Aircraft

mauspaf.masslibrary.aircraft.fuselage_torenbeek(mf=None, vd=None, lt=None, bf=None, hf=None, sg=None, kcomp=None, composite=None, units={'bf': 'm', 'hf': 'm', 'kcomp': None, 'lt': 'm', 'mf': 'kg', 'sg': 'm²', 'vd': 'm/s'}, calc_mode='values')

Returns the estimated fuselage mass by Torenbeek.

Parameters:

mf (float) – Fuselage mass.
vd (float) – Design dive speed.
lt (float) – Defined length (not the total length of the fuselage).
bf (float) – Fuselage width.
hf (float) – Fuselage height.
sg (float) – Gross shell area.
kcomp (float) – Factor for correction in case of composite material.
composite (boolean) – ‘False’: no composite. ‘True’: composite.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_air_conditioning_anti_ice_nicolai(mach=None, mav=None, mdg=None, nocc=None, mac=None, units={'mac': 'kg', 'mach': None, 'mav': 'kg', 'mdg': 'kg', 'nocc': None}, calc_mode='values')

Returns all air conditioning and anti-icing properties for any given set of inputs using Nicolai’s GA air conditioning and anti-icing mass estimating function.

Parameters:

mav (float) – installed avionics mass.
mdg (float) – Design gross mass.
mach (float) – machach number.
nocc (float) – number of occupants.
mac (float) – Ac and anti-icing mass.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_air_conditioning_anti_ice_raymer(mach=None, mav=None, mdg=None, nocc=None, mac=None, units={'mac': 'kg', 'mach': None, 'mav': 'kg', 'mdg': 'kg', 'nocc': None}, calc_mode='values')

Returns all air conditioning and anti-icing properties for any given set of inputs using Raymer’s GA air conditioning and anti-icing mass estimating function.

Parameters:

mav (float) – installed avionics mass.
mdg (float) – Design gross mass.
mach (float) – machach number.
nocc (float) – number of occupants.
mac (float) – Ac and anti-icing mass.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_avionics_system_nicolai(muav=None, mav=None, units={'mav': 'kg', 'muav': 'kg'}, calc_mode='values')

Returns all avionics system properties for any given set of inputs using Nicolai’s GA avionics system mass estimating function.

Parameters:

muav (float) – uninstalled avionics mass.
mav (float) – installed avionics mass.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_avionics_system_raymer(muav=None, mav=None, units={'mav': 'kg', 'muav': 'kg'}, calc_mode='values')

Returns all avionics system properties for any given set of inputs using Raymer’s GA avionics system mass estimating function.

Parameters:

muav (float) – uninstalled avionics mass.
mav (float) – installed avionics mass.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_electrical_system_nicolai(mav=None, mfsy=None, mel=None, units={'mav': 'kg', 'mel': 'kg', 'mfsy': 'kg'}, calc_mode='values')

Returns all electrical system properties for any given set of inputs using Nicolai’s GA electrical system mass estimating function.

Parameters:

mav (float) – installed avionics mass.
mfsy (float) – flight control system mass.
mel (float) – electrical system mass.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_electrical_system_raymer(mav=None, mfsy=None, mel=None, units={'mav': 'kg', 'mel': 'kg', 'mfsy': 'kg'}, calc_mode='values')

Returns all electrical system properties for any given set of inputs using Raymer’s GA electrical system mass estimating function.

Parameters:

mav (float) – installed avionics mass.
mfsy (float) – flight control system mass.
mel (float) – electrical system mass.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_flight_control_system_nicolai(mdg=None, mctrl=None, ctrlsys='manual', units={'mctrl': 'kg', 'mdg': 'kg'}, calc_mode='values')

Returns all flight control system properties for any given set of inputs using Nicolai’s GA flight control system mass estimating function.

Parameters:

mdg (float) – Design gross mass.
mctrl (float) – flight control system mass.
ctrlsys (float) – ‘powered’ for powered control systems, ‘manual’ for manual control systems.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_flight_control_system_raymer(b=None, lfs=None, mdg=None, nz=None, mctrl=None, units={'b': 'm', 'lfs': 'm', 'mctrl': 'kg', 'mdg': 'kg', 'nz': None}, calc_mode='values')

Returns all flight control system properties for any given set of inputs using Raymer’s GA flight control system mass estimating function.

