Japanese technology satellite. One launch, 2002.02.04. 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.
Gross mass: 449 kg (989 lb).
More... - Chronology...
Height: 1.60 m (5.20 ft).
Span: 3.30 m (10.80 ft).
First Launch: 2002.02.04.
Number: 1 .
Associated Launch Vehicles
H-2 Heavy lift Japanese indigenous launch vehicle. The original H-2 version was cancelled due to high costs and poor reliability and replaced by the substantially redesigned H-2A. More...
H-2A Japanese orbital launch vehicle. Low-cost version of H-2 developed for the commercial market. The two SRB-A solid rocket boosters can be supplemented by 4 smaller SSB solid boosters. 0 or 2 SSB's can be fitted for reduced 9,940 kg or 10,740 kg LEO payloads. More...
H-IIA 2024 Japanese orbital launch vehicle. Three stage vehicle consisting of 4 x Castor 4XL + 2 x H-II SRB-A boosters + two-stage core vehicle. More...
Associated Manufacturers and Agencies
NASDA Japanese agency overseeing development of rockets, spacecraft, and rocket engines. National Space Development Agency, Japan. More...
NEC Japanese manufacturer of spacecraft. Nippon Electric Corporation, Japan. More...
McDowell, Jonathan, Jonathan's Space Home Page (launch records), Harvard University, 1997-present. Web Address when accessed: here.
McDowell, Jonathan, Jonathan's Space Report (Internet Newsletter), Harvard University, Weekly, 1989 to Present. Web Address when accessed: here.
NASA/GSFC Orbital Information Group Website, Web Address when accessed: here.
Space-Launcher.com, Orbital Report News Agency. Web Address when accessed: here.
Associated Launch Sites
Tanegashima Japan's main launch site for he larger N and H launch vehicles. In use for sounding rockets from 1967 and orbital launches from 1975. As of 2007 over 140 major launches had been made from the site. More...
2002 February 4 -
02:45 GMT - .
. Launch Complex
: Tanegashima Y
. LV Family
. Launch Vehicle
: H-IIA 2024
. LV Configuration
: H-IIA 2024 H-IIA-2F.
- 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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