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.
The Aerosol Polarimetry Sensor (APS) is a continuous scanning sensor that has the capability to collect visible, near infrared, and short-wave infrared data scattered from aerosols and clouds. It is designed to make extremely accurate multi-angle observations of Earth and atmospheric scene spectral polarization and radiance.
The Total Irradiance Monitor (TIM) is an electrical substitution radiometer (ESR) that records total solar irradiance with extreme accuracy and precision. 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 points the instrument toward the Sun independently of the spacecraft.
The Cloud Camera Sensor Package is a dual-band (blue and near infrared), visible imager utilizing a non-scanning detector arrays that are analogous to star trackers but Earth-viewing. It consists of an optical imaging system that provides continuous cross-track coverage over a field of view centered on the APS along-track footprint.