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enh: moved Flight prints to flight_prints.py
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@MateusStano
MateusStano committed Nov 13, 2022
1 parent bb5d7c5 commit ab23ce8
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273 changes: 4 additions & 269 deletions rocketpy/Flight.py
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Original file line number Diff line number Diff line change
Expand Up @@ -15,6 +15,7 @@
from scipy import integrate

from .Function import Function
from .prints.flight_prints import _FlightPrints


class Flight:
Expand Down Expand Up @@ -629,7 +630,8 @@ def __init__(
self.parachuteEvents = []
self.postProcessed = False
self.latitude = 0 # Function(0)
self.longitude = 0 # Function(0)
self.longitude = 0 # Function(0)'
self.prints = _FlightPrints(self)
# Initialize solver monitors
self.functionEvaluations = []
self.functionEvaluationsPerTimeStep = []
Expand Down Expand Up @@ -2222,262 +2224,7 @@ def info(self):
------
None
"""
# Post-process results
if self.postProcessed is False:
self.postProcess()

# Get index of out of rail time
outOfRailTimeIndexes = np.nonzero(self.x[:, 0] == self.outOfRailTime)
outOfRailTimeIndex = (
-1 if len(outOfRailTimeIndexes) == 0 else outOfRailTimeIndexes[0][0]
)

# Get index of time before parachute event
if len(self.parachuteEvents) > 0:
eventTime = self.parachuteEvents[0][0] + self.parachuteEvents[0][1].lag
eventTimeIndex = np.nonzero(self.x[:, 0] == eventTime)[0][0]
else:
eventTime = self.tFinal
eventTimeIndex = -1

# Print surface wind conditions
print("Surface Wind Conditions\n")
print("Frontal Surface Wind Speed: {:.2f} m/s".format(self.frontalSurfaceWind))
print("Lateral Surface Wind Speed: {:.2f} m/s".format(self.lateralSurfaceWind))

# Print out of rail conditions
print("\n\n Rail Departure State\n")
print("Rail Departure Time: {:.3f} s".format(self.outOfRailTime))
print("Rail Departure Velocity: {:.3f} m/s".format(self.outOfRailVelocity))
print(
"Rail Departure Static Margin: {:.3f} c".format(
self.staticMargin(self.outOfRailTime)
)
)
print(
"Rail Departure Angle of Attack: {:.3f}°".format(
self.angleOfAttack(self.outOfRailTime)
)
)
print(
"Rail Departure Thrust-Weight Ratio: {:.3f}".format(
self.rocket.thrustToWeight(self.outOfRailTime)
)
)
print(
"Rail Departure Reynolds Number: {:.3e}".format(
self.ReynoldsNumber(self.outOfRailTime)
)
)

# Print burnOut conditions
print("\n\nBurnOut State\n")
print("BurnOut time: {:.3f} s".format(self.rocket.motor.burnOutTime))
print(
"Altitude at burnOut: {:.3f} m (AGL)".format(
self.z(self.rocket.motor.burnOutTime) - self.env.elevation
)
)
print(
"Rocket velocity at burnOut: {:.3f} m/s".format(
self.speed(self.rocket.motor.burnOutTime)
)
)
print(
"Freestream velocity at burnOut: {:.3f} m/s".format(
(
self.streamVelocityX(self.rocket.motor.burnOutTime) ** 2
+ self.streamVelocityY(self.rocket.motor.burnOutTime) ** 2
+ self.streamVelocityZ(self.rocket.motor.burnOutTime) ** 2
)
** 0.5
)
)
print(
"Mach Number at burnOut: {:.3f}".format(
self.MachNumber(self.rocket.motor.burnOutTime)
)
)
print(
"Kinetic energy at burnOut: {:.3e} J".format(
self.kineticEnergy(self.rocket.motor.burnOutTime)
)
)

# Print apogee conditions
print("\n\nApogee\n")
print(
"Apogee Altitude: {:.3f} m (ASL) | {:.3f} m (AGL)".format(
self.apogee, self.apogee - self.env.elevation
)
)
print("Apogee Time: {:.3f} s".format(self.apogeeTime))
print("Apogee Freestream Speed: {:.3f} m/s".format(self.apogeeFreestreamSpeed))

# Print events registered
print("\n\nEvents\n")
if len(self.parachuteEvents) == 0:
print("No Parachute Events Were Triggered.")
for event in self.parachuteEvents:
triggerTime = event[0]
parachute = event[1]
openTime = triggerTime + parachute.lag
velocity = self.freestreamSpeed(openTime)
altitude = self.z(openTime)
name = parachute.name.title()
print(name + " Ejection Triggered at: {:.3f} s".format(triggerTime))
print(name + " Parachute Inflated at: {:.3f} s".format(openTime))
print(
name
+ " Parachute Inflated with Freestream Speed of: {:.3f} m/s".format(
velocity
)
)
print(
name
+ " Parachute Inflated at Height of: {:.3f} m (AGL)".format(
altitude - self.env.elevation
)
)

