def test_skywalkerX8_force_x_dir():
control_input = ControlInput()
control_input.throttle = 0.0
t = 0
state = State()
state.vx = 20.0
for j in range(3):
state.pitch = state.pitch + 0.05
state.roll = state.roll + 0.05
state.yaw = state.yaw + 0.05
x_update = np.zeros(11)
constants = SkywalkerX8Constants()
for i in range(0, 11):
control_input.throttle = i * 0.1
prop = IcedSkywalkerX8Properties(control_input)
params = {"prop": prop, "wind": no_wind()}
update = dynamics_kinetmatics_update(t,
x=state.state,
u=control_input.control_input,
params=params)
x_update[i] = update[6]
S_p = constants.propeller_area
C_p = constants.motor_efficiency_fact
k_m = constants.motor_constant
m = constants.mass
K = 2 * m / (AIR_DENSITY * S_p * C_p * k_m**2)
for i in range(0, 10):
throttle_0 = i * 0.1
throttle_1 = (i + 1) * 0.1
assert np.allclose(K * (x_update[i + 1] - x_update[i]),
throttle_1**2 - throttle_0**2)
def test_interconnected_system():
control_input = ControlInput()
control_input.throttle = 0.5
wind_model = no_wind()
state = State()
state.vx = 20
prop = IcedSkywalkerX8Properties(control_input)
outputs = [
"x", "y", "z", "roll", "pitch", "yaw", "vx", "vy", "vz", "ang_rate_x",
"ang_rate_y", "ang_rate_z"
]
aircraft_model = build_nonlin_sys(prop, wind_model, outputs)
initial_control_input_state = ControlInput()
initial_control_input_state.throttle = 0.4
motor_time_constant = 0.001
elevon_time_constant = 0.001
actuator_model = build_flying_wing_actuator_system(elevon_time_constant,
motor_time_constant)
x0 = np.concatenate(
(initial_control_input_state.control_input, state.state))
connected_system = add_actuator(actuator_model, aircraft_model)
t = np.linspace(0.0, 0.5, 10, endpoint=True)
u = np.array([
control_input.control_input,
] * len(t)).transpose()
T, yout_without_actuator = input_output_response(aircraft_model,
t,
U=u,
X0=state.state)
T, yout_with_actuator = input_output_response(connected_system,
t,
U=u,
X0=x0)
assert np.allclose(yout_with_actuator[6, :],
yout_without_actuator[6, :],
atol=5.e-3)
assert np.allclose(yout_with_actuator[7, :],
yout_without_actuator[7, :],
atol=5.e-3)
assert np.allclose(yout_with_actuator[8, :],
yout_without_actuator[8, :],
atol=5.e-3)
assert np.allclose(yout_with_actuator[9, :],
yout_without_actuator[9, :],
atol=5.e-3)
assert np.allclose(yout_with_actuator[10, :],
yout_without_actuator[10, :],
atol=5.e-3)
assert np.allclose(yout_with_actuator[11, :],
yout_without_actuator[11, :],
atol=5.e-3)
def main():
# Initialize gain scheduled controller
# Using two simple P-controllers, see also fcat.longitudinal_controller for more complicated examples
# Note that this is just an example on how to build and simulate an aircraft system
# The controllers are simple not tuned to get desired reference tracking
controllers = [
SaturatedStateSpaceMatricesGS(
A = -1*np.eye(1),
B = np.zeros((1,1)),
C = np.eye(1),
D = np.zeros((1,1)),
upper = 1,
lower = -1,
switch_signal = 0.3
),
SaturatedStateSpaceMatricesGS(
A = -1*np.eye(1),
B = np.zeros((1,1)),
C = np.eye(1),
D = np.zeros((1,1)),
upper = 1,
lower = -1,
switch_signal = 0.6
)
]
# Using similar controllers for simplicity
lat_gs_controller = init_gs_controller(controllers, Direction.LATERAL, 'icing')
lon_gs_controller = init_gs_controller(controllers, Direction.LONGITUDINAL, 'icing')
airspeed_pi_controller = init_airspeed_controller()
control_input = ControlInput()
control_input.throttle = 0.5
state = State()
state.vx = 20
prop = IcedSkywalkerX8Properties(control_input)
aircraft_model = build_nonlin_sys(prop, no_wind(), outputs=State.names+['icing', 'airspeed'])
motor_time_constant = 0.001
elevon_time_constant = 0.001
