faa.tg.aircraft.adm.airframe
Class Airframe

java.lang.Object
  faa.tg.aircraft.adm.airframe.Airframe

All Implemented Interfaces:

Immutable, java.io.Serializable

public class Airframe
extends java.lang.Object
implements java.io.Serializable, Immutable

 Airframe represents the non-dimensional steady aerodynamic
 characteristics of the aircraft.

 See section 9 of the Detailed Design Document for a discussion
 of design issues.
 

See the source: Airframe.java

Version:

$Id: Airframe.java,v 3.5 2008/04/25 15:10:51 lykensj Exp $

Author:

Jocelyn Richardt

See Also:

Serialized Form

Field Summary

private AirframeCoefficients	airframeCoeff The airframe coefficients, including cD, cK, maxLiftCoeff, clMaxLOverD and their current flap settings.
private Coefficient	cdBrakes Coefficient of drag for aircraft wheel brakes.
private Coefficient	cdGear Coefficient of drag for landing gear (from XML).
private Coefficient	cdSpoiler Coefficient of drag for spoilers (from XML).
private Coefficient	cM Compressibility coefficient.
static java.lang.String	CVS_VERSION_ID The CVS Version ID
(package private) static long	serialVersionUID
private boolean	spoilerDeployed Drag parameter indicating whether the spoiler is deployed.
static double	STALL_SAFETY_FACTOR
private boolean	wheelBrakesOn Drag parameter indicating whether wheel brakes are on.
private Area	wingSurface The surface area of the wing.

Constructor Summary

Airframe(Area wingSurfaceArea, Coefficient compress, Coefficient spoiler, Coefficient gear, Coefficient brakes, AirframeCoefficients airframeCoefficients)
Standard Constructor.

Method Summary

Drag	calcDrag(AirframeDragDeviceSettings dragDevices, AircraftWeight acWeight, Coefficient coeffOfLift, TrueAirspeed trueAirspeed, LocalAtm localAtm) Computes the drag force acting upon the aircraft.
Coefficient	calcDragCoefficient(FlapSetting flapSetting, Coefficient coeffOfLift, TrueAirspeed tas, LocalAtm localAtm) Computes and returns the drag coefficient acting upon the aircraft.
static Pressure	calcDynamicPressure(TrueAirspeed trueAirspeed, LocalAtm localAtm) Calculates and returns the value of the dynamic pressure using the equation from the Airframe Object Template.
Lift	calcLift(Coefficient coeffOfLift, TrueAirspeed trueAirspeed, LocalAtm localAtm) Computes the lift force acting upon the aircraft.
LandingSpeedSchedule	getLandingSpeedSchedule(Weight acTotalWeight)
Coefficient	getMaxCoeffOfLift(FlapSetting flapSetting) Returns the maximum coefficient of lift for the given flap setting.
IndicatedAirspeed	getRotationSpeed(Weight acTotalWeight, Engine engine)
Coefficient	getSpeedBrakeCoeff()
TrueAirspeed	getStallSpeed(FlapSetting flapSetting, Weight acTotalWeight, Density localDensity)
Area	getWingSurfaceArea() Return the wing surface area.
Coefficient	temperCoeffOfLift(Coefficient currCoeff, Coefficient desCoeff, FlapSetting flapSetting, SimulationTime timeStep) Returns the next, moderated increment to the coefficient of lift.

Methods inherited from class java.lang.Object

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

Field Detail

serialVersionUID

static final long serialVersionUID

See Also:

Constant Field Values

CVS_VERSION_ID

public static final java.lang.String CVS_VERSION_ID

The CVS Version ID

See Also:

Constant Field Values

STALL_SAFETY_FACTOR

public static final double STALL_SAFETY_FACTOR

See Also:

Constant Field Values

wingSurface

private Area wingSurface

The surface area of the wing.

airframeCoeff

private AirframeCoefficients airframeCoeff

The airframe coefficients, including cD, cK, maxLiftCoeff, clMaxLOverD and their current flap settings.

cdSpoiler

private Coefficient cdSpoiler

Coefficient of drag for spoilers (from XML).

cdGear

private Coefficient cdGear

Coefficient of drag for landing gear (from XML).

cdBrakes

private Coefficient cdBrakes

Coefficient of drag for aircraft wheel brakes.

wheelBrakesOn

private boolean wheelBrakesOn

Drag parameter indicating whether wheel brakes are on.

spoilerDeployed

private boolean spoilerDeployed

Drag parameter indicating whether the spoiler is deployed.

cM

private Coefficient cM

Compressibility coefficient.

