Orbital ICESat-2 - Manual (Page 2)

Orbital Sciences Corporation
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ICESat-2
Specifications
Spacecraft
Launch Mass: 1,387 kg
Solar Arrays: Single wing with fixed and articulating mode (see
illustration below), 3818 W EOL
Stabilization: 3-axis, zero momentum bias, nadir pointing
Pointing Control: 13.3 arcsec (3 s)
Data Storage: 704 Gbits EOL
Data Downlink: X-band, 220 Mbps
Propulsion: Blowdown hydrazine, four 22 N thrusters and eight
4.5 N thrusters, 158 kg tank capacity
Mission Life: 3 years; 7 years propellant
Orbit: 481 km @ 92 ° inclination (91 day repeat cycle)
Orbit Determination: High precision GPS and laser ranging
Current Status:
In development
Launch
Launch Vehicle: Delta II
Launch Site: Vandenberg Air Force Base, California
Date: 1Q 2017
ATLAS
Advanced Topographic Laser Altimeter System (ATLAS) Multi-Beam Visible
Photon-Counting Altimeter. Manufactured by NASA/GSFC.
Mission Partners
NASA Goddard Space Flight Center
Procuring agency and customer program management,
system integration, ATLAS instrument development and
manufacture
Orbital Sciences Corporation
Spacecraft prime contractor and integrator responsible
for spacecraft design and manufacture, instrument
integration, and observatory test; launch vehicle integration
support; launch support; and mission operations control
center
Fibertek, Incorporated
Design, develop, fabricate, test and deliver lasers for the
Advanced Topographic Laser Altimeter System instrument
Articulating Array
Nadir
Velocity
Nadir
Velocity
Airplane Mode (Articulating Array) Sailboat Mode (Fixed Array)
Fixed Array
The single-wing solar array has two operating modes.