actuator_model = build_flying_wing_actuator_system(elevon_time_constant, motor_time_constant)
closed_loop = build_closed_loop(actuator_model, aircraft_model, lon_gs_controller, lat_gs_controller, airspeed_pi_controller)
X0 = get_init_vector(closed_loop, control_input, state)
constant_input = np.array([20, 0.04, -0.00033310605950459315])
sim_time = 15
t = np.linspace(0, sim_time, sim_time*5, endpoint=True)
u = np.array([constant_input, ]*(len(t))).transpose()
T, yout_non_lin, _ = input_output_response(
closed_loop, U=u, T=t, X0=X0, return_x=True, method='BDF')
def test_dynamics_forces():
control_input = ControlInput()
prop = SimpleTestAircraftNoMoments(control_input)
t = 0
for i in range(-50, 101, 50):
control_input.throttle = 0.8
control_input.elevator_deflection = i
control_input.aileron_deflection = i
control_input.rudder_deflection = i
state = State()
state.vx = 20.0
state.vy = 1
state.vz = 0
params = {"prop": prop, "wind": no_wind()}
update = dynamics_kinetmatics_update(t=t,
x=state.state,
u=control_input.control_input,
params=params)
V_a = np.sqrt(np.sum(calc_airspeed(state, params['wind'].get(0.0))**2))
forces_aero_wind_frame = np.array([
-np.abs(control_input.elevator_deflection),
control_input.aileron_deflection, -control_input.rudder_deflection
])
forces_aero_body_frame = wind2body(forces_aero_wind_frame, state,
params['wind'].get(0))
force_propulsion = np.array([(2 * control_input.throttle)**2 - V_a**2,
0, 0])
force_gravity = inertial2body(
np.array([0, 0, prop.mass() * GRAVITY_CONST]), state)
forces_body = forces_aero_body_frame + force_propulsion + force_gravity
vx_update_expect = (1 / prop.mass()) * forces_body[0]
vy_update_expect = (1 / prop.mass()) * forces_body[1]
vz_update_expect = (1 / prop.mass()) * forces_body[2]
# No moments
ang_rate_x_update_expect = 0
ang_rate_y_update_expect = 0
ang_rate_z_update_expect = 0
assert np.allclose(vx_update_expect, update[6])
assert np.allclose(vy_update_expect, update[7])
assert np.allclose(vz_update_expect, update[8])
assert np.allclose(ang_rate_x_update_expect, update[9])
assert np.allclose(ang_rate_y_update_expect, update[10])
assert np.allclose(ang_rate_z_update_expect, update[11])
def test_dynamics_moments():
control_input = ControlInput()
t = 0
for i in range(-50, 51, 50):
control_input.throttle = i
control_input.elevator_deflection = i
control_input.aileron_deflection = i
control_input.rudder_deflection = i
prop = SimpleTestAircraftNoForces(control_input)
state = State()
state.vx = 20.0
state.vy = 1
state.vz = 0
state.ang_rate_x = 0.157079633
state.ang_rate_y = 0.157079633
state.ang_rate_z = 0.157079633
params = {"prop": prop, "wind": no_wind()}
update = dynamics_kinetmatics_update(t=t,
x=state.state,
u=control_input.control_input,
params=params)
moments_aero = np.array([
control_input.elevator_deflection,
control_input.aileron_deflection, control_input.rudder_deflection
])
omega = np.array(
[state.ang_rate_x, state.ang_rate_y, state.ang_rate_z])
coreolis_term = prop.inv_inertia_matrix().dot(
np.cross(omega,
prop.inertia_matrix().dot(omega)))
ang_rate_x_update_expect = (2 / 3) * moments_aero[0] - (
1 / 3) * moments_aero[2] - coreolis_term[0]
ang_rate_y_update_expect = (1 / 2) * moments_aero[1] - coreolis_term[1]
ang_rate_z_update_expect = (2 / 3) * moments_aero[2] - (
1 / 3) * moments_aero[0] - coreolis_term[2]
assert np.allclose(ang_rate_x_update_expect, update[9])
assert np.allclose(ang_rate_y_update_expect, update[10])
assert np.allclose(ang_rate_z_update_expect, update[11])
def linearize_system(infile: str) -> str:
with open(infile) as f:
data = load(f)
aircraft = aircraft_property_from_dct(data['aircraft'])
