Path: ACPro/Trajectory
% AIRCRAFTPOINTMASSCONTROL Control function for a 3D point mass aircraft.
Computes the angle of attack and thrust for a 3D point mass aircraft.
Only the first two elements of the state vector are used.
It calls EquilibriumControls.
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Form
[T, alpha] = AircraftTrajectoryControl( s, d, tauGamma, tauV, vSet, gammaSet )
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Inputs
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s (:,1) State vector [v;gamma;...]
d (.) Data structure
.m (1,1) Aircraft mass (kg)
.g (1,1) Gravitational acceleration (m/s^2)
.thrust (1,1) Thrust (N)
.alpha (1,1) Angle of attack (rad)
.phi (1,1) Roll angle (rad)
.s (1,1) Surface area (m^2)
.cD0 (1,1) Zero lift drag
.k (1,1) Lift drag coupling term
.cLAlpha (1,1) Lift coefficient
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Outputs
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T (1,1) Thrust
alpha (1,1) Angle of attack
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ACPro: Trajectory/EquilibriumControls ACPro: Trajectory/RHSPointMassAircraft
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