import matplotlib.pyplot as plt
import numpy as np
import math
# additional parameters the solver needs
atmosphere = Atmosphere(0)
launchAngle = 84 * math.pi / 180.0 #rad
launchrailLength = 8.0 #m
# Initial conditions
# y_0 is 0.01 instead of 0 so that the hit_ground event works. look into doing it another way
# x, vx, y, vy
y0 = [0., 0., 0.1, 0.]
rocketFilePath = "2019_rocket_doe.csv"
myRocket = Rocket(rocketFilePath)
motorFilePath = "Cesaroni_N5800.eng"
myMotor = Motor(motorFilePath)
solver = TwoDTrajectorySolver(
myRocket, myMotor, atmosphere, y0, launchAngle, launchrailLength,\
dragModel=DragModel.CoefficientsBox
)
parameterKeys = ['finRootChord', 'finTipChord', 'finSpan', 'finSweepLength']
baselineParameters = {}
doe_coeff = np.loadtxt('analysis/doe/lhc_n4_100samples.csv')
apogeeList = []
stabilityList = []
regression_row.append(xs[i])
# x_i**2
for i in range(nParameters):
regression_row.append(xs[i]**2)
# x_i*x_j
for i in range(0, nParameters):
for j in range(1, nParameters - i):
regression_row.append(xs[i] * xs[j])
return regression_row
rocketFilePath = "2019_rocket_doe.csv"
myRocket = Rocket(rocketFilePath)
parameterKeys = ['finRootChord', 'finTipChord', 'finSpan', 'finSweepLength']
baselineParameters = {}
for key in parameterKeys:
baselineParameters[key] = myRocket.geometry[key]
doe_coeff = np.loadtxt('analysis/doe/lhc_n4_1000samples.csv')
y_apogee = np.loadtxt('analysis/doe/apogee_list_lhs1000.csv')
nSamples = len(y_apogee)
nParameters = len(parameterKeys)
xs_regression = []
for row in doe_coeff:
xs_regression.append(getRegressionXs(row))
apogeeReg = linear_model.LinearRegression()
import matplotlib.pyplot as plt
import numpy as np
import math
from sensitivity_analysis import sensitivity_analysis_apogee
atmosphere = Atmosphere(0)
launchAngle = 84 * math.pi / 180.0 #rad
launchrailLength = 8.0 #m
# Initial conditions
# y_0 is 0.01 instead of 0 so that the hit_ground event works. look into doing it another way
# x, vx, y, vy
y0 = [0., 0., 0.1, 0.]
rocketFilePath = "2019_rocket_fineness1.csv"
myRocket = Rocket(rocketFilePath)
motorFilePath = "Cesaroni_N5800.eng"
myMotor = Motor(motorFilePath)
solver = TwoDTrajectorySolver(
myRocket, myMotor, atmosphere, y0, launchAngle, launchrailLength,\
dragModel=DragModel.CoefficientsBox
)
solver.solve()
bApogee = solver.apogee
studyParameters = ["nose_length"]
start = 1
stop = 10