dynamics.models.uav

Class UAVFuselage

java.lang.Object

dynamics.models.uav.NACAAirfoil

dynamics.models.uav.UAVFuselage

public class UAVFuselage
extends NACAAirfoil

Author:

dtdavis

Field Summary

Fields inherited from class dynamics.models.uav.NACAAirfoil

aoa, area, cDrag, chord, cLift, cMoment, controlSetting, controlType, dragVector, FIXED, FLAPPED, liftVector, N0006, N0009, N0010_34, N0010_35, N0012, N0012_64, N1408, N1410, N1412, N23012, N23015, N23018, N23021, N23024, N2408, N2410, N2412, N2415, N2418, N2421, N2424, N4412, N4415, N4418, N4421, N4424, N63_006, N63_009, N63_012, N63_015, N63_018, N63_021, N63_206, N63_209, N63_210, N63_212, N63_215, N63_218, N63_221, n63_412, N63_415, N63_418, N63_421, N63_615, N63_618, N63A010, N63A020, N64_006, N64_009, N64_012, N64_015, N64_018, N64_021, N64_108, N64_110, N64_112, N64_206, N64_208, N64_209, N64_210, N64_212, N64_215, N64_218, N64_221, N64_412, N64_415, N64_418, N64_421, N64_618, N64A010, N64A210, N64A212, N64A215, N64A410, N65_006, N65_009, N65_012, N65_015, N65_018, N65_021, N65_206, N65_209, N65_210, N65_212, N65_215, N65_218, N65_221, N65_410, N65_412, N65_415, N65_418, N65_421, N65_618, N66_006, N66_009, N66_012, N66_015, N66_018, N66_021, N66_206, N66_209, N66_210, N66_212, N66_215, N66_218, N66_221, N66_415, N66_418, normal, position, span, STABILATOR, velocity

Constructor Summary

Constructors

Constructor and Description
UAVFuselage(double length, double width, double efficiency, double lateralDragC) Creates a new UAVFuselage object

Method Summary

Modifier and Type	Method and Description
Vector3D	dragVector(double altitude) Calculates the drag force applied to the airfoil given its current velocity and altitude NOTE: Since this method depends on cDrag, if the velocity changes, setCoefficients should be called prior to this method to ensure accuracy
double	setLiftCoefficient() Computes the airfoil's current lift coefficient Since the C_Drag and C_Moment depend on C_Lift, if AOA (velocity) changes, this method should be called prior to setDragCoefficient and setMomentCoefficient for correct results This method over-rides the super class method and adjusts the basis airfoil Clift to account for reduced lifting efficiency of the UAV fuselage shape
Vector3D	unitDrag(Vector3D velocity) Computes the unit vector direction of airfoil drag given the velocity Drag direction is directly opposite velocity.
Vector3D	unitLift(Vector3D velocity) Computes the unit vector direction of airfoil lift given the velocity Lift direction is perpendicular to drag and in the plane formed by the drag and normal vectors computed as D x (D x N).

Methods inherited from class dynamics.models.uav.NACAAirfoil

dynamicPressure, dynamicPressure, foilVelocity, liftVector, maxNonStallAOA, minNonStallAOA, reynoldsNumber, reynoldsNumber, setAOA, setCoefficients, setControl, setDragCoefficient, torqueVector

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

Constructor Detail

UAVFuselage

public UAVFuselage(double length,
                   double width,
                   double efficiency,
                   double lateralDragC)

Creates a new UAVFuselage object

Parameters:

length - fore-aft length of the airfoil

width - width of airfoil section

efficiency - compared to the documented airfoil upon which the fuselage numbers are based

lateralDragC - coefficient to be applied to calculate lateral drag (-C*Vy*Vy)

Method Detail

setLiftCoefficient

public double setLiftCoefficient()

Computes the airfoil's current lift coefficient Since the C_Drag and C_Moment depend on C_Lift, if AOA (velocity) changes, this method should be called prior to setDragCoefficient and setMomentCoefficient for correct results This method over-rides the super class method and adjusts the basis airfoil Clift to account for reduced lifting efficiency of the UAV fuselage shape

Overrides:

setLiftCoefficient in class NACAAirfoil

unitLift

public Vector3D unitLift(Vector3D velocity)

Computes the unit vector direction of airfoil lift given the velocity Lift direction is perpendicular to drag and in the plane formed by the drag and normal vectors computed as D x (D x N). The y component is zeroed. NOTE: The resultant vector is probably not a unit vector. This will ensure that the magnitude of lift in the x and z directions is still scaled by the actual velocity and not effected by zeroing out the y axis.

Overrides:

unitLift in class NACAAirfoil

Parameters:

velocity - of the airfoil in body coordinates (u, v, w)

Returns:

the vector direction of airfoil lift

unitDrag

public Vector3D unitDrag(Vector3D velocity)

Computes the unit vector direction of airfoil drag given the velocity Drag direction is directly opposite velocity. The y component is zeroed. NOTE: The resultant vector is probably not a unit vector. This ensures that the magnitude of lift in the x and z directions is still scaled by the actual velocity and not effected by zeroing out the y axis.

Overrides:

unitDrag in class NACAAirfoil

Parameters:

velocity - of the airfoil in body coordinates (u, v, w)

dragVector

public Vector3D dragVector(double altitude)

Calculates the drag force applied to the airfoil given its current velocity and altitude NOTE: Since this method depends on cDrag, if the velocity changes, setCoefficients should be called prior to this method to ensure accuracy

Overrides:

dragVector in class NACAAirfoil

Parameters:

altitude - in meters above mean sea level