力学与实践 ›› 2020, Vol. 42 ›› Issue (6): 726-730.DOI: 10.6052/1000-0879-20-254

• 应用研究 • 上一篇    下一篇

飞机方案设计阶段机动载荷快速计算方法研究

张建刚1), 何康乐, 金鑫   

  1. 中国航空工业集团公司第一飞机设计研究院,西安 710089
  • 收稿日期:2020-06-16 出版日期:2020-12-20 发布日期:2020-12-20
  • 通讯作者: 1) 张建刚,高级工程师,主要从事飞机强度及载荷设计研究。E-mail: 155246438@qq.com

A FAST CALCULATION METHOD OF MANEUVERING LOAD IN AIRCRAFT SCHEME DESIGN STAGE

ZHANG Jiangang1), HE Kangle, JIN Xin   

  1. The First Aircraft Institute of the Aviation Industry Corporation of China, Xi'an 710089, China
  • Received:2020-06-16 Online:2020-12-20 Published:2020-12-20

摘要: 提出了一种在方案阶段能快速准确预估飞机设计机动载荷的简捷计算方法。通过静气弹理论计算飞机的气动导数,以气动导数、操纵特性和质量特性为输入对飞机进行了机动模拟,得到各运动参数的时间历程,最后用涡格法计算出部件的分布载荷。将本文的计算结果与后续的传统方法计算结果进行比较,结果表明该方法是准确可靠的,能满足方案阶段飞机设计的载荷需求。该方法在方案阶段能有效克服传统方法需要大量的风洞试验得来的气动特性数据和压力分布数据的不足。本文的方法只需要较少的输入参数就可以进行,可在型号研制中节省时间,加快研制进度。

关键词: 机动载荷, 静气弹, 气动导数, 机动模拟, 分布载荷

Abstract: A simple calculation method is proposed in this paper to quickly and accurately predict the design maneuver load of an aircraft in the preliminary design stage. Aerodynamic derivatives of the aircraft are calculated based on the static aeroelastic theory, and the maneuver simulation of aircraft is carried out with the aerodynamic derivatives, the control characteristics and the mass characteristics as the input. The time history of each motion parameter is obtained. Finally, the distributed load on the components is calculated by the vortex lattice method. The results of this paper are compared with those of traditional methods. It is shown that this method is accurate and reliable, and can meet the load requirements of the aircraft design in the preliminary design stage. This method can effectively overcome the shortcomings of the traditional method which needs a large number of data of aerodynamic characteristics and pressure distribution to be obtained in wind tunnel tests. With the method in this paper, calculations can be carried out with fewer input parameters, which can save time and speed up the development of the model.

Key words: maneuver load, static aeroelastic, aerodynamic derivative, simulation of maneuver, distributed load

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