The Japanese Advanced Meteorological Imager (JAMI) was developed by Raytheon and delivered to Space Systems/Loral as the Imager Subsystem for Japan's MTSAT-1R satellite. MTSAT-1R was launched from the Tanegashima Space Center on 2005 February 26 and became formally operational on 2005 June 28. This paper compares in-flight performance of JAMI with predictions made before launch. The performance areas discussed include radiometric sensitivity (NEDT and SNR) versus spectral channel, calibration accuracy versus spectral channel derived from comparisons of JAMI and AIRS measurements and image navigation and registration.
The Japanese Advanced Meteorological Imager (JAMI) was developed by Raytheon and delivered to Space Systems/Loral as the Imager Subsystem for Japan's MTSAT-1R satellite. Due to Japan's urgent need to replace MTSAT-1, which was destroyed in a launch failure in 1999, JAMI was developed on an expeditious 39-month schedule. Raytheon's success in responding to the needs of MTSAT-1R and delivering an excellent operational geosynchronous Earth orbit (GEO) imager was enabled by an elegant instrument architecture and use of newer but proven technology that simplified design, assembly and test of the Imager while simultaneously supplying superior performance. JAMI breaks through limitations of earlier three-axis stabilized GEO instruments with significant improvements in many areas, including spatial sampling, radiometric sensitivity, calibration and performance around local midnight.
The Japanese Advanced Meteorological Imager (JAMI) was developed by Raytheon and delivered to Space Systems/Loral as the Imager Subsystem for the Japanese MTSAT-1R system. Detailed characterization tests show JAMI meets all MTSAT-1R requirements with margin. JAMI introduces the next generation of operational weather imagers in geosynchronous Earth orbit (GEO) and provides much improved spatial sampling, radiometric sensitivity, Earth coverage and 24-hour observation capability compared with current GEO imagers.
The Earth Sensors on GOES-8 exhibit seasonal pointing errors in both the dual and single chord operating modes of the sensors. The errors were largely compensated for by a software patch uploaded to the satellite. The combination of detailed analyses and laboratory test results established that the observed error signatures are the result of stray solar radiation. The nature of the stray radiation paths giving rise to the seasonal errors is such that only the most significant stray path was eliminated in the GOES-9 hardware. The Earth Sensors on GOES-9 show significantly improved pointing performance over GOES-8, validating the origin of the most significant error source in the GOES-8 Earth Sensors. Low level seasonal pointing errors are observed, as expected, in the GOES-9 Earth Sensors. These errors again are effectively compensated for by an additional software patch developed to permit satisfactory single chord Earth Sensor operation. The operating principles of the Earth Sensor are described. On-orbit data of the seasonal anomalies are presented for both the uncompensated and compensated hardware and operating modes.
In this paper, the improvement in the image navigation and registration (INR) obtained by using two star trackers onboard a GOES satellite is investigated. The star trackers would augment the current INR system to eliminate the nonrepeatable errors caused mainly by the Earth sensor. The focus is on decreasing the spacecraft bus attitude error component in the total INR error budget with minimal changes to the current system.
The GOES I-M image navigation and registration (INR) system was developed and patented by Space Systems/Loral in response to NASA/NOAA pointing requirements of Imager and Sounder payloads. This INR system is divided into space segment and ground segment. The space segment consist of image motion compensation (IMC) system that compensates for deterministic errors caused by orbit and attitude motions and mirror motion compensations system that compensates for spacecraft attitude motion caused by Imager and Sounder scanner mirror motion. The ground segment consists mainly of Orbit and Attitude Tracking System (OATS) that determines the IMC orbit and attitude coefficients from star, landmark, and range measurements.
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.