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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 and component weight correlations for general aviation aircraft. More...
Functions | |
| def | SUAVE.Methods.Weights.Correlations.General_Aviation.empty.empty (vehicle) |
| def | SUAVE.Methods.Weights.Correlations.General_Aviation.fuselage.fuselage (S_fus, Nult, TOW, w_fus, h_fus, l_fus, l_ht, q_c, V_fuse, diff_p_fus) |
| def | SUAVE.Methods.Weights.Correlations.General_Aviation.landing_gear.landing_gear (landing_weight, Nult, strut_length_main, strut_length_nose) |
| def | SUAVE.Methods.Weights.Correlations.General_Aviation.payload.payload (TOW, empty, num_pax, wt_cargo, wt_passenger=225.*Units.lbs, wt_baggage=0.) |
| def | SUAVE.Methods.Weights.Correlations.General_Aviation.systems.systems (W_uav, V_fuel, V_int, N_tank, N_eng, l_fuselage, span, TOW, Nult, num_seats, mach_number, has_air_conditioner=1) |
| def | SUAVE.Methods.Weights.Correlations.General_Aviation.tail_horizontal.tail_horizontal (S_h, AR_h, sweep_h, q_c, taper_h, t_c_h, Nult, TOW) |
| def | SUAVE.Methods.Weights.Correlations.General_Aviation.tail_vertical.tail_vertical (S_v, AR_v, sweep_v, q_c, taper_v, t_c_v, Nult, TOW, t_tail, rudder_fraction=0.25) |
| def | SUAVE.Methods.Weights.Correlations.General_Aviation.wing_main.wing_main (S_wing, m_fuel, AR_w, sweep_w, q_c, taper_w, t_c_w, Nult, TOW) |
Provides structural and component weight correlations for general aviation aircraft.
| def SUAVE.Methods.Weights.Correlations.General_Aviation.empty.empty | ( | vehicle | ) |
output = SUAVE.Methods.Weights.Correlations.Tube_Wing.empty(engine,wing,aircraft,fuselage,horizontal,vertical)
Computes the empty weight breakdown of a General Aviation type aircraft
Inputs:
engine - a data dictionary with the fields:
thrust_sls - sea level static thrust of a single engine [Newtons]
vehicle - a data dictionary with the fields:
reference_area [meters**2]
envelope - a data dictionary with the fields:
ultimate_load - ultimate load of the aircraft [dimensionless]
limit_load - limit load factor at zero fuel weight of the aircraft [dimensionless]
mass_properties - a data dictionary with the fields:
max_takeoff - max takeoff weight of the vehicle [kilograms]
max_zero_fuel - maximum zero fuel weight of the aircraft [kilograms]
cargo - cargo weight [kilograms]
passengers - number of passengers on the aircraft [dimensionless]
design_dynamic_pressure - dynamic pressure at cruise conditions [Pascal]
design_mach_number - mach number at cruise conditions [dimensionless]
networks - a data dictionary with the fields:
keys - identifier for the type of network; different types have different fields
turbofan
thrust_sls - sealevel standard thrust [Newtons]
internal_combustion
rated_power - maximum rated power of the internal combustion engine [Watts]
number_of_engines - integer indicating the number of engines on the aircraft
wt_cargo - weight of the bulk cargo being carried on the aircraft [kilograms]
num_seats - number of seats installed on the aircraft [dimensionless]
ctrl - specifies if the control system is "fully powered", "partially powered", or not powered [dimensionless]
ac - determines type of instruments, electronics, and operating items based on types:
"short-range", "medium-range", "long-range", "business", "cargo", "commuter", "sst" [dimensionless]
w2h - tail length (distance from the airplane c.g. to the horizontal tail aerodynamic center) [meters]
fuel - a data dictionary with the fields:
mass_properties - a data dictionary with the fields:
mass -mass of fuel [kilograms]
density - gravimetric density of fuel [kilograms/meter**3]
number_of_tanks - number of external fuel tanks [dimensionless]
internal_volume - internal fuel volume contained in the wing [meters**3]
wings - a data dictionary with the fields:
wing - a data dictionary with the fields:
