PRoject of OIT Electric-Rocket-Engine Onboard Small Space Ship
The Japanese amateur radio satellite PROITERES was launched Sunday, September 9 at 0423 UT on PSLV-C21 from the Indian Space Research Organisation (ISRO) Satish Dhawan space centre. The satellite SPOT6 was on the same launch into a 654 km × 643 km, 98.28º inclination orbit. The rocket was fitted with the mini Redundant Strapdown Inertial Navigation System (mRESINS).
A team of students and faculty members of Osaka Institute of Technology (OIT) are now developing a small satellite called MicroSat with an electric propulsion rocket engine, which is installed with radio equipment. The project called PROITERES, standing for PRoject of OIT Electric-Rocket-Engine Onboard Small Space Ship, aims to demonstrate powered-flight technology for an ultra-small satellite and to monitor the Kansai District with a high-resolution camera. PROITERES also aims to reduce development costs and shorten the development period drastically by miniaturizing the satellite and its component parts.
437.485, 1k2 AFSK AX.25, FM
437.485 MHz, CW beacon, FM
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NORAD #38756 COSPAR Bezeichnung 2012-047-B Inklination (Grad) 98.293 RAAN 319.322 Excentrizität 0.0011265 ARGP 276.700 Umläufe pro Tag 14.73657225 Periode 1h 37m 42s (97.70 Min) Semi-major axis 7028 km Perigäum x Apogäum 642 x 657 km Bstar (drag Faktor) 0.000000000 1/ER Mean Anomaly 83.294
The main mission is powered flight of nano satellite by electrothermal pulsed plasma thrusters (PPTs). The orbit raising will be carried out by the PPTs. Pulsed plasma thrusters are expected to be used as thrusters for small/nano satellites. The PPT has some features superior to other kinds of electric propulsion. It has no sealing part, simple structure and high reliability, which are benefits of using a solid propellant, mainly Teflon (polytetrafluoroethylene: PTFE). However, performances of PPTs are generally low compared with other electric thrusters.
At Osaka Institute of Technology, the PPT has been studied since 2003 in order to understand physical phenomena and improve thrust performances with both experiments and numerical simulations. They mainly studied electrothermalacceleration-type PPTs, which generally had higher thrust-topower ratios (impulse bit per unit initial energy stored in capacitors) and higher thrust efficiencies than electromagnetic-acceleration-type PPTs. Although the electrothermal PPT has lower specific impulse than the electromagnetic PPT, the low specific impulse is not a significant problem as long as the PPT uses solid propellant, because there is no tank nor valve for liquid or gas propellant which would be a large weight proportion of a thruster system.
proiteres s1 ec 77 91 00 s2 00 00 00 00 proiteres s1 ec 78 91 00 s2 00 00 00 00 proiteres s1 ed 81 87 00 s2 00 00 00 00 proiteres s1 ed 7e 89 00 s2 00 00 00 00 proiteres s1 ec 79 91 00 s2 00 00 00 00 proiteres s1 ec 7d 91 00 s2 00 00 00 00 proiteres s1 ec 76 93 00 s2 00 00 00 00 proiteres s1 ed 77 92 00 s2 00 00 00 00 proiteres s1 ec 7b 8c 00 s2 00 00 00 00
erste CW Baken am 09.09.2012 um 07:36 UTC und 09:08 UTC
PROITERES CW Telemetry Decoder
Ein ganz simpler Dekoder für die CW Telemtrie für PROITERES. Den empfangenen String einfach in das obere Fenster kopieren. Ledigleich der S1 String enthält verwertbare Telemetriedaten (RSSI, Batteriestrom, Batteriespannung).
Es ist unerheblich, ob Leerzeichen zwischen den Zeichen vorhanden sind. Wichtig ist nur, dass jeder Telemetriesatz in einer eigenen Zeile steht. Die einzelnen Telemetriewerte werden wie immer in gewohnter Weise als Graph angezeigt.
PROITERES 1 38756U 12047B 12253.83501871 -.00000054 00000-0 00000+0 0 90 2 38756 098.2926 319.3222 0011265 276.6998 083.2937 14.73657225 94