def test_quadcopter_navigation():
opti = asb.Opti()
N = 300
time_final = 1
time = np.linspace(0, time_final, N)
left_thrust = opti.variable(init_guess=0.5, scale=1, n_vars=N, lower_bound=0, upper_bound=1)
right_thrust = opti.variable(init_guess=0.5, scale=1, n_vars=N, lower_bound=0, upper_bound=1)
mass = 0.1
dyn = asb.FreeBodyDynamics(
opti_to_add_constraints_to=opti,
time=time,
xe=opti.variable(init_guess=np.linspace(0, 1, N)),
ze=opti.variable(init_guess=np.linspace(0, -1, N)),
u=opti.variable(init_guess=0, n_vars=N),
w=opti.variable(init_guess=0, n_vars=N),
theta=opti.variable(init_guess=np.linspace(np.pi / 2, np.pi / 2, N)),
q=opti.variable(init_guess=0, n_vars=N),
X=left_thrust + right_thrust,
M=(right_thrust - left_thrust) * 0.1 / 2,
mass=mass,
Iyy=0.5 * mass * 0.1 ** 2,
g=9.81,
)
opti.subject_to([ # Starting state
dyn.xe[0] == 0,
dyn.ze[0] == 0,
dyn.u[0] == 0,
dyn.w[0] == 0,
dyn.theta[0] == np.radians(90),
dyn.q[0] == 0,
])
opti.subject_to([ # Final state
dyn.xe[-1] == 1,
dyn.ze[-1] == -1,
dyn.u[-1] == 0,
dyn.w[-1] == 0,
dyn.theta[-1] == np.radians(90),
dyn.q[-1] == 0,
])
effort = np.sum( # The average "effort per second", where effort is integrated as follows:
np.trapz(left_thrust ** 2 + right_thrust ** 2) * np.diff(time)
) / time_final
opti.minimize(effort)
sol = opti.solve()
dyn.substitute_solution(sol)
assert sol.value(effort) == pytest.approx(0.714563, rel=0.01)
print(sol.value(effort))
def test_quadcopter_flip():
opti = asb.Opti()
N = 300
time_final = opti.variable(init_guess=1, lower_bound=0)
time = np.linspace(0, time_final, N)
left_thrust = opti.variable(init_guess=0.7, scale=1, n_vars=N, lower_bound=0, upper_bound=1)
right_thrust = opti.variable(init_guess=0.6, scale=1, n_vars=N, lower_bound=0, upper_bound=1)
mass = 0.1
dyn = asb.FreeBodyDynamics(
opti_to_add_constraints_to=opti,
time=time,
xe=opti.variable(init_guess=np.linspace(0, 1, N)),
ze=opti.variable(init_guess=0, n_vars=N),
u=opti.variable(init_guess=0, n_vars=N),
w=opti.variable(init_guess=0, n_vars=N),
theta=opti.variable(init_guess=np.linspace(np.pi / 2, np.pi / 2 - 2 * np.pi, N)),
q=opti.variable(init_guess=0, n_vars=N),
X=left_thrust + right_thrust,
M=(right_thrust - left_thrust) * 0.1 / 2,
mass=mass,
Iyy=0.5 * mass * 0.1 ** 2,
g=9.81,
)
opti.subject_to([ # Starting state
dyn.xe[0] == 0,
dyn.ze[0] == 0,
dyn.u[0] == 0,
dyn.w[0] == 0,
dyn.theta[0] == np.radians(90),
dyn.q[0] == 0,
])
opti.subject_to([ # Final state
dyn.xe[-1] == 1,
dyn.ze[-1] == 0,
dyn.u[-1] == 0,
dyn.w[-1] == 0,
dyn.theta[-1] == np.radians(90 - 360),
dyn.q[-1] == 0,
])
opti.minimize(time_final)
sol = opti.solve(verbose=False)
dyn.substitute_solution(sol)
assert sol.value(time_final) == pytest.approx(0.824, abs=0.01)
def test_airfoil_multielement():
a = asb.AirfoilInviscid(airfoil=[
asb.Airfoil("e423").repanel(n_points_per_side=50),
asb.Airfoil("naca6408").repanel(n_points_per_side=25).scale(
0.4, 0.4).rotate(np.radians(-20)).translate(0.9, -0.05),
],
op_point=asb.OperatingPoint(velocity=1, alpha=5))
def default_CL_function(alpha, Re, mach, deflection):
"""
Lift coefficient.