ctrl = ControlInput.from_dict(data['init_control'])
state = State.from_dict(data['init_state'])
config_dict = {
"outputs": [
"x", "y", "z", "roll", "pitch", "yaw", "vx", "vy", "vz",
"ang_rate_x", "ang_rate_y", "ang_rate_z"
]
}
sys = build_nonlin_sys(aircraft, no_wind(), config_dict['outputs'], None)
actuator = actuator_from_dct(data['actuator'])
xeq = state.state
ueq = ctrl.control_input
aircraft_with_actuator = add_actuator(actuator, sys)
states_lin = np.concatenate((ueq, xeq))
linearized_sys = aircraft_with_actuator.linearize(states_lin, ueq)
A, B, C, D = ssdata(linearized_sys)
linsys = StateSpaceMatrices(A, B, C, D)
return linsys
def test_kinematics():
control_input = ControlInput()
prop = FrictionlessBall(control_input)
outputs = [
"x", "y", "z", "roll", "pitch", "yaw", "vx", "vy", "vz", "ang_rate_x",
"ang_rate_y", "ang_rate_z"
]
system = build_nonlin_sys(prop, no_wind(), outputs)
t = np.linspace(0.0, 10, 500, endpoint=True)
state = State()
state.vx = 20.0
state.vy = 1
for i in range(3):
state.roll = 0
state.pitch = 0
state.yaw = 0
if i == 0:
state.ang_rate_x = 0.157079633
state.ang_rate_y = 0
state.ang_rate_z = 0
elif i == 1:
state.ang_rate_x = 0
state.ang_rate_y = 0.157079633
state.ang_rate_z = 0
elif i == 2:
state.ang_rate_x = 0
state.ang_rate_y = 0
state.ang_rate_z = 0.157079633
T, yout = input_output_response(system, t, U=0, X0=state.state)
pos = np.array(yout[:3])
eul_ang = np.array(yout[3:6])
vel_inertial = np.array(
[np.zeros(len(t)),
np.zeros(len(t)),
np.zeros(len(t))])
for j in range(len(vel_inertial[0])):
state.roll = yout[3, j]
state.pitch = yout[4, j]
state.yaw = yout[5, j]
vel = np.array([yout[6, j], yout[7, j], yout[8, j]])
vel_inertial_elem = body2inertial(vel, state)
vel_inertial[0, j] = vel_inertial_elem[0]
vel_inertial[1, j] = vel_inertial_elem[1]
vel_inertial[2, j] = vel_inertial_elem[2]
vx_inertial_expect = 20 * np.ones(len(t))
vy_inertial_expect = 1 * np.ones(len(t))
vz_inertial_expect = GRAVITY_CONST * t
x_expect = 20 * t
y_expect = 1 * t
z_expect = 0.5 * GRAVITY_CONST * t**2
roll_expect = state.ang_rate_x * t
pitch_expect = state.ang_rate_y * t
yaw_expect = state.ang_rate_z * t
assert np.allclose(vx_inertial_expect, vel_inertial[0], atol=7e-3)
assert np.allclose(vy_inertial_expect, vel_inertial[1], atol=5e-3)
assert np.allclose(vz_inertial_expect, vel_inertial[2], atol=8e-3)
assert np.allclose(x_expect, pos[0], atol=8e-2)
assert np.allclose(y_expect, pos[1], atol=5e-2)
assert np.allclose(z_expect, pos[2], atol=7e-2)
assert np.allclose(roll_expect, eul_ang[0], atol=1e-3)
assert np.allclose(pitch_expect, eul_ang[1], atol=1e-3)
assert np.allclose(yaw_expect, eul_ang[2], atol=1e-3)
def main():
# Script showing how to simulate icedskywalkerX8 from config_file using controllers saved in file
config_file = "examples/skywalkerX8_linearize.yml"
lat_controller_file = "examples/inner_loop_controllers/single_robust_roll_ctrl.json"
lon_controller_file = "examples/inner_loop_controllers/single_robust_pitch_ctrl.json"
K_lat = get_state_space_from_file(lat_controller_file)
K_lon = get_state_space_from_file(lon_controller_file)
K_lat = SaturatedStateSpaceController(A=np.array(K_lat.A),
B=np.array(K_lat.B),
C=np.array(K_lat.C),
D=np.array(K_lat.D),
lower=-0.4,
upper=0.4)
K_lon = SaturatedStateSpaceController(A=np.array(K_lon.A),
B=np.array(K_lon.B),
C=np.array(K_lon.C),
D=np.array(K_lon.D),
lower=-0.4,
upper=0.4)
# Using similar controllers for simplicity
lat_controller = init_robust_controller(K_lat, Direction.LATERAL)
lon_controller = init_robust_controller(K_lon, Direction.LONGITUDINAL)
airspeed_pi_controller = init_airspeed_controller()
