Process Development for Integrated and Distributed Rotorcraft Design

Peter Weiand,Michel Buchwald,Dominik Schwinn

doi:10.3390/aerospace6020023

Abstract

The German Aerospace Center is currently developing a new design environment for rotorcraft, which combines sizing, simulation and evaluation tasks into one toolbox. The complete environment applies distributed computation on the servers of the various institutes involved. A uniform data model with a collaboration and interface software, developed by DLR and open source, are used for exchange and networking. The tools used apply blade element methods in connection with full six degrees of freedom trim, panel methods for aerodynamic loads, different empirical models for sizing, engine properties and component mass estimation and finite element methods for structural design. A special feature is the integration of a higher fidelity overall simulation tool directly into the sizing loop. The paper describes the use of the several tools for the phases of conceptual and preliminary design. A design study is presented demonstrating the sensitivity of the process for a variation of the input parameters exhibiting a broad range for trade-off studies. The possibility to continue for analyzing and sizing of the structural properties is also demonstrated by applying a finite element approach for specific load cases. These features highlight the core of the new design environment and enable the development of goal-oriented design processes for research especially of new and unconventional rotorcraft configurations. The work presented in this paper was conducted throughout the DLR internal project, namely the Technologies for Rotorcraft in Integrated and Advanced Design (TRIAD). TRIAD is a joint project of the institutes of Flight Systems, the institute of Aerodynamics and Flow Technology, the institute of Structures and Design, the System Architectures in Aeronautics and Institute of Aerospace Medicine and receives basic founding.

Highlights

The sum of useable mass andofbasic empty mass mass with resulted in trimvirtual massesand forthe a comparison of the flight performance curves the ratio the usable respect slightly different flight masses as indicated in the legend of Figure where the power required is to the flight mass was varied from 20%, to 100% in increasement of 20% for the virtual and the reference shown for the and the virtual configuration
The features shown in this paper mark the core of the new design environment IRIS
It was essentially possible to follow the guidelines of fixed-wing design in order to show a substantial overlap in the DLR doctrine for aircraft and rotorcraft design

Summary

Introduction

If the dimensions of an aircraft are determined, its maximum take-off mass can be estimated according to the flight performance required. After once the mass of the vehicle is known, the lift producing components, which need to carry its mass, must be scaled, resulting in new dimensions. This is a highly iterative and multidisciplinary design task. In this context the design of vertical lift aircraft and especially rotorcraft is even more complex due to a variety of additional considerations. Extending the flight envelope to vertical take-off, hover and landing implies a sophisticated prediction of performance. If it is desired to take all Aerospace 2019, 6, 23; doi:10.3390/aerospace6020023 www.mdpi.com/journal/aerospace

Methods

Results

Conclusion