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    general navigation structure General ilrs support retroreflector info center of mass

OICETS

Jump to: Mission Objectives, Mission Instrumentation, Mission Parameters, Additional Information

Mission Photos:

OICETS in orbit
Courtesy of JAXA

Mission Objectives:

The JAXA Optical Inter-orbit Communications Engineering Satellite (OICETS) is a demonstration of the optical communications with the ESA geostationary Advanced Relay and Technology MISsion (ARTEMIS).  The experiment will verify important technology for large volume optical communications between satellites, a crucial capability for future space activities, including global-scale data acquisition from Earth observation satellites and stable communications for manned space missions.  Optical communications provides wider bandwidth than radio frequencies and lighter on-board equipment.  The experiment will include acquisition, tracking, and pointing technologies with ARTEMIS, and study the effects of micro-vibrations of the satellites on the communications link. SLR will provide the primary POD for OICETS.

Mission Instrumentation:

The major experiment items considered for OICETS are:

  1. experiments for evaluating on-board equipments capabilities under space environment
  2. experiments for evaluating acquisition and tracking mechanism using stars and planets
  3. inter-orbit optical communications experiments
  4. measurement of micro vibration of satellite to evaluate the effect to communication link
  5. precise orbit determination experiments only by laser ranging (Japanese stations plus the ILRS network)
  6. by operating inter-satellite optical communication equipment on the ground, tracking performance is confirmed; data of the atmosphere fluctuation for low orbit satellite at communication wavelength are acquired (NICT)
Mission Parameters:
OICETS Mission Parameters
Sponsor: JAXA
Expected Life: 1 year
Primary Applications: optical communications
Primary SLR Applications: precision orbit determination
COSPAR ID: 0503101
SIC Code: 1578
NORAD SSC Code: 28809
Launch Date: August 23, 2005
NP Bin Size: 5 seconds
RRA Diameter: 16 cm
RRA Shape: annulus
Reflectors: 6 corner cubes
Orbit: polar
Inclination: 97.83 degrees
Eccentricity: 0
Altitude: ~610 km
Weight: ~550 kg
Additional Information:

 
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