| 摘要 |
Rotor speed is maintained at a reference speed 48 by a closed-loop fuel control system 40,44,46,48,54,58. Load factor potential is enhanced by increasing the reference speed as a function of the helicopter pitch rate 72 and optionally airspeed 80 when undergoing positive pitch rate manoeuvres. The reference may be increased only when a certain airspeed (cruise speed) has been reached. Alternatively load factor can be sensed directly or combined with pitch rate by use of an accelerometer 73. <IMAGE> |