Parameters:

mdg (float) – Design gross mass.
nz (float) – Ultimate load factor.
b (float) – wing span.
lfs (float) – lenght of fuselage structure.
mctrl (float) – flight control system mass.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_fuel_system_nicolai(neng=None, ntank=None, qint=None, qtot=None, mfsy=None, units={'mfsy': 'kg', 'neng': None, 'ntank': None, 'qint': 'm³', 'qtot': 'm³'}, calc_mode='values')

Returns all fuel system properties for any given set of inputs using Nicolai’s GA fuel system mass estimating function.

Parameters:

mfsy (float) – fuel system mass.
qtot (float) – total fuel quantity.
qint (float) – fuel quantity in integral fuel tanks.
ntank (float) – number of fuel tanks.
neng (float) – number of engines.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_fuel_system_raymer(neng=None, ntank=None, qint=None, qtot=None, mfsy=None, units={'mfsy': 'kg', 'neng': None, 'ntank': None, 'qint': 'm³', 'qtot': 'm³'}, calc_mode='values')

Returns all fuel system properties for any given set of inputs using Raymer’s GA fuel system mass estimating function.

Parameters:

mfsy (float) – fuel system mass.
qtot (float) – total fuel quantity.
qint (float) – fuel quantity in integral fuel tanks.
ntank (float) – number of fuel tanks.
neng (float) – number of engines.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_furnishings_nicolai(ncrew=None, qh=None, mfurn=None, units={'mfurn': 'kg', 'ncrew': None, 'qh': 'Pa'}, calc_mode='values')

Returns all furnishings properties for any given set of inputs using Nicolai’s GA furnishings mass estimating function.

Parameters:

mfurn (float) – furnishings mass.
ncrew (float) – number of crew.
qh (float) – dynamic pressure at max level airspeed
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_furnishings_raymer(mdg=None, mfurn=None, units={'mdg': 'kg', 'mfurn': 'kg'}, calc_mode='values')

Returns all furnishings properties for any given set of inputs using: Raymer’s GA furnishings mass estimating function.

Parameters:

mdg (float) – Design gross mass.
mfurn (float) – furnishings mass.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_fuselage_nicolai(df=None, lf=None, mdg=None, nz=None, vh=None, wf=None, mfs=None, units={'df': 'm', 'lf': 'm', 'mdg': 'kg', 'mfs': 'kg', 'nz': None, 'vh': 'm/s', 'wf': 'm'}, calc_mode='values')

Returns all fuselage properties for any given set of inputs using Nicolai’s GA fuselage mass estimating function.

Parameters:

mdg (float) – Design gross mass.
nz (float) – Ultimate load factor.
lf (float) – Fuselage lenght.
mfs (float) – Fuselage mass.
wf (float) – Fuselage max width.
df (float) – Fuselage max depth.
vh (float) – Maximum level airspeed.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_fuselage_raymer(dp=None, dfs=None, lfs=None, lht=None, mdg=None, nz=None, s=None, qc=None, vp=None, mfs=None, units={'dfs': 'm', 'dp': 'Pa', 'lfs': 'm', 'lht': 'm', 'mdg': 'kg', 'mfs': 'kg', 'nz': None, 'qc': 'Pa', 's': 'm²', 'vp': 'm³'}, calc_mode='values')

Returns all fuselage properties for any given set of inputs using Raymer’s GA fuselage mass estimating function.

Parameters:

mdg (float) – Design gross mass.
nz (float) – Ultimate load factor.
s (float) – fuselage wetted area.
mfs (float) – fuselage mass.
lht (float) – horizontal tail arm, from C/4 to HT C/4.
lfs (float) – lenght of fuselage structure.
dfs (float) – depth of fuselage structure.
qc (float) – Dynamic pressure in cruise.
vp (float) – Volume of pressurized cabin section.
dp (float) – cabin pressure differential.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_horizontal_tail_nicolai(bht=None, lht=None, mdg=None, nz=None, s=None, tht=None, mht=None, units={'bht': 'm', 'lht': 'm', 'mdg': 'kg', 'mht': 'kg', 'nz': None, 's': 'm²', 'tht': 'm'}, calc_mode='values')

Returns all horizontal tail properties for any given set of inputs using Nicolai’s GA horizontal tail mass estimating function.

