Laminated composites have important and irreplaceable applications in modern aeronautical structures. They have extraordinary properties, like high strength, stiffness, and lightweight. Nevertheless, a serious obstacle to more widespread use of these materials is their sensitivity to impact loads.
As a consequence of that, impact damage initiation and growth in them are appearing and must be controlled. In general, failures that occur in laminated composite structures can be intralaminar and interlaminar. To date, a lot of models for impact damage in laminates have been developed, with higher or lower accuracy. Those models can replace necessary real and expensive testing in laminated structures with some approximation.
By using specialized software (under specified conditions), the damage parameters in laminate aircraft structures can be predicted and determined.
There are 3 types of impact damage that can occur at the aircraft structure.
The first impact is a low energy impact.
This impact will only create a minor crack or minor fracture & not visible to observe by visual or naked eyes.
The Example for this type of damage is a Dent
The second type of impact is a Medium Energy Impact.
Force energy create half fracture, so half of the panel is broken and the other half is in good condition.
The Example for this type of damage is a Crack
The third type of impact is a High Energy Impact.
Force Energy is higher than the panel strength & Create through Penetration on the panel. The panel will break into two parts.
The Example for this type of damage is a Fracture
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