Model Based Collaborative Design &amp; Optimization of Blended Wing Body Aircraft Configuration : AGILE EU Project

Prakasha, Prajwal S.; Vecchia, Pierluigi Della; Ciampa, Pier Davide; Ciliberti, Danilo; Charbonnier, Dominique; Jungo, Aidan; Fioriti, Marco; Boggero, Luca; Mirzoyan, Artur; Anisimov, Kirill; Zhang, Mengmeng; Voskuijl, Mark

doi:10.2514/6.2018-4006

Cited by 13 publications

(12 citation statements)

References 20 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…[2][3][4] Many studies claim that unconventional aircraft designs, incorporating novel technologies, can offer a solution towards a sustainable air-traffic growth. [5][6][7] These claims are mostly based on "paper designs" and not demonstrated in flight yet. However, the actual performances of an aircraft, such as its dynamics stability and controllability and, eventually, its flying and handling qualities are difficult to predict, especially in the case of unconventional configurations, for which the use of semiempirical or statistics based methods are limited or impossible.…”

Section: Introductionmentioning

confidence: 99%

Assessment of Sub-scale Designs for Scaled Flight Testing

Kulkarni

Varriale

Voskuijl

et al. 2019

AIAA Aviation 2019 Forum

Self Cite

View full text Add to dashboard Cite

Sub-scale Flight Testing (SFT) is potentially useful in predicting aircraft flight behaviour, especially in the case of unconventional designs for which legacy information is unavailable and wind tunnel tests are unable to predict aircraft dynamics. A necessary condition for SFT is the design of properly scaled models. However, even in case of perfect scaling, the sub-scale model needs adequate flight performance and handling qualities to enable the execution of flight tests. Thus, the (static and dynamic) stability and control (S&C) and handling qualities (HQ) of sub-scale designs should be evaluated accurately as well as quickly, to allow conceptual design iterations. To this purpose, we propose the use of a 3D panel method (3DPM) for the generation of the non-linear aerodynamic database, in combination with a non-linear flight dynamics analysis. Two main challenges affect the proposed approach. The first concerns the validity of the low-fidelity 3DPM data for the assessment of the sub-scale design S&C and HQ. The second is about the time consuming and error-prone pre/post-processing activity demanded by the hundreds of analysis cases for the aerodynamic database generation. The first issue is investigated by predicting the longitudinal S&C performance and HQ of a sub-scale design using 3DPM analysis and comparing them with the prediction from wind-tunnel test (static) data supplemented by (dynamic) data from 3DPM. Both models appear trimmable and stable and the difference in their HQ are quantified, thus verifying the suitability of 3DPM analysis for sub-scale design assessment. The pre/post-processing challenge is tackled by the development of a knowledge-based engineering application to automate the aerodynamics database generation, reducing the time needed for geometry modeling, discretization and postprocessing of hundreds of cases from weeks to hours. The proposed methodology and its flexibility are demonstrated in this paper, where a commercial 3DPM code and an in-house developed non-linear flight dynamics analysis tool have been used to assess two sub-scale designs, one conventional and one based on the box-wing configuration.

show abstract

Section: Introductionmentioning

confidence: 99%

Assessment of Sub-scale Designs for Scaled Flight Testing

Kulkarni

Varriale

Voskuijl

et al. 2019

AIAA Aviation 2019 Forum

Self Cite

View full text Add to dashboard Cite

show abstract

“…high-fidelity aerodynamics shape optimization, flight dynamics and control design, and BLI integration), the basic MDA has been re-configured in multiple variants, each leading to an adhoc workflow. It is not in the scope of this paper to show all the variants workflows obtained, but details of the studies performed can be found in [23]. Fig.…”

Section: Fig 20 Xdsm Graph For Mda Formulation In Use Case Bwbmentioning

confidence: 99%

“…Therefore, the AGILE BWB MDO problem focuses on the optimization of the BWB shape and the stability & control aspects (for the podded engine variant), and on the integration of the propulsion system (for the BLI variant). Detailed method and result can be found in [23].…”

Section: Introduction Use Case and Driving Requirementsmentioning

confidence: 99%

Streamlining Cross-Organizational Aircraft Development: Results from the AGILE Project

Ciampa

Prakasha

Torrigiani

et al. 2019

AIAA Aviation 2019 Forum

Self Cite

View full text Add to dashboard Cite

“…This modular MATLAB ® /Simulink toolbox integrates sub-models from different disciplines of aeronautics, in order to perform non-linear flight dynamics simulations. The toolbox has already been used in a variety of research studies to investigate the flight mechanics of novel aircraft configurations [18][19][20][21] and sub-scale aircraft designs [22]. The fidelity of each sub-model depends on available data, while the time domain simulations are driven by the Simscape Multibody Dynamics core.…”

Section: Aircraft Modelmentioning

confidence: 99%