Encyclopedia Astronautica
SERVIS



servis.jpg
Servis
Japanese technology satellite. First launch 2003.10.30.

The Space Environment Reliability Verification Integrated System (SERVIS) project was to verify Commercial Off-The-Shelf (COTS) parts and technologies in the severe space environment so that they could be utilized for space applications, establishing COTS evaluation guidelines and equipment design guidelines to utilize COTS.

The SERVIS project started in 1999 and was to continue until 2007. During this period, two verification satellites were to be launched, in FY2002 and 2005 respectively. The entire project consisted of four parts:

  • Building and launching two SERVIS space verification satellite buses;
  • Ground evaluation test for various COTS, including radiation test;
  • Development of advanced satellite equipment utilizing COTS for space verification;
  • Development of "Virtual Integration" network infrastructure.

SERVIS 1 Satellite Bus Summary

  • Launch: Fiscal Year 2002
  • Lift off Weight: not exceeding 1000kg
  • Orbit: Altitude 1000km, Inclination 100deg.
  • Size: Height approx. 2.3m Length approx. 10.3m (including solar panels)
  • Power: 1200 watts
  • Operating Life: 2 years
  • Control Center: USEF Satellite Operation Center (USOC) in Tokyo
  • Systems:

    • Radiation Environment Monitoring System: Monitors the ambient environment caused by cosmic rays, solar flares, and the Van Allen Radiation Belt.
    • COTS Parts Evaluation System: This contained commercial semiconductor components and would monitor radiation effects such as degradation and single event effect. Such test data would be obtained and evaluated, to establish a Parts Test Guideline and an Equipment Design Guideline.
    • Experimental Subsystem utilizing COTS: Advanced bus components using COTS and commercial technologies in order to verify onboard SERVIS satellite bus. Those components were utilizing most advanced commercial parts to realize very sophisticated commercial technology. This included:

      • Low Cost Propellant Tank
      • Integrated Navigation Subsystem
      • Integrated Power Control Subsystem
      • Advanced Paddle Drive Mechanism
      • Advanced TT&C Transponder
      • On Board Computer
      • Star Tracker Integrated Satellite System Controller
      • Lithium Ion Battery System
      • Optical Fiber Laser Gyro Subsystem

First Launch: 2003.10.30.
Last Launch: 2010.06.02.
Number: 2 .

More... - Chronology...


Associated Countries
See also
  • UR-100N The UR-100N was designed as a replacement for the UR-100 at the end of its ten year storage life. Although it could be installed in the same silos, it was 50% heavier. The competing design of Yangel, the MR-UR-100, was also put into production when the Soviet hierarchy deadlocked and could not pick one design over the other. More...

Associated Launch Vehicles
  • UR-100N Russian intercontinental ballistic missile. The UR-100N was designed as a replacement for the UR-100 at the end of its ten year storage life. Although it could be installed in the same silos, it was 50% heavier. The competing design of Yangel, the MR-UR-100, was also put into production when the Soviet hierarchy deadlocked and could not pick one design over the other. More...
  • Rokot Russian all-solid orbital launch vehicle, consisting of decommissioned UR-100N ICBMs with a Briz-KM upper stage. More...

Bibliography
  • McDowell, Jonathan, Jonathan's Space Home Page (launch records), Harvard University, 1997-present. Web Address when accessed: here.

Associated Launch Sites
  • Plesetsk Plesetsk was the Soviet Union's northern cosmodrome, used for polar orbit launches of mainly military satellites, and was at one time the busiest launch centre in the world. The collapse of the Soviet Union put the main launch site of Baikonur in Kazakh territory. It now seems that once the Proton rocket is retired, Baikonur will be abandoned and Plesetsk will be Russia's primary launch centre. Upgrades to existing launch facilities will allow advanced versions of the Soyuz rocket and the new Angara launch vehicle to be launched from Plesetsk. Plesetsk's major drawback was the lower net payload in geosynchronous orbit from a northern latitude launch site. However Russia is planning to remove the disadvantage by looping geosynchronous satellites around the moon, using lunar gravity to make the necessary orbital plane change. More...

SERVIS Chronology


2003 October 30 - . 13:43 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. LV Family: UR-100N. Launch Vehicle: Rokot. LV Configuration: Rokot 4921921121.
  • Servis-1 - . Mass: 840 kg (1,850 lb). Nation: Japan. Agency: USEF. Class: Technology. Type: Navigation technology satellite. Spacecraft: SERVIS. USAF Sat Cat: 28060 . COSPAR: 2003-050A. Apogee: 1,016 km (631 mi). Perigee: 984 km (611 mi). Inclination: 99.5000 deg. Period: 105.10 min. The mission of the 'Space Environment Reliability Verification of Integrated System' was to flight test a range of commerical-grade spacecraft components including a computer, star tracker, battery, and laser gyro. The objective was to lower the cost of future satellites.

2010 June 2 - . 01:58 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. LV Family: UR-100N. Launch Vehicle: Rokot.
  • Servis 2 - . Mass: 900 kg (1,980 lb). Nation: Japan. Agency: KVR. Class: Technology. Type: Technology satellite. Spacecraft: Servis. USAF Sat Cat: 36588 . COSPAR: 2010-023A. Apogee: 1,212 km (753 mi). Perigee: 1,185 km (736 mi). Inclination: 100.4000 deg. Period: 109.40 min. Summary: Space Environment Reliability Verification Integrated System to test usability of off-the-shelf commercial components in place of space-qualified hardware..

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