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Development of an improved framework for the conceptual design of a rotorcraft

机译：开发旋翼飞机概念设计的改进框架

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Purpose - The purpose of the present paper is to obtain the capability of designing modern rotorcrafts with enhanced accuracy and reliability. Design/methodology/approach - Among the existing rotorcraft design programs, an appropriate program was selected as a baseline for improvement. It was based on a database comprising conventional fleets of rotorcrafts. The baseline program was not robust because it contained a simple iteration loop, which only monitored the gross weight of the aircraft. Therefore, it is not accurate enough to fulfill the quality and sophistication of a conceptual design framework useful for present and future generations of rotorcrafts. In this paper, the estimation formulas for the sizing and weight of the rotorcraft subsystem were updated by referring to modern aircraft data. In addition, trend curves for various turboshaft engines available these days were established. Instead of using the power estimation algorithm based on the momentum theory with empirical corrections, blade element rotor aerodynamics and trim analysis were developed and incorporated into the present framework. Moreover, the simple iteration loop for the aircraft gross weight was reinforced by adding a mathematical optimization algorithm, such as a genetic algorithm. Findings - The improved optimization framework for rotorcraft conceptual design which has the capability of designing modern rotorcrafts with enhanced accuracy and reliability was constructed by using MATLAB optimization toolbox. Practical implications - The optimization framework can be used by the rotorcraft industries at an early stage of the rotorcraft design. Originality/value - It was verified that the improved optimization framework for the rotorcraft conceptual design has the capability of designing modern rotorcrafts with enhanced accuracy and reliability.
机译：目的-本文的目的是获得设计具有更高准确性和可靠性的现代旋翼飞机的能力。设计/方法/方法-在现有的旋翼机设计程序中，选择了一个适当的程序作为改进的基准。它基于一个包括常规旋翼机舰队的数据库。基线程序不可靠，因为它包含一个简单的迭代循环，该循环仅监视飞机的总重量。因此，它不够准确，无法满足对今世后代旋翼飞机有用的概念设计框架的质量和要求。在本文中，参考现代飞机数据更新了旋翼飞机子系统的尺寸和重量的估算公式。此外，建立了当今可用的各种涡轮轴发动机的趋势曲线。代替使用基于动量理论的功率估计算法和经验校正，开发了叶片元件转子空气动力学和修整分析，并将其纳入本框架。此外，通过添加数学优化算法（例如遗传算法），增强了飞机总重的简单迭代循环。研究结果-使用MATLAB优化工具箱构建了改进的旋翼飞机概念设计优化框架，该框架具有设计具有更高准确性和可靠性的现代旋翼飞机的能力。实际意义-旋翼飞机行业可以在旋翼飞机设计的早期阶段使用优化框架。原创性/价值-经验证，改进的旋翼机概念设计优化框架具有设计现代旋翼机的能力，并具有更高的准确性和可靠性。

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