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Icesat-2 – Orbital ICESat-2 User Manual

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Orbital Sciences Corporation

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Dulles, Virginia 20166

www.orbital.com

©2014 Orbital Sciences Corporation

FS009_11_2998

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.