The NASA Goddard Space Flight Center's Global Precipitation Measurement (GPM) mission must meet the challenge of measuring worldwide precipitation every three hours. The GPM core spacecraft, part of a constellation, will be required to maintain a circular orbit in a high drag environment at a near-critical inclination. Analysis shows that a mean orbit altitude of 407 km is necessary to prevent ground track repeating. Combined with goals to minimize maneuver operation impacts to science data collection and to enable reasonable long-term orbit predictions, the GPM roject has decided to fly the GSFC autonomous maneuver system, AutoCon(TM). This system is a follow-up version of the highly successfid New Millennium Program technology flown onboard the Earth Observing-1 formation flying mission. This paper presents the driving science requirements and goals of the GPM mission and shows how they will be met. Selection of the mean semi-major axis, eccentricity, and the lambdaV budget for several ballistic properties are presented. The architecture of the autonomous maneuvering system to meet the goals and requirements is presented along with simulations using GPM parameters. Additionally, the use of the GPM autonomous system to mitigate possible collision avoidance and to aid other spacecraft systems during navigation outages is explored.
Global Precipitation Measurement (GPM) Orbit Design and Autonomous Maneuvers
2003
24 pages
Report
Keine Angabe
Englisch
Global Precipitation Measurement (GPM) Orbit Design and Autonomous Maneuvers (AAS 03-618)
British Library Conference Proceedings | 2004
|AIAA | 1980
|Orbit Maneuvers with Finite Thrust
NTIS | 1983