Limit Cycle Oscillation (LCO) flutter of advanced high modulus graphite/epoxy composite oscillating supersonic wing
This paper presents an optimisation process of reducing the structural weight of the supersonic wing by constraining the structural durability due to limit cycle oscillation. The application of composite material in aeroelasticity contributes to the modification of the expected aeroelastic failure o...
Saved in:
| Main Authors: | , , |
|---|---|
| Format: | Conference or Workshop Item |
| Language: | English English |
| Published: |
2021
|
| Subjects: | |
| Online Access: | http://irep.iium.edu.my/88907/2/Extended%20Abstract%20-LCO.pdf http://irep.iium.edu.my/88907/13/88907_Limit%20Cycle%20Oscillation%20%28LCO%29.pdf http://irep.iium.edu.my/88907/ |
| Tags: |
Add Tag
No Tags, Be the first to tag this record!
|
| Summary: | This paper presents an optimisation process of reducing the structural weight of the supersonic wing by constraining the structural durability due to limit cycle oscillation. The application of composite material in aeroelasticity contributes to the modification of the expected aeroelastic failure on flutter speed. The composite material such that Graphite/epoxy gives high modulus compared to the metallic material such as aluminium. The objective of this tailoring process is to optimise the wing weight while the flutter performance might be improved. As the optimisation process performed, the flutter speed and the plate manufacturing thickness become the restriction in the wing weight reduction. The study shows good agreement to the objective where the reduction of weight for the High Modulus (HM) Graphite/Epoxy wing skin for the skin weight, clean wing and total wing with missile launcher external stores are 75.82%, 61.96% and 22.09% respectively compared to the baseline aluminium wing model. For the tailoring process, it is found that the flutter Mach number increases more than 81% using the as the Graphite/epoxy composite replaced the aluminium as the skin. |
|---|