RCAIDE.Library.Methods.Mass_Properties.Moment_of_Inertia.compute_fuselage_moment_of_inertia

compute_fuselage_moment_of_inertia

compute_fuselage_moment_of_inertia(fuselage, center_of_gravity=[[0, 0, 0]])

computes the moment of ienrtia tensor for a generic fuselage about a given center of gravity.

Assumptions: - Fuselage can be approximated by a hemisphere, cylinder, and cone. - Fuselage is hollow with the inner radius being 85% of the outer radius. - Fuselage is constant density

Source: [1] Moulton, B. C., and Hunsaker, D. F., “Simplified Mass and Inertial Estimates for Aircraft with Components of Constant Density,” AIAA SCITECH 2023 Forum, January 2023, AIAA-2023-2432 DOI: 10.2514/ 6.2023-2432

[2] Weisstein, E. W., “Moment of Inertia – Cone,” Wolfram Research, N.D., https://scienceworld.wolfram.com/physics/MomentofInertiaCone.html

Inputs: - Fuselage - Center of gravity or the point to find the MOI about

Outputs: - Fuselage moment of inertia tensor

Properties Used: N/A

Volume_Fraction(radius_outer, radius_inner, center_length, tail_length)

Calculate the volume fraction of each of the three components that make up the entire fuselage

Assumptions:

Source:

Inputs: - Fuselage dimensions (radii, center length, tail length)

Outputs: - Volume fraction of each fuselage component

Properties Used: N/A