span - span of the wing [meters]
taper - taper ratio of the wing [dimensionless]
thickness_to_chord - thickness-to-chord ratio of the wing [dimensionless]
chords - a data dictionary with the fields:
mean_aerodynamic - mean aerodynamic chord of the wing [meters]
root - root chord of the wing [meters]
sweeps - a data dictionary with the fields:
quarter_chord - quarter chord sweep angle of the wing [radians]
mac - mean aerodynamic chord of the wing [meters]
r_c - wing root chord [meters]
origin - location of the leading edge of the wing relative to the front of the fuselage [meters,meters,meters]
aerodynamic_center - location of the aerodynamic center of the horizontal_stabilizer relative to the leading edge of the wing [meters,meters,meters]
horizontal_stabilizer - a data dictionary with the fields:
areas - a data dictionary with the fields:
reference - reference area of the horizontal stabilizer [meters**2]
exposed - exposed area for the horizontal tail [meters**2]
taper - taper ratio of the horizontal stabilizer [dimensionless]
span - span of the horizontal tail [meters]
sweeps - a data dictionary with the fields:
quarter_chord - quarter chord sweep angle of the horizontal stabilizer [radians]
chords - a data dictionary with the fields:
mean_aerodynamic - mean aerodynamic chord of the horizontal stabilizer [meters]
root - root chord of the horizontal stabilizer
thickness_to_chord - thickness-to-chord ratio of the horizontal tail [dimensionless]
mac - mean aerodynamic chord of the horizontal tail [meters]
origin - location of the leading of the horizontal tail relative to the front of the fuselage [meters,meters,meters]
aerodynamic_center - location of the aerodynamic center of the horizontal_stabilizer relative to the leading edge of the horizontal stabilizer [meters,meters,meters]
vertical - a data dictionary with the fields:
areas - a data dictionary with the fields:
reference - reference area of the vertical stabilizer [meters**2]
span - span of the vertical tail [meters]
taper - taper ratio of the horizontal stabilizer [dimensionless]
t_c - thickness-to-chord ratio of the vertical tail [dimensionless]
sweeps - a data dictionary with the fields:
quarter_chord - quarter chord sweep angle of the vertical stabilizer [radians]
t_tail - flag to determine if aircraft has a t-tail, "yes" [dimensionless]
fuselages - a data dictionary with the fields:
fuselage - a data dictionary with the fields:
areas - a data dictionary with the fields:
wetted - wetted area of the fuselage [meters**2]
differential_pressure - Maximum fuselage pressure differential [Pascal]
width - width of the fuselage [meters]
heights - a data dictionary with the fields:
maximum - height of the fuselage [meters]
lengths- a data dictionary with the fields:
structure - structural length of the fuselage [meters]
mass_properties - a data dictionary with the fields:
volume - total volume of the fuselage [meters**3]
internal_volume - internal volume of the fuselage [meters**3]
number_coach_sets - number of seats on the aircraft [dimensionless]
landing_gear - a data dictionary with the fields:
main - a data dictionary with the fields:
strut_length - strut length of the main gear [meters]
nose - a data dictionary with the fields:
strut_length - strut length of the nose gear [meters]
avionics - a data dictionary, used to determine if avionics weight is calculated, don't include if vehicle has none
air_conditioner - a data dictionary, used to determine if air conditioner weight is calculated, don't include if vehicle has none
Outputs:
output - a data dictionary with fields:
wing - wing weight [kilograms]
fuselage - fuselage weight [kilograms]
propulsion - propulsion [kilograms]
landing_gear_main - main gear weight [kilograms]
landing_gear_nose - nose gear weight [kilograms]
horizonal_tail - horizontal stabilizer weight [kilograms]
