The present invention relates to a device (10) for varying blade pitch of a rotary wing aircraft (50) having a main rotor (11) with a plurality of blades (12), each blade (12) including at least one main flap (13) fastened to the trailing edge of the blade (12). The angle of inclination of each flap
The present invention relates to a device (10) for varying blade pitch of a rotary wing aircraft (50) having a main rotor (11) with a plurality of blades (12), each blade (12) including at least one main flap (13) fastened to the trailing edge of the blade (12). The angle of inclination of each flap (13) is controlled via a swashplate (20). The device (10) makes provision for electric actuators controlled by a flight control system (54) to be mounted in a stationary frame of reference for the purpose of moving and varying the angle of inclination of the non-rotary plate of the swashplate (20). The electric actuators provide primary flight control and also multi-cyclic control for the purpose of attenuating noise and vibration as generated in particular by the blades (12) and the rotor (11).
대표청구항▼
1. A device for varying blade pitch for a rotary wing aircraft including: a main rotor having a plurality of blades;at least one main flap per blade, each main flap being turnable about an axis to modify the pitch of the blade;main actuators controlling the angles of inclination of the main flaps; a
1. A device for varying blade pitch for a rotary wing aircraft including: a main rotor having a plurality of blades;at least one main flap per blade, each main flap being turnable about an axis to modify the pitch of the blade;main actuators controlling the angles of inclination of the main flaps; anda flight control system controlling the main actuators;wherein the device for varying blade pitch comprises at least one secondary flap incorporated in each blade and a swashplate having a non-rotary plate and a rotary plate rotating with the main rotor, the rotary plate acting via a mechanical connection to change the angle of inclination of each main flap and consequently to change the pitch of the corresponding blade, the main actuators being electric actuators for moving and varying the angle of inclination of the non-rotary plate in order to control the main flaps at least cyclically, each secondary flap being subjected to multi-cyclic control by a piezo-ceramic secondary flap electric actuator incorporated in each blade and having a utilization frequency equivalent to at least (b+1)ω, where b corresponds to the number of blades of the main rotor and ω corresponds to the speed of rotation of the main rotor. 2. A device according to claim 1, wherein the main rotor has a number b of blades equal to three or four, and the main actuators have a utilization frequency equivalent to not less than the product bω, where ω corresponds to the speed of rotation of the main rotor in order to control the main flaps both cyclically and multi-cyclically. 3. A device according to claim 2, wherein the device includes at least one computer cooperating with the flight control system, the computer having memory and at least one processor, at least one vibration sensor, a multi-cyclic control algorithm stored in the memory, and operating in a closed loop with continuous identification of the vibratory response of the aircraft by means of the vibration sensors in order to optimize the multi-cyclic control of the main flaps. 4. A device according to claim 1, wherein the main rotor has a number b of blades equal to three or four, and each main actuator comprises a main electric actuator having a utilization frequency equivalent to at least ω, where ω corresponds to the speed of rotation of the main rotor in order to control the main flaps cyclically, and a secondary electric actuator having a utilization frequency equivalent to at least bω in order to control the main flaps multi-cyclically, the main actuator and the secondary actuator being connected in series. 5. A device according to claim 1, wherein the mechanical connection has a number of secondary electric actuators equal to the number of the blades of the main rotor, each secondary actuator being connected between the rotary plate and a the main flap, and having a utilization frequency equivalent to at least (b+1)ω, where b corresponds to the number of the blades of the main rotor and ω corresponds to the speed of rotation of the main rotor, in order to control the main flaps multi-cyclically. 6. A device according to claim 1, wherein the secondary flap actuators are suitable for being controlled cyclically in order to provide primary flight control. 7. A device according to claim 1, wherein the device has at least two computers cooperating with the flight control system, the at least two computers having two different processors and suitable for using algorithms that are identical or different, the at least two computers being used for imparting cyclic control to the main flaps. 8. A device according to claim 1, wherein the device includes at least one computer cooperating with the flight control system, the at least one computer having two different processors and suitable for using algorithms that are identical or different, the at least one computer being used for multi-cyclic control of the secondary flap actuators. 9. A device according to claim 1, wherein the flight control system is either an electric flight control system or an optical flight control system. 10. A rotary wing aircraft comprising: a fuselage;a tail rotor having at least two blades; anda device for varying blade pitch, the device including: a main rotor having a plurality of blades;at least one main flap per blade, each main flap being movable in turning about an axis to modify the pitch of the blade;main actuators controlling the angles of inclination of the main flaps; anda flight control system controlling the main actuators;the device for varying blade pitch comprising at least one secondary flap incorporated in each blade and a swashplate having a non-rotary plate and a rotary plate rotating with the main rotor, the rotary plate acting via a mechanical connection to change the angle of inclination of each main flap and consequently to change the pitch of the corresponding blade, the main actuators being electric actuators for moving and varying the angle of inclination of the non-rotary plate in order to control the main flaps at least cyclically, each secondary flap being subjected to multi-cyclic control by a piezo-ceramic secondary flap electric actuator incorporated in each blade and having a utilization frequency equivalent to at least (b+1)ω, where b corresponds to the number of blades of the main rotor and ω corresponds to the speed of rotation of the main rotor. 11. A rotary wing aircraft according to claim 10, wherein variation of the pitch of the blades of the tail rotor is controlled via at least one tail rotor electric actuator. 12. A rotary wing aircraft according to claim 11, wherein the at least one tail rotor electric actuator is an electric jack. 13. A rotary wing aircraft according to claim 10, wherein the tail rotor is driven in rotation by an electric motor. 14. A rotor control assembly comprising: a main rotor having a rotor blade;a main flap coupled to the rotor blade and configured to pivot about an axis to modify blade pitch of the rotor blade;a swashplate having a non-rotary plate and a rotary plate, the rotary plate being configured to rotate with the main rotor;a mechanical connection arranged between the rotary plate and the main flap, the mechanical connection being configured to change an angle of inclination of the main flap;an electric main flap actuator configured to vary an angle of inclination of the non-rotary plate to control the main flap;a flight control system configured to control the main flap actuator;a secondary flap coupled to the blade; anda piezo-ceramic electric secondary flap actuator arranged in the rotor blade and configured to actuate the secondary flap multi-cyclically at a frequency of least (b+1)ω, where b corresponds to a total number of blades of the main rotor and ω corresponds to the speed of rotation of the main rotor. 15. The rotor control assembly of claim 14, wherein the total number of blades of the main rotor is greater than one. 16. The rotor control assembly of claim 14, wherein the total number of blades of the main rotor is three or four, and wherein the electric main flap actuator is configured to actuate the main flap at a frequency of at least bω. 17. The rotor control assembly of claim 14, further comprising a secondary electric main flap actuator in series with the electric main flap actuator, wherein the total number of blades of the main rotor is three or four, and wherein the electric main flap actuator is configured to actuate the main flap at a frequency of at least ω, and the secondary electric main flap actuator is configured to actuate the main flap at a frequency of least bω. 18. The rotor control assembly of claim 14, wherein the mechanical connection includes a secondary electric main flap actuator configured to actuate the main flap at a frequency of least (b+1)ω.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (4)
Berthie, Pierre, Helicopter provided with a plurality of lift elements for controlling the angles of incidence of its blades.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.