RCAIDE.Library.Methods.Mass_Properties.Moment_of_Inertia.compute_wing_integral_tank_moment_of_inertia

compute_wing_integral_tank_moment_of_inertia#

compute_wing_integral_tank_moment_of_inertia(fuel_tank, wing, center_of_gravity=[[0, 0, 0]])[source]#

computes the moment of inertia tensor for an integral tank within wing about a given center of gravity.

Assumptions: - Fuel tank walls are not considered in MOI calculation - Fuel is uniformly distributed in tank - Fuel in tank 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: - Fuel Tank - Wing - Center of gravity

Outputs: - wing moment of inertia tensor

Properties Used: N/A