TechEdSat-1, -3P


San Jose State University and University of Idaho (c/o NASA Ames Research Center)
TechEdSat 3P

The TechEdSAT-3p will be the first flight test of an Exo-Brake passive de-orbit system. TechEdSAT-3p is a triple cubesat (3U) with a set of dual advanced avionics systems powered by the previous core system. In 2U of the packaging (roughly 2/3 of the volume), there is stowed an erectable deployment system that would place the Exo-Brake in the desired orientation. Scaled as a 10 day experiment, the deployed system has the ballistic coefficient of 5 kg/m2 – and is constructed as a tension-based structure that would not entangle itself. During the de-orbit process, GPS data from the dual avionics as well as collected TLE (Two Line Elements) provided by the USSTRATCOM will be used to analyze the flight dynamics and compared to computational models. This experiment will be the antecedent of related experiments at larger scale (e.g., for a 1.5 day de-orbit) and controllability. The 3U cubesat was deployed from the ISS on the 20 November 2013 at 07:58 UTC



437.465 MHz 1k2 AFSK, AX.25, 800mW



not heard

Orbital Parameter

Inclination             51.650
RA of A. Node           74.600
Eccentricity            0.0001020
Argument of Perigee     107.680
Revs per day            15.50207966
Period                  1h 32m 53s (92.88 min)
Semi-major axis         6 794 km
Perigee x Apogee        415 x 417 km
BStar (drag term)       0.000257330 1/ER
Mean anomaly            280.995


San Jose State University


TechEdSat is a NASA Ames Research Center 1U CubeSat built by San Jose State University Students in partnership with ÅAC Microtec. It’s mission is to evaluate Space Plug-and-play Avionics (SPA) designed in Sweden by ÅAC Microtec, and to perform a communications experiment utilizing the Iridium and Orbcomm satellite phone network.

NASA-Catalog: 38854


437.465 MHz, 1k2 AFSK AX.25, FM



Orbital Parameter

NORAD                   38854
COSPAR designator       1998-067-CP 
Inclination             51.647
RA of A. Node           275.490
Eccentricity            0.0014651
Argument of Perigee     145.137
Revs per day            15.51582271
Period                  1h 32m 48s (92.80 min)
Semi-major axis         6 790 km
Perigee x Apogee        402 x 422 km
BStar (drag term)       0.000898790 1/ER
Mean anomaly            215.074


decayed on 05 May 2013


  • Stensat Radio Beacon
  • 4x nanoRTU (ÅAC Microtec)
  • Main Power Distribution Board (ÅAC Microtec)
  • RTU Lite (ÅAC Microtec)
  • 2 meter band Monopole Antenna
  • 70cm band Monopole Antenna
  • 1600 MHz Patch Antenna
  • Pumpkin, Inc. 1U Skeletonized CubeSat Structure
  • Canon BP-930 Lithium-ion battery

TechEdSat Beacon Format

Operating at TBD MHz FM, the TechEdSat beacon sends an AX.25 packet every 30 seconds. The packet contains data about the spacecraft systems operation. The data portion of a standard AX.25 packet is 64 characters long. The beacon packet contains only standard ASCII characters. Each character after the URL represents a HEX value. All characters are selected from the set 0 – 9 and A – F. Below is an example of the 64-character long raw data string:


Two packet formats will be sent alternately (0 seconds send packet 1, 30 seconds send packet 2, 60 seconds send packet 1, etc…) The packet number, 1 or 2, is included in the packet. The elapsed timer and solar array status appear in both packets.