近地阶段飞机尾涡流场的人工干预机理与减缓措施研究

The purpose of this proposal is aimed at solving the limitation of aircraft wake vortex on following aircraft’s flight safety and airport capacity when leading aircraft is in ground proximity phase. The method of numerical simulation is used on Tianhe Supercomputer to construct aircraft flow field numerical simulation environment. Based on this platform, the internal evolution mechanism, influence factors of aircraft flow field within approximate ground height are studied, together with the research of artificial intervention of wake decay. And then, the optimal layout and size parameters of wake interference plates are studied for speeding up the decay rate of wake vortex strength. Furthermore, a typical airport operation data are used for assessment and evaluation the flight safety, interference effect and operational feasibility of wake interference plates. This project research is expected to shed light on the ground of the secondary vortex induced mechanism, and through the secondary vortex with wake vortex coupling to speed up the inner mechanism of the wake dissipated, and for drafting interference plate to provide theoretical basis for the layout and size optimization. This research can be used for accelerating the decay speed of wake vortex, alleviate the pressure of the busy airport capacity bottlenecks and delays is of great significance. The research can also provide necessary theoretical basis and technical support for drafting interfere with the plate design, evaluation and validation for the start-up and development of emerging industries such as the necessary scientific basis and technical support.

针对在近地阶段飞机尾涡流场对后机飞行安全的影响、以及对机场起降容量的限制问题，本项目采用数值模拟方法在“天河”计算平台上开展近地阶段飞机尾涡流场的内在演变机理、影响因素和人工干预方法研究，以及尾流干扰板的布局与尺寸的优化问题实验研究，并以典型机场的运行数据为例从超障安全性、运行可行性和干扰效果等方面进行评估与仿真。项目研究预期可揭示地面二次涡的诱发机制，以及通过二次涡与尾流主涡的耦合影响来加快尾流消散的内在机理，为在跑道外布置干扰板以加快尾流强度消散提供必要的理论依据和技术支持。项目研究对于加快近地阶段尾流的消散以缩短尾流间隔、缓解繁忙机场容量瓶颈与航班延误压力具有重要的现实意义，同时也可为尾流干扰板的设计、评估和验证等新兴产业的启动与发展提供必要的科学依据和技术基础。

针对在近地阶段飞机尾涡流场对后机飞行安全的影响、以及对机场起降容量的限制问题，采用数值模拟方法在“天河”计算平台上构建飞机尾涡流场数值模拟实验环境，开展了近地阶段飞机尾涡流场的内在演变机理、影响因素和人工干预方法研究，以及尾流干扰板的布局与尺寸的优化问题实验研究，并以典型机场的运行数据为例从超障安全性、运行可行性和干扰效果等方面进行评估与仿真。项目研究预期可揭示地面二次涡的诱发机制，以及通过二次涡与尾流主涡的耦合影响来加快尾流消散的内在机理，为在跑道外布置干扰板以加快尾流强度消散提供必要的理论依据和技术支持。项目研究对于加快近地阶段尾流的消散以缩短尾流间隔、缓解繁忙机场容量瓶颈与航班延误压力具有重要的现实意义，同时也可为尾流干扰板的设计、评估和验证等新兴产业的启动与发展提供必要的科学依据和技术基础。