Method of controlling the wing flaps and horizontal stabilizer of a hybrid helicopter
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-027/57
B64C-019/00
B64D-045/00
B64C-027/26
B64C-013/16
출원번호
US-0895782
(2013-05-16)
등록번호
US-9085352
(2015-07-21)
우선권정보
FR-12 01434 (2012-05-21)
발명자
/ 주소
Eglin, Paul
출원인 / 주소
Airbus Helicopters
대리인 / 주소
Brooks Kushman P.C.
인용정보
피인용 횟수 :
2인용 특허 :
3
초록▼
A method of controlling a high-speed rotary wing aircraft (1) comprising a fuselage (2), at least one main rotor (3), at least one variable-pitch propulsive propeller (4), at least two half-wings (11, 11′) positioned on either side of said fuselage (2), at least one horizontal stabilizer (20) provid
A method of controlling a high-speed rotary wing aircraft (1) comprising a fuselage (2), at least one main rotor (3), at least one variable-pitch propulsive propeller (4), at least two half-wings (11, 11′) positioned on either side of said fuselage (2), at least one horizontal stabilizer (20) provided with a movable surface (21, 21′), and at least one power plant driving said main rotor (3) and said propulsive propeller (4) in rotation. Said method serves to adjust the lift of said half-wings (11, 11′) and the lift of the horizontal stabilizer (20) so that said lift of said half-wings (11, 11′) represents a predetermined percentage of the total lift of said aircraft (1) and so that the power consumed by said main rotor (3) is equal to a setpoint power during a stage of stabilized flight.
대표청구항▼
1. A method of controlling a high-speed rotary wing aircraft, the aircraft comprising: a fuselage;at least one main rotor having a plurality of blades;at least one variable-pitch propulsive propeller;at least two half-wings positioned on either side of said fuselage;aerodynamic control means of said
1. A method of controlling a high-speed rotary wing aircraft, the aircraft comprising: a fuselage;at least one main rotor having a plurality of blades;at least one variable-pitch propulsive propeller;at least two half-wings positioned on either side of said fuselage;aerodynamic control means of said aircraft comprising at least one movable flap on each half-wing, and at least one system for operating said flaps;at least one horizontal stabilizer positioned at one end of said aircraft, said horizontal stabilizer having at least one movable surface; andat least one power plant driving said main rotor and each propulsive propeller in rotation;the method comprising the following steps:determining the total lift of the aircraft assuming that said total lift counters the weight of said aircraft; andadjusting the lift of each half-wing by acting on said system for controlling said flaps so that (i) said lift of said half-wings is equal to a first predetermined percentage of said total lift of said aircraft during a stage of stabilized flight and (ii) the lift of each half-wing is different such that a difference in lift is between two half-wings, the difference in lift between said two half-wings serving to compensate for the effects of said main rotor affecting said half-wings differently. 2. A method according to claim 1, wherein said lift of said half-wings is equal to 40% of said total lift of said aircraft. 3. A method according to claim 1, wherein said weight of said aircraft is determined from the fuel consumption of said power plant. 4. A method according to claim 1, wherein said lift of said half-wings is determined with the help of the following relationship: Zwing=½×ρ×TAS2×S× Cz where: “Zwing” represents said lift of said two half-wings;“ρ” represents the density of the air under the conditions of flight;“TAS” represents the forward speed of said aircraft;“S” represents the total surface area of the two half-wings;“ Cz” represents the mean lift coefficient of said two half-wings, which coefficient is a function of the aerodynamic angle of incidence α of said half-wings, where: α=αfus+αinteraction “αfus” represents the aerodynamic angle of incidence of said aircraft and is determined by: αfus=θ−Arcsin(Vz/TAS)“αinteraction” represents an angle of incidence correction of said half-wings;“Vz” represents the vertical speed of the air relative to said aircraft;“θ” represents the longitudinal attitude of said aircraft; and“×” represents the multiplication sign;and then said lift of said half-wings is adjusted so that said lift of said half-wings is equal to said first predetermined percentage of said total lift of the aircraft. 5. A method according to claim 1, wherein said main rotor is driven by a main gearbox connected to said fuselage by a plurality of support bars, forces in said support bars are measured, and the lift of said main rotor is determined from the measurements of said forces in said support bars, after which the lift of said half-wings is adjusted so that said lift of said main rotor is equal to a second predetermined percentage of said total lift of the aircraft, the sum of said first predetermined percentage plus said second predetermined percentage being equal to 100%. 6. A method according to claim 1, wherein said lift of said half-wings is adjusted when: the roll angle of said aircraft is less than 10%;the forward air speed TAS of said aircraft is greater than 50 kts; andno action is detected on the controls of said aircraft. 7. A method according to claim 1, wherein said lift difference between said two half-wings is determined in order to compensate for said effects of said main rotor on said half-wings. 8. A method according to claim 1, wherein a setpoint lateral cyclic pitch is determined so that said lift difference between said two half-wings enables a lateral cyclic pitch of said blades of said main rotor to be equal to said setpoint lateral cyclic pitch. 9. A method according to claim 1, wherein a setpoint lateral bending moment of a mast of a said main rotor is determined so that said lift difference between said half-wings enables a lateral bending moment of said mast of said main rotor to be equal to said setpoint lateral bending moment of said mast of said main rotor. 10. A method according to claim 1, wherein the lift of said horizontal stabilizer is adjusted by acting on control means for each movable surface so that a longitudinal cyclic pitch of said blades of said main rotor is equal to a setpoint longitudinal cyclic pitch. 11. A method according to claim 1, wherein the lift of said horizontal stabilizer is adjusted by acting on control means for each movable surface so that the power consumed by said main rotor is equal to a setpoint power during said stabilized stage of flight. 