MDS (Mission Demonstration Satellite) was a technology demonstrator to flight-qualify commercial subsystems. MDS-1 flew a parallel computer, a solid state recorder, a nickel-hydrogen battery, and solar cells. It also carried a space environment experiment to monitor heavy ions and magnetic fields.

Length: 1.60 m (5.20 ft). Maximum Diameter: 1.60 m (5.20 ft). Span: 3.30 m (10.80 ft). Mass: 449 kg (989 lb).

• 2002 February 4 - MDS-1 - Launch Site: Tanegashima. Launch Complex: Y. Launch Vehicle: H-2. Mass: 304 kg (670 lb). Perigee: 373 km (231 mi). Apogee: 35,753 km (22,215 mi). Inclination: 28.30 deg. Period: 633.80 min.
  Technology qualification flight - maiden flight of H-2A booster. Launch delayed from January 31 and February 3. The second stage began its first burn at 0251 UTC and at 0257 UTC entered a 500 km circular parking orbit. After a 12 minute coast the second burn put stage 2 in geostationary transfer orbit. At 0315 UTC the small DASH vehicle was meant to separate from the upper adapter, but this apparently did not occur. At 0325 UTC VEP-3/upper adapter/DASH combination separated from the second stage, followed by two semi-cylindrical side panels, revealing the previously enclosed MDS-1 technology satellite which was ejected at 0331 UTC. At 0425 UTC the second stage was scheduled to make a third burn to test engine restart, completing the H-2A-2F mission.