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):
# 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):
"""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 Outdated data, it is preserved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 test_tas2cas():
# sea level
tas = 275
cas_expected = 275
cas = tas2cas(tas, p_0, rho_0)
assert_almost_equal(cas, cas_expected)
# Test at 11000m
_, p, rho, _ = atm(11000)
tas = 275
cas_expected = 162.03569680495048
cas = tas2cas(tas, p, rho)
assert_almost_equal(cas, cas_expected)
def _calculate_aerodynamics_2(self, TAS, alpha, beta, environment):
self.alpha, self.beta, self.TAS = alpha, beta, TAS
# 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_aerodynamics_2(self, TAS, alpha, beta, environment):
self.alpha, self.beta, self.TAS = alpha, beta, TAS
# 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_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_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)
