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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 design method of hypersonic nozzle mainly includes the characteristic line method and the optimization design method based on CFD analysis. When using the characteristic line method to design the nozzle, the flow should be simplified based on the non-stick and non-hypothesis assumptions, which can not ensure the optimal design results under the real flow conditions. When using optimization algorithms such as genetic algorithm or the conventional gradient method to optimize the design, The increase in the number of variables poses a significant challenge in terms of the computational complexity of the design. In order to overcome the shortcomings of the above method in the design process and rely on the companion method has almost no relationship between the amount of calculation and the number of design variables, this paper developed a design method of unilateral expansion nozzle based on discrete adjoint method to control the nozzle along the flow As a parameterized method, the fine design of the prototype nozzle with excellent performance was optimized. The optimized thrust coefficient was 0.8% higher than that of the prototype nozzle.