def test_easy():
b_modes = 3
t_modes = 3
model_num = 1
p = rw.base_params(b_modes + t_modes + 1)
sm = mf.SymbolicModel.from_file(f'tests/{b_modes}B{t_modes}T-M{model_num}.py')
# Set HALE Specific parameters
p.rho.value = 0.0889
p.s_t.value = 16
p.c.value = 1
p.EI.value = 2e4
p.GJ.value = 1e4
p.rho_t.value = 0.75
p.e_0.value = 0.25
p.e_1.value = 0
# set Parameter permutations
vars_ls =[]
#vars_ls.append((p.m_factor,[0.5,1,1.5]))
#vars_ls.append((p.Lambda,np.deg2rad([10,17.5,25])))
#vars_ls.append((p.alpha_r,np.deg2rad([0,5,10])))
#vars_ls.append((p.ratio_fwt,[0,0.1,0.2,0.3]))
#vars_ls.append((p.V,np.linspace(0,200,201))) # ensure velocity last so that fixed points iterats up the velocity
vars_ls.append((p.m_factor,[1]))
vars_ls.append((p.Lambda,np.deg2rad([10])))
vars_ls.append((p.alpha_r,np.deg2rad([0,5,10])))
vars_ls.append((p.ratio_fwt,[0,0.1,0.2,0.3]))
vars_ls.append((p.V,np.linspace(0,40,80))) # ensure velocity last so that fixed points iterats up the velocity
# generate result
res = rw.eigen_perm_params(p,sm,vars_ls,np.isin(model_num,[1,2,3,4]))
assert (3==3)
def Model_Eigen(model_num, b_modes, t_modes):
print(f'Genrating data for model {model_num}')
try:
p = JEC()
dataset_name = 'JEC'
sm = mf.SymbolicModel.from_file(
f'{b_modes}B{t_modes}T-M{model_num}.py')
vars_ls = []
vars_ls.append((p.Lambda, np.deg2rad([10, 17.5, 25])))
#vars_ls.append((p.V,np.linspace(0,40,81))) # V must be second
vars_ls.append((p.V, np.linspace(0, 150, 151))) # V must be second
vars_ls.append((p.alpha_r, np.deg2rad([0, 5, 10])))
vars_ls.append((p.c_dmax, [0, 0.5, 1, 1.5]))
#vars_ls.append((p.ratio_fwt,[0,0.1,0.2,0.3]))
#vars_ls.append((p.ratio_DL,[0,0.05,0.1,0.2]))
vars_ls.append((p.m_factor, [0.5, 1, 1.5]))
calc_fixed = True if np.isin(model_num, np.array([1, 2, 3, 4, 5
])) else False
flutdf = rw.eigen_perm_params(p, sm, vars_ls, calc_fixed, jac=False)
flutdf.to_pickle(
f'Eigen_{b_modes}B{t_modes}T-M{model_num}_{dataset_name}.pkl')
print(f'Genrated data for model {model_num}')
except:
print(f'Model {model_num} exited with an error')
def JEC2():
p = rw.base_params(b_modes + t_modes + 1)
p.rho.value = 1.225
p.s_t.value = 1.345
p.c.value = 0.15
p.EI.value = 61
p.GJ.value = 200
p.rho_t.value = 10
p.e_0.value = 0
p.e_1.value = 0
p.ratio_fwt.value = 0.2
p.alpha_s.value = np.deg2rad(15)
return p
def HALE():
p = rw.base_params(b_modes + t_modes + 1)
p.rho.value = 0.0889
p.s_t.value = 16
p.c.value = 1
p.EI.value = 2e4
p.GJ.value = 1e4
p.rho_t.value = 0.75
p.e_0.value = 0.25
p.e_1.value = 0
p.ratio_fwt.value = 0.2
p.alpha_s.value = np.deg2rad(15)
return p
def JEC():
p = rw.base_params(b_modes + t_modes + 1)
p.rho.value = 1.225
p.s_t.value = 12
p.c.value = 1.8
p.EI.value = 9.77e6
p.GJ.value = 0.99e6
p.rho_t.value = 19.53
p.e_0.value = 0.08
p.e_1.value = 0
p.ratio_fwt.value = 0.2
p.alpha_s.value = np.deg2rad(15)
return p
def GenV2RectWing(b_modes,
t_modes,
aero_model_class,
iwt=True,
iwb=True,
fwt_Iyy=True):
