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US 11,142,301 B2Granted
Methods and apparatus for mitigating aerodynamic flutter of aircraft wing flaps
AssigneeThe Boeing Company
InventorsMark S. Good, Rene T. Nguyen, Gregor W. Dempster, Bryan J. Gruner, Kwan-Ho Bae, Patrick M. Fahey
Life of this patent
Estimating the term…
Abstract
Example methods and apparatus for mitigating aerodynamic flutter of aircraft wing flaps are disclosed. An example apparatus includes a fairing, an actuator, and a damper. The fairing is located on a bottom side of a wing of an aircraft. The actuator is disposed in the fairing. The actuator is coupled to and extends between the wing and a flap of the wing. The damper is disposed in the fairing. The damper is coupled to and extends between the fixed wing and the moveable flap.
Claims25
An apparatus, comprising:
- a fairing located on a bottom side of a wing of an aircraft;
- an actuator disposed in the fairing, the actuator coupled to and extending between the wing and a flap of the wing;
- a damper disposed in the fairing, the damper coupled to and extending between the wing and the flap, the damper including:
- a piston rod having a first end, a second end located opposite the first end, and a rod head located between the first end and the second end, the rod head having a first side and a second side located opposite the first side;
- a cylinder having a fluid chamber containing the rod head, the rod head separating the fluid chamber into a first portion including the first side of the rod head and a second portion including the second side of the rod head;
- a first fluid supply line in fluid communication with the first portion of the fluid chamber;
- a second fluid supply line in fluid communication with the second portion of the fluid chamber, the first and second fluid supply lines respectively configured to receive pressurized hydraulic fluid from a hydraulic system of the aircraft;
- a damping orifice operatively positioned between and in fluid communication with the first and second fluid supply lines;
- a first pressure transducer in fluid communication with the first fluid supply line, the first pressure transducer configured to monitor a first hydraulic pressure associated with the first portion of the fluid chamber;
- and
- a second pressure transducer in fluid communication with the second fluid supply line, the second pressure transducer configured to monitor a second hydraulic pressure associated with the second portion of the fluid chamber.
8 more elements
A method, comprising:
- moving a flap of a wing of an aircraft relative to a fixed portion of the wing between a retracted position and a deployed position, the flap being moved via an actuator coupled to and extending between the fixed portion and the flap, the actuator disposed in a fairing located on a bottom side of the wing and extending between the fixed portion and the flap;
- and
- damping movement of the flap to mitigate aerodynamic flutter of the flap, the movement of the flap being damped via a damper coupled to and extending between the fixed portion and the flap, the damper disposed in the fairing, the damper including:
- a piston rod having a first end, a second end located opposite the first end, and a rod head located between the first end and the second end, the rod head having a first side and a second side located opposite the first side;
- a cylinder having a fluid chamber containing the rod head, the rod head separating the fluid chamber into a first portion including the first side of the rod head and a second portion including the second side of the rod head;
- a first fluid supply line in fluid communication with the first portion of the fluid chamber;
- a second fluid supply line in fluid communication with the second portion of the fluid chamber, the first and second fluid supply lines respectively configured to receive pressurized hydraulic fluid from a hydraulic system of the aircraft;
- a damping orifice operatively positioned between and in fluid communication with the first and second fluid supply lines;
- a first pressure transducer in fluid communication with the first fluid supply line, the first pressure transducer configured to monitor a first hydraulic pressure associated with the first portion of the fluid chamber;
- and
- a second pressure transducer in fluid communication with the second fluid supply line, the second pressure transducer configured to monitor a second hydraulic pressure associated with the second portion of the fluid chamber.
8 more elements
An apparatus, comprising:
- a fairing located on a bottom side of a wing of an aircraft;
- an actuator disposed in the fairing, the actuator coupled to and extending between the wing and a flap of the wing;
- and
- a damper coupled to and extending between the wing and the flap, the damper including:
- a piston rod disposed in the fairing, the piston rod having a first end, a second end located opposite the first end, and a rod head located between the first end and the second end, the rod head having a first side and a second side located opposite the first side;
- a cylinder disposed in the fairing, the cylinder having a fluid chamber containing the rod head, the rod head separating the fluid chamber into a first portion including the first side of the rod head and a second portion including the second side of the rod head;
- a first fluid supply line in fluid communication with the first portion of the fluid chamber;
- a second fluid supply line in fluid communication with the second portion of the fluid chamber, the first and second fluid supply lines respectively configured to receive pressurized hydraulic fluid from a hydraulic system of the aircraft;
- a damping orifice operatively positioned between and in fluid communication with the first and second fluid supply lines;
- a first pressure transducer in fluid communication with the first fluid supply line, the first pressure transducer configured to monitor a first hydraulic pressure associated with the first portion of the fluid chamber;
- and
- a second pressure transducer in fluid communication with the second fluid supply line, the second pressure transducer configured to monitor a second hydraulic pressure associated with the second portion of the fluid chamber.
9 more elements
Dependencies are inferred from the claim text.