Path: FormationFlying/Transformation
% Compute geometric goals given Hills frame state and orbit info
Since version 7.
--------------------------------------------------------------------------
Form:
[g,D] = FFEccHills2Goals( e, nu, xH, n );
--------------------------------------------------------------------------
------
Inputs
------
e (1) Eccentricity
nu (1) True anomaly [rad]
xH (6,1) Hills frame state at nu (time-domain)
n (1) Mean orbit rate [rad/s] (optional)
* uses time-derivatives if provided
* uses nu-derivatives if NOT provided
-------
Outputs
-------
g (.) Data structure of geometric goals
D (6,1) Integration constants for trajectory
dH (1) Integration constant found by setting H = 0 at nu
--------------------------------------------------------------------------
References: Inalhan, Tillerson, How, "Relative Dynamics and Control of
Spacecraft Formations in Eccentric Orbits", Journal of Guidance,
Control & Dynamics, Vol.25, No.1, Jan-Feb 2002.
--------------------------------------------------------------------------
Copyright (c) 2004 Princeton Satellite Systems, Inc.
All rights reserved.
--------------------------------------------------------------------------