초록 ▼

Propeller-driven aircraft ( 30 ) comprising an engine ( 31 ) providing mechanical engine power for rotating a propeller ( 32 ), an engine limiting unit ( 35 ), an engine control unit ( 37 ) for controlling the mechanical engine power of the engine ( 31 ), a system ( 36 ) for measuring the airspeed a

Propeller-driven aircraft ( 30 ) comprising an engine ( 31 ) providing mechanical engine power for rotating a propeller ( 32 ), an engine limiting unit ( 35 ), an engine control unit ( 37 ) for controlling the mechanical engine power of the engine ( 31 ), a system ( 36 ) for measuring the airspeed and providing information concerning the airspeed to the engine limiting unit ( 35 ), wherein the engine limiting unit ( 35 ) automatically reduces the mechanical engine power at airspeeds below a certain first airspeed value (V1).

대표청구항 ▼

1. Propeller-driven aircraft comprisingan engine providing mechanical engine power for rotating a propeller of the aircraft,an engine control unit for controlling the mechanical engine power output of the engine,an engine limiting unit,a system for measuring the airspeed and providing information co

1. Propeller-driven aircraft comprisingan engine providing mechanical engine power for rotating a propeller of the aircraft,an engine control unit for controlling the mechanical engine power output of the engine,an engine limiting unit,a system for measuring the airspeed and providing information concerning the airspeed to the engine limiting unit,wherein the engine limiting unit automatically alters the engine control unit settings according to a predefined schedule independent of pilot input thus reducing the mechanical engine power output at airspeeds below a certain first airspeed value in order to limit adverse effects of high engine torque at low airspeed. 2. The aircraft of claim 1, wherein a reduced yaw moment acts on the aircraft while the engine limiting unit automatically reduces the mechanical engine power at airspeeds below a certain first airspeed value. 3. The aircraft of claim 1 or 2, wherein the engine limiting unit automatically increases the mechanical engine power at airspeeds above a certain second airspeed value. 4. The aircraft of claim 3, wherein the engine limiting unit automatically increases the mechanical engine power applying a pre-defined schedule. 5. The aircraft of one of the preceding claims, wherein the engine limiting unit operates the engine at low airspeeds at or above a lowest allowable mechanical engine power, said lowest allowable mechanical engine power being defined such that sufficient mechanical engine power is available to safely operate the aircraft. 6. The aircraft of claim 3, wherein the engine limiting unit automatically increases the mechanical engine power until a maximum allowable engine power is reached. 7. The aircraft of claim 3, wherein the engine limiting unit automatically increases the mechanical engine power until the engine's mechanical power limit is reached. 8. The aircraft of one of the claims 1 - 4 , wherein the engine limiting unit operates the engine at low airspeeds at a constant mechanical engine power. 9. The aircraft of one of the preceding claims, wherein the first airspeed value is in the range between 30 Knots and 250 Knots, preferably between 150 Knots and 220 Knots. 10. The aircraft of claim 1, enabled to accelerate with a level aircraft acceleration below the acceleration at maximum mechanical engine power while the engine limiting unit automatically reduces the mechanical engine power at airspeeds below a certain first airspeed value. 11. The aircraft of claim 1, wherein the aircraft reaches the same cruising airspeed as a conventional aircraft being operated at maximum mechanical engine power in about the same time. 12. The aircraft of claim 1, having an overall aircraft acceleration time to high aircraft speeds comparable to the overall aircraft acceleration time of a conventional aircraft being operated at maximum mechanical engine power. 13. The engine control system of claim 1, comprising a memory for storing the schedule. 14. The engine control system of claim 1, wherein the schedule either defines the mechanical engine power as a function of the airspeed, or the level aircraft acceleration as a function of the airspeed.