IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0721592
(2010-03-11)
|
등록번호 |
US-8295997
(2012-10-23)
|
우선권정보 |
FR-09 01137 (2009-03-12) |
발명자
/ 주소 |
- De Bono, Karine
- Godard, Michel
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
5 인용 특허 :
2 |
초록
▼
The present invention relates to a pilot assistance method for giving assistance in piloting a rotary wing aircraft, the method consisting in using a scale with collective pitch graduations that is movable on a display screen to indicate the position of the collective pitch, in determining the desyn
The present invention relates to a pilot assistance method for giving assistance in piloting a rotary wing aircraft, the method consisting in using a scale with collective pitch graduations that is movable on a display screen to indicate the position of the collective pitch, in determining the desynchronization pitch, in using a maximum limit value and a minimum limit value for the speed of rotation of the rotor, in transforming the maximum limit value and the minimum limit value in real time and as a function of physical flight parameters respectively into a bottom limit position and a top limit position for the collective pitch, and when a determined difference appears between the real value and the reference value Nr0 for the speed of rotation of the rotor, in displaying at least one item of corrective information about the adjustment of the collective pitch.
대표청구항
▼
1. A pilot assistance method for assisting the piloting of a rotary wing aircraft, the method comprising the steps of using a real value Nr and a reference value Nr0 for a speed of rotation of at least one rotor and using display means to present on a display screen (5) a movable scale (6a) for indi
1. A pilot assistance method for assisting the piloting of a rotary wing aircraft, the method comprising the steps of using a real value Nr and a reference value Nr0 for a speed of rotation of at least one rotor and using display means to present on a display screen (5) a movable scale (6a) for indicating collective pitch position P, the method further comprising: using a maximum limit value Nr+ and a minimum limit value Nr− for rotor rotation speed;determining using a processor a desynchronization pitch Pds corresponding to the position of the collective pitch P from which transmission of mechanical torque from a turbine engine unit and a main gearbox is interrupted;displaying the desynchronization pitch Pds on the movable scale (6a) by using a floating reference marker (9);translating in real time and as a function of physical flight parameters, the maximum limit value Nr+ and the minimum limit value Nr− respectively into a bottom limit position Pinf and a top limit position Psup for the collective pitch P, said limit positions Pinf and Psup being active;displaying the bottom and top limit positions Pinf and Psup on the movable scale (6a);comparing in real time the real value Nr of the speed of rotation of the rotor with the reference value Nr0 for the speed of rotation of the rotor; andwhen a determined difference appears between the real value Nr and the reference value Nr0 for the speed of rotation of the rotor, displaying at least one item of corrective information on the display screen (5), said information being at least visual and concerning action to be undertaken by the pilot on adjustment of the collective pitch P. 2. A pilot assistance method according to claim 1, further comprising using corrective information of presentation that changes when the position of the collective pitch P approaches the bottom limit position Pinf or the top limit position Psup in order to attract the pilot's attention more strongly. 3. A pilot assistance method according to claim 2, further comprising combining the visual corrective information with an audible warning in the event of the real value Nr crossing the maximum limit value Nr+ or the minimum limit value Nr− for the speed of rotation of the rotor. 4. A pilot assistance method according to claim 1, further comprising determining the desynchronization pitch by means of an algorithm involving theoretical data and/or data measured during flight testing. 5. A pilot assistance method according to claim 1, further comprising using a first-limit indicator FLI, using display means to present information on the display screen (5), said information relating to at least one monitoring parameter of the aircraft, for which the real value is closest to the limit value defined for said parameter, and further displaying the movable scale (6a) on said display screen (5). 6. A pilot assistance method according to claim 1, further comprising using an additional dial (14) to display a digital value in a stationary window (15) in the vicinity of the movable scale (6a), the digital value corresponding to a real value Nr of the speed of rotation of the rotor. 7. A pilot assistance method according to claim 6, further comprising associating an additional movable scale (17) with the stationary window (15), which additional movable scale presents zones (20, 21) of different colors together with a neutral central zone (19) including a central graduation (19a), said zones corresponding to real values Nr of the speed of rotation of the rotor, and in moving said additional movable scale (17) to display the colored zones (19, 20, 21) including the real value Nr in register with the stationary window (15) constituting another stationary reference marker (16). 