Integrated Trim and Structural Design Process for Active Aeroelastic Wing Technology

摘要

A new method for concurrent trim and structural optimization of active aeroelastic wing technology is presented. The new process treats trim optimization and structural optimization as an integrated problem in which control surface gear ratios and structural design variables are posed together in the same optimization problem and act toward the same objective of weight minimization. This new design philosophy is in contrast to most existing active aeroelastic wing design processes in which structural optimization and trim optimization, each having their own different objectives and constraints, are performed in an iterative, sequential manner. The new integrated active aeroelastic wing design process is demonstrated on a lightweight fighter-type aircraft and compared to a more traditional, sequential active aeroelastic wing design process. For this demonstration, the integrated process converges to a lower weight and offers an advantage over the sequential process in that optimization is performed in one continuous run, whereas the sequential approach requires pausing and restarting the structural optimization to allow for trim optimization.