Green Aircraft Performance Analysis using Morphing Systems Modeling and Experimental Validation

使用变形系统建模和实验验证进行绿色飞机性能分析

• 批准号: RGPIN-2020-05949
• 负责人: Botez, Ruxandra
• 金额: $ 2.84万
• 依托单位: École de technologie supérieure
• 依托单位国家: 加拿大
• 项目类别: Discovery Grants Program - Individual
• 财政年份: 2020
• 资助国家: 加拿大
• 起止时间: 2020-01-01 至 2021-12-31
• 项目状态: 已结题
• 来源: https://www.nserc-crsng.gc.ca/ase-oro/Details-Detailles_eng.asp?id=718118
• 关键词: Green; Aircraft; Performance; Analysis; using

The proposed research has the aim to improve the aerodynamic performances of morphing aircraft systems in flight that would conduct to minimum fuel reduction of 5%, and would result in green gas-house reduction, that is of high worldwide interest from ecological, economical and social points of view. The aerodynamic performances are expressed in terms of lift increase, drag reduction, lift to drag ratio increase, flow transition delay from laminar to turbulent region, and would result in desired fuel reduction. This research will use the equipments existing at the Laboratory of Applied Research in Active Controls, Avionics and AeroServoElasticity LARCASE. These equipments are two Unmanned Aerial Systems UAS-S4 and UAS-S45 designed by Hydra Technologies in Mexico, two research flight simulators for the Cessna Citation X business aircraft, and for the CRJ-700 commercial aircraft, and the subsonic Price-Padoussis blow down wind tunnel. Both research flight simulators were developed by CAE Inc. in collaboration with aircraft manufacturers, and are equipped with highest level D flight dynamics data certified by the Federal Aviation Administration (FAA). Based on these data, the LARCASE team developed their in-house flight simulators (CAE Inc. and Hydra Technologies have not delivered these models due to confidentiality reasons). The objectives of this research are to improve the aerodynamic performances of the morphing surface systems of aircraft, as follows: 1. UAS-S4 and UAS-S45 Morphing Wing Systems Development Aero-Structural-Controls interactions studies will be performed for the design and analysis of various morphing wing systems. These systems will be manufactured, and experimentally tested using bench, and Price-Padoussis wind tunnel tests. These morphing wing systems will be integrated on both UAS in-house flight simulator models in order to obtain the aerodynamic performance of the morphing UAS with respect to the aerodynamic performance of the baseline UAS. It will be possible to test in flight these systems in collaboration with Hydra Technologies in Mexico on their military controlled airport. 2. Cessna Citation X and CRJ-700 Morphing Horizontal Tail and Winglet Systems Development Aero-Controls studies will be performed for the design and analysis of horizontal tail and winglet morphing systems. The methodology used to design the in-house flight simulator model for the Cessna Citation X will be adapted to design the CRJ-700 in-house aircraft simulator model. Then, the morphing surface systems will be integrated on the flight simulator models of the Cessna Citation X and CRJ-700 in order to compare their aerodynamic performance on the whole flight envelope in comparison with those of the baseline horizontal tail and winglet systems. In fact, some of the design and testing concepts developed for UAS morphing wing systems could be used in the design of both aircraft morphing horizontal tail and winglet systems.

所提出的研究的目的是改善变形飞机系统在飞行中的空气动力学性能，将进行最小的燃料减少5%，并将导致绿色燃气室减少，这是从生态，经济和社会的角度来看，具有很高的全球利益。气动性能用升力增加、阻力减小、升阻比增加、层流到湍流区的流动过渡延迟来表示，并将导致期望的燃料减少。 这项研究将使用现有的设备在主动控制，航空电子和航空伺服弹性LARCASE应用研究实验室。这些设备是由墨西哥Hydra Technologies设计的两个无人机系统UAS-S4和UAS-S45，两个用于Cessna Citation X商用飞机和CRJ-700商用飞机的研究飞行模拟器，以及亚音速Price-Padoussis吹风风洞。这两种研究飞行模拟器都是由CAE公司开发的。与飞机制造商合作，并配备了由联邦航空管理局（FAA）认证的最高级别D飞行动力学数据。基于这些数据，LARCase团队开发了他们的内部飞行模拟器（CAE Inc.由于保密原因，Hydra Technologies尚未交付这些模型）。 本研究的目的是改善飞机变形曲面系统的气动性能，具体如下： 1. UAS-S4和UAS-S45变形机翼系统的研制 气动-结构-控制相互作用研究将用于各种变形机翼系统的设计和分析。这些系统将被制造，并使用台架和Price-Padoussis风洞测试进行实验测试。 这些变形机翼系统将集成在两个UAS内部飞行模拟器模型上，以获得变形UAS相对于基线UAS的空气动力学性能的空气动力学性能。将有可能与墨西哥的Hydra技术公司合作，在其军事控制的机场上对这些系统进行飞行测试。 2. Cessna Citation X和CRJ-700改型平尾和小翼系统的研制 将进行航空控制研究，以设计和分析水平尾翼和小翼变形系统。 用于设计Cessna Citation X内部飞行模拟器模型的方法将适用于设计CRJ-700内部飞机模拟器模型。然后，变形曲面系统将被集成到Cessna Citation X和CRJ-700的飞行模拟器模型上，以便将它们在整个飞行包线上的空气动力性能与基准平尾和小翼系统的空气动力性能进行比较。 事实上，为无人机变形机翼系统开发的一些设计和试验概念可用于飞机变形平尾和小翼系统的设计。