def from_file(file):
diameter = find_parameter(file, "diameter")
length = find_parameter(file, "length")
density = find_parameter(file, "density")
thickness = find_parameter(file, "thickness")
return Body(eval(diameter), eval(length), eval(thickness),
eval(density))
def from_file_with_AoAspeed(initFile, sampleReport, path_to_file=''):
"""
Create an instance of CFDrocket by reading some files
example: initFile.dot as initFile, myMotor.dot as motor and CFD files as drag.dot, lift.dot, moments.dot
-stored in folder 'myRocket2' (see 'Tests' folder)
in 'initFile.dot':
initial_mass = value of initial mass
initial_moi = Ixx, Iyy, Izz
initial_com = x-value of initial COM (this one is negative!)
length = value of rocket total length
motor = myMotor.dot
myRocket = Rocket.from_file('initFile.dot', 'sample-report.dot',
'myRocket2/')
:param initFile: The file with content specified above
:param sampleReport: The CFD file with aero moments about COM.
Add sampling period, alpha_max, delta_v, v0 values to bottom of sampleReport:
period = ..
alpha_max = ..
.
.
.
:param path_to_file: The path to the files above relative to current path (none by default)
return: A rocket instance with specs from initFile and CFD.
"""
path = path_to_file + initFile
# CAD files are using the units mentioned below
initMass = find_parameter(path, 'initial_mass') # in grams
initMOI = find_parameter(path, 'initial_moi')
initMOI = np.diag(
np.array([x.strip()
for x in initMOI.split(',')]).astype(float)) # in g*mm^2
initCOM = find_parameter(path, 'initial_com') # in millimeters
length = find_parameter(path, 'length') # in millimeters
motor = Motor.from_file(path_to_file + find_parameter(path, 'motor'))
path = path_to_file + sampleReport
alpha, air_speed, aeroForces, moment = unwrap_report2(path)
return Rocket(
float(initMass) / 1e3, initMOI / 1e9,
float(initCOM) / 1e3,
float(length) / 1e3, motor, air_speed, alpha, aeroForces, moment)
def from_file(motorFile):
"""
Read a file with motor specs.
ASSUMPTIONS: -
:param motorFile: The file with motor specs in proper format
:return: motor
"""
name = find_parameter(motorFile, "name")
diameter = find_parameter(motorFile, "diameter")
length = find_parameter(motorFile, "length")
propMass = find_parameter(motorFile, "propellant_mass")
frameMass = find_parameter(motorFile, "frame_mass")
totalImpulse = find_parameter(motorFile, "total_impulse")
motorFile = open(motorFile, 'r')
thrust = [[0, 0]]
with motorFile as fp:
for i, line in enumerate(fp):
if i > 5:
row = line.split()
t = eval(row[0])
f = eval(row[1])
thrust.append([t, f])
thrust = np.array(thrust)
return Motor(name, thrust, float(totalImpulse), float(diameter),
float(length), float(propMass), float(frameMass))
def from_file(file):
semiChord = find_parameter(file, "semi_chord")
rootChord = find_parameter(file, "root_chord")
tipChord = find_parameter(file, "tip_chord")
angle = find_parameter(file, "root_angle")
density = find_parameter(file, "density")
thickness = find_parameter(file, "thickness")
return Fin(eval(semiChord), eval(rootChord), eval(tipChord),
eval(angle), eval(thickness), eval(density))
def from_file(rocket_file, path_to_file=""):
"""
Creating an instance of a rocket by reading a rocket file that is located in a folder containing files for all
necessary rocket parts.
Example: folder 'myRocket'
'myRocket' content:
- myNose.dot
- myBody.dot
- myMotor.dot
- myFin.dot
- myPayload.dot
- myRocket.dot <-- rocket file!
If this folder is located in the current working folder, you can simply create an instance of this
rocket with:
myRocket = RocketSimple.from_file('myRocket.dot', 'myRocket')
:param path_to_file: [string] a path to the rocket file relative to the current path (empty by default)
:param rocket_file: [string] name of rocket file
:return: [RocketSimple class] Rocket instance with specs from rocket file.
"""
# get file names of each rocket part
path = path_to_file + rocket_file
noseFile = find_parameter(path, "nose")
bodyFile = find_parameter(path, "body")
finFile = find_parameter(path, "fin")
numberOfFins = find_parameter(path, "number_of_fins")
motorFile = find_parameter(path, "motor")
payloadFile = find_parameter(path, "payload")
payloadPlacement = find_parameter(path, "payload_placement")
finPlacement = find_parameter(path, "fin_placement")
partsPlacement = np.array([eval(finPlacement), eval(payloadPlacement)])
# Initialize rocket parts
path = path_to_file
nose = Nose.from_file(path + noseFile)
body = Body.from_file(path + bodyFile)
fin = Fin.from_file(path + finFile)
motor = Motor.from_file(path + motorFile)
payload = Payload.from_file(path + payloadFile)
return RocketSimple(nose, body, fin, eval(numberOfFins), motor,
payload, partsPlacement)
def from_file(file):
noseType = find_parameter(file, "nose_type")
if noseType.lower() == noseTypes[0] or noseType.lower(
) == noseTypes[2]: # Conic or Ogive
diameter = find_parameter(file, "diameter")
length = find_parameter(file, "length")
density = find_parameter(file, "density")
thickness = find_parameter(file, "thickness")
return Nose(noseType.lower(), eval(diameter), eval(length),
eval(thickness), eval(density))
elif noseType.lower() == noseTypes[1]: # Hemisphere
diameter = find_parameter(file, "diameter")
thickness = find_parameter(file, "thickness")
density = find_parameter(file, "density")
return Nose(noseType.lower(), eval(diameter), eval(thickness),
eval(density))
else:
print("ERROR: invalid nose type '" + noseType +
"' encountered at initialization. "
"Please check your spelling.")
print("Possible options:")
for string in noseTypes:
print("\t" + string)
exit(1)
def from_file(file=''):
width = find_parameter(file, "width")
return Payload(eval(width))