# Print impact conditions
if len(self.impactState) != 0:
print("\n\nImpact\n")
print("X Impact: {:.3f} m".format(self.xImpact))
print("Y Impact: {:.3f} m".format(self.yImpact))
print("Time of Impact: {:.3f} s".format(self.tFinal))
print("Velocity at Impact: {:.3f} m/s".format(self.impactVelocity))
elif self.terminateOnApogee is False:
print("\n\nEnd of Simulation\n")
print("Time: {:.3f} s".format(self.solution[-1][0]))
print("Altitude: {:.3f} m".format(self.solution[-1][3]))

# Print maximum values
print("\n\nMaximum Values\n")
print(
"Maximum Speed: {:.3f} m/s at {:.2f} s".format(
self.maxSpeed, self.maxSpeedTime
)
)
print(
"Maximum Mach Number: {:.3f} Mach at {:.2f} s".format(
self.maxMachNumber, self.maxMachNumberTime
)
)
print(
"Maximum Reynolds Number: {:.3e} at {:.2f} s".format(
self.maxReynoldsNumber, self.maxReynoldsNumberTime
)
)
print(
"Maximum Dynamic Pressure: {:.3e} Pa at {:.2f} s".format(
self.maxDynamicPressure, self.maxDynamicPressureTime
)
)
print(
"Maximum Acceleration: {:.3f} m/s² at {:.2f} s".format(
self.maxAcceleration, self.maxAccelerationTime
)
)
print(
"Maximum Gs: {:.3f} g at {:.2f} s".format(
self.maxAcceleration / self.env.g, self.maxAccelerationTime
)
)
print(
"Maximum Upper Rail Button Normal Force: {:.3f} N".format(
self.maxRailButton1NormalForce
)
)
print(
"Maximum Upper Rail Button Shear Force: {:.3f} N".format(
self.maxRailButton1ShearForce
)
)
print(
"Maximum Lower Rail Button Normal Force: {:.3f} N".format(
self.maxRailButton2NormalForce
)
)
print(
"Maximum Lower Rail Button Shear Force: {:.3f} N".format(
self.maxRailButton2ShearForce
)
)

return None

def printInitialConditionsData(self):
"""Prints all initial conditions data available about the flight
Parameters
----------
None
Return
------
None
"""
# Post-process results
if self.postProcessed is False:
self.postProcess()

print(
"Position - x: {:.2f} m | y: {:.2f} m | z: {:.2f} m".format(
self.x(0), self.y(0), self.z(0)
)
)
print(
"Velocity - Vx: {:.2f} m/s | Vy: {:.2f} m/s | Vz: {:.2f} m/s".format(
self.vx(0), self.vy(0), self.vz(0)
)
)
print(
"Attitude - e0: {:.3f} | e1: {:.3f} | e2: {:.3f} | e3: {:.3f}".format(
self.e0(0), self.e1(0), self.e2(0), self.e3(0)
)
)
print(
"Euler Angles - Spin φ : {:.2f}° | Nutation θ: {:.2f}° | Precession ψ: {:.2f}°".format(
self.phi(0), self.theta(0), self.psi(0)
)
)
print(
"Angular Velocity - ω1: {:.2f} rad/s | ω2: {:.2f} rad/s| ω3: {:.2f} rad/s".format(
self.w1(0), self.w2(0), self.w3(0)
)
)
return None

def printNumericalIntegrationSettings(self):
"""Prints out the Numerical Integration settings
Parameters
----------
None
Return
------
None
"""
print("Maximum Allowed Flight Time: {:f} s".format(self.maxTime))
print("Maximum Allowed Time Step: {:f} s".format(self.maxTimeStep))
print("Minimum Allowed Time Step: {:e} s".format(self.minTimeStep))
print("Relative Error Tolerance: ", self.rtol)
print("Absolute Error Tolerance: ", self.atol)
print("Allow Event Overshoot: ", self.timeOvershoot)
print("Terminate Simulation on Apogee: ", self.terminateOnApogee)
print("Number of Time Steps Used: ", len(self.timeSteps))
print(
"Number of Derivative Functions Evaluation: ",
sum(self.functionEvaluationsPerTimeStep),
)
print(
"Average Function Evaluations per Time Step: {:3f}".format(
sum(self.functionEvaluationsPerTimeStep) / len(self.timeSteps)
)
)

self.prints.allPrints()
return None

def calculateStallWindVelocity(self, stallAngle):
Expand Down Expand Up @@ -3676,21 +3423,9 @@ def allInfo(self):
if self.postProcessed is False:
self.postProcess()

# Print initial conditions
print("Initial Conditions\n")
self.printInitialConditionsData()

# Print launch rail orientation
print("\n\nLaunch Rail Orientation\n")
print("Launch Rail Inclination: {:.2f}°".format(self.inclination))
print("Launch Rail Heading: {:.2f}°\n\n".format(self.heading))

# Print a summary of data about the flight
self.info()

print("\n\nNumerical Integration Information\n")
self.printNumericalIntegrationSettings()

print("\n\nTrajectory 3d Plot\n")
self.plot3dTrajectory()

Expand Down
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