To show the capability of the considered approach, robust multidisciplinary design optimization of an unmanned aerial vehicle (UAV) has been done. Because multidisciplinary design optimization and robust design optimization methods have been used in this study and according to the high cost of the multidisciplinary analysis module, a surrogate model of this module has been made to reduce the imposed costs. Because of the ability of neural networks to approximate the behavior of complex engineering systems, this tool has been used to create a surrogate model. In this paper, the meta-model concept has been used to overcome this problem. This cost will increase sharply for issues with a multidisciplinary and uncertain nature and more than one objective function.
However, variation between subsonic and transonic Mach numbers is observed for both pitch and roll damping.ĭespite the many advantages of the design optimization technique, this method is costly for real engineering problems. The results indicate a minimum impact of reduced frequency on pitch and roll damping derivatives. A parametric study is conducted on SACCON UCAV at a 5° angle of attack to monitor the effects of increasing Mach number and reduced frequency on damping coefficients. In addition, an excellent agreement is found in the damping derivatives in pitch and roll between numerical and experimental data. It is observed that the Reynolds-Averaged-Navier-Stokes (RANS) framework used in this research accurately predicts the static aerodynamic characteristics such as lift-curve slope, stall, and coefficient of drag. The analysis is performed in both pitch and roll directions to find the damping coefficients with varying angles of attack. SACCON UCAV is a blended-wing-body design with a vortex-dominated flow field. This study aims to develop a high fidelity validation test case for the Stability and Control Configuration (SACCON) Unmanned Combat Air Vehicle (UCAV) design. However, due to the availability of high-performance computing resources, Computational Fluid Dynamics (CFD) has emerged as an improved alternative. View Video Presentation: Aircraft designers usually opt for wind-tunnel experiments to determine the aerodynamics and flight stability characteristics of complex configurations. The new method is applied to the aerostructural optimization of the CRM configuration.
#WINGS 3D 3D MODELLING CODE#
The new method is being implemented in the Isight process integration framework, using the NSU3D Reynolds-Averaged Navier-Stokes code for the aerodynamic analysis and adjoint implementation, and a proprietary wing structure sizing code from Bombardier Aviation. The sizing loads are passed to the surrogate as a parameterized loading envelope to keep the number of surrogate inputs small, and allow the surrogate to be trained using a wide variety of representative load envelopes to cover the range of expected designs. Furthermore, by outputting the wing stiffness, the surrogate enables the multipoint design optimization of flexible wings, as the stiffness may be used to determine the elastic response for multiple design load cases. Utilizing this type of surrogate eliminates the need for numerous structural constraints in the aerostructural optimization problem, thereby removing the need for the aggregation of constraints in the coupled-adjoint formulation.
#WINGS 3D 3D MODELLING FULL#
The surrogate model approximates a full structural sizing process, returning the structural weight and equivalent stiffness of an optimized wing structure, given inputs of global geometry parameters and sizing loads. This gives the new strategy a monolithic architecture, and compartmentalizes the structural discipline, for ease of implementation in an industrial environment with distinct teams of disciplinary experts. In this method, the surrogate is trained only once, prior to the optimization, without being updated during the optimization. The new strategy features high-fidelity aerodynamic analysis and a surrogate model of the structure, integrated with the coupled-adjoint method to compute gradients. View Video Presentation: A new multidisciplinary design optimization (MDO) strategy is presented for the coupled aerostructural optimization of an aircraft wing at the preliminary design stage.
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