def get_curve(X_lst, Tdays, benchmark):
WingModel = Wing.Wing()
para = benchmark[benchmark['day'] == Tdays]
tmp = WingModel.volatility_curve(
X_lst, Tdays, para.loc[0, 'alpha'], para.loc[0, 'f_atm'],
para.loc[0, 'f_ref'], para.loc[0, 'ssr'], para.loc[0, 'vol_ref'],
para.loc[0, 'vcr'], para.loc[0, 'slope_ref'], para.loc[0, 'scr'],
para.loc[0, 'dn_cf'], para.loc[0, 'up_cf'], para.loc[0, 'put_curv'],
para.loc[0, 'call_curv'], para.loc[0, 'dn_sm'], para.loc[0, 'up_sm'],
para.loc[0, 'dn_slope'], para.loc[0, 'up_slope']) #得到曲线
return tmp
def Activated(self): import Wing from Gui import WingDialog aviableAirfoils = [] for obj in FreeCAD.ActiveDocument.Objects: if(obj.Type == 'Part::FeaturePython'): if(obj.Proxy.__module__ == 'Airfoil'): aviableAirfoils.append(obj.Name) result = WingDialog.WingDialog.showDialog(aviableAirfoils,None) if(result == None): return elif(result == []): return objlist = [] for name in result: FreeCAD.ActiveDocument.getObject(name).ViewObject.Visibility = False objlist.append(FreeCAD.ActiveDocument.getObject(name)) Wing.makeWing(objlist)
def Activated(self):
import Wing
from Gui import WingDialog
aviableAirfoils = []
for obj in FreeCAD.ActiveDocument.Objects:
if (obj.Type == 'Part::FeaturePython'):
if (obj.Proxy.__module__ == 'Airfoil'):
aviableAirfoils.append(obj.Name)
result = WingDialog.WingDialog.showDialog(aviableAirfoils, None)
if (result == None):
return
elif (result == []):
return
objlist = []
for name in result:
FreeCAD.ActiveDocument.getObject(
name).ViewObject.Visibility = False
objlist.append(FreeCAD.ActiveDocument.getObject(name))
Wing.makeWing(objlist)
def Activated(self):
import RibbedWing
from Gui import RibbedWingDialog
wing = 0
sel = Draft.getSelection()
#must be Wing
if (len(sel) == 1):
if (sel[0].Type == 'Part::FeaturePython'):
if (sel[0].Proxy.__module__ == 'Wing'):
RibbedWing.makeRibbedWing(sel[0])
#must be Airfoils
elif (len(sel) > 1):
Airfoils = []
for obj in sel:
if (obj.Type == 'Part::FeaturePython'):
if (obj.Proxy.__module__ == 'Airfoil'):
Airfoils.append(obj.Shape)
if (len(Airfoils) > 1):
import Wing
wing = Wing.makeWing(Airfoils)
RibbedWing.makeRibbedWing(wing)
def Activated(self): import RibbedWing from Gui import RibbedWingDialog wing = 0 sel = Draft.getSelection() #must be Wing if(len(sel)==1): if(sel[0].Type == 'Part::FeaturePython'): if(sel[0].Proxy.__module__ == 'Wing'): RibbedWing.makeRibbedWing(sel[0]) #must be Airfoils elif(len(sel)>1): Airfoils = [] for obj in sel: if(obj.Type == 'Part::FeaturePython'): if(obj.Proxy.__module__ == 'Airfoil'): Airfoils.append(obj.Shape) if(len(Airfoils)>1): import Wing wing = Wing.makeWing(Airfoils) RibbedWing.makeRibbedWing(wing)
def computeloads(z):
Sectioncenters = np.array([])
dLlist = np.array([])
dDlist = np.array([])
L = 0
D = 0
M = 0
L_moment = 0
D_moment = 0
Llist = np.array([])
Dlist = np.array([])
Lmomentlist = np.array([])
Dmomentlist = np.array([])
L_momentlist = np.array([])
zs = b - (sectionlength / 2)
dL = Q_("0 N")
dD = Q_("0 N")
dM = Q_("0 N*m")
while zs > z: #zs is measured is m from
Areaofsection = sectionlength * Wing.length_chord(zs)
Sectioncenters = np.append(Sectioncenters, zs)
'''Lift drag and moment for the section'''
dL = (cl * 0.5 * rho * (V**2) *
