Temisat's primary mission was demonstration of a data relay system. Environmental measurements were acquired through ground sensors, collected, temporarily stored on the ground, and logged by an autonomous terminal until an upload request was received from TEMISAT.

Characteristics: (a) Mass 42 kg (b) Dimension 35 x 35 x 35 cm, (c) Electric power 62 W Max, (d) Attitude control : 2 magnetic coil, 1 Am2, (e) On-board memories - 2 of 8.5 Mbytes each, (f) Lifetime 5 years. Drift of the ascending node of orbital plane: 0.8 deg/d westwards. Temisat was a co-passenger of the Meteor 2 satellite.

Typical orbit: 932 km x 967 km at 83 degrees inclination. Mass: 42 kg (92 lb).

• 1993 August 31 - Temisat - Launch Site: Plesetsk. Launch Complex: -. Launch Vehicle: Tsiklon. Mass: 42 kg (92 lb). Perigee: 936 km (581 mi). Apogee: 967 km (600 mi). Inclination: 82.60 deg. Period: 104.10 min.
  The Temisat micro-satellite was a piggyback payload designed to collect and re-transmit environmental data from terrestrial sensors and was separated from Meteor-2-21 on the seventh transit of the flight. Temisat was registered by the Telespazio Italian partner in agreement with the Kaiser-Threde Company (Munich). Environmental measurements were acquired through ground sensors, collected, temporarily stored on the ground, and logged by an autonomous terminal until upload request is received from TEMISAT.Characteristics: (a) Mass 42 kg (b) Dimension 35 x 35 x 35 cm, (c) Electric power 62 W Max, (d) Attitude control : 2 magnetic coil, 1 Am**2, (e) On-board memories - 2 of 8.5 Mbytes each, (f) Lifetime 5 years. Drift of the ascending node of orbital plane: 0.8 deg/d westwards. Copassenger of METEOR 2 satellite.