NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Modeling radiation forces acting on satellites for precision orbit determinationModels of the TOPEX/Poseidon spacecraft are developed by means of finite-element analyses for use in generating acceleration histories for various orbit orientations which account for nonconservative radiation forces. The acceleration profiles are developed with an analysis based on the use of the 'box-wing' model in which the satellite is modeled as a combination of flat plates. The models account for the effects of solar, earth-albedo, earth-IR, and spacecraft-thermal radiation. The finite-element analysis gives the total force and induced accelerations acting on the satellite. The plate types used in the analysis have parameters that can be adjusted to optimize model performance according to the micromodel analysis and tracking observations. Acceleration related to solar radiation pressure is modeled effectively, and the techniques are shown to be useful for the precise orbit determinations required for spacecraft such as the TOPEX/Poseidon.
Document ID
19920060633
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Marshall, J. A.
(ST Systems Corp. Lanham, MD, United States)
Antreasian, P. G.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Rosborough, G. W.
(Colorado, University Boulder, United States)
Putney, B. H.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AAS PAPER 91-357
Meeting Information
Meeting: AAS/AIAA Astrodynamics Conference
Location: Durango, CO
Country: United States
Start Date: August 19, 1991
End Date: August 22, 1991
Accession Number
92A43257
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available