- 作者: 李家騵
- 作者服務機構: 空軍航空工業發展中心
- 中文摘要: 本文旨在引用正型法(normal mode method)探討一夾心式(samdwich)旋翼在其母體直升機平飛時沿翼展所發生之橫向振動以及旋翼內部所生之應力情況。 討論時步驟為 〈1〉求在平飛時沿翼展之空氣負荷。 〈2〉視夾心旋翼為一彈性樑,求旋轉時之mass matrix與stiffness matrix。 〈3〉求旋翼自由橫向振動時之頻率及振型。 〈4〉求旋翼在空氣負荷下之橫向振動情況,考慮阻尼在內。 〈5)求旋翼各部所受之力矩與剪力。 (6)求鋁合金外皮與鋁蜂窩夾心旋翼其所受之抗拉應力與抗剪應力。
- 英文摘要: This paper presents(1). an analysis of the transverse vibration of arotor-blade considering visecus Ano structural damping in forward flightand (2). an analysis of corresponding stress distributions within the bladesections. The rotor-blade will have a bonded sandwich structure composedof Al. alloy facings and Al. honeycomb core. The sequence of analysis is to find (1) the air loading along bladespan (2) the mass and stiffness matrices considering blade rotion, (3) frequ-encies and mode shapes of free transverse vibration, (4) displacement-timerelation under forced vibration (5) moments and shear forces within bladeand finally (6) normal stresses in facing and shear stresses in core.
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