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

发展变形翼是世界航空航天工业的战略性研究。其目的是通过改变飞行中机翼的形状来提高飞机的气动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宇航公司合作开发概念变形机翼原型。基于变几何桁架机构原理，研制了一种变几何翼盒机构，建立了两模块系统并进行了试验。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。为了将变形小翼连接到机翼上，第一个模块必须安装到机翼的狭窄干燥部分中，从而施加了严格的空间限制。该模块驱动第二模块，即小翼，需要具有高机械效益的致动系统，从而施加重量约束。实际考虑包括：i）不同的变形选项，包括斜面和前束组合、单独斜面、各种运动范围、在小翼处的柔性后缘与斜面组合、柔性后缘，以权衡重量和复杂性与空气动力学益处; ii）确保所提出的系统从机械角度是可行的; iii）定义变形小翼的重量损失;以及iv）提供具有尺寸适合于真实的负载的致动器的全尺寸原型。拟议的方法将通过三个研究支柱：设计，分析和原型开发。设计支柱的目标是通过利用包括欠驱动、静平衡和柔性后缘在内的技术来克服空间和重量限制。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，研究各种变形方案，以评估重量和复杂性对空气动力学效益的影响，并帮助找到最佳设计。原型支柱的目标是构建和测试全尺寸变形小翼，以演示变形小翼技术。通过这个项目，将培养一批从PDF、博士、硕士到本科的HQP。通过该项目取得的研究成果将使加拿大在变形研究方面处于领先地位。

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.