p = rw.base_params(b_modes + t_modes + 2)
#get shape functions for main wing
z_0, tau_0 = ma.ShapeFunctions_BN_TM(b_modes,
t_modes,
p.q[1:-1],
p.y_0,
p.x_0,
p.x_f0,
0,
factor=p.eta)
wing_bend = sym.atan(z_0.diff(p.y_0).subs({p.x_0: p.x_f0, p.y_0: p.s_0}))
#define wrefernce frames
wing_root_frame = ma.HomogenousTransform().Translate(0, 0,
p.q[0]).R_y(p.alpha_r)
wing_frame = wing_root_frame.Translate(p.x_0, p.y_0, z_0)
wing_flexural_frame = wing_frame.msubs({p.x_0: p.x_f0})
fwt_root_frame = wing_frame.msubs({
p.y_0: p.s_0,
p.x_0: p.x_f0
}).Translate(-p.x_f0, 0, 0).R_x(-p.q[-1])
fwt_flexural_frame = fwt_root_frame.Translate(p.x_f1, p.y_1, 0)
fwt_com_frame = fwt_root_frame.Translate(p.c / 2, p.s_1 / 2, 0)
#Create Element Mass Matriceis
M_wing = ele.MassMatrix(p.rho_t)
I_yy = 0
I_yy += sym.Rational(1, 2) * p.m_1 * p.c + p.m_1 * (p.c / 2)**2
M_fwt = ele.MassMatrix(p.m_1, I_xx=p.I_xx_1, I_yy=I_yy)
#Create Elements
inner_wing_ele = ele.FlexiElement(wing_root_frame,
M_wing,
p.x_0,
p.y_0,
z_0,
p.c,
p.s_0,
p.x_f0,
p.EI,
p.GJ,
gravityPot=True)
fwt_ele = ele.RigidElement(fwt_com_frame, M_fwt, True)
fwt_spring_ele = ele.Spring(p.q[-1] + wing_bend, p.k_fwt)
ac_ele = ele.RigidElement.PointMass(wing_root_frame,
p.m_ac,
gravityPotential=False)
ac_spring_ele = ele.Spring(p.q[0], p.k_ac)
# Create Inner Wing Aero Forces
wing_AeroForces = ef.AeroForce_1.PerUnitSpan(
p,
wing_flexural_frame,
p.a_0,
alphadot=tau_0 if isinstance(tau_0, int) else tau_0.diff(t),
M_thetadot=p.M_thetadot,
e=p.e_0,
rootAlpha=p.alpha_r,
deltaAlpha=tau_0,
alpha_zero=0,
w_g=p.w_g,
V=p.V * sym.cos(p.yaw)).integrate((p.y_0, 0, p.s_0))
#Create FWT Aero Forces
alpha_fwt = p.alpha_1
alphadot_fwt = p.alphadot_1
if not aero_model_class.rot:
fwt_AeroForces_perUnit = ef.AeroForce_1.PerUnitSpan(
p,
fwt_flexural_frame,
p.a_1,
alphadot=p.alphadot_1,
M_thetadot=p.M_thetadot,
e=p.e_1,
rootAlpha=p.alpha_1,
deltaAlpha=0,
alpha_zero=(p.y_1 / p.s_1) * p.tau_1,
#alpha_zero = 0,
w_g=sym.cos(p.alpha_1) * sym.cos(p.q[-1]) * p.w_g,
V=p.V * sym.cos(p.yaw))
else:
fwt_AeroForces_perUnit = ef.AeroForce_4.PerUnitSpan(
p,
fwt_flexural_frame,
p.a_1,
alphadot=p.alphadot_1,
M_thetadot=p.M_thetadot,
e=p.e_1,
rootAlpha=p.alpha_1,
alpha_zero=(p.y_1 / p.s_1) * p.tau_1,
#alpha_zero = 0,
stall_angle=0 if not aero_model_class.stall else p.alpha_s,
c_d_max=0 if not aero_model_class.drag else p.c_dmax,
w_g=sym.cos(p.alpha_1) * sym.cos(p.q[-1]) * p.w_g,
V=p.V * sym.cos(p.yaw))
#calcualte aero force on 5 discrete segments along the length of the fwt
forces = []
segments = 5
for i in range(segments):
seg_width = p.s_1 / segments
yi = seg_width / 2 + i * seg_width
forces.append(fwt_AeroForces_perUnit.subs({p.y_1: yi}) * seg_width)
Q = sym.Matrix([0] * p.qs)
for f in forces:
Q += f.Q()
fwt_AeroForces = ef.ExternalForce(Q)
# Setup AoA of FWT to sub into generated equations
if aero_model_class.aoa_model == AoAModel.GEM:
fwt_aoa = ma.GetAoA(p.alpha_r, p.yaw, p.Lambda, p.q[-1])
