Path: FormationFlying/Derivatives
% Compute the second derivative of x with respect to true anomaly. This is used by the FFEccXExt function. Since version 7. -------------------------------------------------------------------------- Form: ddx = FFEccDDX( nu, e, D, dH ); -------------------------------------------------------------------------- ------ Inputs ------ nu (1,n) True anomaly [rad] e (1) Eccentricity D (6,1) Integration constants computed from i.c.'s dH (1) Integration constant computed from H(nu0)=0 ------- Outputs ------- ddx (1) Second derivative of x with respect to true anomaly -------------------------------------------------------------------------- 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 2004 Princeton Satellite Systems, Inc. All rights reserved. --------------------------------------------------------------------------
FormationFlying: EccDynamics/FFEccRMat
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