status: Being planned
Links: http://en.wikipedia.org/wiki/TJ%5E3Sat
http://biz.yahoo.com/bw/061206/20061206005081.html?.v=1

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

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
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

SSETI Express by many European universities, supported by ESA
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)

HIT-SAT by Hokkaido Institute of Technology, Japan
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)

RAFT1 and MARScom by US Naval Academy Satellite Lab, USA
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

Missions Being Planned or Under Development

Bayernsat by Technische Universität München
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

BLUEsat by University of New South Wales, Australia
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/

HAUSAT-2 by Hankuk Aviation University, South Korea
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

Mars Gravity by Massachustts Institute of Technology, USA and University of Queensland, Australia
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
Description: The students at Penn State have designed, build and launched a number of sounding rocket experiments.
Link: http://spirit.ee.psu.edu

Other General Cubesat / Student Satellite Links

Official Cubesat homepage
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

AMSAT Cubesat Satellites Status Summary
Description: A page showing the status of some cubesat satellites (rarely frequently updated!)
Link: http://www.amsat.org/amsat-new/satellites/cubesats.php

AMSAT Satellites
Description: A page describing AMSAT satellites until 2002
Link: http://www.amsat.org/amsat/sats/n7hpr/history.html

AMSAT Satellites Status Summary
Description: A page showing the status of AMSAT satellites
Link: http://www.amsat.org/amsat-new/satellites/status.php

21 is only half the truth