Encyclopedia Astronautica
DS2000


Japanese communications satellite bus. Operational, first launch 2006.02.18. Mitsubishi Electric developed the DS2000 standard satellite platform based on a design originally created for the DRTS and ETS-8 platforms for NASDA.

The DS2000 features a highly reliable design and production based upon experience derived from participation in more than 280 satellite projects. It was capable of providing an output of up to 15kW, satisfying the power requirements for powerful and multiple communications transponders. At the same time its flexible design matched a variety of applications including hybrid communications payloads.

Leading characteristics:

  • Satellite Power Up to 15kW
  • Launch Mass 5,000 kg
  • Transponders 72 (nominal)
  • Life 15yr
  • Launch Vehicle Compatibility: H-2A, Ariane V, Delta IV, Atlas 5, Sea Launch
  • Subsystems
    • Electrical Power System: 100V regulated dual bus with high-efficiency silicon, multijunction GaAs solar array and NiH2 or Li-Ion batteries
    • Onboard Control System: Attitude control, data handling and satellite management
    • Attitude Control: Controlled bias momentum or zero momentum with satellite controller (SC) and four skew reaction wheels
    • Telemetry Tracking & Command: 1553B interface with SC
    • Structure: Carbon-fiber reinforced plastic, central cylinder type
    • Thermal Control: Heat pipe embedded payload panel, OSR, blanket and heater
    • Propulsion: Integrated Bi-propellant system with apogee and attitude control thrusters. Ion engine available on request.

Gross mass: 5,000 kg (11,000 lb).
Height: 4.00 m (13.10 ft).
Diameter: 4.00 m (13.10 ft).
Span: 30.00 m (98.00 ft).
Thrust: 500 N (110 lbf).
First Launch: 2006.02.18.
Last Launch: 2011.05.20.
Number: 3 .

More... - Chronology...


Associated Countries
See also
  • Ariane 5 The Ariane 5 was a completely new design, unrelated to the earlier Ariane 1 to 4. It consisted of a single-engine Lox/LH2 core stage flanked by two solid rocket boosters. Preparatory work began in 1984. Full scale development began in 1988 and cost $ 8 billion. The design was sized for the Hermes manned spaceplane, later cancelled. This resulted in the booster being a bit too large for the main commercial payload, geosynchronous communications satellites. As a result, development of an uprated version capable of launching two such satellites at a time was funded in 2000. More...
  • 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.

    3 stage vehicle consisted of 2 x H-II SRB + 1 x H-II stage 1 + 1 x H-II stage 2 More...


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-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...
  • Ariane 5ECA French orbital launch vehicle, first version of the evolved Ariane 5. The solid booster motors propellant load was increased by 2.43 tonnes and the case was welded, for a weight saving in dry mass of 1.9 tonnes. The core was powered by an improved Vulcain 2 engine. The oxygen-rich cycle of the engine allowed the oxygen bulkhead to be moved within the stage, resulting in a 15.2 tonne increase in propellant in the core. A new Lox/LH2 upper stage, using the HM7B engine and oxygen tank from the Ariane 4 series, replaced the storable propellant EPS stage of earlier models. The result was an increase in payload to geoscynchronous transfer orbit from 6 tonnes to 10.5 tonnes. More...

Associated Manufacturers and Agencies
  • Mitsubishi Japanese manufacturer of rockets, spacecraft, and rocket engines. Mitsubishi Electric Corp, Japan. More...

Bibliography
  • McDowell, Jonathan, Jonathan's Space Home Page (launch records), Harvard University, 1997-present. 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...
  • Kourou After the agreement with newly independent Algeria for France to evacuate their launch sites in that country, a location near Biscarosse was selected for French missile testing. However since only launches westwards across the Bay of Biscay could be made from this site, it was unsuitable for France's Diamant orbital launch vehicle. After reviewing 14 potential sites, a location in the South American French colony of Guiana was selected. This would allow over-water launches to a tremendous range of possible orbital inclinations -- from -100.5 deg to 1.5 deg. Being near the equator, it would provide the maximum assist from the earth's rotation for launches into equatorial orbits. The decision was formalized in April 1964 and in July 1966 ELDO chose the site for future launches of the Europa II launch vehicle. More...

DS2000 Chronology


2006 February 18 - . 06:27 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2024. LV Configuration: H-IIA 2024 H-IIA-9F.
  • MTSAT-2 - . Payload: MT-Sat 2. Mass: 3,000 kg (6,600 lb). Nation: Japan. Agency: MLIT. Manufacturer: Mitsubishi. Class: Earth. Type: Weather satellite. Spacecraft: DS2000. USAF Sat Cat: 28937 . COSPAR: 2006-004A. Apogee: 35,803 km (22,246 mi). Perigee: 35,771 km (22,227 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Multifunctional Transport Satellite. An aeronautical payload provided communications relay between aircraft and air traffic control; GPS augmentation navigation for aircraft; and transmitted the location of aircraft to air traffic control. A Japan Advanced Meteorological Imager weather camera had one visible and four infrared channels. MTSAT-2 was built by Mitsubishi using the new DS2000 bus. As of 2007 Mar 8 located at 144.93E drifting at 0.016W degrees per day.

2008 August 14 - . 20:44 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5ECA.
  • Superbird 7 - . Nation: Japan. Agency: Arianespace. Program: Superbird. Class: Communications. Type: Military communications satellite. Spacecraft: DS2000. USAF Sat Cat: 33274 . COSPAR: 2008-038A. Apogee: 35,804 km (22,247 mi). Perigee: 35,770 km (22,220 mi). Inclination: 0.1000 deg. Period: 1,436.10 min. Summary: Ku-band Mitsubishi Electric DS2000 class satellite for Japanese television broadcasting..

2011 May 20 - . 20:38 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5ECA.
  • ST-2 - . Mass: 5,090 kg (11,220 lb). Nation: Japan. Program: ST. Class: Communications. Type: Communications satellite. Spacecraft: DS2000. COSPAR: 2011-022B. Apogee: 35,793 km (22,240 mi). Perigee: 35,781 km (22,233 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Summary: Singapore-Taiwan 2 communications satellite with both C and Ku band transmitters..

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