Virtual flight testing in an aircraft sizing and optimization process

Abstract

The approach proposed in this paper aims at increasing knowledge during the conceptual design phase through the addition of new modules or disciplines. Various investigations identified the Stability Augmentation System as a key subsystem to be taken into account as soon as possible since it opens the design space and allows potential performance gains. In parallel, studies demonstrated the strong impact of certification constraints on the sizing of an aircraft. A new Multi Disciplinary Analysis and Optimization process for conceptual studies is then defined. One of its characteristics is that a certification module corresponding to a digital version of the regulatory texts can exchange with the Multi Disciplinary Analysis during the optimization. With such a layout, designers can optimize a configuration given a set of constraints or, they can trace the necessary modifications to the certification rules for a given architecture. Another key feature of the proposed process is the use of a full simulator (6 degrees of freedom) to fly the various reference missions within the sizing process. With this approach aircraft designers have then a high fidelity mission module that provides an important amount of information. Potential benefits can be foreseen for advanced concepts (especially flying technology demonstrators) relying on energy sources other that kerosene. In addition, the possibility to simulate the real routes of the aircraft during the optimization phase opens many options for close collaborations with Air Traffic Management research. Of course, this amount of information comes at a certain computational cost that is unusual for conceptual design tools. However, there are already ideas on how to reduce computational time.

Original document

The different versions of the original document can be found in:

• https://hal.archives-ouvertes.fr/hal-02052009

• http://arc.aiaa.org/doi/pdf/10.2514/6.2015-2546,

http://dx.doi.org/10.2514/6.2015-2546

• https://hal.archives-ouvertes.fr/hal-02052009,

https://arc.aiaa.org/doi/pdf/10.2514/6.2015-2546,

https://academic.microsoft.com/#/detail/2325089494