12. A method according to claim 11, wherein said setpoint power consumed by said main rotor during a stabilized stage of flight corresponds to a value lying in the range 20% to 40% of the power consumed by said main rotor during hovering flight of said aircraft. 13. A method according to claim 1, wherein the lift of said horizontal stabilizer is adjusted by acting on control means for each movable surface so that the longitudinal bending moment of a mast of said main rotor is equal to a setpoint longitudinal bending moment during said stage of stabilized flight. 14. A method according to claim 1, wherein the following are determined simultaneously: the longitudinal cyclic pitch of said blades of said main rotor in order to ensure the longitudinal attitude of said aircraft is equal to a setpoint longitudinal attitude;the collective pitch of said blades of said main rotor in order to ensure that the altitude of said aircraft is equal to a setpoint altitude;the lateral cyclic pitch of said blades of said main rotor in order to ensure that the lateral attitude of said aircraft is equal to a setpoint lateral attitude;the lift of said horizontal stabilizer in order to ensure that the power consumed by said main rotor is equal to a target power;the lift of said half-wings corresponding to said first predetermined percentage of said total lift of said aircraft; andthe difference in lift between the half-wings in order to compensate for the angle of incidence asymmetry generated by said main rotor between said half-wings. 15. A method according to claim 1, wherein information is displayed on display means of said aircraft, the information relating to said lift of said main rotor, to said setpoint lift for said main rotor, to said flaps, and to said horizontal stabilizer. 16. A high-speed rotary wing aircraft comprising: a fuselage;at least one main rotor having a plurality of blades;at least one variable-pitch propulsive propeller;at least one horizontal stabilizer positioned at one end of said aircraft and including at least one movable surface;at least two half-wings positioned on either side of said fuselage, aerodynamic control means for modifying the lift of said two half-wings, said aerodynamic control means comprising at least one movable flap on each half-wing and at least one control system for operating said flaps; andat least one power plant driving said main rotor and said propulsive propeller;wherein said control system enables each flap to be operated so as to adjust the lift of said half-wings in order to ensure that (i) said lift of said half-wings is equal to a first predetermined percentage of the total lift of said aircraft during a stage of stabilized flight and (ii) the lift of each half-wing is different such that a difference in lift is between two half-wings, with the difference in lift between said two half-wings serving to compensate for the effects of said main rotor affecting said half-wings differently. 17. An aircraft according to claim 16, wherein said control means for operating said movable surface makes it possible to adjust the lift of said horizontal stabilizer in order to ensure that the power consumed by said main rotor is equal to a setpoint power. 18. An aircraft according to claim 16, including display means that display: information relating to said lift of said main rotor and to a setpoint lift for said main rotor corresponding to a second predetermined percentage of said total lift of the aircraft, the sum of said first predetermined percentage plus said second predetermined percentage being equal to 100%;information relating to said flaps;a mode of operation activated for said flaps;information relating to said horizontal stabilizer; anda mode of operation activated for said horizontal stabilizer. 19. A method according to claim 1, wherein the following are determined simultaneously: the longitudinal cyclic pitch of said blades of said main rotor in order to ensure the longitudinal attitude of said aircraft is equal to a setpoint longitudinal attitude;the collective pitch of said blades of said main rotor in order to ensure that the angle of incidence of said aircraft is equal to a setpoint angle of incidence;the lateral cyclic pitch of said blades of said main rotor in order to ensure that the lateral attitude of said aircraft is equal to a setpoint lateral attitude;the lift of said horizontal stabilizer in order to ensure that the power consumed by said main rotor is equal to a target power;the lift of said half-wings corresponding to said first predetermined percentage of said total lift of said aircraft; andthe difference in lift between the half-wings in order to compensate for the angle of incidence asymmetry generated by said main rotor between said half-wings. 20. A method of controlling a high-speed rotary wing aircraft, the aircraft comprising: a fuselage;at least one main rotor having a plurality of blades;at least one variable-pitch propulsive propeller;at least two half-wings positioned on either side of said fuselage;aerodynamic control means of said aircraft comprising at least one movable flap on each half-wing, and at least one system for operating said flaps;at least one horizontal stabilizer positioned at one end of said aircraft, said horizontal stabilizer having at least one movable surface; andat least one power plant driving said main rotor and each propulsive propeller in rotation;the method comprising the following steps:determining the total lift of the aircraft assuming that said total lift counters the weight of said aircraft; andadjusting the lift of each half-wing by acting on said system for controlling said flaps so that said lift of said half-wings is equal to a first predetermined percentage of said total lift of said aircraft during a stage of stabilized flight, a difference in lift between said two half-wings serving to compensate for the effects of said main rotor on said half-wings;wherein said main rotor is driven by a main gearbox connected to said fuselage by a plurality of support bars, forces in said support bars are measured, and the lift of said main rotor is determined from the measurements of said forces in said support bars, after which the lift of said half-wings is adjusted so that said lift of said main rotor is equal to a second predetermined percentage of said total lift of the aircraft, the sum of said first predetermined percentage plus said second predetermined percentage being equal to 100%.
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이 특허에 인용된 특허 (3)
Osder, Stephen S.; Thompson, Thomas L., Enhanced flight control systems and methods for a jet powered tri-mode aircraft.
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