Abstract
Lattice structures based on unidirectional composite ribs is currently one of the most promising directions of research aiming to create lightweight and reliable structure of future aircrafts [1]. Hybrid structure concepts based on lattice layouts have been developed for a number of conventional and non-conventional civil aircraft configurations, giving up to 15-20% weight saving as compared to conventional composite structures based on laminated skin and stiffeners [2]. One of the most critical problems of load-bearing lattice composite structures is very high sensitivity to impact loads, which is even more crucial than for the laminated composite structures. At the same time, topology of lattice grid makes it possible to create reliable protective system for the ribs, which can be effective in terms of weight expenses.
Highlights
The impact resistance requirements for a rib composite structure can be satisfied by providing a reliable protection system for the loadbearing ribs against impact influence
The samples of ribs had a square cross-section on the side H = 8 mm, protective caps were made in several versions with different heights and porosity of the internal structure. 2
Tests of each of the samples were carried out according to the following procedure: Input non-destructive testing Installation of a protective cap on the sample and winding with an elastic band Installation of the specimen in the locking device Application of impact damage Removing protective elements Output non-destructive testing
Summary
The impact resistance requirements for a rib composite structure can be satisfied by providing a reliable protection system for the loadbearing ribs against impact influence. 1 Multilevel protection system of the loadbearing rib of lattice composite fuselage structure The main protective elements should be applied only on the faces of the loadbearing ribs adjacent to the outer/inner skin.
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