Path: FormationFlying/EccDynamics
% Compute Hills frame state given initial state, true anomaly, and eccentricity
This method uses a closed-form solution to Lawden's equations.
Since version 7.
--------------------------------------------------------------------------
Form:
xH = FFEccLawdensEqns( xH0, nu0, nu, e, n );
--------------------------------------------------------------------------
------
Inputs
------
xH0 (6,1) Initial Hills frame state
nu0 (1) True anomaly (at initial state) [rad]
nu (1,n) True anomaly (at new state) [rad]
e (1) Eccentricity
n (1) Mean orbit rate [rad/s] (optional)
* if provided, state must have time-derivatives
* if NOT provided, state must have nu-derivatives
-------
Outputs
-------
xH (6,n) New Hills frame state at nu (with nu-derivatives)
--------------------------------------------------------------------------
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/FFEccIntConst FormationFlying: EccDynamics/FFEccRMat FormationFlying: Utility/Nu2TimeDomain FormationFlying: Utility/NuDot FormationFlying: Utility/Time2NuDomain
Back to the FormationFlying Module page