noads.gam_jax.models.generic_airplane_model

noads.gam_jax.models.generic_airplane_model#

Created on Thu Jan 20 20:20:20 2020.

author:

Conceptual Airplane Design & Operations (CADO team) Nicolas PETEILH, Pascal ROCHES, Nicolas MONROLIN, Thierry DRUOT AircraftOperation & Systems, Air Transport Department, ENAC

class noads.gam_jax.models.generic_airplane_model.GAM(battery_specific_energy=400.0, emotor_specific_power=4.5, lh2tank_gravimetric_index=40, fuelcell_specific_power=1, lift_to_drag='model', struct_weight_factor=84, fuelcell_efficiency=50, electronics_specific_power=10)[source]#

Bases: object

climb_energy(mass, alt)[source]#
design_airplane(power_system, mission)[source]#

Perform the design of the aircraft with a target on Range.

  • power_system : a dictionnary with 5 entries:

    • energy_type : “petrol”,”kerosene”,”gasoline”,”compressed_h2”,”liquid_h2”,”liquid_ch4”,”liquid_nh3” or “battery”

    • engine_type : “turbofan”,”turboprop”,”piston” or “emotor” (eletric motor)

    • engine_count : the number of engines

    • thruster_type: “fan” or “propeller”

    • bpr : bypass ratio in the case of a fan truster.

  • design_mission : a dictionnary with 5 entries

    • category : “general” (ex: TB20), “commuter” (PC-6), “regional” (ATR72), “business” (Falcon2000), “short_medium” (A320) or “long_range” (B787).

    • npax : number of passengers. Used to determine the maximum payload.

    • range : the horizontal distance to cover for the design mission

    • speed : Cruise Mach number (adim). Can be obtained from True Air Speed, utils/physical_data.py with mach_from_vtas()

    • altitude : typical cruise altitude.

design_dict(npax, mpax, nominal_range, max_power, total_power, mtow, mzfw, mlw, payload_max, power_system, mission, altitude_data, reserve_data, dict_p, dict_s, storage_energy_density, propulsion_power_density)[source]#
energy_storage(power_system, max_fuel, max_enrg)[source]#

Compute fuel and or energy storage mass.

flight_altitude(airplane_type, cruise_altp=None)[source]#

Return [cruise altitude, diversion altitude, holding altitude].

furnishing(npax, category)[source]#

Semi empirical furnishing mass.

get_design_data(df, airplane, index='name')[source]#
get_lod(mtow)[source]#
get_pax_allowance(category)[source]#

Compute passenger mass allowance WARNING : continuous function to avoid convergence problem within solvings.

get_piston_sfc(energy_type)[source]#
get_pk_o_mass_max(owe)[source]#
get_pk_o_mass_min(owe)[source]#
get_tas(tamb, speed, speed_type)[source]#
get_turbofan_sfc(tas, BPR, energy_type)[source]#
get_turboprop_sfc(max_power, energy_type)[source]#
holding_fuel(start_mass, time, altp, speed, speed_type, mtow, max_power, power_system)[source]#

Compute the fuel for a given holding time.

WARNING: when fuel is used, returned value is fuel mass (kg); when battery is used, returned value is energy (J).

leg_fuel(start_mass, distance, altp, speed, speed_type, mtow, max_power, power_system)[source]#

Compute fuel and or energy over a given distance.

lod_model(fuselage_length, fuselage_width, wing_span, wing_area, htp_area, vtp_area, cruise_altp, cruise_speed, mass, design=None, full_output=False)[source]#

Lift over Drag model construction based on geometrical parameters.

op_item(npax, distance)[source]#

Semi empirical mass for operator items.

owe_performance(payload, mtow, range, cruise_speed, total_power, power_system, altitude_data, reserve_data)[source]#

Compute OWE from the point of view of mission energy_storage_mass contains the battery weight or tank weight for GH2 or LH2 storage.

owe_structure(category, npax, mtow, distance, total_power, max_fuel, max_enrg, power_system)[source]#

Compute OWE from the point of view of structures.

print_design(dict, name=None)[source]#
print_model_data()[source]#
propulsion_mass(power_system, total_power)[source]#

Estimates the mass of the propulsion system according to the selected architecture.

ref_power(mtow)[source]#

Required total power for an airplane with a given MTOW.

reserve_data(airplane_type)[source]#

Return [mission fuel factor, diversion leg, holding time].

standard_mass(mtow)[source]#

Averaged Standard standard MWE for an airplane with a given MTOW (std_mass = MWE - furnishing - operator items).

take_off_energy(total_power)[source]#
total_fuel(tow, distance, cruise_speed, mtow, total_power, power_system, altitude_data, reserve_data)[source]#

Compute the total fuel required for a mission.

WARNING: when fuel is used, returned value is fuel mass (kg); when battery is used, returned value is energy (J).

yearly_utilization(mean_range)[source]#

Compute the yearly utilization from the average range.

Classes

GAM([battery_specific_energy, ...])