Path: ACPro/Trajectory
% RHSPointMassAircraft Right hand side for a point mass aircraft
Includes runway forces. Includes variable mass.
Type
d = RHSPointMassAircraft
to get the default data structure.
The state is [velocity;flight path angle; turn angle; x direction;
y direction; altitude; mass fuel]
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Form
[xDot,lift,drag] = RHSPointMassAircraft( ~, x, d )
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Inputs
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t (1,1) Time (unused)
x (7,1) State [v;gamma;psi;xE;yN;h;mF]
d (.) Data structure
.cD0 (1,1) Drag coefficient with zero lift
.aR (1,1) Wing aspect ratio
.eps (1,1) Oswald efficiency factor
.cLAlpha (1,1) Lift coefficient
.s (1,1) Lift/drag area (m^2)
.g (1,1) Gravitational acceleration (m/s^2)
.alpha (1,1) Angle of attack (rad)
.phi (1,1) Bank angle (rad)
.thrust (1,1) Engine thrust (N)
.m (1,1) Dry mass (kg)
.f (3,1) Force vector (N)
.fSp (1,1) Specific fuel consumption (kg/Ns)
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Outputs
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xDot (7,1) State derivative [v;gamma;psi;xE;yN;h;mF]
lift (1,1) Lift (N)
drag (1,1) Drag (N)
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