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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。
According to the typical mission requirements of solar powered aircraft, a multidisciplinary design optimization model with minimum total weight was established, and the design variables and corresponding constraints of the three disciplines of flight performance, energy and weight were considered. At the same time, the uncertainties of design variables are considered. The method of sequence optimization and reliability assessment is introduced into the parallel sub-space optimization process, and the reliability analysis and multidisciplinary design optimization are performed sequentially to improve the execution efficiency. In the optimization process, the application of response surface approximation and continuously improve the accuracy of the model, reducing the computational cost. Using iSIGHT software to build a solution platform, taking the European solar aircraft “HeliPlat” as an example, the rationality of the analysis model and the effectiveness of the optimization method are verified. Multidisciplinary design optimization framework based on reliability is expected to be applied to solar aircraft design which is more fit to engineering practice.