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.

拟议的研究的目的是改善飞行中变形飞机系统的空气动力学性能，该飞机系统的最低燃料减少了5％，并将导致绿色的气体减少，这是生态，经济和社会观点的全球范围内兴趣。空气动力学性能以升力增加，减速，提升比增加，从层流到湍流区域的流动过渡延迟表示，并导致所需的燃料减少。 这项研究将使用在主动控制，航空电子学和气相弹性范围的应用研究实验室中现有的设备。这些设备是由Hydra Technologies在墨西哥设计的两个无人机UAS-S4和UAS-S45，两个用于Cessna Citation X Business Firsir的研究飞行模拟器，以及CRJ-700商用飞机，以及亚音速价格 - Prices-Pripssississisisisisisisisisisis Billow Windnel。这两个研究飞行模拟器均由CAE Inc.与飞机制造商合作开发，并配备了由联邦航空管理局（FAA）认证的最高D Flight Dynamics数据。基于这些数据，Larcase团队开发了其内部飞行模拟器（CAE Inc.和Hydra Technologies由于机密性原因尚未提供这些模型）。 这项研究的目标是改善飞机变形表面系统的空气动力学性能，如下： 1。UAS-S4和UAS-S45变形机翼系统开发 将对各种变形翼系统的设计和分析进行空气结构对照研究研究。这些系统将是制造的，并使用台式和价格隧道测试进行实验测试。 这些变形机翼系统将集成在UAS内部飞行模拟器模型上，以获得相对于基线UAS的空气动力学性能，以获得变形UA的空气动力学性能。可以在其军事控制机场与墨西哥的Hydra技术合作在飞行中测试这些系统。 2。塞斯纳引用X和CRJ-700变形水平尾部和翼系统的开发 将对水平尾部和翅膀变形系统的设计和分析进行空气控制研究。 用于设计塞斯纳引用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，将变形的表面系统集成在塞斯纳引用X和CRJ-700的飞行模拟器模型中，以便将其在整个飞行信封上的空气动力学性能与基线水平尾尾和翼系统的空气动力学进行比较。 实际上，为UAS变形机翼系统开发的一些设计和测试概念都可以用于飞机变形水平尾部和翼系统的设计。