Structural dynamics and smart helicopter rotor blades

结构动力学和智能直升机旋翼叶片

• 批准号: 41735-2010
• 负责人: Afagh, Fred
• 金额: $ 1.53万
• 依托单位: Carleton University
• 依托单位国家: 加拿大
• 项目类别: Discovery Grants Program - Individual
• 财政年份: 2011
• 资助国家: 加拿大
• 起止时间: 2011-01-01 至 2012-12-31
• 项目状态: 已结题
• 来源: https://www.nserc-crsng.gc.ca/ase-oro/Details-Detailles_eng.asp?id=474884
• 关键词: Structural; dynamics; smart; helicopter; rotor

A major focus of the applicant's research program in the recent years has been the development of a mathematical model for a helicopter smart rotor blade with a high degree of fidelity. Such a model will be used to investigate the possibility of attenuating undesirable dynamic responses associated with operation of helicopter rotor blades. A continuous model of a smart blade has already been developed in the previous phase of this research program. The model represents a thin wall, closed-section, active composite beam that incorporates piezoelectric fibres as actuators that are integrated structurally into a carbon fibre composite to form Macro Fibre Composites (MFC). This proposal has two objectives: 1) the existing model of smart rotor blades does not take into account the effect of initial twist that could be present in modern helicopter rotor blades. This capability will be integrated into the existing mathematical model under the current proposal. Moreover, the idea of using open cross-section thin-wall adaptive beams in various terrestrial and aerospace structures, e.g., rotor blades with spars consisting of adaptive thin-wall open sections, is also being proposed as a novel concept. In the next phase the governing equations to determine the cross-sectional stiffnesses of open-section, thin wall, active MFC beams will also be developed. 2) Investigation of the effectiveness of smart MFC rotor blades to control Blade Sailing Phenomenon (BSP) in ship-board helicopters is the second objective of this proposal. BSP refers to large elastic deformation of blades that can occur at low rpms of rotors on shipboard helicopters, especially under the combined effect of high wind-induced aerodynamic loads and severe ship deck motion at high seas. As the result, the blades can come into contact with the fuselage or tailboom of the helicopter causing substantial airframe damage and comprising the safety of flight crew and the ship deck personnel.

申请人近年来的主要研究方向是开发具有高度保真度的直升机智能旋翼桨叶的数学模型。这样的模型将用于研究衰减与直升机旋翼叶片操作相关的不良动态响应的可能性。在该研究计划的前一阶段，已经开发出智能刀片的连续模型。该模型代表了一个薄壁、封闭截面、主动复合材料梁，其中包含压电纤维作为驱动器，在结构上集成到碳纤维复合材料中，形成宏纤维复合材料（MFC）。该建议有两个目的：1)现有的智能旋翼叶片模型没有考虑到现代直升机旋翼叶片中可能存在的初始扭转的影响。根据目前的建议，这种能力将被纳入现有的数学模型。此外，在各种地面和航空航天结构中使用开截面薄壁自适应梁的想法，例如，由自适应薄壁开截面组成的翼梁的转子叶片，也被作为一种新概念提出。在下一阶段，还将开发用于确定开截面薄壁主动MFC梁截面刚度的控制方程。2)研究智能MFC旋翼控制舰载直升机桨叶航行现象（BSP）的有效性是本文的第二个目标。BSP是指舰载直升机在旋翼转速较低的情况下，特别是在高风致气动载荷和船舶甲板剧烈运动的共同作用下，桨叶会发生较大的弹性变形。因此，叶片可能会接触到机身或直升机尾梁，造成机身严重损坏，并危及机组人员和舰载甲板人员的安全。