def test_rotation_about_axis(self):
"""
Tests the rotations about the cartesian axes
"""
i = np.array([1, 0, 0])
j = np.array([0, 1, 0])
k = np.array([0, 0, 1])
angle = 90 * np.pi / 180
# Testing rotations about the x axis - rotation3d_x
out = algebra.rotation3d_x(angle).dot(j)
for ax in range(3):
self.assertAlmostEqual(out[ax], k[ax])
out = algebra.rotation3d_x(angle).dot(k)
for ax in range(3):
self.assertAlmostEqual(out[ax], -j[ax])
# Testing rotations about the y axis - rotation3d_y
out = algebra.rotation3d_y(angle).dot(i)
for ax in range(3):
self.assertAlmostEqual(out[ax], -k[ax])
out = algebra.rotation3d_y(angle).dot(k)
for ax in range(3):
self.assertAlmostEqual(out[ax], i[ax])
# Testing rotations about the z axis - rotation3d_z
out = algebra.rotation3d_z(angle).dot(i)
for ax in range(3):
self.assertAlmostEqual(out[ax], j[ax])
out = algebra.rotation3d_z(angle).dot(j)
for ax in range(3):
self.assertAlmostEqual(out[ax], -i[ax])
def generate_strip(node_info,
airfoil_db,
aligned_grid,
orientation_in=np.array([1, 0, 0]),
calculate_zeta_dot=False):
"""
Returns a strip of panels in ``A`` frame of reference, it has to be then rotated to
simulate angles of attack, etc
"""
strip_coordinates_a_frame = np.zeros((3, node_info['M'] + 1),
dtype=ct.c_double)
strip_coordinates_b_frame = np.zeros((3, node_info['M'] + 1),
dtype=ct.c_double)
zeta_dot_a_frame = np.zeros((3, node_info['M'] + 1), dtype=ct.c_double)
# airfoil coordinates
# we are going to store everything in the x-z plane of the b
# FoR, so that the transformation Cab rotates everything in place.
if node_info['M_distribution'] == 'uniform':
strip_coordinates_b_frame[1, :] = np.linspace(0.0, 1.0,
node_info['M'] + 1)
elif node_info['M_distribution'] == '1-cos':
domain = np.linspace(0, 1.0, node_info['M'] + 1)
strip_coordinates_b_frame[1, :] = 0.5 * (1.0 - np.cos(domain * np.pi))
elif node_info['M_distribution'].lower() == 'user_defined':
# strip_coordinates_b_frame[1, :-1] = np.linspace(0.0, 1.0 - node_info['last_panel_length'], node_info['M'])
# strip_coordinates_b_frame[1,-1] = 1.
strip_coordinates_b_frame[
1, :] = node_info['user_defined_m_distribution']
else:
raise NotImplemented('M_distribution is ' +
node_info['M_distribution'] +
' and it is not yet supported')
strip_coordinates_b_frame[2, :] = airfoil_db[node_info['airfoil']](
strip_coordinates_b_frame[1, :])
# elastic axis correction
for i_M in range(node_info['M'] + 1):
strip_coordinates_b_frame[1, i_M] -= node_info['eaxis']
# chord_line_b_frame = strip_coordinates_b_frame[:, -1] - strip_coordinates_b_frame[:, 0]
cs_velocity = np.zeros_like(strip_coordinates_b_frame)
# control surface deflection
if node_info['control_surface'] is not None:
b_frame_hinge_coords = strip_coordinates_b_frame[:, node_info[
'M'] - node_info['control_surface']['chord']]
# support for different hinge location for fully articulated control surfaces
if node_info['control_surface']['hinge_coords'] is not None:
# make sure the hinge coordinates are only applied when M == cs_chord
if not node_info['M'] - node_info['control_surface']['chord'] == 0:
node_info['control_surface']['hinge_coords'] = None
else:
b_frame_hinge_coords = node_info['control_surface'][
'hinge_coords']
for i_M in range(
node_info['M'] - node_info['control_surface']['chord'],
node_info['M'] + 1):
relative_coords = strip_coordinates_b_frame[:,
i_M] - b_frame_hinge_coords
