考虑短舱安装参数的全机气动外形优化设计

许丹阳; 白俊强; 雷锐午

doi:10.7652/xjtuxb201904022

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考虑短舱安装参数的全机气动外形优化设计

更新时间：2025-07-09

- 考虑短舱安装参数的全机气动外形优化设计
- An Aerodynamic Shape Optimization Design of the Full Configuration Considering Nacelle Installation Parameters
- 西安交通大学学报 2019年53卷第4期页码：150-157
- 作者机构：
  
  西北工业大学航空学院,西安,710072
- 作者简介：
- 基金信息：
  
  : 2018-09-13。作者简介: 许丹阳(1996—),女,硕士生;白俊强(通信作者),男,教授,博士生导师。基金项目: 航空工业航空科学基金资助项目(20161453011)
- DOI：10.7652/xjtuxb201904022
  中图分类号： V211
- 网络首发：2019-04-10，
  
  纸质出版：2019
- 稿件说明：
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许丹阳, 白俊强, 雷锐午. 考虑短舱安装参数的全机气动外形优化设计[J]. 西安交通大学学报, 2019,53(4):150-157.

An Aerodynamic Shape Optimization Design of the Full Configuration Considering Nacelle Installation Parameters[J]. 2019, 53(4): 150-157.
许丹阳, 白俊强, 雷锐午. 考虑短舱安装参数的全机气动外形优化设计[J]. 西安交通大学学报, 2019,53(4):150-157. DOI： 10.7652/xjtuxb201904022.

An Aerodynamic Shape Optimization Design of the Full Configuration Considering Nacelle Installation Parameters[J]. 2019, 53(4): 150-157. DOI： 10.7652/xjtuxb201904022.

摘要

针对跨声速宽体客机机翼、机身、短舱、挂架、平尾、垂尾全机构型中各部件之间存在的气动干扰和力矩耦合问题

采用多块拼接自由变形(FFD)方法进行全机多部件的参数化

利用雷诺平均Navier-Stokes方程(RANS)进行流场求解

结合离散伴随技术和序列二次规划优化算法进行考虑短舱安装参数变化和平尾配平的气动外形优化设计。经过优化之后

短舱附近机翼的压力分布形态变光顺

设计点阻力减小3.82%

并且获得了无激波的压力分布形态。

Abstract

An aerodynamic optimization research of multi-component coupling design is carried out for the aerodynamic interference and torque coupling problems in the full configuration. The components are parameterized by the multiblock free form deformation(FFD)method and Reynolds-averaged Navier-Stokes(RANS)method is used to evaluate the aerodynamics of the aircraft. The derivative of an aerodynamic objective function and geometric constraints on the large-scale design variables are obtained quickly and efficiently by using a discrete adjoint technique. Bases on a sequence quadratic programming algorithm(SQP)

the aerodynamic optimization design considering the nacelle position change and tail-twist trimming is performed. Optimization result shows that the aerodynamic interference between the nacelle and the wing is slightly reduced

the design point resistance reduces by 3.82%

and the shock free pressure distribution is obtained.

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references

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