MODIS Airborne Simulator (MAS)

CAMPAIGN SUMMARY INFORMATION

Winter Experiment Dates: 15 March - 04 April 1999 Location: Northern Midwest, Great Lakes, & Canada Principal Investigators: Dr. Chris Moeller (UWisc) Additional Sensors: Camera (RC-10), NAST-I, NAST-M, & S-HIS Objective: Objective: There are two major objectives in this campaign. First, to validate atmospheric soundings observed across polar frontal systems. Second, WINTEX will test the ability of the imaging and sounding sensors to detect the geometrical and optical properties of clouds, which are particularly difficult to detect over snow and ice surfaces.
Processing Information Flights Processed: 10 of 10 Total Flight Tracks: Total Scanlines: Level-1B Version: #1 Calibration Type: Final Calibration Version: WINTEX Mar-99 0.1 Temperature Adjustment: None Status: Level-1B Data in HDF format is available. Noted Irregularities
Spectral Information Spectral Band Configuration Spectral Response Function Table
Level-1B Data Distribution Level 1 / Atmosphere Archive and Distribution System (LAADS) NASA Distributive Active Archive Centers (DAACs)
WINTEX Missions Click on a Track Map to view a particular mission March 1999 15 Mar 1999 Flight: 99-050 18 Mar 1999 Flight: 99-051 20 Mar 1999 Flight: 99-053 21 Mar 1999 Flight: 99-054 25 Mar 1999 Flight: 99-055 26 Mar 1999 Flight: 99-056 29 Mar 1999 Flight: 99-057 31 Mar 1999 Flight: 99-058 April 1999 01 Apr 1999 Flight: 99-059 04 Apr 1999 Flight: 99-060
Related Web Sites Official WINTEX Home Page NAST-I Home Page NAST-M Home Page S-HIS Home Page NASA Airborne Science Program
Noted Irregularities Banding in port 4 channels was likely due to voltage transients in the preamplifers or power supplies. The banding appears in many different flights and takes on many different patterns. The voltage transients are thought to have been caused by pressure blowoffs in the port 4 dewar. These blowoffs were probably caused by severe aircraft motion, which occured as a result of excessive turbulance experienced throughout the campaign. The dewar was more suseptable to turbulance because during post-deployment inspection, the shockmounts on which the instrument is mounted were found to have been worn. They have subsequently been replaced. Channel 48 is the most sensitive to pressure blowoffs and was therefore effected most severly. Examples-Flight 99-057 track 11, channel 48 and Flight 99-058 track 5, channel 48. Oscillations in channels 35 and 39. The oscillations appear in many flights. They are due to an electrical crosshop, which was caused by a wiring problem within the insrument. Example-Flight 99-051 track 6 channel 39. Transparent banding in chanel 43. This was due to a calibration error that was created when the blackbody counts were recorded incorrectly by the instrument. Example-Flight 99-054 track 1 channel 43.

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