基于离散型伴随方法的单边膨胀喷管优化设计研究  

Research on the Optimization of Unilateral Expansion Nozzle Based on the Discrete Adjoint Method

作　　者：宋红超 李鑫[1] 季路成[1] 

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《工程热物理学报》2017年第9期1849-1854,共6页Journal of Engineering Thermophysics

基　　金：国家自然科学基金资助项目(No.51376023;51676015)

摘　　要：目前高超声速喷管的设计方法主要有特征线方法与基于CFD分析的优化设计方法。采用特征线法设计喷管时流动需基于无黏、无旋假设进行简化,无法确保设计结果在真实流动情况下达到最优;采用遗传算法或常规梯度类方法等优化算法进行优化设计时,设计变量数目的增多为设计带来计算量方面极大的挑战。为克服上述方法在设计过程中的不足,依托伴随方法具有计算量与设计变量数目几乎无关的特点,本文发展了基于离散型伴随方法的单边膨胀喷管的设计方法,以控制喷管沿流程的面积分布作为参数化方法,在初步设计的性能优良的原型喷管基础上实现了精细化伴随优化设计,优化后推力系数比原型喷管提升0.8个百分点。At present, the characteristic line method and the optimization method based on the CFD analysis are the mainly methods for hypersonic nozzles designing. However, the characteristic line method can＇t come over the shortcoming of the assumptions that the flow is no-viscosity and no-rotation. Besides, the genetic algorithm and general gradient-based algorithms used for hypersonic nozzles designing can＇t handle the challenges of increasing number of design variables. Considering the calculation cost of the adjoint method isn＇t sensitive with the number of design variables, this paper uses the discrete adjoint method to design the unilateral expansion nozzle, accomplishing the parametric model of controlling the area distribution of the nozzle along the streamline. On the base of the initial nozzle designed by the genetic algorithm, which already has the great performance, the optimization can improve the thrust coefficient with 0.8 percentage points.

关 键 词：离散型伴随方法 单边膨胀喷管 参数化方法 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]