Performance characteristics of single rotor compound helicopter

In order to analysis the performance of the compound helicopter, a performance calculation model consisting of all the aerodynamics mathematical model parts is established. Based on the calculation model, using various flight conditions, we constructed the compound helicopter transition flight border, studied the characteristic variation of flight power from hover flight mode to high-speed flight mode by selecting different routes, and investigated the effects of multiple factors including rotor speed, forward speed, rotor and wing loading distribution in high-speed mode. The results indicated that the reduction of flight power could be achieved by increasing the offload lift from the rotor to the wing; moreover, it was more effective to reduce the rotor speed than reduce the rotor collective pitch, during the compound helicopter transits from hover mode to high-speed mode. The rotor could not operate at very low speed, which might increase the power consumption during high-speed flight mode. Furthermore, the low rotor speed could also influence the trim of the aircraft model, and made its calculation iteratively divergent.