Path: Interplanetary/AsteroidProspector
% Simulation of low thrust maneuver to rendezvous with target orbit.
Applies constant magnitude, variable direction thrust to optimally
change each element one at a time, according to specified order.
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Form:
[t,el,r,v,mass,acc,accRSW] = LowThrustRendezvousSim( ...
el0, elT, mass0, thrust, Isp, elemOrder, mu);
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Inputs
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el0 (1,6) Initial Keplerian orbital elements [a,i,W,w,e,M]
elT (1,6) Target Keplerian orbital elements
mass0 (1,1) Initial mass (kg)
thrust (1,1) Thrust magnitude (kN)
Isp (1,1) Specific impulse (s)
elemOrder (1,5) Order in which to change elements
mu (1,1) Gravitational constant
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Outputs
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t (1,:) Simulation time vector
el (:,6) Orbital elements
r (3,:) Inertial position
v (3,:) Inertial velocity
mass (1,:) Mass
acc (3,:) Accleration in inertial frame
accRSW (3,:) Acceleration in RSW (radial / tangent / normal)
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See also: LowThrustTimeToTransfer, LowThrustGVE_EventFcn, LowThrustGVERHS
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