Title:
Dynamic Simulation of Vehicle Maneuvers for Loads Analysis

dc.contributor.author Jing, Xiao
dc.contributor.author Berthon, Benjamin P.
dc.contributor.author Somers, Luke A.
dc.contributor.author Morgan, James R.
dc.contributor.author Rairigh, Geoffrey R.
dc.contributor.author Sarojini, Darshan
dc.contributor.author Harrison, Evan D.
dc.contributor.author Mavris, Dimitri N.
dc.contributor.corporatename Georgia Institute of Technology. Aerospace Systems Design Laboratory en_US
dc.contributor.corporatename American Institute of Aeronautics and Astronautics
dc.contributor.corporatename Georgia Institute of Technology. Aerospace Systems Design Laboratory
dc.date.accessioned 2020-06-15T20:49:36Z
dc.date.available 2020-06-15T20:49:36Z
dc.date.issued 2020-06
dc.description Presented at AIAA Aviation 2020 Forum en_US
dc.description.abstract Testing critical loads during specific dynamic maneuvers is essential to aircraft structural design, and several such dynamic load cases must be demonstrated during the certification process. A simulation capability is developed in this work to calculate critical loads on the vertical tail of a business jet resulting from yaw maneuvers required for certification. The data produced from these simulations can be used to inform future structural design decisions. Models for the pilot and flight control system are developed to simulate the pilot control actions needed to perform the maneuvers within the boundaries of pilot capabilities and flight control system limits. Aerodynamic and propulsive data are used to calculate the forces and moments on the aircraft and solve the 6-degree of freedom equations of motion to accurately model the aircraft’s trajectory. Sectional aerodynamic characteristics of the horizontal and vertical tail are used to calculate the structural loads at each section of the tail. The summation of these forces and moments yields the loads at the vertical tail root, which can be used to assess the structural design of the tail. The simulation is demonstrated on a T-tail business jet with three weight conditions and at flight conditions throughout the flight test envelope. The ultimate loading conditions and the number of control application cycles required to reach ultimate loads at the vertical tail are determined using the maneuver simulation. en_US
dc.identifier.citation Jing, X., Berthon, B., Somers, L. A., Rairigh, G., Morgan, J., Sarojini, D., Harrison, E. D., & Mavris, D. (2020). Dynamic Simulation of Vehicle Maneuvers for Loads Analysis. In AIAA AVIATION 2020 FORUM. American Institute of Aeronautics and Astronautics. https://doi.org/10.2514/6.2020-2651 en_US
dc.identifier.doi 10.2514/6.2020-2651 en_US
dc.identifier.uri http://hdl.handle.net/1853/62935
dc.language.iso en_US en_US
dc.publisher Georgia Institute of Technology en_US
dc.publisher Georgia Institute of Technology
dc.publisher.original American Institute of Aeronautics and Astronautics (AIAA)
dc.relation.ispartofseries ASDL; en_US
dc.subject Dynamic maneuvers en_US
dc.title Dynamic Simulation of Vehicle Maneuvers for Loads Analysis en_US
dc.type Text
dc.type.genre Paper
dspace.entity.type Publication
local.contributor.author Mavris, Dimitri N.
local.contributor.corporatename Daniel Guggenheim School of Aerospace Engineering
local.contributor.corporatename Aerospace Systems Design Laboratory (ASDL)
local.contributor.corporatename College of Engineering
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relation.isOrgUnitOfPublication a8736075-ffb0-4c28-aa40-2160181ead8c
relation.isOrgUnitOfPublication 7c022d60-21d5-497c-b552-95e489a06569
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