850 Sligo Ave. Suite 600
Silver Spring, MD 20910
1-888-322-6728
 Satellite Detail - Mexico-OSCAR 30
Launch Pad Navigator Sat Status Keps News Store Members Contact Us Return
Photo of Mexico-OSCAR 30

Mexico-OSCAR 30
(UNAMSAT-2)


Spacecraft Summary

OSCAR Designation:  Mexico-OSCAR 30     Oscar Number:  MO-30    
International Designator:  1996-052B     Norad Number:  24305    
Common Name:  UNAMSAT-2     Satellite Type:  Microsatellite    
Launch Date:  5 September, 1996     Launch Location:  PKMTR    
Apogee:  1010.00     Perigee:  964.00    
Inclination:  82.94     Period:  104.84    
Dimensions:  15 x 15 x 15 cm     Weight:  10.700 Kg    
Organization: National University of Mexico


Frequency Information
 
Mode V/U (J) PacSat BBS: Non-Operational
Downlink 435.1380 MHz AFSK 1200 BPS
Downlink 435.2060 MHz AFSK 1200 BPS
Uplink: 145.8150 MHz AFSK 1200 BPS
Uplink: 145.8350 MHz AFSK 1200 BPS
Uplink: 145.8550 MHz AFSK 1200 BPS
Uplink: 145.8750 MHz AFSK 1200 BPS

Current Keplerian Elements

MO-30
1 24305U 96052B   09325.00904450  .00000013  00000-0 -25259-5 0  2735
2 24305  82.9366 238.0394 0029768 175.2563 184.8895 13.73575093662202


Detailed Description

Launched September 5, 1996. MO-30 is the twin spacecraft of UNAMSAT-1 (see above). Unfortunately, it failed after about a day of transmitting due to a dead uplink receiver.

MO-30 was constructed at the National University of Mexico (UNAM). The satellite had two telemetry transmitters with BPSK modulation at 1200 baud using AX.25 protocol in Ultra High Frequency of 437 MHz. Every telemetry frame sends to Earth about 60 parameters, consisting of voltages, currents, temperatures and binary states.

The main computer had a V40 microprocessor from NEC (equivalent to Intel's 80186), hardened to radiation, a bank of EDAC memory of 256 Kbytes, and a SRAM memory bank of 4 Mbytes. The typical power consumption of this computer was 1 watt.

In one of the modules, the energy collected from the solar panels was stored in niquel-cadmium batteries. In this same module there was a circuit that regulates the voltages in use in the rest of the satellite. The use of internal batteries guaranties proper operation even when the satellite is in eclipse.

The experiment requires a pulse transmitter, a broad band echo receiver in the same frequency of the transmitter, and a controller based in a HC05 family microcontroller from Motorola. This controller digitized the echoes received by the receptor and, with help of the main computer, evaluated if those echoes met the criteria to be considered a valid event, in which case the event was stored in the main computer.

The satellite had a 5 channel digital receptor that allowed communication from earth. Four channels were for users, and one was reserved for commanding and software loading purposes.

Externally, the satellite had a set of antennas for UHF transmission using circular polarization, a dipole antenna for pulse transmission and reception and, in the upper part, an antenna for reception of telecommands and software sent from Earth.

The body of the satellite is surrounded by Gallium Arseniure solar cells, recovered with a thin quartz crystal as protection against erosion


Reference Documents:


  Copyright©The Radio Amateur Satellite Corporation 2004 ,2009 - All Rights Reserved
  Report a bug on this page