Path: FormationFlying/EccDynamics
% Compute extreme y-values and associated true anomalies for given relative motion. -------------------------------------------------------------------------- Form: [y,nu] = FFEccYExt( e, D, dH, epsilon, nMax ) -------------------------------------------------------------------------- ------ Inputs ------ e (1) Eccentricity D (6,1) Integration constants computed from i.c.'s dH (1) Integration constant found by setting H = 0 at nu0 epsilon (1) Angular tolerance [rad] nMax (1) Maximum number of iterations ------- Outputs ------- y (1,#) Extreme values of along-track offsets [km] nu (1,#) True anomaly where extreme along-track offsets occur [rad] -------------------------------------------------------------------------- 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. -------------------------------------------------------------------------- Since version 7. --------------------------------------------------------------------------
FormationFlying: EccDynamics/FFEccDH FormationFlying: EccDynamics/FFEccGoals FormationFlying: EccDynamics/FFEccProp FormationFlying: EccDynamics/FFEccRMat EccDynamics: Derivatives/FFEccDDY EccDynamics: Derivatives/FFEccDY FormationFlying: Visual/FFEccAnalyzeShape Math: Linear/Mag Math: Solvers/NewtRaph Math: Trigonometry/WrapPhase
Back to the FormationFlying Module page