|
|
olutions in Aerospace Industry
The cost of design, production and operation,
and time-to-market in general are of increasing importance in aerospace
projects. Like other industries, future success will depend to a
large extend in the ability to leverage the use simulation technologies
and integrate the often complex processes of design, modeling, analysis,
manufacturing and test.
The integration of finite element analysis
with structural testing is a key area to look for synergy when optimizing
processes. FEMtools can be used to increase the productivity of
analysts and test engineers in many ways. Following is just an non-exhaustive
overview of tasks in aerospace engineering where FEMtools can be
applied:
- Target mode selection - The results from baseline
finite element analysis can be used for target mode selection.
- Selection of optimal locations for sensors, actuators
and suspension -
- Identifying and exporting maser DOFs for system matrices
reduction
- Construction and export of a test model - Using this
information, the FE model can be reduced to construct
a test model which makes geometrical mapping of the FE and test
model trivial.
- Test-verification of FE models - Predictions of resonance
frequencies and mode shapes can be validated against experimental
results using commonly used criteria like Modal Assurance Criterion
(MAC) and cross-orthogonality. The diagonal and off-diagonal
values of these matrices are used in standard acceptance criteria.
- Identification of damping
- Structural dynamic modification
- Substructuring
- Sensitivity analysis
- Component model updating
- Assembled structure model updating
- Multi-model updating
- Force identification
Application Cases
Study of a Rotating Helicopter Blade
One of the most important analysis to determine the dynamic behavior
of a rotating part is the determination of the Campbell diagram,
that shows the variation of natural frequencies versus angular velocities.
The basic idea is to validate the FE model of the blade using FEMtools
and then to investigate the difference between the Campbell diagram
obtained with the non updated model and the updated one. The model
geometry and experimental results are provided by the NASA Technical
Memorandum 4760.
(POLITECNICO DI TORINO)
References
J. Guggenberger, MI 17 Fire Firefighting Helicopter Boom -
Validation and Updating of the Analytical Models. Presented
at the 2002 NAFEMS Conference on Validation of FEM Analysis,
November 13-14, Wiesbaden, Germany.
Download
(PDF, 500 KB)
M. Mergeay, J.-S. Servaye, E. Dascotte, Integration
of NVH Testing: A Case Study on a Spatial Structure. Presented
at the 2002 International Seminar on Modal Analysis (ISMA),
September 16-18, 2002, Leuven, Belgium.
Download
(PDF, 755 KB)
E. Dascotte, A. Schoenrock, Validation and Updating of
an Aeroengine Finite Element Model based on Static Stiffness Testing.
Presented at the 2nd MSC Aerospace Conference, June 7-11, 1999,
Long Beach, CA, USA.
Download
(PDF, 233 KB)
For more, information on the topics and cases that are
presented, contact us at info@femtools.com.
|