with open(config_file, 'r') as infile:
data = load(infile)
aircraft = aircraft_property_from_dct(data['aircraft'])
ctrl = ControlInput.from_dict(data['init_control'])
state = State.from_dict(data['init_state'])
updates = {
'icing': [PropUpdate(0.5, 0.5),
PropUpdate(5.0, 1.0)],
}
updater = PropertyUpdater(updates)
aircraft_model = build_nonlin_sys(aircraft,
no_wind(),
outputs=State.names +
['icing', 'airspeed'],
prop_updater=updater)
actuator = actuator_from_dct(data['actuator'])
closed_loop = build_closed_loop(actuator, aircraft_model, lon_controller,
lat_controller, airspeed_pi_controller)
X0 = get_init_vector(closed_loop, ctrl, state)
constant_input = np.array([20, 0.2, -0.2])
sim_time = 15
t = np.linspace(0, sim_time, sim_time * 5, endpoint=True)
u = np.array([
constant_input,
] * (len(t))).transpose()
T, yout_non_lin, _ = input_output_response(closed_loop,
U=u,
T=t,
X0=X0,
return_x=True,
method='BDF')
plot_respons(T, yout_non_lin)
plt.show()
def test_constant_wind():
wind_model = no_wind()
assert np.allclose(wind_model.get(2.0), np.zeros(6))
wind_model = ConstantWind(np.array([1.0, 2.0, 3.0, 4.0, 5.0, 6.0]))
assert np.allclose(wind_model.get(4.0), wind_model.wind)
def linearize(config: str,
out: str,
template: bool = False,
trim: bool = False):
"""
Linearize the model specified via the config file
"""
if template:
generate_linearize_template()
return
with open(config, 'r') as infile:
data = load(infile)
aircraft = aircraft_property_from_dct(data['aircraft'])
ctrl = ControlInput.from_dict(data['init_control'])
state = State.from_dict(data['init_state'])
iu = [2, 3]
config_dict = {
"outputs": [
"x", "y", "z", "roll", "pitch", "yaw", "vx", "vy", "vz",
"ang_rate_x", "ang_rate_y", "ang_rate_z"
]
}
sys = build_nonlin_sys(aircraft, no_wind(), config_dict['outputs'], None)
idx = [2, 6, 7, 8, 9, 10, 11]
y0 = state.state
iy = [0, 1, 2, 5, 9, 10, 11]
xeq = state.state
ueq = ctrl.control_input
if trim:
print("Finding equillibrium point...")
xeq, ueq = find_eqpt(sys,
state.state,
u0=ctrl.control_input,
idx=idx,
y0=y0,
iy=iy,
iu=iu)
print("Equillibrium point found")
print()
print("Equilibrium state vector")
print(f"x: {xeq[0]: .2e} m, y: {xeq[1]: .2e} m, z: {xeq[2]: .2e} m")
print(
f"roll: {rad2deg(xeq[3]): .1f} deg, pitch: {rad2deg(xeq[4]): .1f} deg"
f", yaw: {rad2deg(xeq[5]): .1f} deg")
print(
f"vx: {xeq[6]: .2e} m/s, vy: {xeq[7]: .2e} m/s, vz: {xeq[8]: .2e} m/s"
)
print(
f"Ang.rates: x: {rad2deg(xeq[9]): .1f} deg/s, y: {rad2deg(xeq[10]): .1f} deg/s"
f", z: {rad2deg(xeq[11]): .1f} deg/s")
print()
print("Equilibrium input control vector")
print(
f"elevator: {rad2deg(ueq[0]): .1f} deg, aileron: {rad2deg(ueq[1]): .1f} deg"
f", rudder: {rad2deg(ueq[2]): .1f} deg, throttle: {ueq[3]: .1f}")
print()
actuator = actuator_from_dct(data['actuator'])
if isinstance(actuator, InputOutputSystem):
aircraft_with_actuator = add_actuator(actuator, sys)
states_lin = np.concatenate((ueq, xeq))
linearized = aircraft_with_actuator.linearize(states_lin, ueq)
else:
linearized = sys.linearize(xeq, ueq)
print("Linearization finished")
A, B, C, D = ssdata(linearized)
print("Found linear state space model on the form")
print()
print(" dx ")
print(" ---- = Ax + Bu")
print(" dt ")
print()
print("With observarion equation")
print()
print("y = Cx + Du")
print()
print("Eigenvalues of A:")
eig = np.linalg.eigvals(A)
print('\n'.join(f'{x:.2e}' for x in eig))
linsys = {
'A': A.tolist(),
'B': B.tolist(),
'C': C.tolist(),
'D': D.tolist(),
'xeq': xeq.tolist(),
'ueq': ueq.tolist()
}
if out is not None:
with open(out, 'w') as outfile:
json.dump(linsys, outfile, indent=2, sort_keys=True)
print(f"Linear model written to {out}")