A Comparative Study of the Calculation of Partial Derivatives in Space Dynamics
Abstract
In the rigorous treatment of the partial derivatives of the instantaneous state vector of a spacecraft with respect to the initial state vector the pertinent variational equations are usually integrated numerically. Since the procedure is a laborious one, its optimization is desirable. It is to be expected that a broader knowledge of the mathematical aspects of the variational equations is remunerated by an improved computational efficiency. The means for making the integration of the equations faster and more accurate in applications to orbit determination and error analysis are elaborated and compared in relation to the choices of coordinates and independent variables, and the types of spacecraft orbits.
 Publication:

Satellite Dynamics
 Pub Date:
 1975
 Bibcode:
 1975sady.proc..180W
 Keywords:

 Equations Of Motion;
 Numerical Integration;
 Orbit Calculation;
 Partial Differential Equations;
 Satellite Orbits;
 Celestial Mechanics;
 Earth Orbits;
 Linear Equations;
 Astrodynamics