Abstract:
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. The objective of this paper is to present the results of a simulation-based study for a coaxial/pusher rotorcraft configuration in trim. The paper shows the effects on trim of increased control redundancy achieved through the use of a pusher propeller. The impact of different trim approaches on performance, acoustics, and fatigue life is compared. It is shown that the different metrics may have conflicting requirements necessary to maximize performance.