Landing gear system for an aircraft
Retraction of a landing gear assembly on an aircraft is actuated by a hydraulic actuator. The actuator includes a piston that travels within a cylinder along a stroke length between a first position corresponding to the landing gear assembly when extended and a second position corresponding to the landing gear assembly when retracted. The movement of the piston along its stroke length is snubbed at one end by a different amount according to the direction of travel, for example by use of an orifice plate that has a discharge coefficient that is greater in one direction than in the opposite direction. Asymmetric snubbing is thus provided, which enables the landing gear to retract faster.
1. A landing gear system for an aircraft, wherein the system includes
a retractable landing gear assembly, and
a hydraulic actuator for actuating retraction of at least a part of the landing gear assembly from an extended configuration to a retracted configuration,
the hydraulic actuator including a piston that travels within a cylinder along a stroke length between a first position corresponding to the extended configuration of said part of the landing gear assembly and a second position corresponding to the retracted configuration of said part of the landing gear assembly, and
movement of the piston along its stroke length being snubbed for a portion of the stroke length when proximate to, and moving in a direction towards, one of the first position and the second position, and wherein the snubbing, if any, is less when moving in the opposite direction, there thus being provided asymmetric snubbing,
the asymmetric snubbing being provided by the flow of hydraulic fluid during both directions of travel of the piston through a passageway connected to a first hydraulic supply line and including a cross-sectional shape which tapers in one direction such that there is more snubbing for fluid flow in one direction than in the opposite direction, as a result of the shape of the passageway, and
wherein the passageway has a discharge coefficient of 0.9 or more in a flow direction corresponding to the snubbing, if any, when the piston is moving in said opposite direction.
2. The landing gear system according to claim 1 , wherein the shape of the passageway is asymmetric along its length, and the shape when there is snubbing with fluid flowing in one direction is the same as the shape when there is snubbing with fluid flowing in the opposite direction.
3. The landing gear system according to claim 1 , wherein the passageway has a cross-sectional shape which presents a corner or step to the flow of fluid in one direction.
4. The landing gear system according to claim 1 , wherein the hydraulic actuator is arranged to actuate retraction of the landing gear assembly from its extended configuration to its retracted configuration.
5. The landing gear system according to claim 1 , wherein the landing system comprises a main strut at an extreme end of which there are mounted one or more aircraft wheels.
6. The landing gear system according to claim 1 , wherein the passageway has a shape between its extreme ends which reduces to a minimum cross-sectional area in one direction along the passageway faster than it reduces to the same minimum cross-sectional area in the opposite direction.
7. The landing gear system according to claim 6 , wherein a portion of the passageway has a shape extending from a position at or proximate to one of its extreme ends having a constant cross-section which has an area equal to the minimum cross-sectional area.
8. An aircraft landing gear retraction actuator for the landing gear system of claim 1 , wherein the actuator is configured to provide asymmetric snubbing at an end of its stroke length with the use of an orifice plate that has a discharge coefficient that is greater in one direction than in an opposite direction.
9. The actuator according to claim 8 , wherein the actuator has a stroke length of 300 mm or more.
10. An aircraft comprising the landing gear retraction actuator of claim 8 .
11. A hydraulic actuator configured for use as the hydraulic actuator of the landing gear system according to claim 1 .
12. An aircraft comprising the landing gear system of claim 1 .
13. A landing gear system for an aircraft, wherein the system includes
a retractable landing gear assembly, and
a hydraulic actuator for actuating retraction of at least a part of the landing gear assembly from an extended configuration to a retracted configuration,
the hydraulic actuator including a piston that travels within a cylinder along a stroke length between a first position corresponding to the extended configuration of said part of the landing gear assembly and a second position corresponding to the retracted configuration of said part of the landing gear assembly,
movement of the piston along its stroke length being snubbed for a portion of the stroke length when proximate to, and moving in a direction towards, one of the first position and the second position, and wherein the snubbing, if any, is less when moving in the opposite direction, there thus being provided asymmetric snubbing,
the asymmetric snubbing being provided by the flow of hydraulic fluid during both directions of travel of the piston through a passageway connected to a first hydraulic supply line and including a cross-sectional shape which tapers in one direction such that there is more snubbing for fluid flow in one direction than in the opposite direction, as a result of the shape of the passageway, and
wherein a portion of the passageway comprises a structure with a plurality of perforations through which the hydraulic fluid flows.
14. A landing gear system for an aircraft, wherein the system includes
a retractable landing gear assembly, and
a hydraulic actuator for actuating retraction of at least a part of the landing gear assembly from an extended configuration to a retracted configuration,
the hydraulic actuator including a piston that travels within a cylinder along a stroke length between a first position corresponding to the extended configuration of said part of the landing gear assembly and a second position corresponding to the retracted configuration of said part of the landing gear assembly,
movement of the piston along its stroke length being snubbed for a portion of the stroke length when proximate to, and moving in a direction towards, one of the first position and the second position, and wherein the snubbing, if any, is less when moving in the opposite direction, there thus being provided asymmetric snubbing,
the asymmetric snubbing being provided by the flow of hydraulic fluid during both directions of travel of the piston through a passageway connected to a first hydraulic supply line and including a cross-sectional shape which tapers in one direction such that there is more snubbing for fluid flow in one direction than in the opposite direction, as a result of the shape of the, and
wherein the passageway has a discharge coefficient of 0.7 or less in a flow direction corresponding to the greater snubbing of the piston.
15. The landing gear system according to claim 14 , wherein the shape of the passageway is asymmetric along its length, and the shape when there is snubbing with fluid flowing in one direction is the same as the shape when there is snubbing with fluid flowing in the opposite direction.
16. The landing gear system according to claim 14 , wherein the passageway has a shape between its extreme ends which reduces to a minimum cross-sectional area in one direction along the passageway faster than it reduces to the same minimum cross-sectional area in the opposite direction.
17. The landing gear system according to claim 14 , wherein the passageway has a cross-sectional shape which presents a corner or step to the flow of fluid in one direction.
18. A method of operating an aircraft landing gear comprising the landing gear system of claim 1 , wherein the landing gear is movable between a deployed position suitable for supporting a portion of the weight of the aircraft on the ground and a stowed position, the method comprising the steps of
moving the landing gear from the stowed position to the deployed position, the last 5% of the distance to be travelled by the landing gear as a percentage of the total distance from the stowed position to the deployed position being at an average speed, V 1 , that is lower than the average speed, V 2 , for the middle 90% of the distance, and then
moving the landing gear from the deployed position to the stowed position, the first 5% of the distance to be travelled by the landing gear as a percentage of the total distance from the deployed position to the stowed position being at an average speed, V 3 , that is greater than V 1 by at least 10%.
19. The method according to claim 18 , wherein
V 1 <50% of V 2 , and
V 2 >V 3 >120% of V 1 .