This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Investigation of Flight Loads Prediction using Multi-Body Simulation
Technical Paper
2013-01-2317
ISSN: 0148-7191, e-ISSN: 2688-3627
Annotation ability available
Sector:
Language:
English
Abstract
Flight load prediction is used to identify the maximum structural loads in an aircraft during flight manoeuvres and gusts. The motivation for this research activity was to assess the feasibility of using Commercial-off-the-shelf (COTS) software applications in the context of flight loads prediction during the early phases of design for commercial airline aircraft, which may drive significant time saving. The COTS that was used was the multi-body software LMS Virtual.Lab Motion.
To build a relatively accurate model within the given time, existing FE models and aerodynamic data for a given aircraft model were used. Initially, the model was trimmed to a steady-level 1-g state. Subsequently, several gust cases were simulated. The results showed that a steady state was achieved before and after the gust, demonstrating the ability of the model to recover. It was also observed that the trends of the pitch angle and pitch rate response were very similar to the results obtained from validated “in-house” tools. Most importantly, two of the three main quantities for flight loads, namely shear force and bending moment were captured quite well with a post processing of LMS Virtual.Lab Motion outputs. The results compare reasonable well with other validated data, although differences can be observed mainly due to different assumptions and simplifications in the model. The wing tip deflection was also assessed during this research activity. However, these results deviated from the validated data gathered. This could be due to the simplification of the aerodynamic forces applied or the aeroelastic response.
Authors
Citation
Lemmens, Y., de Boer, J., Calvo-Blanco, M., and Cooper, J., "Investigation of Flight Loads Prediction using Multi-Body Simulation," SAE Technical Paper 2013-01-2317, 2013, https://doi.org/10.4271/2013-01-2317.Also In
References
- De Cuyper , J. , Furmann , M. , Kading , D. et al. Vehicle dynamics with LMS Virtual Lab Motion 45 2007 199 206
- Wright , J. R. and Cooper , J. E. Introduction to Aircraft Aeroelastics and Loads John Wiley and Sons Ltd Publishers England 2007
- Nelson , R. C. Flight Stability and Automatic Control 2nd McGraw-Hill International Editions Singapore 1998
- Titurus , B. Aircraft Dynamics 4 University of Bristol 4th Year Lecture Notes 2012
- European Aviation Safety Agency Certification Specifications, CS-25 (Large Aircraft) http://easa.europa.eu/agency-measures/certification-specifications.php
- Lomax , T. L. Structural Analysis for Commercial Transport Aircraft Theory and Practice, AIAA Education Series Virginia 1996
- Stevens , B. L. and Lewis , F. L. Aircraft Control and Simulation John Wiley and Sons Ltd USA 1992
- Inman , D. J. Engineering Vibrations 2nd Prentice Hall 2001
- Hobit , F. M. Gust Loads on Aircraft, Concepts and Applications AIAA Education Series Washington 1988
- LMS International Optimizing real-life performance of mechanical systems www.lmsintl.com/lmsworldwide
- Airbus UK Airbus Validation Data 2012
- Airbus UK LMS Virtual.Lab Tutorials, Motion & Flex 2012