The Glory spacecraft uses Orbital Science Corporation's LEOStar bus design, with deployable solar panels, 3-axis stabilization, and X-band/S-band RF communications capabilities. The structure consists of an octagonal aluminum space frame and a hydrazine propulsion module containing enough fuel for at least 36 months of service. The spacecraft bus also provides payload power; command, telemetry, and science data interfaces, including onboard storage of data; and an attitude control subsystem to support instrument requirements.

Spacecraft Specifications
  + Launch Mass: 545kg
  + Redundancy: Selected Redundancy
  + Solar Arrays: Bi-axial articulated
  + Stability: 3-axis, stabilized, zero momentum
  + Propulsion: 45kg, monopropellant blowdown, 4-4N thrusters
  + Power: Supports ~400 WO.A. Load (140W Payload)
  + Lifetime: 3 years (goal of 5 years)
  + Orbit: 705 ± 2km, circular - low earth orbit (LEO)

Total Irradiance Monitor
The Total Irradiance Monitor (TIM) is an active cavity radiometer that records total solar irradiance. It has four identical radiometers to provide redundancy and to help detect changes in the instrument from exposure to solar radiation. TIM is mounted on a platform that moves the instrument independent of the spacecraft.
+ Read More

SENSOR PACKAGE

Cloud Camera
The cloud camera is a dual-band, visible imager utilizing a non-scanning staring detector array that is analogous to a star tracker, but Earth-viewing. It consists of an optical imaging system that provides continuous cross-track coverage over a narrow swath centered on the APS along-track footprint.
+ Read More