/
wing_skin.py
56 lines (47 loc) · 1.92 KB
/
wing_skin.py
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" wing skin "
from gpkit import Model, Variable, parse_variables
class WingSkin(Model):
""" Wing Skin model
Variables
---------
rhocfrp 1.6 [g/cm^3] density of CFRP
W [lbf] wing skin weight
g 9.81 [m/s^2] gravitational acceleration
t [in] wing skin thickness
tmin 0.012 [in] wing skin min gauge
Jtbar 0.01114 [1/mm] torsional moment of inertia
taucfrp 570 [MPa] torsional stress limit
Cmw 0.121 [-] negative wing moment coeff
rhosl 1.225 [kg/m^3] sea level air density
Vne 45 [m/s] never exceed vehicle speed
Upper Unbounded
---------------
W
LaTex Strings
-------------
W W_{\\mathrm{skin}}
t t_{\\mathrm{skin}}
tmin t_{\\mathrm{min}}
Jtbar \\bar{J/t}
taucfrp \\tau_{\\mathrm{CFRP}}
Cmw C_{m_w}
rhosl \\rho_{\\mathrm{SL}}
Vne V_{\\mathrm{NE}}
"""
def setup(self, surface):
exec parse_variables(WingSkin.__doc__)
self.loading = WingSkinL
return [W >= rhocfrp*surface.S*2*t*g,
t >= tmin,
taucfrp >= (1/Jtbar/surface.croot**2/t*Cmw
* surface.S*rhosl*Vne**2)
]
class WingSkinL(Model):
"wing skin loading model for torsional loads in skin"
def setup(self, static):
taucfrp = Variable("\\tau_{CFRP}", 570, "MPa", "torsional stress limit")
Cmw = Variable("C_{m_w}", 0.121, "-", "negative wing moment coefficent")
rhosl = Variable("\\rho_{sl}", 1.225, "kg/m^3",
"air density at sea level")
Vne = Variable("V_{NE}", 45, "m/s", "never exceed vehicle speed")
return []