TY - GEN
T1 - Lessons learned developing a 3U communication CubeSat
AU - Aslan, Alim Rustem
AU - Yagci, Bulent
AU - Umit, Ertan
AU - Bas, Mustafa Erdem
AU - Uludaǧ, Mehmet Şevket
AU - Özen, Okan Emre
AU - Süer, Murat
AU - Sofyali, Ahmet
PY - 2013
Y1 - 2013
N2 - A 3-Unit CubeSat, called "3USAT", is developed for voice communication in Low Earth Orbit (LEO). The spacecraft was launched on 26 th of April 2013 from China Jiaquan Satellite Launch centre with a LM2D launch vehicle. The main payload of the 3USAT is a linear transponder operating in VHF/UHF. The 3USAT includes many sensors and a camera for taking pictures, as well. Most subsystems of the CubeSat have redundancy which is provided by COTS equipment and/or in-house developed systems. The two transponders are developed genuinely by the project team. The project team have gained valuable experience from developing subsystems, integrating COTS equipment's, and carrying out space simulation testing. The payload power requirements resulted in temperatures exceeding 100°C. A remedy was developed to remove heat resulting from high power amplifier. Other problems encountered and resolved include grounding issues of electronic and RF systems, the transfer of data and power using PC104 form factor between 1U sections of for 3U COTS structures, thermal vacuum testing of payloads with supporting equipment outside of the chamber, cabling and "cold solder joint" among others.
AB - A 3-Unit CubeSat, called "3USAT", is developed for voice communication in Low Earth Orbit (LEO). The spacecraft was launched on 26 th of April 2013 from China Jiaquan Satellite Launch centre with a LM2D launch vehicle. The main payload of the 3USAT is a linear transponder operating in VHF/UHF. The 3USAT includes many sensors and a camera for taking pictures, as well. Most subsystems of the CubeSat have redundancy which is provided by COTS equipment and/or in-house developed systems. The two transponders are developed genuinely by the project team. The project team have gained valuable experience from developing subsystems, integrating COTS equipment's, and carrying out space simulation testing. The payload power requirements resulted in temperatures exceeding 100°C. A remedy was developed to remove heat resulting from high power amplifier. Other problems encountered and resolved include grounding issues of electronic and RF systems, the transfer of data and power using PC104 form factor between 1U sections of for 3U COTS structures, thermal vacuum testing of payloads with supporting equipment outside of the chamber, cabling and "cold solder joint" among others.
UR - http://www.scopus.com/inward/record.url?scp=84904607419&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:84904607419
SN - 9781629939094
T3 - Proceedings of the International Astronautical Congress, IAC
SP - 7992
EP - 7997
BT - 64th International Astronautical Congress 2013, IAC 2013
PB - International Astronautical Federation, IAF
T2 - 64th International Astronautical Congress 2013, IAC 2013
Y2 - 23 September 2013 through 27 September 2013
ER -