Parameters:

mdg (float) – Design gross mass.
nz (float) – Ultimate load factor.
s (float) – Surface area.
mht (float) – horizontal tail mass.
lht (float) – horizontal tail arm, from C/4 to HT C/4
bht (float) – HT span
tht (float) – max root chorf thickness
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_horizontal_tail_raymer(ar=None, mdg=None, nz=None, phi=None, qc=None, s=None, tc=None, tr=None, mht=None, units={'ar': None, 'mdg': 'kg', 'mht': 'kg', 'nz': None, 'phi': 'rad', 's': 'm²', 'tc': None, 'tr': None}, calc_mode='values')

Returns all horizontal tail properties for any given set of inputs using Raymer’s GA horizontal tail mass estimating function

Parameters:

ar (float) – Aspect ratio.
mdg (float) – Design gross mass.
nz (float) – Ultimate load factor.
phi (float) – horizontal tail sweep at 25% MAC.
s (float) – Surface area.
tc (float) – Thickness to chord ratio.
tr (float) – Taper ratio.
mht (float) – horizontal tail mass.
qc (float) – Dynamic pressure in cruise.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_hydraulic_system_raymer(mdg=None, mhyd=None, units={'mdg': 'kg', 'mhyd': 'kg'}, calc_mode='values')

Returns all hydraulic system properties for any given set of inputs using Raymer’s GA hydraulic system mass estimating function.

Parameters:

mdg (float) – Design gross mass.
mhyd (float) – hydraulic system mass.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_installed_engine_nicolai(meng=None, neng=None, mei=None, units={'mei': 'kg', 'meng': 'kg', 'neng': None}, calc_mode='values')

Returns all installed engine properties for any given set of inputs using Nicolai’s GA installed engine mass estimating function.

Parameters:

mei (float) – installed engine mass.
meng (float) – uninstalled engine mass.
neng (float) – number of engines.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_installed_engine_raymer(meng=None, neng=None, mei=None, units={'mei': 'kg', 'meng': 'kg', 'neng': None}, calc_mode='values')

Returns all installed engine properties for any given set of inputs using Raymer’s GA installed engine mass estimating function.

Parameters:

mei (float) – installed engine mass.
meng (float) – uninstalled engine mass.
neng (float) – number of engines.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_main_landing_gear_nicolai(lm=None, ml=None, nl=None, mmnlg=None, units={'lm': 'm', 'ml': 'kg', 'mmnlg': 'kg', 'nl': None}, calc_mode='values')

Returns all main landing gear properties for any given set of input using Nicolai’s GA entire landing gear mass estimating function.

Parameters:

ml (float) – Design landing weight.
nl (float) – Ultimate landing load factor.
lm (float) – Lenght of main landing gear structure.
mmnlg (float) – entire landing gear mass.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_main_landing_gear_raymer(lm=None, ml=None, nl=None, mlg=None, units={'lm': 'm', 'ml': 'kg', 'mlg': 'kg', 'nl': None}, calc_mode='values')

Returns all main landing gear properties for any given set of inputs using Raymer’s GA main landing gear mass estimating function.

Parameters:

ml (float) – Design landing weight.
nl (float) – Ultimate landing load factor.
lm (float) – Lenght of main landing gear structure.
mlg (float) – main landing gear mass.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_nose_landing_gear_raymer(l_n=None, ml=None, nl=None, mnlg=None, units={'l_n': 'm', 'ml': 'kg', 'mnlg': 'kg', 'nl': None}, calc_mode='values')

Returns all nose landing gear properties for any given set of inputs using Raymer’s GA nose landing gear mass estimating function.

Parameters:

ml (float) – Design landing weight.
nl (float) – Ultimate landing load factor.
ln (float) – Lenght of nose landing gear structure.
mnlg (float) – nose landing gear mass.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_vertical_tail_nicolai(bvt=None, mdg=None, nz=None, s=None, tvt=None, mvt=None, units={'bvt': 'm', 'mdg': 'kg', 'mvt': 'kg', 'nz': None, 's': 'm²', 'tvt': 'm'}, calc_mode='values')

Returns all vertical tail properties for any given set of inputs using Nicolai’s GA vertical tail mass estimating function.

