航空科学技术2025，Vol.36Issue(2)：38-45,8.DOI:10.19452/j.issn1007-5453.2025.02.003
受油机构型的尾涡危险区域影响分析
Analysis on Tail Vortex Risk Area Affected by Follower Configuration
摘要
Abstract
The stability and safety of the follower are the key issues in the implementation of unmanned aerial refueling technology.In order to successfully realize the autonomous docking technology of the follower,it is necessary to divide the dangerous area of the tail vortex behind the oil tanker.In this paper,the rolling moment coefficient of the follower is used as the risk criterion of the tail vortex after the tanker.When calculating the rolling moment coefficient,this paper selects different string length distribution simplification formulas for different wing shapes,and proposes the lift line slope correction formula for three wing shapes according to the tail vortex encounter,and uses the strip method for integral operation.The danger zone and the safety zone are divided as the safety threshold,and the criterion for dividing the tail vortex danger zone is established.On the premise of the same parameters of the aircraft,this paper analyzes the influence of the wing shape of different oil engines on the area of the danger area,and the influence of the trapezoidal wing on the area of the danger area.By reanalyzing the range of danger area and danger degree of different types of follower after CRM tanker of large transport aircraft,it is found that the danger area of large follower is large and low dangerous,and almost not affected by the flat tail vortex,while the danger area of small and medium-sized follower is small and highly dangerous,and is affected by the flat tail vortex within the half wingspan distance of the tanker.This paper provides technical support and theoretical basis for the implementation of autonomous aerial refueling technology based on the classification of wake vortex danger areas with different follower configurations.关键词
尾涡遭遇/滚转力矩系数/弦长分布公式/升力线斜率/条带状法/危险区域Key words
tail vortex encounter/rolling moment coefficient/string length distribution formula/lift line slope/strip method/dangerous area分类
航空航天引用本文复制引用
王玉琰,肖峰,刘峰博,张文豪,梁益华..受油机构型的尾涡危险区域影响分析[J].航空科学技术,2025,36(2):38-45,8.基金项目
航空科学基金(2023M006031001) （2023M006031001）
陕西省自然科学基础研究计划(2024JC-YBQN-0070) Aeronautical Science Foundation of China(2023M006031001) （2024JC-YBQN-0070）
Shaanxi Provincial Natural Science Basic Research Program(2024JC-YBQN-0070) （2024JC-YBQN-0070）
