The Geostationary Operational Environmental Satellite-R (GOES-R), scheduled for launch in 2014, will be the first in a series of next generation weather satellites. It will be 3-axis stabilized in geostationary orbit, and will have an Advanced Baseline Imager (ABI) that can make full-Earth disk images, covering most of the Western Hemisphere, in spectral bands ranging from 0.47-13.3 μm. We are now designing a Full-Disk Ratioing Radiometer (FDRR) to determine the ratio of the full-disk irradiance to the solar irradiance in spectral bands that match the four shortest wavelengths of the ABI's Visible and Near IR (VNIR) spectral bands. When hard-mounted to the nadir face of a GOES-R satellite, this FDRR can determine the full-disk albedo in each band, with the added benefit that the ABI's corresponding channels can be calibrated by comparison of these measurements to the Earth's irradiance measurements derived from simultaneous full disk images made by the ABI. The FDRR uses an integrating sphere with two baffled pinholes. One pinhole has a baffle that restricts its field-of-view (FOV) to a circle 20.1° in diameter, centered at nadir, viewing the Earth's full disk continuously throughout its daily cycle. This baffle has a shutter that allows it to be closed for dark current measurements during the day and to prevent solar intrusion at night. The second pinhole, with a much smaller diameter, has a baffle that restricts its FOV to about 1° in the East-West direction and +/-25° in the North/South direction, allowing the direct solar irradiance to enter the sphere for a brief interval once each night. A radiationhardened fiber optic light pipe couples the output of the sphere to filters and detectors in an electronics box. These filters and detectors have spectral bands matched to those in the ABI. This technique measures the ratio of the full-disk irradiance to the direct solar irradiance, determining the Earth's albedo independent of the detector's response, the transmission of the filters and the fibers, and the sphere's reflectivity.
An experiment occurring in an orbiting platform examines the mass transfer across gas-liquid and liquid-liquid interfaces. It employs an imaging system with real time image analysis. The design includes optical design imager selection and integration positioner control image recording software development for processing and interfaces to telemetry. It addresses the constraints of weight volume and electric power associated with placing the experiment in the Space Shuttle cargo bay. Challenging elements of the design are Imaging and recording of a 200 micron diameter bubble with a resolution of 2 microns to serve as a primary source of data Varying frame rates from 500 per second to 1 frame per second depending on the experiment phase Providing three dimensional information to determine the shape of the bubble. 1.
Access to the requested content is limited to institutions that have purchased or subscribe to SPIE eBooks.
You are receiving this notice because your organization may not have SPIE eBooks access.*
*Shibboleth/Open Athens users─please
sign in
to access your institution's subscriptions.
To obtain this item, you may purchase the complete book in print or electronic format on
SPIE.org.
INSTITUTIONAL Select your institution to access the SPIE Digital Library.
PERSONAL Sign in with your SPIE account to access your personal subscriptions or to use specific features such as save to my library, sign up for alerts, save searches, etc.