public static void Constructor_ExpectedValues()
{
// Setup
var random = new Random(21);
AircraftData aircraftData = AircraftDataTestFactory.CreateRandomAircraftData();
// Call
var calculator = new NormalTakeOffDynamicsCalculator(aircraftData, random.NextDouble(), random.NextDouble());
// Assert
Assert.IsInstanceOf <TakeOffDynamicsCalculatorBase>(calculator);
Assert.IsInstanceOf <INormalTakeOffDynamicsCalculator>(calculator);
}
public static void Calculate_WithAircraftStateHeightSmallerThanThresholdAndLiftSmallerThanTakeOffWeight_ReturnsExpectedTrueAirspeedRate(AircraftData aircraftData)
{
// Setup
const double airspeed = 10.0;
const double threshold = 0.01;
var random = new Random(21);
var aircraftState = new AircraftState(aircraftData.MaximumPitchAngle,
random.NextAngle(),
airspeed,
threshold - random.NextDouble(),
random.NextDouble());
Angle angleOfAttack = aircraftState.PitchAngle - aircraftState.FlightPathAngle;
// Precondition
double lift = AerodynamicsHelper.CalculateLift(aircraftData.AerodynamicsData,
angleOfAttack,
airDensity,
airspeed);
double takeOffWeightNewton = aircraftData.TakeOffWeight * 1000; // N
Assert.IsTrue(lift < takeOffWeightNewton);
var calculator = new NormalTakeOffDynamicsCalculator(aircraftData, airDensity, gravitationalAcceleration);
// Call
AircraftAccelerations accelerations = calculator.Calculate(aircraftState);
// Assert
double liftCoefficient = AerodynamicsHelper.CalculateLiftCoefficient(aircraftData.AerodynamicsData, angleOfAttack);
double normalForce = takeOffWeightNewton - lift;
double dragForce = AerodynamicsHelper.CalculateDragWithoutEngineFailure(aircraftData.AerodynamicsData,
liftCoefficient,
airDensity,
airspeed)
+ normalForce * aircraftData.RollingResistanceCoefficient;
double thrustForce = aircraftData.NrOfEngines * aircraftData.MaximumThrustPerEngine * 1000;
double horizontalWeightComponent = takeOffWeightNewton * Math.Sin(aircraftState.FlightPathAngle.Radians);
double expectedAcceleration = (gravitationalAcceleration * (thrustForce - dragForce - horizontalWeightComponent))
/ takeOffWeightNewton;
Assert.AreEqual(expectedAcceleration, accelerations.TrueAirSpeedRate, tolerance);
}
public static void Calculate_WithAircraftStateSpeedHigherThanRotationSpeedAndPitchAngleAtMaximumPitch_ReturnsExpectedZeroPitchRate(AircraftData aircraftData)
{
// Setup
double rotationSpeed = GetRotationSpeed(aircraftData);
var random = new Random(21);
var aircraftState = new AircraftState(aircraftData.MaximumPitchAngle,
random.NextAngle(),
rotationSpeed + random.NextDouble(),
random.NextDouble(),
random.NextDouble());
var calculator = new NormalTakeOffDynamicsCalculator(aircraftData, airDensity, random.NextDouble());
// Call
AircraftAccelerations accelerations = calculator.Calculate(aircraftState);
// Assert
Assert.Zero(accelerations.PitchRate.Degrees);
}
public void Calculate_WithAircraftStateAndSpeedHigherThanRotationSpeedAndPitch_ReturnsExpectedPitchRate(AircraftData aircraftData)
{
// Setup
var random = new Random(21);
double rotationSpeed = GetRotationSpeed(aircraftData);
double pitchAngle = aircraftData.MaximumPitchAngle.Degrees - random.NextDouble();
var aircraftState = new AircraftState(Angle.FromDegrees(pitchAngle),
random.NextAngle(),
rotationSpeed + random.NextDouble(),
random.NextDouble(),
random.NextDouble());
var calculator = new NormalTakeOffDynamicsCalculator(aircraftData, airDensity, random.NextDouble());
// Call
AircraftAccelerations accelerations = calculator.Calculate(aircraftState);
// Assert
Angle expectedPitchRate = aircraftData.PitchAngleGradient;
Assert.AreEqual(expectedPitchRate, accelerations.PitchRate);
}
