Dynamics models of flexible aircraft

Recent trends in aircraft design owing to requirements of high performance and weight reduction have resulted in aircraft possessing significant structural flexibility. Under these conditions, flight vehicles become vulnerable to unfavourable interactions between the structural dynamics of flexible...

Full description

Saved in:
Bibliographic Details
Main Author: Yogeshwaran Jayaraman
Other Authors: Hungsun Son
Format: Theses and Dissertations
Language:English
Published: 2014
Subjects:
Online Access:https://hdl.handle.net/10356/61444
Tags: Add Tag
No Tags, Be the first to tag this record!
Institution: Nanyang Technological University
Language: English
id sg-ntu-dr.10356-61444
record_format dspace
spelling sg-ntu-dr.10356-614442023-03-11T17:58:43Z Dynamics models of flexible aircraft Yogeshwaran Jayaraman Hungsun Son Yongki Go Moon Seung Ki School of Mechanical and Aerospace Engineering DRNTU::Engineering::Aeronautical engineering::Flight simulation DRNTU::Engineering::Aeronautical engineering::Aircraft Recent trends in aircraft design owing to requirements of high performance and weight reduction have resulted in aircraft possessing significant structural flexibility. Under these conditions, flight vehicles become vulnerable to unfavourable interactions between the structural dynamics of flexible components, aerodynamics and the overall motion of the body. In order to utilize automatic flight control systems to mitigate these effects, integrated flight models that account for the internal dependencies in the system must be developed. To this end, this work presents the derivation of flight models describing the dynamics of flexible aircraft. The equations are expressed in compact matrix-vector form, suitable for integration with state-space control systems. The dynamics of elastic bodies are first discussed, followed by numerical simulation results of a slender beam undergoing a spin-up maneuver. Finally, the equations governing the dynamics of flexible aircraft are derived and simplifications to obtain lower complexity models are discussed. The formulation is demonstrated through an example aircraft and some preliminary simulation results are presented. It is hoped that the integrated dynamics models derived in this work can be used for control design, flight simulation, parameter estimation and other studies, which are traditionally performed on six degree-of-freedom rigid-body flight models. MASTER OF ENGINEERING (MAE) 2014-06-10T06:16:54Z 2014-06-10T06:16:54Z 2014 2014 Thesis Yogeshwaran Jayaraman. (2014). Dynamics models of flexible aircraft. Master’s thesis, Nanyang Technological University, Singapore. https://hdl.handle.net/10356/61444 10.32657/10356/61444 en 71 p. application/pdf
institution Nanyang Technological University
building NTU Library
continent Asia
country Singapore
Singapore
content_provider NTU Library
collection DR-NTU
language English
topic DRNTU::Engineering::Aeronautical engineering::Flight simulation
DRNTU::Engineering::Aeronautical engineering::Aircraft
spellingShingle DRNTU::Engineering::Aeronautical engineering::Flight simulation
DRNTU::Engineering::Aeronautical engineering::Aircraft
Yogeshwaran Jayaraman
Dynamics models of flexible aircraft
description Recent trends in aircraft design owing to requirements of high performance and weight reduction have resulted in aircraft possessing significant structural flexibility. Under these conditions, flight vehicles become vulnerable to unfavourable interactions between the structural dynamics of flexible components, aerodynamics and the overall motion of the body. In order to utilize automatic flight control systems to mitigate these effects, integrated flight models that account for the internal dependencies in the system must be developed. To this end, this work presents the derivation of flight models describing the dynamics of flexible aircraft. The equations are expressed in compact matrix-vector form, suitable for integration with state-space control systems. The dynamics of elastic bodies are first discussed, followed by numerical simulation results of a slender beam undergoing a spin-up maneuver. Finally, the equations governing the dynamics of flexible aircraft are derived and simplifications to obtain lower complexity models are discussed. The formulation is demonstrated through an example aircraft and some preliminary simulation results are presented. It is hoped that the integrated dynamics models derived in this work can be used for control design, flight simulation, parameter estimation and other studies, which are traditionally performed on six degree-of-freedom rigid-body flight models.
author2 Hungsun Son
author_facet Hungsun Son
Yogeshwaran Jayaraman
format Theses and Dissertations
author Yogeshwaran Jayaraman
author_sort Yogeshwaran Jayaraman
title Dynamics models of flexible aircraft
title_short Dynamics models of flexible aircraft
title_full Dynamics models of flexible aircraft
title_fullStr Dynamics models of flexible aircraft
title_full_unstemmed Dynamics models of flexible aircraft
title_sort dynamics models of flexible aircraft
publishDate 2014
url https://hdl.handle.net/10356/61444
_version_ 1761781685528035328