Improvement of experimental capabilities in aerodynamic control

气动控制实验能力提升

• 批准号: RTI-2019-00323
• 负责人: Sullivan, Pierre
• 金额: $ 4.83万
• 依托单位: University of Toronto
• 依托单位国家: 加拿大
• 项目类别: Research Tools and Instruments
• 财政年份: 2018
• 资助国家: 加拿大
• 起止时间: 2018-01-01 至 2019-12-31
• 项目状态: 已结题
• 来源: https://www.nserc-crsng.gc.ca/ase-oro/Details-Detailles_eng.asp?id=666172
• 关键词: Improvement; experimental; capabilities; aerodynamic; control

Within current aerospace design, it is necessary to over-engineer features to ensure stability and safety under emergency conditions. It would be ideal to develop capabilities to reduce the size of large elements of commercial aircraft with reliable technologies that ensure safe operation under hazardous conditions. Most major***aerospace corporations are pursuing this technology in various forms. The proposed use of active control would allow fixed-wing geometries that through careful aerodynamic flow control mimic the behaviour of flaps and other external mechanisms. Focusing on the vertical tail of modern aircraft, this provides directional stability within cross-winds, the ability of the aircraft to resist slipping into a relative wind not aligned with the longitudinal axis of the aircraft. The size of the vertical tail is often sized for the shortest version of a model family and is oversized for longer aircraft in the series. In the case of engine failure, the tail provides trim to create drag. If it were possible to delay or eliminate flow separation over a highly deflected rudder thereby improving the side force created by the vertical tail, it would be possible to significantly reduce the size of the vertical tail and would allow improved control and better fuel economy To do this, it is necessary to modernize the existing wind tunnel with a modern motor and control and a high capacity particle image velocimetry system for measurement. The tunnel is not operational at this time and this is crucial to the ongoing research needs of students.***This is crucial to the long-term viability of the tunnel and access by HQPs of this unique resource.

在目前的航空航天设计中，有必要对功能进行过度设计，以确保在紧急情况下的稳定性和安全性。理想的做法是发展能力，利用可靠的技术缩小商用飞机大型部件的尺寸，确保在危险条件下安全运行。大多数主要的航空航天公司都在以各种形式追求这项技术。主动控制的建议使用将允许固定翼几何形状，通过仔细的气动流动控制模仿襟翼和其他外部机构的行为。关注现代飞机的垂直尾翼，这提供了侧风内的方向稳定性，飞机抵抗滑入与飞机纵向轴线不对准的相对风的能力。垂尾的尺寸通常是为最短的型号系列设计的，而为系列中较长的飞机设计的尺寸则过大。在发动机故障的情况下，尾翼提供配平以产生阻力。如果有可能延迟或消除大偏转方向舵上的气流分离，从而改善垂尾产生的侧向力，就有可能显著减小垂尾的尺寸，并允许改进控制和更好的燃料经济性。因此，有必要对现有的风洞进行现代化改造，使之具有现代化的发动机和控制系统，以及高容量的粒子图像测速系统，以便测量.隧道目前尚未投入使用，这对学生正在进行的研究需求至关重要。这对隧道的长期可行性和HQP使用这一独特资源至关重要。