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首页> 外文期刊>Journal of the American Helicopter Society >Structural Sizing of a Rotorcraft Fuselage Using an Integrated Design Approach
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Structural Sizing of a Rotorcraft Fuselage Using an Integrated Design Approach

机译：使用综合设计方法结构尺寸旋翼机身机身

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摘要

For many years, the primary design objective of new helicopters was the design of the main rotor(s). Within the last couple of years, this approach has changed into an assessment of all helicopter components as an overall system, thus turning rotorcraft design into a highly interdisciplinary process. For instance, aerodynamics, flight mechanics, and the structural evaluation strongly affect each other, and these mutual influences are taken into account from the early phase of the conceptual design. Weight prediction in early design stages represents an essential part of the design process as it determines the basic properties of the rotorcraft. Owing to its function to carry crew and payload but also to serve as the central mounting for all components, the fuselage represents a major part of the rotorcraft. Therefore, the structural design of the fuselage airframe constitutes a significant factor of the rotorcraft design at the preliminary level. In this paper, an approach to include a higher fidelity method using finite elements for the structural analysis of rotorcraft fuselages within an integrated design environment is presented. Model generation and static analysis are conducted automatically. The helicopter is described using a common parametric data model during the complete design process, therefore providing a fast analysis of model changes. The generic finite element model presented in this paper was generated and structurally sized in about 2.5 min using a standard office computer, thus offering the integration of higher fidelity methods into early design sizing loops.
机译：多年来，新直升机的主要设计目标是主转子的设计。在过去的几年内，这种方法已经改变为所有直升机组件作为整体系统的评估，从而将旋翼设计设计成高度互学科的过程。例如，空气动力学，飞行力学和结构评估彼此强烈影响，并且从概念设计的早期阶段考虑了这些相互影响。早期设计阶段的重量预测代表了设计过程的重要组成部分，因为它决定了旋翼飞行器的基本属性。由于其功能携带机组人员和有效载荷，而且还用作所有组件的中央安装，机身代表旋翼飞行器的主要部分。因此，机身机身的结构设计构成了初级水平旋翼设计的重要因素。在本文中，提出了一种利用用于在集成设计环境中使用有限元进行旋翼飞机机身结构分析的有限元的较高保真方法的方法。模型生成和静态分析自动进行。在完整的设计过程中使用常见的参数数据模型描述直升机，因此提供了对模型变化的快速分析。本文提出的通用有限元模型在大约2.5分钟内产生和在结构上大小，使用标准办公计算机在大约2.5分钟内大小，从而提供更高保真方法将更高保真方法的整合到早期设计尺寸环。

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  • 来源
    《Journal of the American Helicopter Society》 |2020年第4期|042008.1-042008.12|共12页
  • 作者

    Dominik B. Schwinn; P. Weiand; M. Buchwald;

  • 作者单位

    Institute of Structures and Design German Aerospace Center (DLR) Stuttgart Germany;

    Institute of Flight Systems German Aerospace Center (DLR) Braunschweig Germany;

    Institute of Flight Systems German Aerospace Center (DLR) Braunschweig Germany;

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