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SUAVE
2.5.2
An Aerospace Vehicle Environment for Designing Future Aircraft
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SUAVE
2.5.2
An Aerospace Vehicle Environment for Designing Future Aircraft
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Provides structural weight correlations for a human-powered aircraft; applicable to solar-UAVs. More...
Functions | |
| def | SUAVE.Methods.Weights.Correlations.Human_Powered.empty.empty (vehicle, settings=None) |
| def | SUAVE.Methods.Weights.Correlations.Human_Powered.fuselage.fuselage (Sts, qm, Ltb) |
| fuselage.py More... | |
| def | SUAVE.Methods.Weights.Correlations.Human_Powered.tail.tail (Sts, bts, cts, Ntsr, t_cts, qm) |
| tail.py More... | |
| def | SUAVE.Methods.Weights.Correlations.Human_Powered.wing.wing (Sw, bw, cw, Nwr, t_cw, Nwer, nult, GW) |
| wing.py More... | |
Provides structural weight correlations for a human-powered aircraft; applicable to solar-UAVs.
| def SUAVE.Methods.Weights.Correlations.Human_Powered.empty.empty | ( | vehicle, | |
settings = None |
|||
| ) |
Computes weights estimates for human powered aircraft
Assumptions:
All of this is from AIAA 89-2048, units are in kg. These weight estimates
are from the MIT Daedalus and are valid for very lightweight
carbon fiber composite structures. This may need to be solved iteratively since
gross weight is an input.
Source:
MIT Daedalus
Inputs:
wing - a data dictionary with the fields:
Sw - wing area [meters**2]
bw - wing span [meters]
cw - average wing chord [meters]
deltaw - average rib spacing to average chord ratio [dimensionless]
Nwr - number of wing surface ribs (bw**2)/(deltaw*Sw) [dimensionless]
t_cw - wing airfoil thickness to chord ratio [dimensionless]
Nwer - number of wing end ribs (2*number of individual wing panels -2) [dimensionless]
horizontal - a data dictionary with the fields:
Sts - tail surface area [meters]
bts - tail surface span [meters]
cts - average tail surface chord [meters]
deltawts - average rib spacing to average chord ratio [dimensionless]
Ntsr - number of tail surface ribs (bts^2)/(deltats*Sts) [dimensionless]
t_cts - tail airfoil thickness to chord ratio [dimensionless]
vertical - a data dictionary with the fields:
Sts - tail surface area [meters]
bts - tail surface span [meters]
cts - average tail surface chord [meters]
deltawts - average rib spacing to average chord ratio [dimensionless]
Ntsr - number of tail surface ribs (bts**2)/(deltats*Sts) [dimensionless]
t_cts - tail airfoil thickness to chord ratio [dimensionless]
aircraft - a data dictionary with the fields:
nult - ultimate load factor [dimensionless]
GW - aircraft gross weight [kilogram]
qm - dynamic pressure at maneuvering speed [Pascals]
Ltb - tailboom length [meters]
Outputs:
Wws - weight of wing spar [kilogram]
Wtss - weight of tail surface spar [kilogram]
Wwr - weight of wing ribs [kilogram]
Wtsr - weight of tail surface ribs [kilogram]
Wwer - weight of wing end ribs [kilogram]
WwLE - weight of wing leading edge [kilogram]
WtsLE - weight of tail surface leading edge [kilogram]
WwTE - weight of wing trailing edge [kilogram]
Wwc - weight of wing covering [kilogram]
Wtsc - weight of tail surface covering [kilogram]
Wtb - tailboom weight [kilogram]
Properties Used:
N/A
| def SUAVE.Methods.Weights.Correlations.Human_Powered.fuselage.fuselage | ( | Sts, | |
| qm, | |||
| Ltb | |||
| ) |
fuselage.py
Created: Jun 2014, E. Botero Modified: Feb 2016, E. Botero
Compute weifht estimate of human-powered aircraft fuselage
Assumptions:
All of this is from AIAA 89-2048, units are in kg. These weight estimates
are from the MIT Daedalus and are valid for very lightweight
carbon fiber composite structures. This may need to be solved iteratively since
gross weight is an input.
Source:
MIT Daedalus
Inputs:
Sts - tail surface area [meters]
qm - dynamic pressure at maneuvering speed [Pascals]
Ltb - tailboom length [meters]
Outputs:
Wtb - tailboom weight [kilogram]
Properties Used:
N/A
| def SUAVE.Methods.Weights.Correlations.Human_Powered.tail.tail | ( | Sts, | |
| bts, | |||
| cts, | |||
| Ntsr, | |||
| t_cts, | |||
| qm | |||
| ) |
tail.py
Created: Jun 2014, E. Botero Modified: Feb 2016, E. Botero
Compute weight of human-powered aircraft tail
Assumptions:
All of this is from AIAA 89-2048, units are in kg. These weight estimates
are from the MIT Daedalus and are valid for very lightweight
carbon fiber composite structures. This may need to be solved iteratively since
gross weight is an input.
Source:
MIT Daedalus
Inputs:
Sts - tail surface area [meters]
bts - tail surface span [meters]
cts - average tail surface chord [meters]
deltats - average rib spacing to average chord ratio [dimensionless]
Ntsr - number of tail surface ribs (bts^2)/(deltats*Sts)[dimensionless]
t_cts - tail airfoil thickness to chord ratio [dimensionless]
qm - dynamic pressure at maneuvering speed [Pascals]
Outputs:
Wtss - weight of tail surface spar [kilogram]
Wtsr - weight of tail surface ribs [kilogram]
WtsLE - weight of tail surface leading edge [kilogram]
Wtsc - weight of tail surface covering [kilogram]
Properties Used:
N/A
| def SUAVE.Methods.Weights.Correlations.Human_Powered.wing.wing | ( | Sw, | |
| bw, | |||
| cw, | |||
| Nwr, | |||
| t_cw, | |||
| Nwer, | |||
| nult, | |||
| GW | |||
| ) |
wing.py
Created: Jun 2014, E. Botero Modified: Feb 2016, E. Botero
Compute weight of human-powered aircraft wing
Assumptions:
All of this is from AIAA 89-2048, units are in kg. These weight estimates
are from the MIT Daedalus and are valid for very lightweight
carbon fiber composite structures. This may need to be solved iteratively since
gross weight is an input.
Source:
MIT Daedalus
Inputs:
Sw - wing area [meters**2]
bw - wing span [meters]
cw - average wing chord [meters]
eltaw - average rib spacing to average chord ratio [dimensionless]
Nwr - number of wing or tail surface ribs (bw^2)/(deltaw*Sw) [dimensionless]
t_cw - wing airfoil thickness to chord ratio [dimensionless]
Nwer - number of wing end ribs (2*number of individual wing panels -2) [dimensionless]
nult - ultimate load factor [dimensionless]
GW - aircraft gross weight [kilogram]
Outputs:
Wws - weight of wing spar [kilogram]
Wwr - weight of wing ribs [kilogram]
Wwer - weight of wing end ribs [kilogram]
WwLE - weight of wing leading edge [kilogram]
WwTE - weight of wing trailing edge [kilogram]
Wwc - weight of wing covering [kilogram]
Properties Used:
N/A
1.8.15