Re-engineering of a Helicopter Structural Components Using Laminated Composite Materials Based on Crashworthiness Concepts

Crashworthiness of aircraft and helicopter structures in terms of impact energy absorption is a fundamental design consideration in structural design of such a flight vehicles. In fact, crashworthiness of the lower fuselage structure is often considered as a key factor in assessing damages and hazards encountered in emergency landing cases. This reseach focused on a structural component of a naval utility helicopter, in which an aluminium structural component attached to the seats is considered for re-engineering to achieve an improved safety. This structural component has a significant effect on impact energy in vertical crash of the helicopter to the ground or sea water surface. In this respect, the origional metallic component is repalced by a laminated composite material one, and its effect on structural weight, cost and maintenance and repair are studied. Computer simulations as well as experimental tests are performed to validate the superior characteristics of the re-engineered component. The results show the re-engineered component has improved safety factors, weight and manufacturing cost when compared to the origional one.