def test_stationary_condition_trimming_Cessna172_ISA1972_NoWind_VerticalConstant(
TAS, h0, turn_rate, gamma):
import numpy as np
from pyfme.aircrafts import Cessna172
from pyfme.environment.environment import Environment
from pyfme.environment.atmosphere import ISA1976
from pyfme.environment.gravity import VerticalConstant
from pyfme.environment.wind import NoWind
from pyfme.models.state import EarthPosition
from pyfme.utils.trimmer import steady_state_trim
aircraft = Cessna172()
atmosphere = ISA1976()
gravity = VerticalConstant()
wind = NoWind()
environment = Environment(atmosphere, gravity, wind)
# Initial conditions.
psi0 = 1.0 # rad
x0, y0 = 0, 0 # m
pos0 = EarthPosition(x0, y0, h0)
controls0 = {
'delta_elevator': 0.05,
'delta_aileron': 0.2 * np.sign(turn_rate),
'delta_rudder': 0.2 * np.sign(turn_rate),
'delta_t': 0.5,
}
trimmed_state, trimmed_controls = steady_state_trim(
aircraft,
environment,
pos0,
psi0,
TAS,
controls0,
gamma,
turn_rate,
)
# Acceleration
np.testing.assert_almost_equal(trimmed_state.acceleration.value,
np.zeros_like(
trimmed_state.acceleration.value),
decimal=2)
# Angular acceleration
np.testing.assert_almost_equal(trimmed_state.angular_accel.value,
np.zeros_like(
trimmed_state.angular_accel.value),
decimal=2)
def test_simulation():
atmosphere = ISA1976()
gravity = VerticalConstant()
wind = NoWind()
environment = Environment(atmosphere, gravity, wind)
aircraft = Cessna172()
initial_position = EarthPosition(0, 0, 1000)
controls_0 = {
'delta_elevator': 0.05,
'delta_aileron': 0,
'delta_rudder': 0,
'delta_t': 0.5,
}
trimmed_state, trimmed_controls = steady_state_trim(aircraft,
environment,
initial_position,
psi=1,
TAS=50,
controls=controls_0)
system = EulerFlatEarth(t0=0, full_state=trimmed_state)
controls = {
'delta_elevator': Doublet(2, 1, 0.1,
trimmed_controls['delta_elevator']),
'delta_aileron': Constant(trimmed_controls['delta_aileron']),
'delta_rudder': Constant(trimmed_controls['delta_rudder']),
'delta_t': Constant(trimmed_controls['delta_t'])
}
simulation = Simulation(aircraft, system, environment, controls)
simulation.propagate(10)
""" import numpy as np import matplotlib.pyplot as plt from mpl_toolkits.mplot3d import Axes3D from pyfme.aircrafts import Cessna172 from pyfme.environment.environment import Environment from pyfme.environment.atmosphere import ISA1976 from pyfme.environment.gravity import VerticalConstant from pyfme.environment.wind import NoWind from pyfme.models.systems import EulerFlatEarth from pyfme.simulator import BatchSimulation from pyfme.utils.trimmer import steady_state_flight_trimmer aircraft = Cessna172() atmosphere = ISA1976() gravity = VerticalConstant() wind = NoWind() environment = Environment(atmosphere, gravity, wind) # Initial conditions. TAS = 45 # m/s h0 = 3000 # m psi0 = 1.0 # rad x0, y0 = 0, 0 # m turn_rate = 0.005 # rad/s gamma0 = 0.0 # rad system = EulerFlatEarth(lat=0, lon=0, h=h0, psi=psi0, x_earth=x0, y_earth=y0)
