Development of a full-size morphing winglet with space and weight constraints

开发具有空间和重量限制的全尺寸变形小翼

• 批准号: 490715-2015
• 负责人: Xi, Fengfeng
• 金额: $ 8.74万
• 依托单位: Ryerson University
• 依托单位国家: 加拿大
• 项目类别: Collaborative Research and Development Grants
• 财政年份: 2017
• 资助国家: 加拿大
• 起止时间: 2017-01-01 至 2018-12-31
• 项目状态: 已结题
• 来源: https://www.nserc-crsng.gc.ca/ase-oro/Details-Detailles_eng.asp?id=618525
• 关键词: Development; full; size; morphing; winglet

Development of morphing wings is a strategic research for aerospace industry worldwide. The goal is to improve the aerodynamic performance and minimize the fuel consumption by changing the shape of the aircraft wing on-the-fly. For the last three years, Ryerson had worked on a conceptual morphing wing prototype in collaboration with Bombardier Aerospace. A variable geometry wingbox (VGWB) based on the principle of variable geometry truss mechanism (VGTM) was developed and a two-module system was built and tested. In this project, we propose applying this technology to develop a full-size morphing winglet. To attach a morphing winglet to the wing, the first module will have to fit into a narrow dry section of the wing, imposing a tight space constraint. This module drives the second module, i.e. winglet, requiring an actuation system with high mechanical advantage, thus imposing a weight constraint. The practical considerations include: i) different morphing options including cant and toe combined, cant alone, various ranges of motion, flexible trailing edge at the winglet combined to cant, flexible trailing edge, to trade weight and complexity against aerodynamics benefit; ii) ensure that the proposed system is feasible from a mechanical perspective; iii) define the weight penalty of the morphing winglet; and iv) deliver a full scale prototype with actuators sized for the real loads. The proposed methodology will be developed through three research pillars: design, analysis and prototyping. The goal of the design pillar is to overcome the space and weight constraints through utilization of technologies including under-actuation, static balancing and flexible trailing edge. The goal of the analysis pillar is to develop a kineto-structural-aerodynamics analysis method looking at various morphing scenarios to evaluate weight and complexity against aerodynamics benefit and help find an optimal design. The goal of the prototyping pillar is to construct and test a full-size morphing winglet to demonstrate the morphing winglet technology. Through this project a number of HQP from PDF, PhD, Master's to undergraduate will be trained. Research results achieved through this project would put Canada in a leading position of morphing research.

可变形机翼的发展是世界航空航天工业的一项战略性研究。其目标是通过改变飞行中机翼的形状来提高空气动力学性能，并最大限度地减少燃油消耗。在过去的三年里，瑞尔森一直在与庞巴迪航空航天公司合作开发一种概念性变形机翼原型。基于变几何桁架机构（VGTM）原理研制了一种变几何翼箱（VGWB），并对其两模块系统进行了搭建和测试。在这个项目中，我们建议应用这项技术来开发一个全尺寸的变形小翼。为了将变形小翼安装到机翼上，第一个模块必须安装在机翼的一个狭窄的干燥部分，这对空间施加了严格的限制。该模块驱动第二个模块，即小翼，需要具有高机械优势的驱动系统，从而施加重量约束。实际考虑因素包括：i)不同的变形选择，包括前肢和趾部的组合、前肢单独、各种运动范围、小翼灵活的后缘与前肢的结合、灵活的后缘，以权衡重量和复杂性与空气动力学的好处；Ii)确保拟议的系统从机械角度来看是可行的；Iii)定义变形小波的权重惩罚；iv)提供一个全尺寸的原型与执行器的实际负载大小。提出的方法将通过三个研究支柱：设计、分析和原型设计来发展。设计支柱的目标是通过利用欠驱动、静平衡和柔性后缘等技术来克服空间和重量的限制。分析支柱的目标是开发一种运动-结构-空气动力学分析方法，研究各种变形情况，以评估空气动力学效益的重量和复杂性，并帮助找到最佳设计。原型支柱的目标是构建和测试一个全尺寸的变形小翼，以演示变形小翼技术。通过该项目将培养一批从PDF、博士、硕士到本科生的高素质人才。通过该项目的研究成果将使加拿大在变形研究方面处于领先地位。