elif aero_model_class.aoa_model == AoAModel.SAM:
fwt_aoa = sym.atan(sym.sin(p.q[-1]) *
sym.sin(p.Lambda)) + p.alpha_r * sym.cos(p.q[-1])
elif aero_model_class.aoa_model == AoAModel.LIN:
fwt_aoa = (sym.atan(sym.tan(p.q[-1]) * sym.sin(p.Lambda)) +
p.alpha_r) * sym.cos(p.q[-1])
# augment fwt_aoa as required due to the shape of the inner wing
if iwb:
fwt_aoa = me.msubs(fwt_aoa, {p.q[-1]: p.q[-1] - wing_bend})
if iwt:
tau_s0 = tau_0.subs(p.y_0, p.s_0)
fwt_aoa = me.msubs(fwt_aoa, {p.alpha_r: p.alpha_r + tau_s0})
## Sub in Aero Forces
fwt_AeroForces = fwt_AeroForces.subs({
p.alpha_1: fwt_aoa,
p.alphadot_1: fwt_aoa.diff(t)
})
#Create Composite force
CompositeForce = ef.CompositeForce([wing_AeroForces, fwt_AeroForces])
# Create the SYmbolic Model
sm = ma.SymbolicModel.FromElementsAndForces(
p, [ac_ele, inner_wing_ele, fwt_ele, fwt_spring_ele, ac_spring_ele],
CompositeForce)
return sm, p
def Gen2DofModel(fwt_free, fwt_frot, rot_AoA=True):
p = rw.base_params(2)
#define wrefernce frames
if rot_AoA:
fwt_root_frame = ma.HomogenousTransform().Translate(0, 0, p.q[0]).R_y(
p.alpha_r).R_x(-p.q[-1])
else:
fwt_root_frame = ma.HomogenousTransform().Translate(
0, 0, p.q[0]).R_x(-p.q[-1])
fwt_flexural_frame = fwt_root_frame.Translate(p.x_f1, p.y_1, 0)
fwt_com_frame = fwt_root_frame.Translate(p.c / 2, p.s_1 / 2, 0)
#Create Elemnts
M_fwt = ele.MassMatrix(p.m_1, I_xx=p.I_xx_1)
fwt_ele = ele.RigidElement(fwt_com_frame, M_fwt, True)
spring_ele = ele.Spring(p.q[0], p.EI)
alpha_fwt = 0
alphadot_fwt = 0
if fwt_free:
alpha_fwt += p.alpha_1
alphadot_fwt += p.alphadot_1
if fwt_frot:
fwt_AeroForces_perUnit = ef.AeroForce_2.PerUnitSpan(
p,
fwt_flexural_frame,
p.a_1,
alphadot=p.alphadot_1,
M_thetadot=p.M_thetadot,
e=p.e_1,
rootAlpha=p.alpha_1,
alpha_zero=0)
else:
fwt_AeroForces_perUnit = ef.AeroForce_1.PerUnitSpan(
p,
fwt_flexural_frame,
p.a_1,
alphadot=p.alphadot_1,
M_thetadot=p.M_thetadot,
e=p.e_1,
rootAlpha=p.alpha_1,
deltaAlpha=0,
alpha_zero=0)
forces = []
segments = 5
for i in range(segments):
seg_width = p.s_1 / segments
yi = seg_width / 2 + i * seg_width
forces.append(fwt_AeroForces_perUnit.subs({p.y_1: yi}) * seg_width)
Q = sym.Matrix([0] * p.qs)
for f in forces:
Q += f.Q()
fwt_AeroForces = ef.ExternalForce(Q)
# Setup AoA of FWT
fwt_aoa = ma.GetAoA(p.alpha_r, 0, p.Lambda, 0 if not fwt_free else p.q[-1])
## Sub in Aero Forces
fwt_AeroForces = fwt_AeroForces.subs({
p.alpha_1: fwt_aoa,
p.alphadot_1: fwt_aoa.diff(t)
})
# Create the SYmbolic Model
sm = ma.SymbolicModel.FromElementsAndForces(p, [fwt_ele, spring_ele],
fwt_AeroForces)
return sm, p
def GenRectWingModel(b_modes,
t_modes,
fwt_free,
iwt,
iwb,
fwt_Iyy=False,
fwt_ke_simp=False,
aero_model=AeroModel.LiftOnly):
p = rw.base_params(b_modes + t_modes + 1)
#get shape functions for main wing
z_0, tau_0 = ma.ShapeFunctions_BN_TM(b_modes,
t_modes,
p.q[:-1],
p.y_0,
p.x_0,
p.x_f0,
0,
factor=p.eta)
#define wrefernce frames
wing_root_frame = ma.HomogenousTransform().R_y(p.alpha_r)
