RCAIDE.Library.Methods.Mass_Properties.Moment_of_Inertia.compute_wing_moment_of_inertia

compute_wing_moment_of_inertia

compute_wing_moment_of_inertia(wing, mass=0, center_of_gravity=[[0, 0, 0]], fuel_flag=False)

computes the moment of inertia tensor for a wing about a given center of gravity. Includes the ability to modela wing fuel tank as a condensed wing

Assumptions: - Wing is solid - Wing has a 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] Fuel tank references: These were used to estimate the length percentages. - https://assets.publishing.service.gov.uk/media/5422fa1aed915d13710007a1/2-2007_G-YMME.pdf - https://oat.aero/2023/03/17/airbus-a380-general-familiarisation-fuel-storage/ - http://www.b737.org.uk/fuel.htm - https://slideplayer.com/slide/3854059/

Inputs: - Wing - Wing mass - Center of gravity - Fuel flag (whether the wing is considered a fuel tank or not)

Outputs: - wing moment of inertia tensor

Properties Used: N/A