"""
print_default_warning()
Cl_inc = 2 * np.pi * np.radians(alpha)
beta = (1 - mach)**2
Cl = Cl_inc * beta
return Cl
def compute_rotation_matrix_wind_to_geometry(self) -> np.ndarray:
"""
Computes the 3x3 rotation matrix that transforms from wind axes to geometry axes.
Returns: a 3x3 rotation matrix.
"""
alpha_rotation = np.rotation_matrix_3D(angle=np.radians(self.alpha),
axis=np.array([0, 1, 0]),
_axis_already_normalized=True)
beta_rotation = np.rotation_matrix_3D(angle=np.radians(self.beta),
axis=np.array([0, 0, 1]),
_axis_already_normalized=True)
axes_flip = np.rotation_matrix_3D(
angle=np.pi,
axis=np.array([0, 1, 0]),
_axis_already_normalized=True
) # Since in geometry axes, X is downstream by convention, while in wind axes, X is upstream by convetion. Same with Z being up/down respectively.
r = axes_flip @ alpha_rotation @ beta_rotation # where "@" is the matrix multiplication operator
return r
def scattering_factor(elevation_angle):
"""
Calculates a scattering factor (a factor that gives losses due to atmospheric scattering at low elevation angles).
Source: AeroSandbox/studies/SolarPanelScattering
:param elevation_angle: Angle between the horizon and the sun [degrees]
:return: Fraction of the light that is not lost to scattering.
"""
elevation_angle = np.clip(elevation_angle, 0, 90)
theta = 90 - elevation_angle # Angle between panel normal and the sun, in degrees
# # Model 1
# c = (
# 0.27891510500505767300438719757949,
# -0.015994330894744987481281839336589,
# -19.707332432605799255043166340329,
# -0.66260979582573353852126274432521
# )
# scattering_factor = c[0] + c[3] * theta_rad + cas.exp(
# c[1] * (
# cas.tan(theta_rad) + c[2] * theta_rad
# )
# )
# Model 2
c = (
-0.04636,
-0.3171
)
scattering_factor = np.exp(
c[0] * (
np.tand(theta * 0.999) + c[1] * np.radians(theta)
)
)
# # Model 3
# p1 = -21.74
# p2 = 282.6
# p3 = -1538
# p4 = 1786
# q1 = -923.2
# q2 = 1456
# x = theta_rad
# scattering_factor = ((p1*x**3 + p2*x**2 + p3*x + p4) /
# (x**2 + q1*x + q2))
# Keep this:
# scattering_factor = cas.fmin(cas.fmax(scattering_factor, 0), 1)
return scattering_factor
plt.ylim(-4, 1.1)
plt.gca().invert_yaxis()
plt.xlabel(r"$x/c$")
plt.ylabel(r"$C_p$")
plt.title(r"$C_p$ on Surface")
plt.tight_layout()
if show:
plt.show()
if __name__ == '__main__':
a = AirfoilInviscid(
airfoil=[
# Airfoil("naca4408")
# .repanel(50)
Airfoil("e423").repanel(n_points_per_side=50),
Airfoil("naca6408").repanel(n_points_per_side=25).scale(
0.4, 0.4).rotate(np.radians(-20)).translate(0.9, -0.05),
],
op_point=OperatingPoint(
velocity=1,
alpha=5,
))
a.draw_streamlines()
a.draw_cp()
opti2 = Opti()
b = AirfoilInviscid(airfoil=Airfoil("naca4408"),
op_point=OperatingPoint(velocity=1, alpha=5),
opti=opti2)
def display_graph(n_clicks, alpha, height, streamline_density,
