Spacecraft & Instruments

The Aura spacecraft was launched into a near polar, sun-synchronous orbit with a period of approximately 100 minutes. The spacecraft repeats its ground track every 16 days to provide atmospheric measurements over virtually every point on the Earth in a repeatable pattern, permitting assessment of atmospheric phenomena changes in the same geographic locations throughout the life of the mission. The Aura spacecraft is designed for a six-year lifetime. The spacecraft orbits at 705 km in a sun-synchronous orbit (98o inclination) with a 1:45 PM ±15 minute equator crossing time. Aura limb instruments are all designed to observe roughly along the orbit plane. MLS is on the front of the spacecraft (the forward velocity direction) while HIRDLS, TES and OMI are mounted on the nadir side. EOS Aura's Instruments, HIRDLS, MLS, OMI, and TES contain advancd technologies that have been developed for use on environmental satellites. Each instrument provides unique and complementary capabilities that will enable daily global observations of Earth's atmospheric ozone layer, air quality, and key climate parameters.

Artist Rendering of Aura Spacecraft Spacecraft Assembly Browse Entire Photo Gallery

Satellite Equipment Layout

The following figures illustrate the various systems and configurations of the spacecraft.

spacecraft configuration	spacecraft equipment configuration
launch vehicle interfaces	instrument field of view accommodation

Spacecraft Subsystems

The spacecraft structure is a lightweight 'eggcrate' compartment construction made of graphite epoxy composite over honeycomb core, providing a strong but light base for the science instruments. The weight of the structure is approximately 700 kg., significantly lighter than a comparable aluminium structure, leaving more of the launcher weight-lift capability for science measurements.

A deployable flat-panel solar array with over 20,000 silicon solar cells provides 4600 watts of power in sunlight. While in sunlight, a portion of the solar array power, driven to always face the sun, charges a 24 cell nickel-hydrogen battery which powers the spacecraft and the instruments when the spacecraft is in night phase of the orbit.

The data system can handle over 100 gigabits of scientific data stored on-board. All spacecraft data are then relayed via an X-band communication system to one of two polar region ground stations each orbit. The spacecraft can also broadcast scientific data directly to ground stations over which it is passing. The ground stations also have an S-band uplink capability for spacecraft and science instrument operations.

The S-band communication subsystem also can communicate through NASA's TDRSS synchronous satellites in order to periodically track the spacecraft, calculate the orbit precisely, and issue commands to adjust the orbit to maintain it within defined limits.

Spacecraft attitude is maintained by stellar-inertial, and momentum wheel-based attitude controls with magnetic momentum unloading, through interaction with the magnetic field of the Earth that provide accurate pointing for the instruments. Typical pointing knowledge of the line of sight of the instruments to the Earth is on the order of one arc minute (about 0.02 degrees)

Electronic components are housed on panels internally, leaving the spacecraft 'deck' available for the four science instruments, and providing them a wide field of view. The side of the spacecraft away from the Sun is devoted to thermal radiators, which radiate excess heat to space and provide the proper thermal balance for the entire spacecraft.

A propulsion system of four small one-pound thrust hydrazine monopropellant rockets gives the spacecraft a capability to adjust its orbit periodically to compensate for the effects of atmospheric drag, so that the orbit can be precisely controlled to maintain altitude and the assigned ground track.