Areaofsection).magnitude #lift of the section
dD = (cd * 0.5 * rho * (V**2) *
Areaofsection).magnitude #drag of the section
dM = (cm * 0.5 * rho * (V**2) * Areaofsection *
Wing.length_chord(zs)).magnitude #moment of the section
dL *= Q_('kg * m / s**2')
dD *= Q_('kg * m / s**2')
dM *= Q_('kg * m**2 / s**2')
if zs < Geometry.Fuselage.b_f * 0:
dL = 0
dD = 0
dM = 0
dLlist = np.append(dLlist, dL)
dDlist = np.append(dDlist, dD)
'''Total lift, drag and moment for the wing'''
L = L + dL # Total lift for one wing
D = D + dD # Total drag for one wing
M = M + dM # Total moment for one wing
Llist = np.append(Llist,
L) # put the values in a list so we can plot them
Dlist = np.append(Dlist, D)
zs = zs - sectionlength # Select other section for the next loop
for i in range(0, len(Sectioncenters)):
arm = (Sectioncenters[i] - z.magnitude)
dLmoment = (arm * dLlist[i])
dDmoment = (arm * dDlist[i])
L_moment = L_moment + dLmoment
D_moment = D_moment + dDmoment
Lmomentlist = np.append(Lmomentlist, L_moment)
Dmomentlist = np.append(Dmomentlist, D_moment)
'''For the 20G manoeuver'''
MTOW = Geometry.Masses.W_MTOW
Max_20G_N = MTOW * 9.81 * 20
Tot_L = 2 * totallift
if Tot_L.magnitude > 0.:
fac_20G = Max_20G_N / Tot_L
fac_20G = fac_20G.magnitude
else:
fac_20G = 0
L_moment = L_moment * fac_20G
D_moment = D_moment * fac_20G
L = L * fac_20G
D = D * fac_20G
M = M * fac_20G
return L, D, M, L_moment, D_moment, dL, dD, dM
Lmomentlist = np.array([])
Dmomentlist = np.array([])
dLlist = np.array([])
dDlist = np.array([])
Llist = np.array([])
Dlist = np.array([])
Sectioncenters = np.array([])
sectionlength = (b.magnitude -
0 * Geometry.Fuselage.b_f.magnitude) / n * ureg.meter
zs = b - (sectionlength / 2)
while zs.magnitude > 0: # zs is measured is m from
Areaofsection = sectionlength * Wing.length_chord(zs)
Sectioncenters = np.append(Sectioncenters, zs)
'''Lift drag and moment for the section'''
dL = cl * 0.5 * rho * (V**2) * Areaofsection.magnitude * Q_(
"m**2") # lift of the section
if zs < Geometry.Fuselage.b_f * 0:
dL = Q_('0 kg * m / s**2')
'''Total lift, drag and moment for the wing'''
L = L + dL # Total lift for one wing
zs = zs - sectionlength # Select other section for the next loop
totallift = L
"Wing.createWrapLeadingEdge()", "Wing"))
FreeCADGui.addCommand(
'Wing_LeadingEdge',
_CommandWing("LeadingEdge", "LeadingEdge-icon.svg",
"Wing.createLeadingEdge()", "Wing"))
FreeCADGui.addCommand(
'Wing_CutWire',
_CommandWing("CutWire", "CutWire-icon.svg", "Wing.createCutWire()",
"Wing"))
FreeCADGui.addCommand(
'Wing_Section',
_CommandWing("Section", "Section.svg", "Wing.createSection()", "Wing"))
FreeCADGui.addCommand("WingDialog", WingDialogs.CommandWingDialog())
FreeCADGui.addCommand("SectionsDialog",
WingDialogs.CommandSectionsDialog())
FreeCADGui.addCommand("RecomputeSelection", Wing.CommandRecompute())
class WingWorkbench(Workbench):
'''Wing workbench object'''
Icon = iconPath + 'Aile-icon.svg'
MenuText = "Wing toolkit"
ToolTip = "Create wing and nervures for aeromodels"
def Initialize(self):
"This function is executed when FreeCAD starts"
self.appendToolbar("Wing", [
"Wing_ImportProfil", "Wing_Wing", "Wing_CoordSys", "Wing_Rod",
"Wing_WrapLeadingEdge", 'Wing_LeadingEdge', "Wing_CutWire",
