Electronic flight control system for an aircraft capable of hovering
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G01C-023/00
G05D-001/00
G06F-007/00
G05D-001/08
B64C-027/57
출원번호
US-0377308
(2010-06-10)
등록번호
US-8989921
(2015-03-24)
우선권정보
IT-TO20090079 U (2009-06-10)
국제출원번호
PCT/IB2010/001396
(2010-06-10)
§371/§102 date
20120307
(20120307)
국제공개번호
WO2010/143051
(2010-12-16)
발명자
/ 주소
Nannoni, Fabio
Abdel Nour, Pierre
Cicale′, Marco
출원인 / 주소
Agustawestland S.p.A.
대리인 / 주소
Ohlandt Greeley Ruggiero & Perle L.L.P.
인용정보
피인용 횟수 :
5인용 특허 :
20
초록▼
An electronic flight control system for an aircraft capable of hovering and having at least one rotor. The flight control system is configured to operate in a manual flight control mode, in which the flight control system controls rotor speed in response to direct commands from the pilot; and in at
An electronic flight control system for an aircraft capable of hovering and having at least one rotor. The flight control system is configured to operate in a manual flight control mode, in which the flight control system controls rotor speed in response to direct commands from the pilot; and in at least two automatic flight control modes corresponding to respective flight modes of the aircraft, and in which the flight control system controls rotor speed automatically on the basis of flight conditions. The flight control system is also configured to memorize, for each automatic flight control mode, a respective flight table relating different speed values of the rotor to different values of at least one flight quantity; and to automatically control rotor speed in the automatic flight control modes on the basis of the respective flight tables.
대표청구항▼
1. A flight control system that is electronic and is for an aircraft capable of hovering and comprising at least one rotor, the flight control system comprising: a manual flight control mode that the flight control system is configured to operate in, in which the flight control system controls rotor
1. A flight control system that is electronic and is for an aircraft capable of hovering and comprising at least one rotor, the flight control system comprising: a manual flight control mode that the flight control system is configured to operate in, in which the flight control system controls rotor speed in response to direct commands from a pilot; andat least two automatic flight control modes that the flight control system is configured to operate in corresponding to respective flight modes of the aircraft, and in which the flight control system controls the rotor speed automatically on a basis of flight conditions;the flight control system being characterized by also being configured to: memorize, for each of said automatic flight control modes, a respective flight table relating different speed values of said rotor to different values of at least one flight quantity; andautomatically control the rotor speed in said automatic flight control modes on a basis of the respective flight tables. 2. The flight control system as claimed in claim 1, wherein the values of said at least one flight quantity in each respective flight table are divided into ranges, each associated with a corresponding rotor speed value. 3. A flight control system as claimed in claim 1, and also configured to control switching between different rotor speed values in the same automatic flight control mode automatically and in stair-step profiles. 4. A flight control system as claimed in claim 3, wherein the stair-step profiles have a size of steps in ranges between 1% and 10% of a range spanned by values between which switching is performed. 5. A flight control system as claimed in claim 1, and wherein said automatic flight control modes are such that the aircraft flies in: a low-noise and/or low-fuel-consumption flight mode; anda high-performance flight mode. 6. A flight control system as claimed in claim 5, wherein said high-performance flight mode is such as to maximize a flight envelope. 7. A flight control system as claimed in claim 1, wherein said flight table relates different speed values of said rotor to different values of at least two different flight quantities; and the values of the at least two different flight quantities in each flight table are divided into areas, each associated with a corresponding rotor speed value. 8. A flight control system as claimed in claim 7, wherein said at least two different flight quantities are selected from quantities indicating aircraft flying speed, density altitude, pressure altitude, height above ground level, aircraft weight, orientation, flying direction, air temperature, atmospheric pressure, weather conditions, and wind force and direction. 9. A flight control system as claimed in claim 1, and also configured to automatically control switching between the two automatic flight control modes in response to pilot command. 10. A flight control system as claimed in claim 9, and also configured to enable or disable switching between the two automatic flight control modes on a basis of an in-flight weight of the aircraft. 11. A flight control system that is electronic and is for an aircraft capable of hovering and comprising at least one rotor, the flight control system comprising: a manual flight control mode that the flight control system is configured to operate in, in which the flight control system controls rotor speed in response to direct commands from a pilot; andat least two automatic flight control modes that the flight control system is configured to operate in corresponding to respective flight modes of the aircraft, and in which the flight control system controls the rotor speed automatically on a basis of flight conditions;the flight control system being characterized by also being configured to: memorize, for each of said automatic flight control modes, a respective flight table relating different speed values of said rotor to different values of at least one flight quantity; andautomatically control the rotor speed in said automatic flight control modes on a basis of the respective flight tables, wherein the electronic flight control system is in the aircraft. 12. A computer readable non-transitory memory storing instructions, which when executed by a computer system results in providing a flight control system that is electronic and is for an aircraft capable of hovering and comprising a main rotor and a tail rotor, comprising: providing a manual flight control mode, in which the flight control system controls rotor speed in response to direct commands from a pilot;providing at least two automatic flight control modes corresponding to respective flight modes of the aircraft, and in which the flight control system controls the rotor speed automatically on a basis of flight conditions;providing, for each of said automatic flight control modes, a respective flight table relating different speed values of said rotor to different values of at least one flight quantity; andautomatically controlling the rotor speed in said automatic flight control modes on a basis of the respective flight tables.
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이 특허에 인용된 특허 (20)
Murphy Richard D. (Trumbull CT) Perez Ricardo L. (Southington CT) Clelford Douglas H. (Trumbull CT), Aircraft short-term roll attitude retention system.
Ebert Frederick J. (Westport CT) Rice Robert W. (Sandy Hook CT), Helicopter engine speed enhancement during heavy rotor load and rapid descent rate maneuvering.
Salesse-Lavergne, Marc, Flight control system and method for a rotary wing aircraft, enabling it to maintain either track or heading depending on its forward speed.
Salesse-Lavergne, Marc, Method and system for engaging hovering flight for a rotary wing aircraft, enabling it to maintain either track or heading depending on its forward speed.
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