Path: AC/Aircraft
% Generic aircraft sensor.
Outputs are:
* z acceleration
* roll rate (rad/sec)
* angle of attack (deg)
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Form:
g = ACSensor( x, d, opt )
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Inputs
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x (:) acstate data structure
d (:) Aircraft data structure
opt 'rhs' outputs state derivatives
'meas' outputs measurements
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Outputs
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g (:) Sensor output
.aN (1,1) Normal acceleration
.q (1,1) Pitch rate
.alpha (1,1) Angle of attack
.p (1,1) Roll rates
.r (1,1) Yaw rates
.altitude (1,1) Altitude
.machNo (1,1) Mach number
.qBar (1,1) Dynamic pressure
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AC: ACCoord/AlphBeta AerospaceUtils: AeroData/AtmData AerospaceUtils: AtmosphericCalculations/AirData Common: Atmosphere/StdAtm Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DeBlankLT Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS Common: Transform/Altitude Math: Linear/Mag
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