def setup(self, **kwargs):
self.wns = WingNoStruct()
self.wb = WingBox(self.wns, "wing")
Wwing = Variable('W_{wing}', 'N', 'Wing System Weight')
Cwing = Variable('C_{wing}', 1, '-', 'Wing Weight Margin and Sensitivity Factor')
# w.r.t. the quarter chord of the root of the wing.
dxACwing = Variable('\\Delta x_{AC_{wing}}','m','Wing Aerodynamic Center Shift')
#wing induced drag reduction due to wing tip devices
TipReduct = Variable('TipReduct', '-', 'Induced Drag Reduction Factor from Wing Tip Devices')
constraints = []
with SignomialsEnabled():
constraints.extend([
self.wns['\\lambda'] == self.wb['taper'],
TCS([Wwing >= Cwing * self.wb['W_{struct}'] + self.wb['W_{struct}']*(self.wns['f_{flap}'] + \
self.wns['f_{slat}'] + self.wns['f_{aileron}'] + self.wns['f_{lete}'] + self.wns['f_{ribs}'] + \
self.wns['f_{spoiler}'] + self.wns['f_{watt}'])]),
TCS([dxACwing <= 1./24.*(self.wns['c_{root}'] + 5.*self.wns['c_{tip}'])/self.wns['S'] \
*self.wns['b']**2*self.wns['\\tan(\\Lambda)']]),
])
return self.wns, self.wb, constraints
def setup(self):
self.HTns = HorizontalTailNoStruct()
self.wb = WingBox(self.HTns, "horizontal_tail")
#HT system weight variable
Wht = Variable('W_{ht}', 'N', 'HT System Weight')
fht = Variable('f_{ht}' ,'-', 'Rudder etc. fractional weight')
#margin and sensitivity
Cht = Variable('C_{ht}', 1, '-', 'HT Weight Margin and Sensitivity Factor')
#variables only used for the TASOPT tail drag formulation
cdfh = Variable('c_{d_{fh}}', '-', 'VT friction drag coefficient')
cdph = Variable('c_{d_{ph}}', '-', 'VT pressure drag coefficient')
coslamcube = Variable('\\cos(\\Lambda_{ht})^3', '-', 'Cosine of tail sweep cubed')
constraints = []
with SignomialsEnabled():
constraints.append([
self.wb['L_{ht_{rect}}'] >= self.HTns['L_{ht_{max}}']/2.*self.HTns['c_{tip_{ht}}']*self.HTns['b_{ht}']/self.HTns['S_{ht}'],
self.wb['L_{ht_{tri}}'] >= self.HTns['L_{ht_{max}}']/4.*(1-self.wb['taper'])*self.HTns['c_{root_{ht}}']*self.HTns['b_{ht}']/self.HTns['S_{ht}'], #[SP]
Wht >= Cht*(self.wb['W_{struct}'] + self.wb['W_{struct}'] * fht),
])
return self.HTns, self.wb, constraints
def setup(self, **kwargs):
self.vtns = VerticalTailNoStruct()
self.wb = WingBox(self.vtns, "vertical_tail")
#total weight variables
Wvt = Variable('W_{vt}', 'N', 'Total VT System Weight')
fVT = Variable('f_{VT}', '-', 'VT Fractional Weight')
#Margin and Sensitivity
CVT = Variable('C_{VT}', 1, '-', 'VT Weight Margin and Sensitivity')
#variables only used for the TASOPT tail drag formulation
cdfv = Variable('c_{d_{fv}}', '-', 'VT friction drag coefficient')
cdpv = Variable('c_{d_{pv}}', '-', 'VT pressure drag coefficient')
coslamcube = Variable('\\cos(\\Lambda_{vt})^3', '-',
'Cosine of tail sweep cubed')
numspar = Variable(
'N_{spar}', '-',
'Number of Spars in Each VT Carrying Stress in 1 in 20 Case')
constraints = [
self.vtns['\\lambda_{vt}'] == self.wb['taper'],
Wvt >= numspar * CVT *
(self.wb['W_{struct}'] + self.wb['W_{struct}'] * fVT),
]
return self.vtns, self.wb, constraints