# rotate the control surface
relative_coords = np.dot(
algebra.rotation3d_x(
-node_info['control_surface']['deflection']),
relative_coords)
# deflection velocity
try:
cs_velocity[:, i_M] += np.cross(
np.array([
-node_info['control_surface']['deflection_dot'], 0.0,
0.0
]), relative_coords)
except KeyError:
pass
# restore coordinates
relative_coords += b_frame_hinge_coords
# substitute with new coordinates
strip_coordinates_b_frame[:, i_M] = relative_coords
# chord scaling
strip_coordinates_b_frame *= node_info['chord']
# twist transformation (rotation around x_b axis)
if np.abs(node_info['twist']) > 1e-6:
Ctwist = algebra.rotation3d_x(node_info['twist'])
else:
Ctwist = np.eye(3)
# Cab transformation
Cab = algebra.crv2rotation(node_info['beam_psi'])
rot_angle = algebra.angle_between_vectors_sign(orientation_in, Cab[:, 1],
Cab[:, 2])
if np.sign(np.dot(orientation_in, Cab[:, 1])) >= 0:
rot_angle += 0.0
else:
rot_angle += -2 * np.pi
Crot = algebra.rotation3d_z(-rot_angle)
c_sweep = np.eye(3)
if np.abs(node_info['sweep']) > 1e-6:
c_sweep = algebra.rotation3d_z(node_info['sweep'])
# transformation from beam to beam prime (with sweep and twist)
for i_M in range(node_info['M'] + 1):
strip_coordinates_b_frame[:, i_M] = np.dot(
c_sweep,
np.dot(Crot, np.dot(Ctwist, strip_coordinates_b_frame[:, i_M])))
strip_coordinates_a_frame[:, i_M] = np.dot(
Cab, strip_coordinates_b_frame[:, i_M])
cs_velocity[:, i_M] = np.dot(Cab, cs_velocity[:, i_M])
# zeta_dot
if calculate_zeta_dot:
# velocity due to pos_dot
for i_M in range(node_info['M'] + 1):
zeta_dot_a_frame[:, i_M] += node_info['pos_dot']
# velocity due to psi_dot
omega_a = algebra.crv_dot2omega(node_info['beam_psi'],
node_info['psi_dot'])
for i_M in range(node_info['M'] + 1):
zeta_dot_a_frame[:,
i_M] += (np.dot(algebra.skew(omega_a),
strip_coordinates_a_frame[:,
i_M]))
# control surface deflection velocity contribution
try:
if node_info['control_surface'] is not None:
node_info['control_surface']['deflection_dot']
for i_M in range(node_info['M'] + 1):
zeta_dot_a_frame[:, i_M] += cs_velocity[:, i_M]
except KeyError:
pass
else:
zeta_dot_a_frame = np.zeros((3, node_info['M'] + 1), dtype=ct.c_double)
# add node coords
for i_M in range(node_info['M'] + 1):
strip_coordinates_a_frame[:, i_M] += node_info['beam_coord']
# add quarter-chord disp
delta_c = (strip_coordinates_a_frame[:, -1] -
strip_coordinates_a_frame[:, 0]) / node_info['M']
if node_info['M_distribution'] == 'uniform':
for i_M in range(node_info['M'] + 1):
strip_coordinates_a_frame[:, i_M] += 0.25 * delta_c
else:
warnings.warn(
"No quarter chord disp of grid for non-uniform grid distributions implemented",
UserWarning)
# rotation from a to g
for i_M in range(node_info['M'] + 1):
strip_coordinates_a_frame[:, i_M] = np.dot(
node_info['cga'], strip_coordinates_a_frame[:, i_M])
zeta_dot_a_frame[:, i_M] = np.dot(node_info['cga'],
zeta_dot_a_frame[:, i_M])
return strip_coordinates_a_frame, zeta_dot_a_frame
def generate_strip(node_info,
airfoil_db,
aligned_grid,
orientation_in=np.array([1, 0, 0])):
"""
Returns a strip in "a" frame of reference, it has to be then rotated to
simulate angles of attack, etc
:param node_info:
:param airfoil_db:
:param aligned_grid:
:param orientation_in:
:return:
"""
strip_coordinates_a_frame = np.zeros((3, node_info['M'] + 1),
dtype=ct.c_double)
strip_coordinates_b_frame = np.zeros((3, node_info['M'] + 1),
dtype=ct.c_double)