operating_checklist, *kulfan_inputs):
### Figure out if a button was pressed
global n_clicks_last
if n_clicks is None:
n_clicks = 0
analyze_button_pressed = n_clicks > n_clicks_last
n_clicks_last = n_clicks
### Parse the checklist
ground_effect = "ground_effect" in operating_checklist
### Start constructing the figure
airfoil = asb.Airfoil(coordinates=asb.get_kulfan_coordinates(
lower_weights=np.array(kulfan_inputs[n_kulfan_inputs_per_side:]),
upper_weights=np.array(kulfan_inputs[:n_kulfan_inputs_per_side]),
TE_thickness=0,
enforce_continuous_LE_radius=False,
n_points_per_side=200,
))
### Do coordinates output
coordinates_output = "\n".join(
["```"] + ["AeroSandbox Airfoil"] +
["\t%f\t%f" % tuple(coordinate)
for coordinate in airfoil.coordinates] + ["```"])
### Continue doing the airfoil things
airfoil = airfoil.rotate(angle=-np.radians(alpha))
airfoil = airfoil.translate(0, height + 0.5 * np.sind(alpha))
fig = go.Figure()
fig.add_trace(
go.Scatter(
x=airfoil.x(),
y=airfoil.y(),
mode="lines",
name="Airfoil",
fill="toself",
line=dict(color="blue"),
))
### Default text output
text_output = 'Click "Analyze" to compute aerodynamics!'
xrng = (-0.5, 1.5)
yrng = (-0.6, 0.6) if not ground_effect else (0, 1.2)
if analyze_button_pressed:
analysis = asb.AirfoilInviscid(
airfoil=airfoil.repanel(50),
op_point=asb.OperatingPoint(
velocity=1,
alpha=0,
),
ground_effect=ground_effect,
)
x = np.linspace(*xrng, 100)
y = np.linspace(*yrng, 100)
X, Y = np.meshgrid(x, y)
u, v = analysis.calculate_velocity(x_field=X.flatten(),
y_field=Y.flatten())
U = u.reshape(X.shape)
V = v.reshape(Y.shape)
streamline_fig = ff.create_streamline(
x,
y,
U,
V,
arrow_scale=1e-16,
density=streamline_density,
line=dict(color="#ff82a3"),
name="Streamlines",
)
fig = go.Figure(data=streamline_fig.data + fig.data)
text_output = make_table(
pd.DataFrame({
"Engineering Quantity": ["C_L"],
"Value": [f"{analysis.Cl:.3f}"]
}))
fig.update_layout(
xaxis_title="x/c",
yaxis_title="y/c",
showlegend=False,
yaxis=dict(scaleanchor="x", scaleratio=1),
margin={"t": 0},
title=None,
)
fig.update_xaxes(range=xrng)
fig.update_yaxes(range=yrng)
return fig, text_output, [coordinates_output]
plt.tight_layout()
if show:
plt.show()
if __name__ == '__main__':
a = AirfoilInviscid(
airfoil=[
# Airfoil("naca4408")
# .repanel(50)
Airfoil("e423")
.repanel(n_points_per_side=50),
Airfoil("naca6408")
.repanel(n_points_per_side=25)
.scale(0.4, 0.4)
.rotate(np.radians(-20))
.translate(0.9, -0.05),
],
op_point=OperatingPoint(
velocity=1,
alpha=5,
)
)
a.draw_streamlines()
a.draw_cp()
opti2 = Opti()
b = AirfoilInviscid(
airfoil=Airfoil("naca4408"),
op_point=OperatingPoint(
velocity=1,
def CL_function(alpha, Re, mach, deflection):
return 2 * np.pi * np.radians(alpha)
