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Time-domain simulation for flight loads analysis
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics. (Flygdynamik, Flight Dynamics)
2012 (English)Report (Other academic)
Abstract [en]

A method for performing flight simulations considering both the motion of the center of gravity and the elastic deformation of the aircraft structure is developed. The time history of the included states is intended to be used for analysis of structural loads. The utilized time-integration scheme, the evaluation of ex- ternal forces and the solution of the equations of motion for the included states are presented. The effect of including elastic ef- fects and quasi-steady aerodynamic modeling is investigated for a simple longitudinal maneuver with a generic commuter aircraft.

Place, publisher, year, edition, pages
2012. , 19 p.
National Category
Aerospace Engineering
Identifiers
URN: urn:nbn:se:kth:diva-94871OAI: oai:DiVA.org:kth-94871DiVA: diva2:526281
Note
QC 20120511Available from: 2012-05-11 Created: 2012-05-11 Last updated: 2012-05-29Bibliographically approved
In thesis
1. Analysis of Dynamic Flight Loads
Open this publication in new window or tab >>Analysis of Dynamic Flight Loads
2012 (English)Licentiate thesis, comprehensive summary (Other academic)
Abstract [en]

This thesis deals with the determination of loads on an aircraft struc- ture during flight. The focus is on flight conditions where the loads are significantly time-dependent. Analysis of flight loads is primarily motivated to ensure that structural failure is avoided. The ability to ac- curately determine the resulting structural loads which can occur during operation allows for a reduction of the safety margins in the structural design. Consequently it is then possible to decrease the aircraft struc- tural weight. The demand for safe and fuel efficient aircraft creates a desire for efficient and accurate methods for determining the structural loads.

The first paper of this thesis discusses the use of control laws for robust atmospheric turbulence load alleviation in the time domain. A numerical aircraft model including structural elasticity and unsteady aerodynamic effects is used. A limited set of longitudinal flight mechanic degrees of freedom are considered and two methods for structural load analysis are compared for evaluation of the wing root bending moment.

In the second paper a method to perform time domain simulation of both motion of center of gravity and elastic deformation is described. The intention with the development of this simulation method is to enable efficient analysis of dynamic flight loads.

A third study is finally included, where steady and unsteady pressure measurements have been carried out during wind tunnel testing. The motivation for performing these experiments is that knowledge about the aerodynamic force distribution which affect an aircraft structure is needed to correctly determine the structural loads.

Place, publisher, year, edition, pages
KTH Royal Institute of Technology, 2012. 27 p.
Series
Trita-AVE, ISSN 1651-7660 ; 2012:27
National Category
Aerospace Engineering
Identifiers
urn:nbn:se:kth:diva-94881 (URN)
Presentation
2012-05-28, D3, Lindstedsvägen 5, Stockholm, 10:15 (English)
Opponent
Supervisors
Note
QC 20120529Available from: 2012-05-29 Created: 2012-05-11 Last updated: 2012-05-29Bibliographically approved

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CiteExportLink to record
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Citation style
  • apa
  • harvard1
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Output format
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