Path: AC/ACDynamics
% Initialize the aircraft model.
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Form:
d = ACInit( x, d, stateName )
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Inputs
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x (:) Aircraft state
r (3,1) ECI position vector
q (4,1) Quaternion from ECI to body
w (3,1) Inertial body rate in body frame
v (3,1) Velocity of cm wrt air
wR (:,1) Angular velocity of rotors
mass (1,1) Mass
inertia (6,1) Inertia
cG (3,1) Center of mass
engine (:,1) Engine states
actuator (:,1) Actuator states
sensor (:,1) Sensor states
flex (:,1) Flex model states organized [x;v] by appendage
disturb (:,1) Disturbance model states
d (:) Aircraft data structure
d.wPlanet (3,1) Planet rate
d.mu (1,1) Planet gravitational parameter
d.theta0 (1,1) Initial angle between planet
x-axis and ECI x-axis
d.atmData (1,:) Atmospheric data
d.atmUnits (1,:) Atmospheric data units
d.rotor (:) Rotor data structure
.u (3,1) Unit vector
.inertia (1,1) Spin axis inertia
d.flex (:) See get BldFlex
d.engine (:) Private engine data structure
d.aero (:) Private aerodynamics data structure
d.actuator (:) Private actuator data structure
d.sensor (:) Private sensor data structure
.name (:,:) Names
d.disturb (:) Private disturbance data structure
d.control (:) Control data structure
.elevator
.aileron
.rudder
.throttle
stateName (1,1)
.sensor {:} Names for the sensor states
.actuator {:} Names for the actuator states
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Outputs
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d (:) Aircraft data structure
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