Constructor Detail

Airframe

public Airframe(Area wingSurfaceArea,
                Coefficient compress,
                Coefficient spoiler,
                Coefficient gear,
                Coefficient brakes,
                AirframeCoefficients airframeCoefficients)

Standard Constructor.

Parameters:

wingSurfaceArea - Surface area of the wing.

compress - Compressibility coefficient.

spoiler - The coefficient for describing the spoilers.

gear - The coefficient describing the landing gear.

brakes - The coefficient describing the braking system.

airframeCoefficients - Encapsulates other airframe coefficients.

Method Detail

calcLift

public Lift calcLift(Coefficient coeffOfLift,
                     TrueAirspeed trueAirspeed,
                     LocalAtm localAtm)

Computes the lift force acting upon the aircraft.

Parameters:

coeffOfLift - Lift coefficient to use in calculations.

trueAirspeed - Airspeed to use for calculations.

localAtm - The local atmospheric conditions.

Returns:

Force object containing the calculated lift

calcDrag

public Drag calcDrag(AirframeDragDeviceSettings dragDevices,
                     AircraftWeight acWeight,
                     Coefficient coeffOfLift,
                     TrueAirspeed trueAirspeed,
                     LocalAtm localAtm)

Computes the drag force acting upon the aircraft.

Parameters:

dragDevices - This airframe's current drag device settings.

acWeight - This aircraft's current weight.

coeffOfLift - Lift coefficient to use in calculations.

trueAirspeed - Airspeed to use for calculations.

localAtm - The local atmospheric conditions.

Returns:

Force object containing the calcualted drag

getSpeedBrakeCoeff

public Coefficient getSpeedBrakeCoeff()

calcDragCoefficient

public Coefficient calcDragCoefficient(FlapSetting flapSetting,
                                       Coefficient coeffOfLift,
                                       TrueAirspeed tas,
                                       LocalAtm localAtm)

Computes and returns the drag coefficient acting upon the aircraft.

Parameters:

flapSetting - The flap setting to calculate the drag for.

coeffOfLift - Lift coefficient to use in calculations.

tas - Airspeed to use for calculations.

localAtm - The local atmospheric conditions.

Returns:

Coefficient object containing the calculated drag coefficient

calcDynamicPressure

public static Pressure calcDynamicPressure(TrueAirspeed trueAirspeed,
                                           LocalAtm localAtm)

Calculates and returns the value of the dynamic pressure using the equation from the Airframe Object Template.

Parameters:

trueAirspeed - Airspeed to use for calculations.

localAtm - The atmosphere at the position.

Returns:

Pressure object containing the calculated dynamic pressure

getWingSurfaceArea

public Area getWingSurfaceArea()

Return the wing surface area.

Returns:

Area object containing the wing surface area

temperCoeffOfLift

public Coefficient temperCoeffOfLift(Coefficient currCoeff,
                                     Coefficient desCoeff,
                                     FlapSetting flapSetting,
                                     SimulationTime timeStep)

Returns the next, moderated increment to the coefficient of lift.

Parameters:

currCoeff - The current coefficient of lift.

desCoeff - The desired coefficient of lift.

flapSetting - The current flap setting.

timeStep - Time between updates.

getMaxCoeffOfLift

public Coefficient getMaxCoeffOfLift(FlapSetting flapSetting)

Returns the maximum coefficient of lift for the given flap setting.

getStallSpeed

public TrueAirspeed getStallSpeed(FlapSetting flapSetting,
                                  Weight acTotalWeight,
                                  Density localDensity)

Returns:

TrueAirspeed if you give localAtm, Indicated = True on ground.

getRotationSpeed

public IndicatedAirspeed getRotationSpeed(Weight acTotalWeight,
                                          Engine engine)

getLandingSpeedSchedule

public LandingSpeedSchedule getLandingSpeedSchedule(Weight acTotalWeight)