Analytical determination of trim values for nonlinear fixed wing aircraft models

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Scopus citations

Abstract

This work presents a technique for analytically determining the trim conditions of a fixed wing aircraft from the parameters of its nonlinear mathematical model. Specifically, the elevator, aileron, and rudder deflections are determined in addition to the necessary thrust force and resulting angle of attack and sideslip angles for this flight condition. The technique is demonstrated using three established nonlinear aircraft models: NAVION, F104-A, and Convair 880. These aircraft were selected to represent three different types of fixed wing aircraft: general aviation, fighter jet, and passenger jet, respectively. The results from these aircraft indicate the validity and usefulness of this technique for simulation and control experiments.

Original languageEnglish (US)
Title of host publicationAIAA Modeling and Simulation Technologies Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624104299
DOIs
StatePublished - Jan 1 2016
EventAIAA Modeling and Simulation Technologies Conference, 2016 - Washington, United States
Duration: Jun 13 2016Jun 17 2016

Publication series

NameAIAA Modeling and Simulation Technologies Conference, 2016

Other

OtherAIAA Modeling and Simulation Technologies Conference, 2016
CountryUnited States
CityWashington
Period6/13/166/17/16

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Modeling and Simulation

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