AirshipStabConDerivatives:

Path: Airships/Control

% Compute the stability and control derivatives for an airship model.

     The subscripts are given after an underscore. For example,
      _V is a "V" subscript. Each subscript indicates the
      variable (state or control) that the partial derivative
      is taken with respect to. 
 
     The dimensional derivatives are named with the force or 
     moment abbreviation, followed by a subscript.
 
     The non-dimensional derivatives are named with "C"
     then the force or moment abbreviation, followed by a
     subscript.
 
     For eample:
       - M_alpha is the dimensional derivative for the pitch
         moment "M" with respect to angle of attack "alpha".
       - Cm_alpha is the corresponding non-dimensional
       derivative.

--------------------------------------------------------------------------
   Form:
   [dim,nonDim] = AirshipStabConDerivatives( mdl, h, theta, alpha, V )
--------------------------------------------------------------------------

   ------
   Inputs
   ------

   -------
   Outputs
   -------
   dim     (.)   Data structure with fields for dimensional derivatives
                   - Partial derivatives of body frame forces with respect
                     to small changes in various states and controls, then
                     divided by mass.
                   - Partial derivatives of body frame moments with
                     respect to small changes in various states and
                     controls, then divided by the inertia of that axis.
                   
   nonDim  (.)   Data structure with fields for non-dimensional
                 derivatives. Each non-dimensional derivative is equal to
                 the corresponding dimensional derivative, multiplied by a
                 scaling factor. The following scaling factors are used:

                   - FORCE_VELOCITY :      V *    mass / (qBar * S)
                   - FORCE_ANGLE :                mass / (qBar * S)
                   - FORCE_ANGLE-RATE:   2*V *    mass / (qBar * S * c)

                   - MOMENT_VELOCITY :     V * inertia / (qBar * S * c)
                   - MOMENT_ANGLE :            inertia / (qBar * S * c)
                   - MOMENT_ANGLE-RATE : 2*V * inertia / (qBar * S * c * c)
                 
                 where V is the airspeed, qBar is the dynamic pressure, S
                 is the reference area, c is the reference length. The
                 inertia quantity used is for the corresponding axis of 
                 the moment, and is computed in the wind-frame.

--------------------------------------------------------------------------

Children:

AC: ACCoord/AlphBeta
AC: ACCoord/BToW
AC: ACCoord/ECIToNED
AC: ACCoord/QECI
AC: ACData/ACTConstants
AC: ACDynamics/AC
AC: ACDynamics/ACInit
AC: Classes/@acstate/abs.m
AC: Classes/@acstate/acstate.m
AC: Classes/@acstate/get.m
AC: Classes/@acstate/length.m
AC: Classes/@acstate/minus.m
AC: Classes/@acstate/mrdivide.m
AC: Classes/@acstate/mtimes.m
AC: Classes/@acstate/plus.m
AC: Classes/@acstate/subsasgn.m
AC: Classes/@acstate/subsref.m
AC: Classes/@acstate/zeros.m
AerospaceUtils: AeroData/AtmData
AerospaceUtils: AtmosphericCalculations/AirData
AerospaceUtils: Coord/CoordinateTransform
AerospaceUtils: Coord/ECIToEF
AerospaceUtils: Coord/EFToLatLonAlt
AerospaceUtils: Coord/LatLonAltToEF
AerospaceUtils: Coord/QIToBDot
Airships: Control/AirshipState
Airships: Control/AirshipTrim
Airships: Mass/AirshipMassModel
Airships: Mass/BuildAirshipMassModel
Airships: Mass/IntegrateMassProps
Airships: Modeling/AddedMass
Airships: Modeling/AirshipCV
Airships: Modeling/AirshipCoefficients
Airships: Modeling/AirshipGeometry
Airships: Modeling/AirshipInertiaFactors
Airships: Modeling/AirshipIntegrals
Airships: Modeling/BuildAirshipModel
Airships: Modeling/FinFactors
Airships: Modeling/FinGeometry
Airships: Modeling/GondolaGeometry
Airships: Modeling/HalfEllipsoid
Airships: Simulation/AirshipAero
Airships: Simulation/AirshipInit
SC: Ephem/EOfE
SC: Ephem/EarthNut
SC: Ephem/EarthPre
SC: Ephem/EarthRot
SC: Ephem/GMSTime
SC: Ephem/MSidDay
SC: Ephem/NutDelta
SC: Ephem/ObOfE
SC: Ephem/TruEarth
SC: SCData/sCTConstants
Common: Atmosphere/StdAtm
Common: Classes/@statespace/and.m
Common: Classes/@statespace/close.m
Common: Classes/@statespace/connect.m
Common: Classes/@statespace/eig.m
Common: Classes/@statespace/get.m
Common: Classes/@statespace/getabcd.m
Common: Classes/@statespace/getsub.m
Common: Classes/@statespace/isempty.m
Common: Classes/@statespace/mtimes.m
Common: Classes/@statespace/plus.m
Common: Classes/@statespace/series.m
Common: Classes/@statespace/set.m
Common: Classes/@statespace/statespace.m
Common: CommonData/Constants
Common: CommonData/SwooshWatermark
Common: CommonData/xSplashSmall
Common: Control/Append
Common: Control/C2DZOH
Common: Control/Parallel
Common: Control/Series
Common: Control/SizeABCD
Common: Database/Constant
Common: General/CellToMat
Common: General/DeBlankLT
Common: General/DeleteCell
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: Quaternion/Mat2Q
Common: Quaternion/Q2Eul
Common: Quaternion/Q2Mat
Common: Quaternion/QForm
Common: Quaternion/QMult
Common: Quaternion/QPose
Common: Quaternion/QTForm
Common: Quaternion/QUnit
Common: Time/DTSToDTA
Common: Time/Date2JD
Common: Time/JD2000
Common: Time/JD2T
Common: Time/JDToMidnight
Common: Time/T2JD
Common: Transform/Altitude
Common: Transform/Eul2Q
Common: Transform/IConvP
Common: Transform/Mat2Eul
Math: Linear/Cross
Math: Linear/DupVect
Math: Linear/Mag
Math: Linear/SkewSq
Math: Linear/SkewSymm
Math: Linear/Unit
Math: MathUtils/R2P5
Math: Trigonometry/CosD
Math: Trigonometry/SinD

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