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MDS
MDS-1
MDS-1
Credit: Manufacturer Image
Japanese technology satellite. MDS (Mission Demonstration Satellite) was a technology demonstrator to flight-qualify commercial subsystems.

Status: Operational 2002. First Launch: 2002-02-04. Last Launch: 2002-02-04. Number: 1 . Gross mass: 449 kg (989 lb). Height: 1.60 m (5.20 ft). Span: 3.30 m (10.80 ft).

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.



Subtopics

MDS 1 (Tsubasa) Technology satellite built by NEC for NASDA, Japan. Launched 2002.

MDS 2 Technology satellite operated by NASDA, Japan.

Family: Technology, Technology satellite. Country: Japan. Launch Vehicles: H-II, H-IIA, H-IIA 2024. Launch Sites: Tanegashima, Tanegashima Y. Agency: NASDA, NEC. Bibliography: 2, 4, 552, 554.
Photo Gallery

MDS 2MDS 2
Credit: Manufacturer Image


MDS-1MDS-1
Credit: Manufacturer Image



2002 February 4 - . 02:45 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2024.
  • MDS-1 - . Mass: 304 kg (670 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: MDS. USAF Sat Cat: 27367 . COSPAR: 2002-003A. Apogee: 35,753 km (22,215 mi). Perigee: 373 km (231 mi). Inclination: 28.3000 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.



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