IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0149300
(2005-06-10)
|
등록번호 |
US-7363120
(2008-04-22)
|
우선권정보 |
FR-04 06274(2004-06-10) |
발명자
/ 주소 |
|
출원인 / 주소 |
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대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
5 인용 특허 :
6 |
초록
▼
The present invention relates to a method of adjusting at least one defective, main or anti-torque rotor of a particular rotorcraft. The method uses a neural network representing the relationships between firstly accelerations representative of vibration generated on at least a portion of a referen
The present invention relates to a method of adjusting at least one defective, main or anti-torque rotor of a particular rotorcraft. The method uses a neural network representing the relationships between firstly accelerations representative of vibration generated on at least a portion of a reference rotorcraft, and secondly defects and adjustment parameters. After determining the defects, if any, of a defective rotor, an adjustment value α is defined for at least one of the adjustment parameters, advantageously by minimizing the following relationship:
대표청구항
▼
What is claimed is: 1. A method of adjusting at least one defective main or anti-torque rotor (6, 10) of a particular rotorcraft, comprising the steps of: using a neural network that represents relationships between firstly accelerations representative of a vibration generated on at least a portion
What is claimed is: 1. A method of adjusting at least one defective main or anti-torque rotor (6, 10) of a particular rotorcraft, comprising the steps of: using a neural network that represents relationships between firstly accelerations representative of a vibration generated on at least a portion of a reference rotorcraft and secondly rotor defects and adjustment parameters, wherein each adjustment parameter is with respect to adjusting an element that affects the generated vibration; determining any defects of said rotor, wherein each one of said determined defects relates to a corresponding element that generated the vibration; determining an adjustment value α for at least one of said adjustment parameters by minimizing the following relationship: in which: γc, γa, γh, and γB-1 are weighting coefficients depending respectively on the stage of flight c, an accelerometer a, harmonics h, and the number of blades B of the rotor minus one; Rc,a,h is an output cell of the neural network corresponding to the harmonic h, the accelerometer a, and the stage of flight c; Rc,a,B-1 is an output cell of the neural network corresponding to the harmonic B-1, the accelerometer a, and the stage of flight c; γc,a,h is an acceleration signal at the frequency h measured by the accelerometer a for the stage of flight c; γc,a,B is an acceleration signal at the frequency B measured by the accelerometer a for the stage of flight c; and γc,a,B-1 is an acceleration signal at the frequency (B-1) measured by the accelerometer a for the stage of flight c; and based on the determined adjustment value, making an adjustment of at least one element to reduce the generated vibration. 2. A method according to claim 1, wherein said neural network is obtained from at least a first series of measurements using said reference rotorcraft (1) considered as being a deformable body, in which defect-free main and anti-torque rotors (6, 10) are adjusted to a reference adjustment at which the vibration level of at least said portion (3, 8) of said reference rotorcraft (1) is at a minimum. 3. A method according to claim 2, wherein said first series of measurements is taken during a particular operation of said reference rotorcraft by measuring the values of at least one acceleration, said measurements are taken at arbitrary locations on said portion (3, 8) of the reference rotorcraft and are representative of the vibration generated at said portion (3, 8) of the reference rotorcraft: a) firstly with the defect-free main or anti-torque rotor (6, 10) of the reference rotorcraft (1) adjusted to said reference adjustment; b) secondly by introducing defects in said defect-free main or anti-torque rotor (6, 10); and c) then by varying the adjustment values of a plurality of adjustment parameters of said main or anti-torque rotor (6, 10). 4. A method according to claim 3, wherein said first series of measurements is performed during at least the following test flights: a reference flight with the main or anti-torque rotor (6, 10) adjusted to said reference adjustment; flights with defects in said main or anti-torque rotor (6, 10); a flight with a particular wrong adjustment of at least one balance weight (25) of a blade (7); a flight with a particular wrong adjustment of at least one rod (27) of said blade (7); and a flight with a particular wrong adjustment of at least one compensator tab (28) provided on the trailing edge (29) of said blade (7). 5. A method according to claim 4, wherein at least one of said test flights includes the following stages, during which measurements are taken: a stage of hovering flight; a stage of cruising flight at about 50 m/s; a stage of flight at maximum continuous power; and a test on the ground with the main and the anti-torque rotors (6, 10) turning. 6. A method according to claim 3, wherein, in order to detect said defects of said rotor (6, 10), the following steps are performed: d) taking a second set of measurements on said particular rotorcraft (1) by measuring the values of at least some of said accelerations at said portion (3, 8) of the particular rotorcraft during particular operation of said particular rotorcraft; and e) detecting from said second series of measurements of accelerations and from the neural network, said defects of said rotor (6, 10). 7. A method according to claim 1, wherein adjustment elements defining said adjustment parameters comprise at least: a balance weight (25) for each of the blades (7) of the rotor (6, 10); a rod (27) on each of the blades (7) of the rotor (6, 10), with the exception of a blade that represents a reference blade; and a compensator tab (27) on the trailing edge (29) of each of the blades (7) of the rotor if it is the main rotor (6), each of the balance weight, the rod, and the compensator tab being adjustable to affect the generated vibration.
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