vertical_tail - vertical stabilizer weight [kilograms]
systems - total systems weight [kilograms]
systems_breakdown - a data dictionary with fields:
control_systems - control systems weight [kilograms]
hydraulics - hydraulics weight [kilograms]
avionics - avionics weight [kilograms]
electric - electrical systems weight [kilograms]
air_conditioner - air conditioner weight [kilograms]
furnish - furnishing weight [kilograms]
fuel_system - fuel system weight [ kilograms]
Wing, empannage, fuselage, propulsion and individual systems masses updated with their calculated values
Assumptions:
calculated aircraft weight from correlations created per component of historical aircraft
| def SUAVE.Methods.Weights.Correlations.General_Aviation.fuselage.fuselage | ( | S_fus, | |
| Nult, | |||
| TOW, | |||
| w_fus, | |||
| h_fus, | |||
| l_fus, | |||
| l_ht, | |||
| q_c, | |||
| V_fuse, | |||
| diff_p_fus | |||
| ) |
Calculate the weight of a fuselage for a GA aircraft
Source: Raymer: Aircraft Design, a Conceptual Approach (pages 460-461 in 4th edition)
Inputs:
S_f - fuselage wetted area [meters**2]
Nult - ultimate load of the aircraft [dimensionless]]
TOW - maximum takeoff weight of the aircraft [kilograms]
w_fus - width of the fuselage [meters]
h_fus - height of the fuselage [meters]
l_fus - length of the fuselage [meters]
l_ht - length of tail arm [meters]
q_c - dynamic pressure at cruise [Pascals]
V_fuse - volume of pressurized cabin [meters**3]
diff_p_fus - Maximum fuselage pressure differential [Pascals]
Outputs:
weight - weight of the fuselage [kilograms]
Assumptions:
fuselage for a general aviation type aircraft
| def SUAVE.Methods.Weights.Correlations.General_Aviation.landing_gear.landing_gear | ( | landing_weight, | |
| Nult, | |||
| strut_length_main, | |||
| strut_length_nose | |||
| ) |
Calculate the weight of the landing gear
Source: Raymer- Aircraft Design: a Conceptual Approach (pg 460 in 4th edition)
Inputs:
Nult - ultimate landing load factor
landing_weight- landing weight of the aircraft [kilograms]
Outputs:
weight - weight of the landing gear [kilograms]
Assumptions:
calculating the landing gear weight based on the landing weight, load factor, and strut length
| def SUAVE.Methods.Weights.Correlations.General_Aviation.payload.payload | ( | TOW, | |
| empty, | |||
| num_pax, | |||
| wt_cargo, | |||
wt_passenger = 225.*Units.lbs, |
|||
wt_baggage = 0. |
|||
| ) |
Calculate the weight of the payload and the resulting fuel mass
Inputs:
TOW - [kilograms]
wt_empty - Operating empty weight of the aircraft [kilograms]
num_pax - number of passengers on the aircraft [dimensionless]
wt_cargo - weight of cargo being carried on the aircraft [kilogram]
wt_passenger - weight of each passenger on the aircraft [kilograms]
wt_baggage - weight of the baggage for each passenger [kilograms]
Outputs:
output - a data dictionary with fields:
payload - weight of the passengers plus baggage and paid cargo [kilograms]
pax - weight of all the passengers [kilograms]
bag - weight of all the baggage [kilograms]
fuel - weight of the fuel carried [kilograms]
empty - operating empty weight of the aircraft [kilograms]
| def SUAVE.Methods.Weights.Correlations.General_Aviation.systems.systems | ( | W_uav, | |
| V_fuel, | |||
| V_int, | |||
| N_tank, | |||
| N_eng, | |||
| l_fuselage, | |||
| span, | |||
| TOW, | |||
| Nult, | |||
| num_seats, | |||
| mach_number, | |||
has_air_conditioner = 1 |
|||
| ) |
output = SUAVE.Methods.Weights.Correlations.General_Avation.systems(num_seats, ctrl_type, S_h, S_v, S_gross_w, ac_type)
Calculate the weight of the different engine systems on the aircraft
Source:
Raymer, Aircraft Design: A Conceptual Approach (pg 461 in 4th edition)
Inputs:
V_fuel - total fuel volume [meters**3]
V_int - internal fuel volume [meters**3]
N_tank - number of fuel tanks [dimensionless]
N_eng - number of engines [dimensionless]
span - wingspan [meters]
