NASA Information Contact: Website maintained by the If you have trouble viewing or navigating this page, please contact Defense Meteorological Satellite Program (DMSP) Satellite F13 Source/Platform Summary: This document contains information about the DMSP F13 Satellite. The DMSP F13 satellite is a in a near circular, sun synchronous, polar orbit. The DMSP mission is to provide global visible and infrared cloud data and other specialized meteorological, oceanographic and solar-geophysical data in support of world wide Department of Defense (DoD) operations. A description of the mission is provided as is information about the spacecraft and its environment. The ground data system is briefly described. Rustin Parr. Table of Contents: Platform or Data Collection Environment Overview Platform or Data Collection Environment Long Name, Platform Acronym: Defense Meteorological Satellite Program (DMSP) Block 5D-2 Satellite F13, DMSP F13 Platform Introduction: DMSP, originally known as the Defense System Applications Program (DSAP) and the Defense Acquisition and Processing Program (DAPP), is a long-term USAF effort in space to monitor the meteorological, oceanographic and solar-geophysical environment of the Earth in support of DoD operations.

All spacecraft launched have had a tactical (direct readout) and a strategic (stored data) capacity. In December 1972, DMSP data was declassified and made available to the civil/scientific community. The USAF maintains an operational constellation of two near-polar, sun-synchronous satellites Collection Environment: Satellite Platform Program Management: The DMSP program office is located at the Space Systems Division, Air Force Material Command, Los Angeles Air Force Station, Los Angeles, California. Funding is provided by the Department of Defense (DoD). Platform Mission Objectives: The DMSP mission is to provide global visible and infrared cloud data and other specialized meteorological, oceanographic and solar-geophysical data in support of world wide Department of Defense (DoD) operations.

Platform Parameters: DMSP Satellite F13 was built by General Electrics Astro-Space Division (now part of Martin Marietta Astro Space). It was launched on March 24, 1995 from Vandenberg AFB, California using an Atlas E rocket. The spacecraft is 3.7 meters in length with a diameter of 1.2 meters with an on-orbit mass of 831 kilograms. It has a design lifetime of 48 months. Power is provided though a 9.29 sq-m solar cell panel. Attitude is controlled using momentum wheels and magnetic coils using a strap-down star sensor and gyros as the reference. Coverage Information: DMSP Satellite F13 is in a near circular, sun synchronous, polar orbit.

Satellite Data Estimation of Gas Flaring Volumes. Air Force Defense Meteorological Satellite Program. Operational Linescan. System (OLS). Fire Detects from the Defense Meteorological Satellite Program, Operational Linescan System (DMSP/OLS), Nighttime Lights Algorithm. The Scanning Radiometer on DMSP-5B-F3 and the Operational Line Scanner (OLS) on DMSP. Operational Linescan System. Defense Meteorological Satellite Program. Earth At Night (WMS) Visualizations by Craig Mayhew Released on February 16, 2004 This image of Earth's city lights was created with data from the Defense Meteorological Satellite Program (DMSP) Operational Linescan System (OLS).

• Maximum Altitude: 856 km • Minimum Altitude: 844 km • Inclination: 98.8 deg • Period: 102.0 minutes • Eccentricity: 0.00083 • Ascending Equator Crossing Time (Local Time): • At Launch: 17:42 • Current (09/02/95): 17:43 • Swath Width: • Visible and Infrared Imagery - 3000 km • Microwave Imagery - 1400 km • Temperature Sounder - 1500 km • Water Vapor Profiler - 1500 km • Launch Date - March 24, 1995 • End Mission (Operational Support - F13 is currently (9/02/95) providing primary support with sensors OLS, SSM/I, SSM/T, SSM/T-2, SSJ/4, SSIES2, SSM, SSB/X and SSZ still providing data. Attitude Characteristics: Pointing Accuracy: 0.01 deg (primary), 0.12 deg (backup) Stability: maximum rate - 0.03 deg/sec per axis. Short term changes in attitude are measured using three orthogonal gyroscopes. A strap down star sensor is used to bound the effects of gyroscope drift. The desired attitude is computed based upon a star catalog and an ephemeris table up-linked to the spacecraft daily. Three-axis attitude control is maintained in the orbital configuration by automatic momentum exchange between three momentum wheels. On-board magnetic coils provide controlled interaction with the earth's magnetic field to prevent the accumulation of wheel secular momentum.