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Update Rocket.py #1

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79 changes: 26 additions & 53 deletions rocketpy/Rocket.py
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Original file line number Diff line number Diff line change
Expand Up @@ -234,6 +234,9 @@ def __init__(

# Parachute data initialization
self.parachutes = []

# Parachute's Calculated Cds data initialization
self.calculated_cds = []

# Rail button data initialization
self.railButtons = None
Expand Down Expand Up @@ -662,63 +665,27 @@ def cnalfa1(cn):
# Return self
return self.aerodynamicSurfaces[-1]

def calculateCds(
self,
finalSpeed = 9,
finalAirDensity = None,
parachuteKind = None,
Cd = None,
area = None
):
"""Calculates the parachute's Cds using its final speed and
air density or its area, that can be given or calculated through
the Cd or kind of the parachute
def calculate_cds(self, final_speed = 9, final_air_density):
"""Returns the parachute's Cds calculated through its final speed and
air density.

Parameters
----------
finalSpeed : float
Final speed of the system rocket/parachute.
finalAirDensity : float
Air density at the lowest height in which the parachute
is being used.
parachuteKind : string
Indicates the format of the parachute.
Cd : float
Value of the parachute's dragg coefficient.
area : float
Surface area of the parachute in squared meters.
final_speed : float, optional
Rocket's speed when landing.
final_air_density : float
Air density right before the rocket lands.

Returns
-------
Cds : float
Estimated Cds of the parachute.
cds : float
Number equal to drag coefficient times reference area for parachute.

"""

if finalAirDensity != None:
Cds = 2 * self.mass * 9.80665 / ((finalSpeed ** 2) * finalAirDensity)

elif Cd != None:
Cds = area * Cd

else:
if parachuteKind == "quarter spherical":
Cd = 0.88

if parachuteKind == "semi-ellipsoidal":
Cd = 0.6

if parachuteKind == "hemispherical":
Cd = 0.7

if parachuteKind == "flat circular":
Cd = 0.75

if parachuteKind == "conical":
Cd = 0.8

if parachuteKind == "toroidal":
Cd = 0.8
Cds = area * Cd
return Cds
cds = 2 * self.mass * 9.80665 / ((final_speed ** 2) * final_air_density)
self.calculated_cds.append(cds)
return cds

def addParachute(
self, name, CdS, trigger, samplingRate=100, lag=0, noise=(0, 0, 0)
Expand Down Expand Up @@ -951,7 +918,10 @@ def info(self):
# Print parachute data
for chute in self.parachutes:
print("\n" + chute.name.title() + " Parachute")
print("CdS Coefficient: " + str(chute.CdS) + " m2")
if chute.CdS in self.calculated_cds:
print("Calculated CdS Coefficient: " + str(chute.CdS) + " m2")
else:
print("CdS Coefficient: " + str(chute.CdS) + " m2")

# Show plots
print("\nAerodynamics Plots")
Expand Down Expand Up @@ -1029,8 +999,11 @@ def allInfo(self):

# Print parachute data
for chute in self.parachutes:
print("\n" + chute.name.title() + " Parachute")
print("CdS Coefficient: " + str(chute.CdS) + " m2")
print("\n" + chute.name.title() + " Parachute")
if chute.CdS in self.calculated_cds:
print("Calculated CdS Coefficient: " + str(chute.CdS) + " m2")
else:
print("CdS Coefficient: " + str(chute.CdS) + " m2")
if chute.trigger.__name__ == "<lambda>":
line = getsourcelines(chute.trigger)[0][0]
print(
Expand Down