• Title/Summary/Keyword: 반디호(Firefly)

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복합재료 선미익 항공기 날개 하중해석

  • Han, Chang-Hwan;Kim, Eung-Tai;Ahn, Seok-Min;Kim, Jin-Won
    • Aerospace Engineering and Technology
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    • v.1 no.1
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    • pp.8-27
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    • 2002
  • In this study, the load analysis of a composite canard aircraft is performed numerically. Excel visual basic program for PC is used to calculate aerodynamic coefficients, loads and moments etc.. The basic data required for the load analysis such as aircraft configuration and dimension, parts and its weight and coordinate etc. are obtained from Catia modeling, measurement or material density. Aircraft weight, center of gravity, inertia moment, structural design speeds, wing load distribution, forces and moments are evaluated by using these data. V-n diagram is also represented for selecting critical loads applied to the wing and fuselage. The V-n diagram is investigated to decide the flight envelope of canard aircraft for design speed VA, VC, VD and load factor +3.8G, -1.52G at maximum weight of 2,573 lbs and sea level. In the future, the results of the wing and fuselage load analysis is to represented by using selected critical loads.

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