Parameters:

mdg (float) – Design gross mass.
nz (float) – Ultimate load factor.
s (float) – Surface area.
mvt (float) – vertical tail mass.
bvt (float) – Vertical tail span.
tvt (float) – max root chord thickness.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_vertical_tail_raymer(ar=None, F=None, mdg=None, nz=None, phi=None, qc=None, s=None, tc=None, tr=None, mvt=None, units={'F': None, 'ar': None, 'mdg': 'kg', 'mvt': 'kg', 'nz': None, 'phi': 'rad', 'qc': 'Pa', 's': 'm²', 'tc': None, 'tr': None}, calc_mode='values')

Returns all vertical tail properties for any given set of inputs using Raymer’s GA vertical tail mass estimating function.

Parameters:

ar (float) – Vertical tail aspect ratio
mdg (float) – Design gross mass.
nz (float) – Ultimate load factor.
s (float) – Surface area.
mvt (float) – vertical tail mass.
tc (float) – Thickness to chord ratio.
tr (float) – Taper ratio.
qc (float) – Dynamic pressure in cruise.
phi (float) – vertical tail sweep at 25% MAC.
F (float) – 0 for conventional tail, 1 fot T-tail.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_wing_nicolai(ar=None, mdg=None, nz=None, phi=None, s=None, tc=None, tr=None, vh=None, mw=None, units={'ar': None, 'mdg': 'kg', 'mw': 'kg', 'nz': None, 'phi': 'rad', 's': 'm²', 'tc': None, 'tr': None, 'vh': 'm/s'}, calc_mode='values')

Returns all wing properties for any given set of inputs using: Nicolai’s GA wing mass estimating function.

Parameters:

ar (float) – Aspect ratio.
mdg (float) – Design gross mass.
nz (float) – Ultimate load factor.
phi (float) – Wing sweep at 25% MAC.
s (float) – Surface area.
tc (float) – Thickness to chord ratio.
tr (float) – Taper ratio.
mw (float) – Wing mass.
vh (float) – maximum level airspeed
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.ga_wing_raymer(ar=None, mdg=None, mf=None, nz=None, phi=None, qc=None, s=None, tc=None, tr=None, mw=None, units={'ar': None, 'mdg': 'kg', 'mf': 'kg', 'mw': 'kg', 'nz': None, 'phi': 'rad', 'qc': 'Pa', 's': 'm²', 'tc': None, 'tr': None}, calc_mode='values')

Returns all wing properties for any given set of inputs using: Raymer’s GA wing mass estimating function.

Parameters:

ar (float) – Aspect ratio.
mdg (float) – Design gross mass.
mf (float) – Mass of fuel in wing.
nz (float) – Ultimate load factor.
phi (float) – Wing sweep at 25% MAC.
qc (float) – Dynamic pressure in cruise.
s (float) – Surface area.
tc (float) – Thickness to chord ratio.
tr (float) – Taper ratio.
mw (float) – Wing mass.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.landing_gear_torenbeek(mlg=None, mtow=None, a=None, b=None, c=None, d=None, conf=None, kcomp=None, composite=None, units={'a': None, 'b': None, 'c': None, 'd': None, 'kcomp': None, 'mlg': 'kg', 'mtow': 'kg'}, calc_mode='values')

Returns the estimated landing gear weight by Torenbeek.

Parameters:

mlg (float) – Landing gear mass.
mtow (float) – Maximum take-off weight.
a (float) – Factor given in a table.
b (float) – Factor given in a table.
c (float) – Factor given in a table.
d (float) – Factor given in a table.
conf (float) – ‘low’ for low-wing configuration. ‘high’ for high-wing configuration.
kcomp (float) – Factor for correction in case of composite material.
composite (boolean) – ‘False’: no composite. ‘True’: composite.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.structural_mass_torenbeek(ms=None, mtow=None, ks=None, nult=None, bf=None, hf=None, lf=None, kcomp=None, composite=None, units={'bf': 'm', 'hf': 'm', 'kcomp': None, 'lf': 'm', 'ms': 'kg', 'mtow': 'kg', 'nult': None}, calc_mode='values')

Returns the structural weight of an aircraft according to Torenbeek.