# airfoil coordinates
# we are going to store everything in the x-z plane of the b
# FoR, so that the transformation Cab rotates everything in place.
if node_info['M_distribution'] == 'uniform':
strip_coordinates_b_frame[1, :] = np.linspace(0.0, 1.0,
node_info['M'] + 1)
elif node_info['M_distribution'] == '1-cos':
domain = np.linspace(0, 1.0, node_info['M'] + 1)
strip_coordinates_b_frame[1, :] = 0.5 * (1.0 - np.cos(domain * np.pi))
else:
raise NotImplemented('M_distribution is ' +
node_info['M_distribution'] +
' and it is not yet supported')
strip_coordinates_b_frame[2, :] = airfoil_db[node_info['airfoil']](
strip_coordinates_b_frame[1, :])
# elastic axis correction
for i_M in range(node_info['M'] + 1):
strip_coordinates_b_frame[1, i_M] -= node_info['eaxis']
# chord scaling
strip_coordinates_b_frame *= node_info['chord']
# twist transformation (rotation around x_b axis)
if np.abs(node_info['twist']) > 1e-6:
Ctwist = algebra.rotation3d_x(node_info['twist'])
else:
Ctwist = np.eye(3)
# Cab transformation
Cab = algebra.crv2rot(node_info['beam_psi'])
# sweep angle correction
# angle between orientation_in and chord line
chord_line_b_frame = strip_coordinates_b_frame[:,
-1] - strip_coordinates_b_frame[:,
0]
chord_line_a_frame = np.dot(Cab, chord_line_b_frame)
sweep_angle = algebra.angle_between_vectors_sign(orientation_in,
chord_line_a_frame,
np.array([0, 0, 1]))
# rotation matrix
Csweep = algebra.rotation3d_z(-sweep_angle)
# transformation from beam to aero
for i_M in range(node_info['M'] + 1):
strip_coordinates_a_frame[:, i_M] = np.dot(
Cab,
np.dot(Csweep, np.dot(Ctwist, strip_coordinates_b_frame[:, i_M])))
# add node coords
for i_M in range(node_info['M'] + 1):
strip_coordinates_a_frame[:, i_M] += node_info['beam_coord']
return strip_coordinates_a_frame
def generate_strip(node_info, airfoil_db, aligned_grid, orientation_in=np.array([1, 0, 0]), calculate_zeta_dot = False):
"""
Returns a strip in "a" frame of reference, it has to be then rotated to
simulate angles of attack, etc
:param node_info:
:param airfoil_db:
:param aligned_grid:
:param orientation_in:
:return:
"""
strip_coordinates_a_frame = np.zeros((3, node_info['M'] + 1), dtype=ct.c_double)
strip_coordinates_b_frame = np.zeros((3, node_info['M'] + 1), dtype=ct.c_double)
