def update(self, controls, system, environment):
# If a control is not given, the previous value is assigned.
for control_name, control_value in controls.items():
limits = self.control_limits[control_name]
if limits[0] <= control_value <= limits[1]:
self.controls[control_name] = control_value
else:
# TODO: maybe raise a warning and assign max deflection
msg = "Control {} out of range ({} when max={} and min={" \
"}".format(control_name, limits[1], limits[0])
raise ValueError(msg)
# Velocity relative to air: aerodynamic velocity.
aero_vel = system.vel_body - environment.body_wind
self.alpha, self.beta, self.TAS = calculate_alpha_beta_TAS(
u=aero_vel[0], v=aero_vel[1], w=aero_vel[2])
self.p, self.q, self.r = system.vel_ang
# Setting velocities & dynamic pressure
self.CAS = tas2cas(self.TAS, environment.p, environment.rho)
self.EAS = tas2eas(self.TAS, environment.rho)
self.Mach = self.TAS / environment.a
self.q_inf = 0.5 * environment.rho * self.TAS**2
# Setting environment
self.rho = environment.rho
# Gravity force
self.gravity_force = environment.gravity_vector * self.mass
def update(self, controls, system, environment):
# If a control is not given, the previous value is assigned.
for control_name, control_value in controls.items():
limits = self.control_limits[control_name]
if limits[0] <= control_value <= limits[1]:
self.controls[control_name] = control_value
else:
# TODO: maybe raise a warning and assign max deflection
msg = "Control {} out of range ({} when max={} and min={" \
"}".format(control_name, limits[1], limits[0])
raise ValueError(msg)
# Velocity relative to air: aerodynamic velocity.
aero_vel = system.vel_body - environment.body_wind
self.alpha, self.beta, self.TAS = calculate_alpha_beta_TAS(
u=aero_vel[0], v=aero_vel[1], w=aero_vel[2])
self.p, self.q, self.r = system.vel_ang
# Setting velocities & dynamic pressure
self.CAS = tas2cas(self.TAS, environment.p, environment.rho)
self.EAS = tas2eas(self.TAS, environment.rho)
self.Mach = self.TAS / environment.a
self.q_inf = 0.5 * environment.rho * self.TAS ** 2
# Gravity force
self.gravity_force = environment.gravity_vector * self.mass
def update(self, controls, system, environment):
"""Update the aircraft data using the values computed by the simulator
Parameters
----------
controls : dictionary
Dictionary with the control values. Outdated data, it is preserved
just for backward compatibility.
system : System
Current simulator system
environment : Enviroment
Current Environment settings
"""
self.__environment = environment
self.aero_vel = system.vel_body - environment.body_wind
self.alpha, self.beta, self.TAS = calculate_alpha_beta_TAS(
u=self.aero_vel[0], v=self.aero_vel[1], w=self.aero_vel[2])
self.p, self.q, self.r = system.vel_ang
# Setting velocities & dynamic pressure
self.CAS = tas2cas(self.TAS, environment.p, environment.rho)
self.EAS = tas2eas(self.TAS, environment.rho)
self.Mach = self.TAS / environment.a
def _calculate_aerodynamics(self, state, environment):
