This paper will present background on the SDO mission, an overview of the design and development activities associated specifically with the SDO electrical power system (EPS), as well as the major driving requirements behind the mission design. It will perform its operations in a geosynchronous orbit of the earth. The SDO spacecraft was designed to help us understand the Sun's influence on Earth and Near-Earth space by studying the solar atmosphere on small scales of space and time and in many wavelengths simultaneously. Inertial mode has two sub-modes, one tracks a Sun-referenced target orientation, and another maintains an absolute (star-referenced) target orientation, that both employ a Kalman filter to process data from a digital Sun sensor andÄesign and Development of the Solar Dynamics Observatory ( SDO) Electrical Power SystemÄenney, Keys Burns, Michael Kercheval, Bradford Science mode, during which most science data is collected, uses specialized guide telescopes to point accurately at the Sun. All four of SDO s wheel-actuated control modes involve Sun-pointing controllers, as might be expected from such a mission. More details about the ACS in general and the control modes in particular can be found in Refs. The ACS has four reaction wheel modes and 2 thruster actuated modes. A three-axis stabilized attitude control system (ACS) is needed both to point at the Sun accurately and to keep the roll about the Sun vector correctly positioned. At the time of this publication, the SDO spacecraft bus is well into the integration and testing phase at the NASA Goddard Space Flight Center (GSFC). These goals guided the design of the spacecraft bus that will carry and service the three-instrument payload. Links describing the instruments in detail may be found through the SDO web site.2 The basic mission goals are to observe the Sun for a very high percentage of the 5-year mission (10-year goal) with long stretches of uninterrupted observations and with constant, high-data-rate transmission to a dedicated ground station. To this end, the SDO spacecraft will carry three Sun-observing instruments to geosynchronous orbit: Helioseismic and Magnetic Imager (HMI), led by Stanford University Atmospheric Imaging Assembly (AIA), led by Lockheed Martin Space and Astrophysics Laboratory and Extreme Ultraviolet Variability Experiment (EVE), led by the University of Colorado. ![]() The Solar Dynamics Observatory ( SDO) mission is the first Space Weather Research Network mission, part of NASA s Living With a Star program.1 This program seeks to understand the changing Sun and its effects on the Solar System, life, and society. Guaranteeing Pointing Performance of the SDO Sun-Pointing Controllers in Light of Nonlinear Effects
0 Comments
Leave a Reply. |