Path: Orbit/OrbitCoord
% Planar elements to flight path states
Type ElToFPA for a demo. With an input set of orbital (Kepler) elements, this
compute the flight path states. The Kepler elements consist of:
a: Semi-major Axis
i: Inclination
W: Longitude of the ascending node
w: Argument of perigee
e: Eccentricity
M: Mean anomaly
The flight path states consist of:
v: Velocity magnitude
gamma: Flight path angle (velocity wrt horizon)
r: Position magnitude
theta: Position angle in X/Y plane
The built-in demo simulates the states for a highly eccentric orbit.
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Form:
ElToFPA; % built-in demo
x = ElToFPA(el)
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Inputs
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el (1,6) [a i W w e M] Kepler elements
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Outputs
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x (4,1) [v;gamma;r;theta]
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See also: El2RV
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Orbit: OrbitMechanics/FlightPathAngle Orbit: OrbitMechanics/Period Orbit: OrbitSim/RVOrbGen Common: Graphics/NewFig Common: Graphics/TimeHistory Common: Graphics/TimeLabl Common: Graphics/XLabelS Common: Graphics/YLabelS Math: Integration/RK4 Math: Linear/Mag
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