# airfoil coordinates
# we are going to store everything in the x-z plane of the b
# FoR, so that the transformation Cab rotates everything in place.
if node_info['M_distribution'] == 'uniform':
strip_coordinates_b_frame[1, :] = np.linspace(0.0, 1.0, node_info['M'] + 1)
elif node_info['M_distribution'] == '1-cos':
domain = np.linspace(0, 1.0, node_info['M'] + 1)
strip_coordinates_b_frame[1, :] = 0.5*(1.0 - np.cos(domain*np.pi))
else:
raise NotImplemented('M_distribution is ' + node_info['M_distribution'] +
' and it is not yet supported')
strip_coordinates_b_frame[2, :] = airfoil_db[node_info['airfoil']](
strip_coordinates_b_frame[1, :])
# elastic axis correction
for i_M in range(node_info['M'] + 1):
strip_coordinates_b_frame[1, i_M] -= node_info['eaxis']
chord_line_b_frame = strip_coordinates_b_frame[:, -1] - strip_coordinates_b_frame[:, 0]
# control surface deflection
if node_info['control_surface'] is not None:
b_frame_hinge_coords = strip_coordinates_b_frame[:, node_info['M'] - node_info['control_surface']['chord']]
# support for different hinge location for fully articulated control surfaces
if node_info['control_surface']['hinge_coords'] is not None:
# make sure the hinge coordinates are only applied when M == cs_chord
if not node_info['M'] - node_info['control_surface']['chord'] == 0:
cout.cout_wrap('The hinge coordinates parameter is only supported when M == cs_chord')
node_info['control_surface']['hinge_coords'] = None
else:
b_frame_hinge_coords = node_info['control_surface']['hinge_coords']
for i_M in range(node_info['M'] - node_info['control_surface']['chord'], node_info['M'] + 1):
relative_coords = strip_coordinates_b_frame[:, i_M] - b_frame_hinge_coords
# rotate the control surface
relative_coords = np.dot(algebra.rotation3d_x(-node_info['control_surface']['deflection']),
relative_coords)
# restore coordinates
relative_coords += b_frame_hinge_coords
# substitute with new coordinates
strip_coordinates_b_frame[:, i_M] = relative_coords
# chord scaling
strip_coordinates_b_frame *= node_info['chord']
# twist transformation (rotation around x_b axis)
if np.abs(node_info['twist']) > 1e-6:
Ctwist = algebra.rotation3d_x(node_info['twist'])
else:
Ctwist = np.eye(3)
# Cab transformation
Cab = algebra.crv2rot(node_info['beam_psi'])
rot_angle = algebra.angle_between_vectors_sign(orientation_in, Cab[:, 1], Cab[:, 2])
Crot = algebra.rotation3d_z(-rot_angle)
c_sweep = np.eye(3)
if np.abs(node_info['sweep']) > 1e-6:
c_sweep = algebra.rotation3d_z(node_info['sweep'])
# transformation from beam to beam prime (with sweep and twist)
for i_M in range(node_info['M'] + 1):
strip_coordinates_b_frame[:, i_M] = np.dot(c_sweep, np.dot(Crot,
np.dot(Ctwist, strip_coordinates_b_frame[:, i_M])))
strip_coordinates_a_frame[:, i_M] = np.dot(Cab, strip_coordinates_b_frame[:, i_M])
# zeta_dot
if calculate_zeta_dot:
zeta_dot_a_frame = np.zeros((3, node_info['M'] + 1), dtype=ct.c_double)
# velocity due to pos_dot
for i_M in range(node_info['M'] + 1):
zeta_dot_a_frame[:, i_M] += node_info['pos_dot']
# velocity due to psi_dot
Omega_b = algebra.crv_dot2Omega(node_info['beam_psi'], node_info['psi_dot'])
for i_M in range(node_info['M'] + 1):
zeta_dot_a_frame[:, i_M] += (
np.dot(algebra.skew(Omega_b), strip_coordinates_a_frame[:, i_M]))
else:
zeta_dot_a_frame = np.zeros((3, node_info['M'] + 1), dtype=ct.c_double)
# add node coords
for i_M in range(node_info['M'] + 1):
strip_coordinates_a_frame[:, i_M] += node_info['beam_coord']
# rotation from a to g
for i_M in range(node_info['M'] + 1):
strip_coordinates_a_frame[:, i_M] = np.dot(node_info['cga'],
strip_coordinates_a_frame[:, i_M])
zeta_dot_a_frame[:, i_M] = np.dot(node_info['cga'],
zeta_dot_a_frame[:, i_M])
return strip_coordinates_a_frame, zeta_dot_a_frame