Abstract Mission optimisation for a conceptual coaxial rotorcraft for taxi applications
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Mission optimisation for a conceptual coaxial rotorcraft for taxi applications

机译：用于滑行应用的概念同轴旋翼飞机的任务优化

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AbstractThis paper presents the development and an application of a multidisciplinary methodology for the preliminary design assessment of compound coaxial rotorcraft with a counter-rotating rotor system and a rear-mounted propeller. A comprehensive optimisation strategy is deployed to evaluate the environmental and operational benefits of the aforementioned rotorcraft architecture. The code is validated against experimental data prior to the application of the methodology to the evaluation of a conceptual vehicle for intercity taxi applications. Response Surface Models (RSMs) are generated to mimic the rotorcraft performance in order to accelerate the optimisation process. The effects of the defined mission input parameters such as cruise speed, altitude, climb rate or mission length are evaluated. Pareto fronts for fuel burn,NOxemissions and mission duration are obtained. The method was applied to a hypothetical scenario of mission length ranging from 50 to 300 km. Best estimate mission scenario are selected from the Pareto fronts, providing on average 23%, 20%, and 13% simultaneous reductions in mission duration, fuel burn, andNOxemissions when compared to a conventional flight procedure. The picked scenarios coincide with the fuel optimised mission scenarios for each mission length, thus the multi-disciplinary environment was not required. Besides, an “improved” mission procedure is outlined, defining the mission characteristics independently of the mission's length. This procedure yields on average 22%, 14%, and 8% reductions in mission duration, fuel burn, andNOxemissions, respectively.
机译： 摘要 本文介绍了多学科方法的发展和应用，该方法用于带有反向旋转旋翼系统和后置螺旋桨的复合同轴旋翼飞机的初步设计评估。部署了全面的优化策略来评估上述旋翼飞机架构的环境和运营优势。在将该方法应用于城际出租车应用的概念车评估之前，要根据实验数据对代码进行验证。生成响应面模型（RSM）来模拟旋翼飞机的性能，以加快优化过程。评估定义的任务输入参数（例如巡航速度，高度，爬升率或任务长度）的效果。帕累托燃料燃烧前沿， < mml：mi> N O x 获得了发射和任务持续时间。该方法应用于任务长度为50至300 km的假设情景。从帕累托战线中选择最佳估计任务方案，可以同时平均减少23％，20％和13％的任务持续时间，燃油消耗和 N O x 与常规飞行程序相比，排放。所选择的方案与每个任务长度的燃料优化任务方案相吻合，因此不需要多学科环境。此外，概述了“改进的”任务程序，定义任务特征与任务的时间无关。此过程平均使任务持续时间，燃料消耗和 N O x 排放。

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