wing_frame = wing_root_frame.Translate(p.x_0, p.y_0, z_0)
wing_flexural_frame = wing_frame.msubs({p.x_0: p.x_f0})
fwt_root_frame = wing_frame.msubs({
p.y_0: p.s_0,
p.x_0: p.x_f0
}).Translate(-p.x_f0, 0, 0)
if fwt_free:
fwt_root_frame = fwt_root_frame.R_x(-p.q[-1])
fwt_flexural_frame = fwt_root_frame.Translate(p.x_f1, p.y_1, 0)
fwt_com_frame = fwt_root_frame.Translate(p.c / 2, p.s_1 / 2, 0)
#Create Elemnts
M_wing = ele.MassMatrix(p.rho_t)
inner_wing_ele = ele.FlexiElement(wing_root_frame,
M_wing,
p.x_0,
p.y_0,
z_0,
p.c,
p.s_0,
p.x_f0,
p.EI,
p.GJ,
gravityPot=True)
I_yy = 0
if fwt_Iyy:
I_yy += sym.Rational(1, 2) * p.m_1 * p.c + p.m_1 * (p.c / 2)**2
if fwt_ke_simp:
M_fwt = ele.MassMatrix(p.m_1,
I_xx=p.I_xx_1 + p.m_1 * (p.s_1 / 2)**2,
I_yy=I_yy)
fwt_ele = ele.RigidElement(fwt_root_frame,
M_fwt,
True,
com_pos=[0, p.s_1 / 2, 0])
else:
M_fwt = ele.MassMatrix(p.m_1, I_xx=p.I_xx_1, I_yy=I_yy)
fwt_ele = ele.RigidElement(fwt_com_frame, M_fwt, True)
# Create AeroForces
wing_AeroForces = ef.AeroForce_1.PerUnitSpan(
p,
wing_flexural_frame,
p.a_0,
alphadot=tau_0 if isinstance(tau_0, int) else tau_0.diff(t),
M_thetadot=p.M_thetadot,
e=p.e_0,
rootAlpha=p.alpha_r,
deltaAlpha=tau_0,
alpha_zero=0).integrate((p.y_0, 0, p.s_0))
alpha_fwt = 0
alphadot_fwt = 0
if fwt_free:
alpha_fwt += p.alpha_1
alphadot_fwt += p.alphadot_1
if aero_model == AeroModel.LiftOnly:
fwt_AeroForces_perUnit = ef.AeroForce_1.PerUnitSpan(
p,
fwt_flexural_frame,
p.a_1,
alphadot=p.alphadot_1,
M_thetadot=p.M_thetadot,
e=p.e_1,
rootAlpha=p.alpha_1,
deltaAlpha=0,
alpha_zero=0)
elif aero_model == AeroModel.LiftOnly_rot:
fwt_AeroForces_perUnit = ef.AeroForce_2.PerUnitSpan(
p,
fwt_flexural_frame,
p.a_1,
alphadot=p.alphadot_1,
M_thetadot=p.M_thetadot,
e=p.e_1,
rootAlpha=p.alpha_1,
alpha_zero=0,
include_drag=False)
else:
fwt_AeroForces_perUnit = ef.AeroForce_3.PerUnitSpan(
p,
fwt_flexural_frame,
p.a_1,
alphadot=p.alphadot_1,
M_thetadot=p.M_thetadot,
e=p.e_1,
rootAlpha=p.alpha_1,
alpha_zero=0,
stall_angle=p.alpha_s,
c_d_max=p.c_dmax)
forces = []
segments = 5
for i in range(segments):
seg_width = p.s_1 / segments
yi = seg_width / 2 + i * seg_width
forces.append(fwt_AeroForces_perUnit.subs({p.y_1: yi}) * seg_width)
Q = sym.Matrix([0] * p.qs)
for f in forces:
Q += f.Q()
fwt_AeroForces = ef.ExternalForce(Q)
# Setup AoA of FWT
fwt_aoa = ma.GetAoA(p.alpha_r, 0, p.Lambda, 0 if not fwt_free else p.q[-1])
if iwb:
wing_bend = sym.atan(
z_0.diff(p.y_0).subs({
p.x_0: p.x_f0,
p.y_0: p.s_0
}))
fwt_aoa = me.msubs(fwt_aoa, {p.q[-1]: p.q[-1] - wing_bend})
if iwt:
tau_s0 = tau_0.subs(p.y_0, p.s_0)
fwt_aoa = me.msubs(fwt_aoa, {p.alpha_r: p.alpha_r + tau_s0})
## Sub in Aero Forces
fwt_AeroForces = fwt_AeroForces.subs({
p.alpha_1: fwt_aoa,
p.alphadot_1: fwt_aoa.diff(t)
})
#Create Composite force
CompositeForce = ef.CompositeForce([wing_AeroForces, fwt_AeroForces])
# Create the SYmbolic Model
sm = ma.SymbolicModel.FromElementsAndForces(p, [inner_wing_ele, fwt_ele],
CompositeForce)
return sm, p