在翼身融合布局客机总体设计阶段，为评估设计方案的总体性能，建立了翼身融合布局客机总体参数综合分析与优化平台，该平台以翼身融合布局客机的几何参数为输入，完成动力、几何、重量、气动、性能和经济性等模块分析，并以此为基础建立优化设计模型。为快速评估设计方案的性能及优化设计效果，动力分析模块采用了部件级分析模型，重量分析模块采用半经验估算方法，气动分析模块采用面元法结合工程估算方法，性能分析模块采用简化运动学方法，优化模型采用可并行计算的子集模拟优化算法。以某555座级翼身融合布局客机方案为例，应用开发的分析与优化平台，完成了总体参数分析，结果表明分析模型合理。在此方案的基础上，以客机的外形参数和发动机海平面最大推力为设计变量，分别建立了以最大起飞重量最小为目标的单目标优化，以及同时以直接使用成本和进场速度最小为目标的多目标优化，单目标优化结果最大起飞重量降低了约7.17%，多目标优化结果表明直接使用成本降低8.77%的同时进场速度会增加3.32%。
In the conceptual design phase of the blended-body-wing commercial aircraft, a comprehensive analysis and an optimization platform are established to evaluate the overall performance of the design. The platform takes the geometric parameters of the airliner as the input, and completes the analysis of propulsion, geometry, weight, aerodynamics, and performance modules. An optimization model is built based on these modules. In order to efficiently evaluate the performance of the design and conduct the optimization design, the propulsion analysis module adopts a component-based model; semi empirical methods are used in the weight analysis module; the aerodynamics analysis module adopts the panel method combined with the engineering method; a simplified kinematic method is used in the performance analysis module; and the optimization model uses an evolutionary optimization algorithm with the capacity of parallel calculation. A 555-seats blended wing body commercial aircraft is taken as an example to analyze its performance based on the analysis and optimization platform. The results show that the models used in the platform were reasonable. Single objective and multiobjective optimizations are performed based on the initial design, in which the design variables include aircraft geometry parameters and engine maximum take-off thrust. In the single objective optimization, the maximum take-off weight is minimized. In the multiobjective optimization, the direct operating cost, and approach velocity are considered as the objectives simultaneously. The maximum take-off weight of the single objective optimization is reduced by about 7.17% compared to the initial design. The Pareto front for minimizing both the direct operating cost and the approach velocity shows that the DOC decreases by 8.77% while the approach speed increases by 3.32%.
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