Granted Patent B2

US 12,428,141 · App. 18/679,702 · Granted Sep 30, 2025

Inventor: Efraim Kastiel (Tel Aviv, IL)

Assignee: EFIX AVIATION LTD

B64C27/26B64C27/52B64C27/72

Abstract

Claims (44)

1. A fixed wing rotorcraft configured for forward flight, the fixed wing rotorcraft comprising:

a) a fuselage;

b) at least one pair of fixed wings;

c) a forward propulsion unit for providing forward thrust; and

d) at least one rotor system including:

a mast configured to have at least two rotor blades attached thereto,

a rotor drive unit for driving said mast whereupon said at least two rotor blades act as a rotor disc,

a controllable collective rotor blade pitch, and

a controllable cyclic rotor blade pitch,

wherein said mast being tiltable with respect to said fuselage in the direction of forward flight such that its associated rotor disc presents a variable Angle of Attack (AOA) with respect to airflow,

wherein, during the fixed wing rotorcraft's straight and level forward flight,

said fuselage being substantially horizontal,

at a first airspeed, said mast being tilted backwards such that its rotor disc autorotates at a positive rotor disc Angle of Attack (AOA) relative to airflow and said at least two rotor blades being set at a first collective rotor blade pitch, and

at a second airspeed faster than said first airspeed, said mast being tilted forward such that its rotor disc autorotates at a negative rotor disc Angle of Attack (AOA) relative to airflow,

and said at least two rotor blades being set at a second collective rotor blade pitch different from said first collective rotor blade pitch and configured to maintain said rotor disc's spin direction at said first airspeed.

2. The rotorcraft according to claim 1 wherein during transition between said positive rotor disc Angle of Attack (AOA) relative to airflow at said first airspeed and said negative rotor disc Angle of Attack (AOA) relative to airflow at said second airspeed, said collective rotor blade pitch is controlled to approximately maintain said rotor disc's rotational speed.

3. The rotorcraft according to claim 1 and further comprising a mechanical arrangement for tilting said tiltable mast.

4. The rotorcraft according to claim 1 wherein said rotor system autorotates unpowered.

5. The rotorcraft according to claim 1 wherein said rotor system autorotates partially powered.

6. The rotorcraft according to claim 1 and further comprising a Flight Control System for controlling the fixed wing rotorcraft.

7. A flight control system configured to control the fixed wing rotorcraft according to claim 1 , wherein controlling the fixed wing rotorcraft during straight and level forward flight includes,

maintaining the fuselage being substantially horizontal,

at the first airspeed, tilting the mast backwards such that its rotor disc autorotates at the positive rotor disc Angle of Attack (AOA) relative to airflow and setting the at least two rotor blades at the first collective rotor blade pitch, and

at the second airspeed faster than the first airspeed, tilting the mast forward such that its rotor disc autorotates at the negative rotor disc Angle of Attack (AOA) relative to airflow, and

setting the at least two rotor blades at the second collective rotor blade pitch different from the first collective rotor blade pitch and configured to maintain the rotor disc's spin direction at the first airspeed.

8. The flight control system according to claim 7 wherein during transition between the positive rotor disc Angle of Attack (AOA) relative to airflow at the first airspeed and the negative rotor disc Angle of Attack (AOA) relative to airflow at the second airspeed, the collective rotor blade pitch is controlled to approximately maintain the rotor disc's rotational speed.

9. A computer readable storage medium comprising instructions which cause the flight control system to control the fixed wing rotorcraft according to claim 8 when executed by a flight control system in the fixed wing rotorcraft.

10. The computer readable storage medium according to claim 9 wherein during transition between the positive rotor disc Angle of Attack (AOA) relative to airflow at the first airspeed and the negative rotor disc Angle of Attack (AOA) relative to airflow at the second airspeed, the collective rotor blade pitch is controlled to approximately maintain the rotor disc's rotational speed.

11. A method operating a fixed wing rotorcraft comprising the steps of:

a) providing a rotorcraft having

a fuselage;

at least one pair of fixed wings;

a forward propulsion unit for providing forward thrust; and

at least one rotor system including:

a mast configured to have at least two rotor blades attached thereto,

a rotor drive unit for driving said mast whereupon said at least two rotor blades act as a rotor disc,

a controllable collective rotor blade pitch, and

a controllable cyclic rotor blade pitch,

wherein the mast being tiltable with respect to the fuselage in the direction of forward flight such that its associated rotor disc presents a variable Angle of Attack (AOA) with respect to airflow, and

b) controlling the fixed wing rotorcraft during straight and level forward flight such that the fuselage is substantially horizontal,

at a first airspeed, the mast is tilted backwards such that its rotor disc autorotates at a positive rotor disc Angle of Attack (AOA) relative to airflow and the at least two rotor blades are set at a first collective rotor blade pitch, and

at a second airspeed faster than the first airspeed, the mast is tilted forward such that its rotor disc autorotates at a negative rotor disc Angle of Attack (AOA) relative to airflow, and the

at least two rotor blades are set at a second collective rotor blade pitch different from the first collective rotor blade pitch and configured to maintain the rotor disc's spin direction at the first airspeed.

12. The method according to claim 11 wherein during transition between the positive rotor disc Angle of Attack (AOA) relative to airflow at the first airspeed and the negative rotor disc Angle of Attack (AOA) relative to airflow at the second airspeed, the collective rotor blade pitch is controlled to approximately maintain the rotor disc's rotational speed.

Assignments (1)

Priority Claims (1)

Continuity (1)

References Cited (41)