Honeycomb Sandwich Panel Case Study

The main objective of this work is to characterize the strength of a honeycomb sandwich panel according to the type and time of curing and to the core-skin bonding.
This project aims to find a good setup of core and skin of a sandwich panel for future aeronautical applications that fulfil the resistance requirements. It is necessary to ensure a solid bond or adhesion between the honeycomb core and skin in order to achieve these high aeronautical requirements.
For this reason, it is very important the type of curing of the sandwich panel once have been joined the different layers, as well as the nature of the layers that are placed between the core and the skin to enhance bonding, and thus upgrade the final properties of the composite.
First of all, the different applications of sandwich panels in the aeronautical sector will be explained. Then, the current theoretical framework will be discussed, as well as the existing methods of manufacturing.
The objective is to see how the actual market for composite materials in the aerospace sector is developing and
External structures face a wide range of operational temperatures and high aerodynamic loads. Radomes and leading edge fairings are exposed to impacts due to bird strike and hail, lightning strikes and abrasion caused by rain and dust. Moreover electromagnetic transmissibility for radar and avionics is required. Foreign object damage (FOD) caused by runway debris is a characteristic threat for all surfaces on the lower side of the aircraft. Floor panels in the passenger compartment must withstand transverse, discrete loads caused by passengers. These examples underline the diversity of operational and environmental requirements for the different sandwich applications. It is crucial to be aware of the different requirements early in the design process in order to develop an appropriate structure accordingly.