68
different impact velocities (V i ). The coordinates of the projectile center of gravity are estimated to assess with DIC. This
method proved efficient to measure the projectile kinematic and the residual velocity after perforation. Using these measurements an energy balance of the projectile has been computed, which enables the determination of the ballistic limit (V BLV )
from one test even in the case of impact with an angle. This approach makes it possible to assess the energy absorbed by the
composite plate. The limit velocity has been estimated whatever of the panel angle and shows good agreement for two impact
angles studied.
12.3 Conclusion
An experimental protocol is developed to assess the strength of composite fuselage substructures (stiffened panels) to the
debris impact. The Digital Images Correlation (DIC) method was successfully applied to measure the local distribution displacement on the panel rear side under high-velocity impact conditions. The DIC method proved also efficient to measure
the projectile kinematic and the residual velocity during the impact. An energy balance of the projectile has been computed,
which enables the determination of the ballistic limit. This experimental method proved useful during the development of
technical solution to absorb more energy during impact. Furthermore, this new experimental approach has allowed attesting
a projectile shape dependency on the ballistic limit [4].
Acknowledgments The works presented in the communication have been funded by the Adec project under the European Community’s CleanSKy
2. The authors are also grateful to the French Ministry of Defense, the Elsat2020, the FEDER, and the Région Haut de France for their financial
support.
References
1. Xuan, H.-J., Wu, R.-R.: Aeroengine turbine blade containment tests using high-speed rotor spin testing facility. Aerospace Sci. Technol. 10(6),
501–508 (2006)
2. Pernas-Sánchez, J., Artero-Guerrero, J.A., Varas, D., López-Puente, J.: Experimental analysis of normal and oblique high velocity impacts on
carbon/epoxy tape laminates. Compos. A Appl. Sci. Manuf. 60, 24–31 (2014)
3. Varas, D., Artero-Guerrero, J.A., Pernas-Sánchez, J., López-Puente, J.: Analysis of high velocity impacts of steel cylinders on thin carbon/
epoxy woven laminates. Compos. Struct. 95, 623–629 (2014)
4. Ulven, C., Vaidya, U.K., Hosur, M.V.: Effect of projectile shape during ballistic perforation of VARTM carbon/epoxy composite panels.
Compos. Struct. 61, 143–150 (2003)
G. Portemont et al.
different impact velocities (V i ). The coordinates of the projectile center of gravity are estimated to assess with DIC. This
method proved efficient to measure the projectile kinematic and the residual velocity after perforation. Using these measurements an energy balance of the projectile has been computed, which enables the determination of the ballistic limit (V BLV )
from one test even in the case of impact with an angle. This approach makes it possible to assess the energy absorbed by the
composite plate. The limit velocity has been estimated whatever of the panel angle and shows good agreement for two impact
angles studied.
12.3 Conclusion
An experimental protocol is developed to assess the strength of composite fuselage substructures (stiffened panels) to the
debris impact. The Digital Images Correlation (DIC) method was successfully applied to measure the local distribution displacement on the panel rear side under high-velocity impact conditions. The DIC method proved also efficient to measure
the projectile kinematic and the residual velocity during the impact. An energy balance of the projectile has been computed,
which enables the determination of the ballistic limit. This experimental method proved useful during the development of
technical solution to absorb more energy during impact. Furthermore, this new experimental approach has allowed attesting
a projectile shape dependency on the ballistic limit [4].
Acknowledgments The works presented in the communication have been funded by the Adec project under the European Community’s CleanSKy
2. The authors are also grateful to the French Ministry of Defense, the Elsat2020, the FEDER, and the Région Haut de France for their financial
support.
References
1. Xuan, H.-J., Wu, R.-R.: Aeroengine turbine blade containment tests using high-speed rotor spin testing facility. Aerospace Sci. Technol. 10(6),
501–508 (2006)
2. Pernas-Sánchez, J., Artero-Guerrero, J.A., Varas, D., López-Puente, J.: Experimental analysis of normal and oblique high velocity impacts on
carbon/epoxy tape laminates. Compos. A Appl. Sci. Manuf. 60, 24–31 (2014)
3. Varas, D., Artero-Guerrero, J.A., Pernas-Sánchez, J., López-Puente, J.: Analysis of high velocity impacts of steel cylinders on thin carbon/
epoxy woven laminates. Compos. Struct. 95, 623–629 (2014)
4. Ulven, C., Vaidya, U.K., Hosur, M.V.: Effect of projectile shape during ballistic perforation of VARTM carbon/epoxy composite panels.
Compos. Struct. 61, 143–150 (2003)
G. Portemont et al.