RCAIDE.Library.Methods.Mass_Properties.Weight_Buildups.Conventional.Transport.FLOPS

FLOPS

RCAIDE Package Setup

Modules

compute_fuselage_weight(vehicle)	Calculate the weight of the fuselage of a transport aircraft
compute_horizontal_tail_weight(vehicle, wing)	Calculate the horizontal tail weight
compute_landing_gear_weight(vehicle)	Calculate the weight of the main and nose landing gear of a transport aircraft
compute_operating_empty_weight(vehicle[, ...])	Computes the empty weight breakdown of a transport aircraft:
compute_operating_items_weight(vehicle)	Calculate the weight of operating items, including: - crew - baggage - unusable fuel - engine oil - passenger service - ammunition and non-fixed weapons - cargo containers (not included)
compute_propulsion_system_weight(vehicle, ...)	Calculate the weight of propulsion system, including: - dry engine weight - fuel system weight - thurst reversers weight - electrical system weight - starter engine weight - nacelle weight - cargo containers
compute_systems_weight(vehicle)	Calculate the system weight of the aircraft using the FLOPS methodology. :param vehicle: Data dictionary with vehicle properties - networks : list List of network objects containing propulsion properties - propulsors : list List of propulsor objects - wing_mounted : bool Flag indicating if propulsor is wing-mounted - nacelle : Data, optional Nacelle properties - diameter : float Nacelle diameter [m] - wings : list List of wing objects - areas.reference : float Wing reference area [m²] - flap_ratio : float Flap surface area over wing surface area - spans.projected : float Projected span of wing [m] - sweeps.quarter_chord : float Quarter chord sweep [deg] - fuselages : list List of fuselage objects - lengths.total : float Fuselage total length [m] - width : float Fuselage width [m] - heights.maximum : float Fuselage maximum height [m] - mass_properties.max_takeoff : float Maximum takeoff weight [kg] - flight_envelope.design_mach_number : float Design mach number for cruise flight - flight_envelope.design_range : float Design range of aircraft [nmi] - passengers : int Number of passengers in aircraft - NPF : int Number of first class passengers - NPB : int Number of business class passengers - NPE : int Number of tourist/economy class passengers - reference_area : float Aircraft reference area [m²] :type vehicle: Data.
compute_vertical_tail_weight(vehicle, wing)	Calculate the vertical tail weight
compute_wing_weight(vehicle, wing, WPOD, ...)	Calculate the wing weight based on the flops method. The wing weight consists of: