基于可靠性的太阳能飞机多学科设计优化

Reliability Based Multidisciplinary Design Optimization of Solar Powered Aircraft

针对太阳能飞机典型任务要求,建立了以总重最小为目标的多学科设计优化模型,考虑飞行性能、能量、重量3个学科的设计变量和相应约束条件。同时考虑设计变量的不确定性影响,将序列优化及可靠性评估方法引入到并行子空间优化过程中,顺序执行可靠性分析和多学科设计优化以提高执行效率。在优化过程中应用响应面近似并不断提高模型精度,降低了计算成本。利用iSIGHT软件搭建求解平台,以欧洲太阳能飞机"HeliPlat"作为算例,验证了分析模型的合理性和优化方法的有效性。基于可靠性的多学科设计优化框架有望用于更贴合工程实际的太阳能飞机设计。

A model of multidisciplinary design optimization （MDO） is established for the typical mission requirements of solar powered aircraft. It takes the total weight as the objective of optimization, considering the design variables and constraints dealt with three main subsystems including flying performance, energy, and weight. Considering the uncertainty of design variables, sequential optimization and reliability assessment （SORA） is introduced to the concurrent subspace optimization （CSSO） process. The reliability analysis and MDO are performed sequentially in order to improve the execution efficiency. The response surface approximate model with updating function is used to reduce the computational cost. The solving architecture is constructed with the iSIGHT software. Taking the European solar powered aircraft ＂HeliPlat＂ as an example, the rationality of the MDO model and the effectiveness of the proposed method are validated. The reliability based MDO framework can be applied to practical engineering solar powered aircraft design.