FFEccIntConst:

Path: FormationFlying/EccDynamics

% Integration constants for eccentric relative motion
 Compute integration constants for homogeneous solution to LTV diff eqs of
 relative orbit motion.
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   Form:
   [D,dH,R] = FFEccIntConst( xH0, nu0, e );
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   ------
   Inputs
   ------
   xH0             (6,1)  Initial state in Hills frame. Velocity terms
                             are expressed as derivatives with respect to
                             true anomaly, rather than time.
   nu0              (1)   True anomaly (at initial state) [rad]
   e                (1)   Eccentricity

   -------
   Outputs
   -------
   D               (6,1)  Vector of integration constants
   dH               (1)   Integration constant found by setting H = 0 at nu0
   R               (6,6)  State transition matrix

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   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.
--------------------------------------------------------------------------

Children:

FormationFlying: EccDynamics/FFEccRMat

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