# Velocity relative to air: aerodynamic velocity.
aero_vel = state.velocity.vel_body - environment.body_wind
self.alpha, self.beta, self.TAS = calculate_alpha_beta_TAS(
u=aero_vel[0], v=aero_vel[1], w=aero_vel[2])
# Setting velocities & dynamic pressure
self.CAS = tas2cas(self.TAS, environment.p, environment.rho)
self.EAS = tas2eas(self.TAS, environment.rho)
self.Mach = self.TAS / environment.a
self.q_inf = 0.5 * environment.rho * self.TAS**2
def test_calculate_alpha_beta_TAS():
u, v, w = 10, 0, 10
expected_TAS = sqrt(200)
expected_alfa = atan(1)
expected_beta = 0
alfa, beta, TAS = calculate_alpha_beta_TAS(u, v, w)
assert_almost_equal((expected_alfa, expected_beta, expected_TAS),
(alfa, beta, TAS))
u, v, w = 10, 10, 0
expected_alfa = 0
expected_beta = asin(10 / sqrt(200))
alfa, beta, TAS = calculate_alpha_beta_TAS(u, v, w)
assert_almost_equal((expected_alfa, expected_beta, expected_TAS),
(alfa, beta, TAS))
def test_calculate_alpha_beta_TAS():
u, v, w = 10, 0, 10
expected_TAS = sqrt(200)
expected_alfa = atan(1)
expected_beta = 0
alfa, beta, TAS = calculate_alpha_beta_TAS(u, v, w)
assert_almost_equal((expected_alfa, expected_beta, expected_TAS),
(alfa, beta, TAS))
u, v, w = 10, 10, 0
expected_alfa = 0
expected_beta = asin(10 / sqrt(200))
alfa, beta, TAS = calculate_alpha_beta_TAS(u, v, w)
assert_almost_equal((expected_alfa, expected_beta, expected_TAS),
(alfa, beta, TAS))
def _calculate_aerodynamics(self, state, environment):
# Velocity relative to air: aerodynamic velocity.
aero_vel = state.velocity.vel_body - environment.body_wind
self.alpha, self.beta, self.TAS = calculate_alpha_beta_TAS(
u=aero_vel[0], v=aero_vel[1], w=aero_vel[2]
)
# Setting velocities & dynamic pressure
self.CAS = tas2cas(self.TAS, environment.p, environment.rho)
self.EAS = tas2eas(self.TAS, environment.rho)
self.Mach = self.TAS / environment.a
self.q_inf = 0.5 * environment.rho * self.TAS ** 2
def calculate_aero_conditions(self, state):
# Getting conditions from environment
body_wind = self.body_wind(state)
T, P, rho, a = self.atmosphere.variables(state)
# Velocity relative to air: aerodynamic velocity.
aero_vel = (state.velocity - body_wind)
alpha, beta, TAS = calculate_alpha_beta_TAS(aero_vel)
# Setting velocities & dynamic pressure
CAS = tas2cas(TAS, P, rho)
EAS = tas2eas(TAS, rho)
Mach = TAS / a
q_inf = 0.5 * rho * np.square(TAS)
# gravity vector
gravity_vector = self.gravity_vector(state)
return Conditions(TAS, CAS, Mach, q_inf, rho, T, P, a, alpha, beta,
gravity_vector)
forces_and_moments = cessna_310.get_forces_and_moments
for ii, t in enumerate(time[1:]):
forces, moments = forces_and_moments(
TAS[ii], rho, alpha[ii], beta[ii], d_e[ii], 0,
d_a[ii], d_r[ii], d_t[ii], attitude)
results[ii+1, :] = equations.propagate(mass, inertia, forces, moments,
dt)
lin_vel = results[ii+1, 0:3]
ang_vel = results[ii+1, 3:6]
attitude = results[ii+1, 6:9]
position = results[ii+1, 9:12]
alpha[ii+1], beta[ii+1], TAS[ii+1] = calculate_alpha_beta_TAS(*lin_vel)
_, _, rho, _ = atm(position[2])
velocities = results[:, 0:6]
attitude_angles = results[:, 6:9]
position = results[:, 9:12]
# PLOTS
plt.close('all')
plt.style.use('ggplot')
plt.figure('pos')
plt.plot(time, position[:, 0], label='x')
plt.plot(time, position[:, 1], label='y')
plt.plot(time, position[:, 2], label='z')
def to_wind_frame(data):
alpha, beta, TAS = calculate_alpha_beta_TAS(data[vel].values)
for i, ind in enumerate(data.index):
data.loc[ind, aerof] = body2wind(data.loc[ind, frc], alpha[i],
beta[i]) * np.array([-1, 1, -1])
return data
