Method of controlling the yawing movement of an aircraft running along the ground
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0211659
(2011-08-17)
|
등록번호 |
US-8666598
(2014-03-04)
|
우선권정보 |
FR-10 56655 (2010-08-18) |
발명자
/ 주소 |
- Lemay, David
- Frank, David
- Basset, Michel
- Chamaillard, Yann
|
출원인 / 주소 |
|
대리인 / 주소 |
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인용정보 |
피인용 횟수 :
1 인용 특허 :
6 |
초록
▼
A method of controlling a yawing movement of an aircraft running along the ground, the aircraft comprising at least one first landing gear with a steerable bottom part bearing wheels. The method comprises the steps of (1) on the basis of a yaw rate setpoint {dot over (φ)}c, determining a wheel-steer
A method of controlling a yawing movement of an aircraft running along the ground, the aircraft comprising at least one first landing gear with a steerable bottom part bearing wheels. The method comprises the steps of (1) on the basis of a yaw rate setpoint {dot over (φ)}c, determining a wheel-steering prepositioning angle θp; and (2) using closed-loop control which as its input has the yaw rate setpoint and which generates a command to steer the bottom part in order to steer it through a steering angle θc equal to the sum of this prepositioning angle θp and of an angle θz which is determined taking account of an error between the yaw rate setpoint {dot over (φ)}c and the measured yaw rate {dot over (φ)}m when the steerable bottom part is steered by the steering angle θc.
대표청구항
▼
1. A method of controlling a yawing movement of an aircraft having a fuselage and running along the ground, the aircraft comprising at least one first landing gear with a steerable bottom part bearing wheels, the method being characterized in that it comprises the steps of: on the basis of a yaw rat
1. A method of controlling a yawing movement of an aircraft having a fuselage and running along the ground, the aircraft comprising at least one first landing gear with a steerable bottom part bearing wheels, the method being characterized in that it comprises the steps of: on the basis of a yaw rate, determining a wheel-steering prepositioning angle θp;using closed-loop control, which as its input has the yaw rate and which generates a command to steer the steerable bottom part in order to steer the steerable bottom part through a required steering angle θc equal to the sum of said prepositioning angle θp and an angle θz, which is determined by taking account of an error, between the yaw rate and a measured yaw rate φm, when the steerable bottom part is steered by the required steering angle θc;the method applied to an aircraft further comprising at least two main landing gears with wheels and being positioned, respectively, a left main landing gear on a left side of the fuselage and a right main landing gear on a right side of the fuselage and the wheels each of said left and fight main landing gears being associated with torque application members, the method further comprising the step of generating, for attention of the torque application members of the left and fight main landing gears, two acceleration setpoints, a left setpoint {acute over (Γ)}g and a right setpoint {acute over (Γ)}d, so that the torque application members thus stimulated generate, on the aircraft, a yaw moment Mzp that complements the yaw moment Mza generated by the first landing gear, so that the total yaw moment generated on the aircraft allows the aircraft to comply with the yaw setpoint φc; andthe method in which the acceleration setpoints {acute over (Γ)}g, {acute over (Γ)}d are generated taking account of saturations in the accelerations on the right side (Satg) and on the left side (Satd) of the wheels of the right and left main landing gears, respectively. 2. The method according to claim 1, in which the required steering angle θ, is equal to a sum of the prepositioning angle θp and the angle θz, which is further determined taking account of an error between the required steering angle θc and a measured steering angle θm. 3. The method according to claim 1, in which the acceleration setpoints {acute over (Γ)}g, {acute over (Γ)}d are generated taking account of an error between the yaw rate setpoint φc and the measured yaw rate φm. 4. The method according to claim 3, in which the acceleration setpoints Γg, Γd are generated taking further account of an error between a rotation differential setpoint Δωc that is the differential in rotation between the wheels of the left and right main landing gears and a measured rotation differential Δωm that is the differential in rotation between the wheels of the right and left main landing gears.
이 특허에 인용된 특허 (6)
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Kilner Jerome R. (Bellevue WA) Warren Steven M. (Seattle WA), Automatic control system for directional control of an aircraft during landing rollout.
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Thacker Clarke Fisk ; Restauri Robert Daniel, Automotive vehicle steering column lock mechanism.
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Soltis Michael W. (Dearborn MI), Control system for multistable suspension unit.
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Baumann Janet,DEX ; Schafer Burkhard,DEX, Motor vehicle steering column assembly unit.
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Tandy, Jr., Donald Frank; Tandy, Sr., Donald Frank, Stability enhancing system for tow-vehicle and trailer assembly combination with two processors.
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Tandy, Jr., Donald Frank; Tandy, Sr., Donald Frank, Stability enhancing system for tow-vehicle towing trailer assembly.
이 특허를 인용한 특허 (1)
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Guignard, Fabien; Venilal, Priteche, Method and device for estimating a lateral speed and a lateral position of an aircraft, during a phase where the aircraft is traveling on the ground.
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