S80/T [SSTL]
Official name S80/T
Alternative name S80 T
Cospar ID 1992-052C
Norad ID 22078
Launch date 1992-08-10
Launch site FRGUI
Launch vehicle Ariane-42P H10
Country/Organization France
Type application Communication, experimental
Operator CNES
RCS size MEDIUM
Decay date ON ORBIT
Period (min) 111.9
Inclination (deg) 66.08
Perigee (km) 1301
Apogee (km) 1327
Eccentricity 0.00989345509893455
Mean motion (revs. per day) 12.8686327077748
Semi-Major axis (km) 7692.135
Raan (deg) 82.3242
Arg of perigee (deg) 279.053
Shape Hex Poly
Mass (kg) 49.55
Height (m) 0.35
Width (m) 0.35
Depth (m) 0.35
Span (m^2) 0.7
Contractors Matra Marconi Space (Prime), SSTL (Bus)
Equipment 148/138 MHz transponder
Propulsion None
Configuration Microsat-70
Power Solar cells, batteries

The S80/T satellite was built for CNES by Matra Marconi Space using the Surrey Satellite Technology Microbus (Uosat) bus. The 0.35 × 0.35m, 50 kg satellite had a 6-m gravity gradient mast. It was launched on 1992 Aug 10 on an ASAP Ariane from Kourou. S80/T carried an experimental 148/138 MHz transponder for tests of mobile communications and location-finding for a proposed, but later abandoned, LEO constellation named S80 or Taos.

The spacecraft finally suffered electrical failure due to total dose effects in October 1999.

Satellite COSPAR Date LS Launch Vehicle Remarks
S80/T 1992-052C 1992-08-10 FRGUI Ariane-42P H10 with TOPEX Poseidon, Kitsat 1