8. A pilot assistance method according to claim 1, further comprising using as physical flight parameters, in particular measured values of temperature and altitude, speed of advance values, and/or values of other vehicle parameters of the aircraft. 9. A pilot assistance method according to claim 5, further comprising using a computer of the first-limit indicator FLI to act in real time to determine the top and bottom limit positions Psup and Pinf for the collective pitch and also the desynchronization pitch Pds. 10. A pilot assistance method according to claim 5, further comprising using a computer independent of the first-limit indicator FLI to determine in real time the top and bottom limit positions Psup and Pinf of the collective pitch P and also the desynchronization pitch Pds. 11. A pilot assistance method according to claim 1, further comprising using data measured during flight testing to determine in real time the top and bottom limit positions Psup and Pinf for the collective pitch P. 12. A pilot assistance method according to claim 6, wherein, when the aircraft has at least two engine units, the method further includes indicating a malfunction of one of the engine units at least visually on the additional dial (14) in the vicinity of the additional movable scale (17). 13. An aircraft flight indicator system including sensors suitable for delivering information relating to various monitoring parameters of the aircraft, a processor for processing said information, and a display for presenting information on a display screen (5), wherein the indicator system comprises: a screen that is movable relative to a stationary reference marker (6b) on the display screen (5), the scale indicating a position of the collective pitch P;an additional processor for processing in real time predetermined maximum and minimum limit values Nr+ and Nr− for the speed of rotation of the rotor respectively in bottom and top limit positions Pinf and Psup for the collective pitch P, said limit positions Pinf and Psup being active;said additional processor serving to determine the desynchronization pitch Pds corresponding to a position of the collective pitch beyond which transmission of mechanical torque between the turbine engine unit and the main gearbox is interrupted;a display for displaying in real time the bottom and top limit positions Pinf and Psup together with the desynchronization pitch Pds on the movable scale (6a);the additional processor including a comparator for comparing in real time a real value Nr with a reference value Nr0 for speed of rotation of the rotor; andthe additional processor also including an activator for activating the display to display corrective information on the display screen (5) as a function of a result of a difference between the real value Nr and the reference value Nr0 for a speed of rotation of the rotor, the corrective information being at least visual and concerning an action to be taken on the collective pitch. 14. A flight indicator system according to claim 13, wherein the processor, the additional processor, the display, and the activator are controlled by a computer of a first-limit indicator FLI. 15. A flight indicator system according to claim 13, wherein the additional processor and the activator are controlled by a computer distinct from the computer in communication with a first-limit indicator FLI. 16. A flight indicator system according to claim 14, wherein the computer includes software resources for determining by calculation firstly the top and bottom limit positions Psup and Pinf for the collective pitch P, and secondly the desynchronization pitch Pds. 17. A flight indicator system according to claim 14, wherein the computer also includes a memory having stored therein predetermined data together with flight test data, said data being used in calculations. 18. A flight indicator system according to claim 13, wherein the display screen (5) includes two juxtaposed dials (6, 7), one of the dials (7) being used for a first-limit indicator (FLI) and the other dial (6) being used in particular to display the movable scale (6a) indicating the pitch limit positions and the desynchronization pitch. 19. A flight indicator system according to claim 13, wherein the display screen (5) has a single dial used for a first-limit indicator FLI and for displaying the movable scale (6a) indicating pitch limit positions and desynchronization pitch. 20. A flight indicator system according to claim 13, including an additional dial (14) indicating: a real value Nr of the speed of rotation of the rotor in a stationary window (15) that also constitutes another stationary reference marker (16); at least one item of additional visual information concerning the difference between the real value Nr and the reference value Nr0 of the speed of rotation of the rotor; and/or at least one item of information concerning state(s) of operation of engine unit(s).
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