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.
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.
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.
32 Bit or 64 Bit hardware architecture (x86 or 圆4).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. Includes Plugin Manager for adding and removing plugins. Add textures to your model using the AutoUV facility. Use virtual mirror for symmetrical modelling. Perform plane cut, circularize, intersect, bend, shear etc. Includes UV mapper, vertex colors, materials, lights etc. Right click menus for easy access to common commands. Wide range of selection and mesh tools. Easy to use intuitive interface with powerful tools.
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