A semi-analytic theory for the motion of a close-earth artificial satellite with dragA semi-analytic method is used to estimate the decay history/lifetime and to generate orbital ephemeris for close-earth satellites perturbed by the atmospheric drag and earth oblateness due to the spherical harmonics J2, J3, and J4. The theory maintains efficiency through the application of the theory of a method of averaging and employs sufficient numerical emphasis to include a rather sophisticated atmospheric density model. The averaged drag effects with respect to mean anomaly are evaluated by a Gauss-Legendre quadrature while the averaged variational equations of motion are integrated numerically with automatic step size and error control.
Document ID
19790035535
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Liu, J. J. F. (USAF, Office of Astrodynamics, Peterson AFB Colo., United States)
Alford, R. L. (Northrop Services, Inc. Huntsville, Ala., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1979
Subject Category
Astrodynamics
Report/Patent Number
AIAA PAPER 79-0123
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting
Location: New Orleans, LA
Start Date: January 15, 1979
End Date: January 17, 1979
Sponsors: American Institute of Aeronautics, Astronautics