Landing gear systems and methods of testing
A method of extending a landing gear of an aircraft is disclosed. The aircraft includes an uplock arranged to retain the landing gear in a retracted position, a primary landing gear system configured to retract and extend the landing gear, and an alternate landing gear system, independent from the primary landing gear system. The method includes the primary landing gear system holding the landing gear in place while the uplock is moved from a first configuration to a second configuration by the alternate landing gear system.
1 . A method of extending a landing gear of an aircraft, the aircraft comprising:
an uplock arranged to retain the landing gear in a retracted position,
a primary landing gear system having a main actuator configured to retract and extend the landing gear, and
an alternate landing gear system, independent from the primary landing gear system,
wherein the alternate landing gear system comprises an actuator arranged to move the uplock between a first configuration and a second configuration,
wherein the method comprises the main actuator of the primary landing gear system holding the landing gear in place while the uplock is moved from the first configuration to the second configuration by the actuator of the alternate landing gear system.
2 . The method according to claim 1 , wherein the aircraft has a monitoring system comprising one or more sensors arranged to detect whether the uplock is in the first and/or second configuration, the method comprises the monitoring system determining the configuration of the uplock in dependence on a signal received from said one or more sensors, and the monitoring system is configured to provide an indication to a control system of the aircraft and/or to a user in the case that the alternate landing gear system fails to move the uplock from the first configuration to the second configuration.
3 . The method according to claim 2 , wherein the alternate landing gear system comprises at least one isolation valve, positioned on a hydraulic line of the primary landing gear system so that closure of the isolation valve isolates the primary landing gear system from the rest of the hydraulic systems of the aircraft and/or the hydraulic supply, and the method comprises the alternate landing gear system moving the isolation valve(s) to a closed position, and then, optionally, the alternate landing gear system returning the isolation valve(s) to an open position.
4 . The method according to claim 3 , wherein the monitoring system also comprises one or more sensors arranged to detect the position of the or each isolation valve and/or vent valve of the alternate landing gear system, and the method comprises the monitoring system determining the position of the valve(s) in dependence on the signal received from said one or more sensors and the monitoring system being configured to provide an indication to a control system of the aircraft and/or to a user in the case that the alternate landing gear system fails to move the isolation valve(s) to an closed position and/or the vent valve(s) to an open position.
5 . The method according to claim 1 , wherein the first configuration is a locked and closed configuration and the second configuration is an unlocked and closed configuration or an open configuration.
6 . The method according to claim 1 , wherein the primary landing gear system continues to hold the landing gear in place while the uplock is returned to the first configuration from the second configuration by the alternate landing gear system.
7 . The method according to claim 1 , further comprising the primary landing gear system moving the landing gear within a body of the aircraft to a lifted position in which weight of the landing gear upon the uplock is reduced and/or removed, and the primary landing gear system then holds the landing gear in the lifted position while the alternate landing gear system moves the uplock between the first configuration and the second configuration.
8 . The method according to claim 1 , wherein a step of opening one or more landing gear bay doors is carried out after the uplock is moved from the first configuration to the second configuration by the alternate landing gear system.
9 . The method according to claim 1 , wherein the method is carried out while the aircraft is in the air.
10 . The method according to claim 1 , wherein the alternate landing gear system comprises at least one vent valve, positioned on a hydraulic line of the primary landing gear system so that opening the vent valve reduces the hydraulic pressure in the primary landing gear system by connecting the hydraulics of the primary landing gear system to tank or return, and the method comprises the alternate landing gear system moving the vent valve(s) to an open position, and then, optionally, the alternate landing gear system returning the vent valve(s) to a closed position.
11 . The method according to claim 10 , wherein the method comprises the alternate landing gear system moving the isolation valve(s) to the closed position and/or the vent valve(s) to an open position for less than ten seconds, for example for less than one second, and then returning the isolation valve(s) to an open position and/or the vent valve(s) to a closed position.
12 . The method of claim 1 , wherein the step of the primary landing gear system holding the landing gear in place while the uplock is moved from a first configuration to a second configuration by the alternate landing gear system is carried out periodically, for example at least once for every fifty landings.
13 . A method of testing a landing gear system in an aircraft, the aircraft comprising:
an uplock arranged to retain the landing gear in a retracted position;
a primary landing gear system having a main actuator configured to extend and retract the landing gear; and
an alternate landing gear system, independent of the primary landing gear system,
wherein the alternate landing gear system comprises an actuator arranged to move the uplock between a first configuration and a second configuration,
wherein the method comprises the alternate landing gear system moving the uplock from the first configuration to the second configuration while the landing gear is extended and the aircraft is on the ground.
14 . The method of claim 13 , wherein the method comprises the alternate landing gear system returning the uplock to the first configuration from the second configuration while the landing gear is extended and the aircraft is on the ground.
15 . An aircraft comprising a landing gear, the aircraft comprising:
a primary landing gear system configured to retract and extend the landing gear;
an alternate landing gear system, independent of the primary landing gear system; and
a control system configured to operate the primary landing gear system and the alternate landing gear system in order to perform the method of claim 1 .