Agreed with this, the overall aim being to reproduce the astronomical data for any orbit as precisely as possible, for example the solar system orbits, binary pulsar orbits and S2 orbit. By now the astronomers may have discovered more retrograde orbits. agreed also about the typo in Eq. (25). The observed precession for any given planar orbit must be reproduced theoretically, as you know, with the right initial conditions. I am gradually working more of the field and potential equations into the orbital force equation.

To: EMyrone@aol.com

Sent: 26/05/2017 16:33:49 GMT Daylight Time

Subj: Re: 378(3): Initial Condition Method

Actually the orbit is determined by initial conditions of X, Xdot, Y, Ydot. The initial quantities Xdotdot and Ydotdot do not enter the time integration. However eq.(2) opens a possibility of choosing the accelerations in a defined way, insofar this is an extensions of the usual mechanism.

In eq. (25) the denominator c^2 has to be removed.

Horst

Am 22.05.2017 um 14:20 schrieb EMyrone:

This is the initial condition method for aether engineering an orbit, using the general result (3) for any orbit from the field equations. The orbit will depend on the values chosen for the initial kappa vector components.The ratio of kappa sub X(0) and kappa sub Y(0) is a constant input parameter. Then the force component equations are solved simultaneously for this initial condition.

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