Robust design and analysis of a conformal expansion nozzle with inverse-design idea  

作　　者：Wenbiao GAN Xiaocui ZHANG Tielin MA Qinling ZHANG Wu YUAN 

机构地区：[1]Research Institute of Unmanned System,Beihang University [2]The First Aircraft Institute,Aviation Industry Corporation of China [3]Computer Network Information Center,Chinese Academy of Sciences

出　　处：《Chinese Journal of Aeronautics》2018年第1期79-88,共10页中国航空学报（英文版）

基　　金：co-supported by the Aeronautical Science Foundation of China(No.2016ZA51003);Aerospace Science and Technology Foundation of China(No.2017129001);National Key R&D Program of China(No.2016YFB1200100);National Natural Science Foundation of China(No.11502267)

摘　　要：This paper examines robust optimization design and analysis of a conformal expansion nozzle of flying wing Unmanned Aerial Vehicle （UAV） with the inverse-design idea. In view of flow features and stealth constraints, the inverse-design idea is described and the uncertainty-based robust design model is presented. A robust design system employs this model to combine deterministic optimization and robust optimization and is applied into design of a conformal expansion nozzle. The results indicate that design optimization can conform to the anticipation of the inversedesign idea and significantly improve the aerodynamic performance that meet the requirement of 6σ. The present method is a feasible nozzle design strategy that integrates robust optimization and inverse-design.This paper examines robust optimization design and analysis of a conformal expansion nozzle of flying wing Unmanned Aerial Vehicle （UAV） with the inverse-design idea. In view of flow features and stealth constraints, the inverse-design idea is described and the uncertainty-based robust design model is presented. A robust design system employs this model to combine deterministic optimization and robust optimization and is applied into design of a conformal expansion nozzle. The results indicate that design optimization can conform to the anticipation of the inversedesign idea and significantly improve the aerodynamic performance that meet the requirement of 6σ. The present method is a feasible nozzle design strategy that integrates robust optimization and inverse-design.

关 键 词：Aerodynamic analysis Inverse-design NOZZLE OFF-DESIGN Robust optimization 

分 类 号：V279[航空宇航科学与技术—飞行器设计]