TOW - gross takeoff weight of the aircraft [kg]
num_seats - total number of seats on the aircraft [dimensionless]
mach_number - mach number [dimensionless]
has_air_conditioner - integer of 1 if the vehicle has ac, 0 if not
Outputs:
output - a data dictionary with fields:
wt_flt_ctrl - weight of the flight control system [kilograms]
wt_apu - weight of the apu [kilograms]
wt_hyd_pnu - weight of the hydraulics and pneumatics [kilograms]
wt_avionics - weight of the avionics [kilograms]
wt_opitems - weight of the optional items based on the type of aircraft [kilograms]
wt_elec - weight of the electrical items [kilograms]
wt_ac - weight of the air conditioning and anti-ice system [kilograms]
wt_furnish - weight of the furnishings in the fuselage [kilograms]
| def SUAVE.Methods.Weights.Correlations.General_Aviation.tail_horizontal.tail_horizontal | ( | S_h, | |
| AR_h, | |||
| sweep_h, | |||
| q_c, | |||
| taper_h, | |||
| t_c_h, | |||
| Nult, | |||
| TOW | |||
| ) |
Calculate the weight of the horizontal tail for a General Aviation-type aircraft
Source:
Aircraft Design: A Conceptual Approach by Raymer (pg 460 in 4th edition)
Inputs:
S_h = trapezoidal area of horizontal tail [meters**2]
Ar_h = aspect ratio of horizontal tail [dimensionless]
sweep_h = quarter chord sweep of the horizontal tail [radians]
q_c = dynamic pressure at cruise [Pascals]
Outputs:
weight - weight of the horizontal tail [kilograms]
Assumptions:
calculated weight of the horizontal tail including the elevator
Assume that the elevator is 25% of the horizontal tail
| def SUAVE.Methods.Weights.Correlations.General_Aviation.tail_vertical.tail_vertical | ( | S_v, | |
| AR_v, | |||
| sweep_v, | |||
| q_c, | |||
| taper_v, | |||
| t_c_v, | |||
| Nult, | |||
| TOW, | |||
| t_tail, | |||
rudder_fraction = 0.25 |
|||
| ) |
Calculate the weight of the vertical fin of an aircraft without the weight of the rudder and then calculate the weight of the rudder
Source:
Raymer, Aircraft Design: A Conceptual Approach (pg 460 in 4th edition)
Inputs:
S_v - area of the vertical tail (combined fin and rudder) [meters**2]
M_w -mass of wing [kilograms]
AR_v -aspect ratio of vertial tail [dimensionless]
sweep_v - sweep angle of the vertical tail [radians]
q_c - dynamic pressure at cruise [Pascals]
taper_v - taper ratio of vertical tail [dimensionless]
t_c_v -thickness to chord ratio of wing [dimensionless]
Nult - ultimate load of the aircraft [dimensionless]
TOW - maximum takeoff weight of the aircraft [kilograms]
S_gross_w - wing gross area [meters**2]
t_tail - flag to determine if aircraft has a t-tail [dimensionless]
rudder_fraction - fraction of the vertical tail that is the rudder [dimensionless]
Outputs:
output - a dictionary with outputs:
wt_tail_vertical - weight of the vertical fin portion of the vertical tail [kilograms]
Assumptions:
Vertical tail weight is the weight of the vertical fin without the rudder weight.
| def SUAVE.Methods.Weights.Correlations.General_Aviation.wing_main.wing_main | ( | S_wing, | |
| m_fuel, | |||
| AR_w, | |||
| sweep_w, | |||
| q_c, | |||
| taper_w, | |||
| t_c_w, | |||
| Nult, | |||
| TOW | |||
| ) |
Calculate the weight of the main wing of an aircraft
Source:
Raymer, Aircraft Design: A Conceptual Approach (pg 460 in 4th edition)
Inputs:
S_wing- area of the main wing [meters**2]
m_fuel - predicted weight of fuel in the wing [kilograms]
AR_w -aspect ratio of main wing [dimensionless]
sweep_w - quarter chord sweep of the main wing [radians]
q_c - dynamic pressure at cruise [Pascals]
taper_w - taper ratio of wing [dimensionless]
t_c_w -thickness to chord ratio of wing [dimensionless]
Nult - ultimate load of the aircraft [dimensionless]
TOW - maximum takeoff weight of the aircraft [kilograms]
Outputs:
output - a dictionary with outputs:
wt_main_wing - weight of the vertical fin portion of the vertical tail [kilograms]
1.8.15