Time elementsTime elements are introduced for use with Sundman time transformations of the type dt = r(alpha)ds for satellite equations of motion. Two time elements are given, one providing maximum accuracy for alpha = 1, the other for alpha = 2. Time elements and time transformations reduce local truncation error and Liapunov (in track) instability, and provide analytical step size control. Numerical results show accuracy improvements of more than one order of magnitude when time elements are employed with time transformations in the numerical integration of the satellite equations, compared with using time transformations alone.
Document ID
19740055088
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Nacozy, P. E. (Texas, University Austin, Tex., United States)
Date Acquired
August 7, 2013
Publication Date
August 1, 1974
Subject Category
Space Sciences
Report/Patent Number
AIAA PAPER 74-841
Meeting Information
Meeting: Mechanics and Control of Flight Conference
Location: Anaheim, CA
Start Date: August 5, 1974
End Date: August 9, 1974
Sponsors: American Institute of Aeronautics and Astronautics