考虑多重不确定性的机体/进排气稳健设计机制研究

Airframe/intake-exhaust is always used in advanced aircraft such as new bombers, sensorcraft. Airframe/intake-exhaust design has attracted increasing attention and made significant progresses. However, a certainty design mechanism is widely used in current studies and it neglect some important uncertainty factors such as the manufacturing tolerance, fight disturbance and the error of aerodynamic analysis method. This mechanism is not suitable for the essence and robust requirements of aerodynamic design. For this reason, the project aims to consider uncertainty factors to research the new robust design mechanic. For airframe/intake-exhaust system, a fundamental principle model, where fuzzy optimization method is combined with multilevel collaborative method, will be established, meanwhile, a modified numerical simulation method also will be developed in order to acquire a fuzzy evidence theory about numerical analysis. Based on those studies, the robust design framework and the optimization process of airframe/intake-exhaust can be established, which form a complete design mechanism and realize the organic unification of multi-level physical mechanism analysis and fuzzy optimization processes. And then, an example of airframe/intake-exhaust design will be practiced to verify the principle of the design mechanism. In a word, the project aims to deeply investigate the uncertainty of the aerodynamic mechanism to explore a new approach of airframe/intake-exhaust design, which is beneficial for keeping the sustainable development of the aerodynamic design and is considerable important for the research and development of advanced aircraft .

机体/进排气融合布局广泛应用于新型轰炸机、传感器飞机等先进飞行器，其设计研究受到了人们的广泛关注并取得了长足进步。但是，现有研究往往采用确定性设计机制，忽视了制造公差、飞行状态扰动和气动分析误差等不确定性影响，偏离了气动设计的实质和稳健性需求。为此，本项目考虑多重不确定性，开展机体/进排气稳健设计新机制研究；针对机体/进排气，建立分层协同与模糊优化相结合的基础原理模型；通过发展改进的数值模拟方法，形成数值模拟分析的模糊证据理论；在此基础之上，构建稳健设计架构及优化流程，形成完整的设计机制，实现物理机理和模糊优化的有机统一，并通过相关实例完成设计机制的原理验证。本项目旨在深入不确定性气动机理来探索机体/进排气设计的新途径，有利于保持气动设计领域的可持续发展，对促进先进飞行器的设计研发具有重要意义。

机体/进排气广泛应用于先进飞行器设计领域，长期以来，机体/进排气设计往往采用确定性设计机制，针对这种机制偏离气动设计实质和稳健需求的不足，本项目考虑制造公差、飞行状态扰动等多重不确定性，开展了数值模拟分析证据理论方法、稳健设计机制基础原理建模、稳健设计机制架构等研究工作，完成了机体/进排气稳健设计机制研究。项目取得的主要进展有： (1) 采用分离、转捩和压缩性等修正，发展了适用于机体/进排气的改进数值模拟方法，提高了典型进气道、尾喷管和机体/推进一体复杂流动特征和气动特性的模拟精度； (2)针对机体/进排气，通过基于不确定性的模糊优化建模、基于分层协同与模糊优化的结合建模，建立了机体/进排气稳健设计新机制的基础原理模型； (3)建立了稳健设计的架构、完善了架构所需的优化流程，支撑形成了完整的机体/进排气稳健设计新机制，并通过飞翼机体/进排气的S进气道、尾喷管和一体化优化实现了设计机制的原理验证。在本项目支撑下，成果应用于军科委、中科院的重点计划项目，为新型翼身融合飞行器设计提供了基础技术支撑。