Multidisciplinary, Multiobjective Trim Optimization for a Coaxial-Pusher Rotorcraft Configuration

The control redundancy inherent to a coaxial helicopter facilitates multiple achievable configurations for trimmed flight conditions. These redundancies can be exploited to optimize performance across multiple disciplines including the minimization of noise and the maximization of component life. Improved trim methodologies are required to identify the control allocation for optimal multidisciplinary flight performance. Previously, the authors of this paper presented