RCAIDE.Library.Methods.Mass_Properties.Weight_Buildups.Conventional.General_Aviation.FLOPS.compute_horizontal_tail_weight

compute_horizontal_tail_weight#

compute_horizontal_tail_weight(vehicle)[source]#

Calculates the weight of an aircraft’s horizontal tail using FLOPS methodology.

Parameters:

vehicle (RCAIDE.Vehicle()) –

Vehicle data structure containing:

  • wings.horizontal_tail.areas.reference

  • mass_properties.max_takeoff

  • flight_envelope.ultimate_load

  • design_dynamic_pressure

Returns:

horizontal_tail_weight – Estimated weight of the horizontal tail assembly in kilograms

Return type:

float

Notes

The function implements the FLOPS (Flight Optimization System) weight estimation method for horizontal tail surfaces for general aviation aircraft. The calculation accounts for geometric parameters and design loads based on maximum takeoff weight.

Major Assumptions

  • The weight is a function of the horizontal tail area, ultimate load factor, takeoff weight, and design dynamic pressure

Theory

The FLOPS horizontal tail weight estimation follows:

\[W_{ht} = 0.016 * S_{ht}^{0.873} * (N_{ult} * W_{TO})^{0.414} * q^{0.122}\]
Where:

  • W_{ht} is horizontal tail weight [lb]

  • S_{ht} is horizontal tail area [ft^2]

  • N_{ult} is ultimate load factor

  • W_{TO} is maximum takeoff weight [lb]

  • q is design dynamic pressure [psf]