Parameters:

ms (float) – Structural weight.
mtow (float) – Maximum take-off weight.
nult (float) – Ultimate load factor.
bf (float) – Fuselage width.
hf (float) – Fuselage heigth.
lf (float) – Fuselage length.
kcomp (float) – Factor for correction in case of composite material.
composite (boolean) – ‘False’: no composite. ‘True’: composite.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.surface_controls_torenbeek(msc=None, mtow=None, ksc=None, kcomp=None, composite=None, units={'kcomp': None, 'ksc': None, 'msc': 'kg', 'mtow': 'kg'}, calc_mode='values')

Returns estimated weight of the surface controls by Torenbeek.

Parameters:

msc (float) – Surface controls mass.
mtow (float) – Maximum take-off weight.
ksc (float) – Factor.
kcomp (float) – Factor for correction in case of composite material.
composite (boolean) – ‘False’: no composite. ‘True’: composite.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.tailplane_mass_torenbeek(mtail=None, nult=None, stail=None, kcomp=None, composite=None, units={'kcomp': None, 'mtail': 'kg', 'nult': None, 'stail': 'm²'}, calc_mode='values')

Tailplane mass estimation according to Torenbeek.

Parameters:

mtail (float) – Tailplane mass.
nult (float) – Ultimate load factor.
stail (float) – Surface area.
kcomp (float) – Factor for correction in case of composite material.
composite (boolean) – ‘False’: no composite. ‘True’: composite.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.wing_mass_howe(mwing=None, mc=None, mr=None, ar=None, s=None, tr=None, phi=None, tc=None, theta=None, fa=None, m0=None, n=None, r=None, mzw=None, ni=None, conf=None, composite=False, kcomp=None, units={'ar': None, 'fa': 'MPa', 'kcomp': None, 'm0': None, 'mc': 'kg', 'mr': 'kg', 'mwing': 'kg', 'mzw': 'kg', 'n': None, 'ni': None, 'phi': 'rad', 'r': None, 's': 'm²', 'tc': None, 'theta': 'rad', 'tr': None}, calc_mode='values')

Returns the mass of a wing based on the formula by Howe.

Parameters:

mwing (float) – Wing mass.
mc (float) – Structural box covers mass.
mr (float) – Spanwise shear webs mass.
ar (float) – Aspect ratio.
s (float) – Wing area.
tr (float) – Taper ratio.
phi (float) – Quarter chord sweep.
tc (float) – Thickness to chord ratio.
theta (float) – Sweep of the structure.
fa (float) – Allowable working stress of the material.
m0 (float) – Take-off mass of the aircraft.
n (float) – Ultimate design factor.
r (float) – Factor which allows inertial relief dependant on wing confuiguration.
conf (float) – ‘1’ for no wing-mounted powerplant or stores. ‘2’ for two wing-mounted powerplants. ‘3’ for four wing-mounted powerplants.
mzw (float) – Design zero fuel mass.
ni (float) – Manoeuvre factor.
kcomp (float) – Factor for correction in case of composite material.
composite (boolean) – ‘False’: no composite. ‘True’: composite.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.

mauspaf.masslibrary.aircraft.wing_mass_torenbeek(mw=None, mtow=None, kw=None, bs=None, b=None, nult=None, tr=None, s=None, ar=None, phi=None, kcomp=None, composite=None, units={'b': 'm', 'bs': 'm', 'kcomp': None, 'kw': None, 'mtow': 'kg', 'mw': 'kg', 'nult': None, 'phi': 'rad', 's': 'm²', 'tr': 'm'}, calc_mode='values')

Wing mass estimation according to Torenbeek.

Parameters:

mw (float) – Wing mass.
mtow (float) – Maximum take-off weight.
kw (float) – Factor.
bs (float) – Structural wing span.
b (float) – Wing span.
nult (float) – Ultimate load factor.
tr (float) – Maximum root thickness.
s (float) – Surface area.
ar (float) – Aspect ratio.
phi (float) – Half chord sweep angle (structural sweep angle).
kcomp (float) – Factor for correction in case of composite material.
composite (boolean) – ‘False’: no composite. ‘True’: composite.
units (dict) – Dictionary with units of every variable. Default value is all SI-units.
calc_mode (str) – Calculation mode. Either ‘values’ (to calculate missing numerical values) or ‘sets’ (to calculate valid input sets of variables). Default value is ‘values’.