Static Stress Analysis And Normal Mode Analysis of Horizontal Tail Structure of An Aircraft Using Analysis Software

Abstract

Aircraft consist of Horizontal tail and elevator at the rear end of the fuselage. Whose job is to provide stability for the aircraft to keep it flying straight. The horizontal stabilizer prevents up-and-down or pitching, motion of the aircraft nose. The material used for construction of horizontal tail are aluminum alloy, titanium alloy, fiber reinforced composites. Now a day's all aircraft manufacturing industry are using composite materials instead of metallic materials. Composite materials are well known for their excellent combination of high structural stiffness and low weight. CFC is seen to have a modulus twice &strength three times that of aluminum alloy, the conventional material used in aircraft construction. In the present work we are going to compare the percentage of weight for both carbon fiber composite material and aluminum alloy 2124 series. The parametric study conducted using Msc Nastran and Hypermesh. From the studies conducted regarding the weight reduction, it is estimated that replacement of Al alloy by CFC results in 54.73% saving in the total structural weight of the aircraft Horizontal Tail. The normal mode analysis the resonance frequency of aircraft is 10Hz but for Horizontal tail the frequency is almost zero so the design is safe.