Method and apparatus for changing a deployed position for a tail skid assembly
AssigneeThe Boeing Company
InventorJustin Duane Cottet
Life of this patent
Estimating the term…
Abstract
A method and apparatus for positioning a tail skid assembly for a maximum rotation angle for an aircraft may be provided. A determination may be made as to whether the tail skid assembly is to be deployed for takeoff or landing. A set of parameters may be identified based on a determination of whether the tail skid assembly is to be deployed for takeoff or landing. A desired maximum rotation angle for the aircraft may be identified using the set of parameters. The tail skid assembly may be deployed to allow the desired maximum rotation angle for the aircraft.
Claims15
A method for positioning a tail skid assembly for a maximum rotation angle for an aircraft, the method comprising:
- determining whether the tail skid assembly is to be deployed for takeoff or landing;
- identifying a set of parameters based on a determination of whether the tail skid assembly is to be deployed for takeoff or landing;
- identifying a desired maximum rotation angle for the aircraft using the set of parameters;
- and
- deploying the tail skid assembly to allow the desired maximum rotation angle by adjusting an actuator system connected:
- at a first end to the aircraft at an axis connecting a first end of an elongate structure of the tail skid assembly to the aircraft, and at a second end to a pin also connected to:
- a deployment device connected to a shock absorber, and an elongate opening in the elongate structure.
A method for positioning a tail skid assembly for a maximum rotation angle for an aircraft, the method comprising:
- determining whether the tail skid assembly is to be deployed for takeoff or landing;
- identifying a set of parameters based on a determination of whether the tail skid assembly is to be deployed for takeoff or landing;
- identifying a desired maximum rotation angle for the aircraft using the set of parameters;
- and
- moving a deployment device in the tail skid assembly to change a deployed position for an elongate structure in the tail skid assembly allowing the desired maximum rotation angle for the aircraft by adjusting an actuator system connected:
- at a first end directly to the aircraft at an axis directly connecting a first end of the elongate structure to the aircraft, and at a second end to a pin, the pin also connected to:
- a deployment device connected to a shock absorber, and an elongate opening in the elongate structure.
Dependencies are inferred from the claim text.