Daniel Böhnke

An approach to multi-fidelity in conceptual aircraft design in distributed design environments

In the present study we introduce a design environment consisting of a framework, a central model and a newly developed conceptual design module. The Common Parametric Aircraft Configuration Scheme (CPACS) is the standard syntax definition for the exchange of information within preliminary airplane design at DLR. Several higher fidelity analysis modules are already connected to CPACS, including aerodynamics, primary structures, mission analysis and climate impact. The analysis modules can be interfaced via a distributed framework. To initialize the design processes, capabilities are needed to close the gap between top-level requirements and preliminary design. Additionally, results of a design loop need to be merged to generate inputs for further iterations and convergence control. For this purpose we developed a conceptual design module based on handbook methods where the focus is set on multi-fidelity. For the upward change in level of detail a knowledge-based approach is used for the generation of CPACS models. This includes the geometry generation, as well as additional data such as the mass breakdown and the tool-specific inputs for further analyses in higher fidelity modules. The feedback loop is closed downwards by reducing the granularity from the CPACS data set back to the level of conceptual design methods. The conceptual design module is object-oriented and concepts, both for parameter and method replacement, are introduced. First results for multi-fidelity calculations are shown.

Towards a collaborative and integrated set of open tools for aircraft design

A third generation Multi-Disciplinary Analysis & Optimization setup includes the collaboration of a distributed team of disciplinary experts and their respective anylsis tool to perform aircraf ...

On the Design of a Strut-Braced Wing Configuration in a Collaborative Design Environment

Due to its drag saving potential through application of high aspect ratio wings, the strut-braced wing configuration is considered a promising candidate as a next generation single-aisle aircraft. This potential is reflected in the results of the renowned Sugar and Albatross projects of Boeing and ONERA. In the course of DLRs project future enhanced aircraft configurations (FrEACs), a strut-braced wing configuration is examined with focus on the interaction of aerodynamics, loads, structures and aeroelastics. The present study outlines the applied design process for the strut-braced wing configuration in DLRs collaborative design environment and highlights lessons learnt from an organizational and technical point of view. It proves that the level of confidence in the design process is largely increased by effectively combining both the explicit and implicit knowledge of the heterogeneous specialists involved. The explicit knowledge is incorporated through automated execution of the specialists tools in structured simulation workflows. Implicit knowledge of the specialists is required to interpret results both in the respective disciplinary context as well as on overall aircraft design level. Applying the collaborative design process enables statements on the possible gain of strut-braced wing over conventional tube and wing configurations. The paper describes the applied collaborative design procedure, shows results concerning the physical aspects of the strut-braced wing configuration and concludes by providing lessons learnt and an outlook into the application of collaborative design.