Concepts for truss based aerofoil constructions

Thulasi Durai, D and Venkatesh, S and Byji, Varughese and Ramanaiah, B and Dayananda, GN (2009) Concepts for truss based aerofoil constructions. Technical Report. NAL.

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Abstract

This report presents the preliminary studies for introducing advanced light weight truss based structural concepts in civil aircraft structures. The structure is an unconventional structure with Iso-truss T-section spar, rib and orthogonal grid skin which replaces full web J- - section spar and rib. The role of the skin is mainly to obtain aerodynamic shape and transfer the load to the sub structure. The skin buckling is avoided by introducing the orthogonal grid. The main loading members are rib and spar. A truss based test box has been designed, analyzed, fabricated and tested between stations 1 to 4 on LHS of HT in GFRP material. The overall dimension of the fabricated box is 780 mm* 1260 mm* 192mm, which includes four truss rib stations, four truss spars, and three skin stiffeners. Tensile tests have been carried out on GRFP laminates and elemental truss elements for arriving at the material property. A static deflection test has been carried out for PSD Gust case which is the critical load case for a typical civil aircraft HT which has magnitude of load in the order of 1177 Kg on LHS and 491 Kg on RHS. The GFRP segment is loaded upto 40% of critical load of LHS where maximum deflection of 21.4mm was observed experimentally. The deflections are monitored at the tip station 4 and compared with FE model.

Item Type: Proj.Doc/Technical Report (Technical Report)
Uncontrolled Keywords: Truss structure,Glass braids,Static testing
Subjects: CHEMISTRY AND MATERIALS > Composite Materials
Division/Department: Advanced Composites Division , Advanced Composites Division, Advanced Composites Division, Advanced Composites Division, Advanced Composites Division
Depositing User: Mr. Guest NAL
Date Deposited: 27 Jul 2010 10:30
Last Modified: 27 Jul 2010 10:30
URI: http://nal-ir.nal.res.in/id/eprint/8770

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