Landing gear disconnect mechanism for emergency deployment of landing gear actuator

Abstract

An aircraft (40) landing gear includes a main beam (52) coupled to an aircraft (40) for reciprocal movement between a stowed position and a deployed position. The actuator (100) is configured to drive reciprocating movement of the main beam (52). The actuator (100) includes a ball screw (140) and a motor (110). The motor (110) has an output shaft (112) operably coupled to the ball screw (140) by a gear train and configured to drive selective rotation of the ball screw (140). The actuator (100) also includes a disconnect mechanism (300) having a disconnect fitting (330), the disconnect fitting (330) being rotatably mounted to the ball screw (140). The biasing fitting (302) engages the disconnect fitting (330) to rotate the disconnect fitting (330) between a first position and a second position. The disconnect fitting (330) transmits rotation of the output shaft (112) to the ball screw (140) when the disconnect fitting (330) is in the first position. When the disconnect fitting (330) is in the second position, the ball screw (140) is isolated from the output shaft (112).

Description

Background Art

[0001] Aircraft landing gear assemblies are typically movable between a deployed (extended) condition for takeoff, landing, and taxiing, and a stowed (retracted) condition for flight.

[0002] An actuator may be provided for moving the landing gear assembly between the deployed and stowed conditions. This type of actuator is referred to in the art as a "retraction actuator". The retraction actuator may have one end coupled to the fuselage and another end coupled to the main strut, such that extension and retraction of the actuator causes movement of the main strut between the deployed and stowed conditions.

[0003] The landing gear actuator needs to have an emergency deployment mechanism in the event of a system failure (e.g., loss of power). In such a failure, the landing gear will be able to deploy under gravity. Hydraulic actuators achieve this function with the help of hydraulic release, which allows the system to backdrive and deploy the landing gear. However, with electromechanical actuators, backdriving the actuator requires a larger external force due to the inherent system resistance.

[0004] The present invention provides embodiments of a disconnect mechanism suitable for use with a landing gear assembly having an electromechanical actuator. The disclosed embodiments include a ball screw driven by an electric motor through a gear train. The disconnect mechanism selectively isolates the gear train output from the ball screw to reduce inherent system drag, allowing the landing gear to be deployed under gravity. Summary of the invention

[0005] Embodiments of landing gear disconnect mechanisms are described below in accordance with the techniques and methods of the present invention. The disconnect mechanism is configured such that in the event of a system failure, the actuator can be placed in a disconnected state to reduce inherent system resistance so that the landing gear can be deployed under gravity.

[0006] A first representative embodiment of a landing gear system for an aircraft landing gear includes a main beam, which is coupled to the aircraft for reciprocating between a stowed position and a deployed position. An actuator is configured to drive the reciprocating movement of the main beam. The actuator includes a ball screw and a motor. The motor has an output shaft, which is operably coupled to the ball screw through a gear train and is configured to drive the selective rotation of the ball screw. The actuator also includes a disconnect mechanism having a disconnect accessory, which is rotatably mounted to the ball screw. The offset accessory engages the disconnect accessory to rotate the disconnect accessory between a first position and a second position. When the disconnect accessory is in the first position, the disconnect accessory transmits the rotation of the output gear shaft to the ball screw. When the disconnect accessory is in the second position, the ball screw is isolated from the output gear shaft.

[0007] In any embodiment, the motor drives a gear having a splined surface to rotate, and the disconnect fitting includes an engagement element disposed on the elongated member, wherein rotation of the disconnect fitting engages and disengages the engagement element from the splined surface.

[0008] In any of the embodiments, the elongated member has a first end and a second end, the first end and the second end defining an angle therebetween.

[0009] In any embodiment, the angle is between 100° and 150°.

[0010] In any embodiments, the biasing accessory is configured for sliding translation along the centerline of the ball screw between a connected position and a disconnected position, wherein translation of the biasing accessory from the disconnected position to the connected position engages the biasing accessory with the first end of the elongated member to rotate the disconnecting accessory.

[0011] In any embodiment, engagement of the biasing fitting with the elongated member maintains engagement of the engagement element with the spline surface when the biasing fitting is in the connected position.

[0012] In any embodiment, translation of the biasing fitting from the connected position to the disconnected position engages the biasing fitting with the second end of the elongated member to rotate the disconnect fitting.

[0013] In any embodiment, engagement of the biasing fitting with the second end of the elongated member when the biasing fitting is in the isolated position prevents engagement of the engagement element with the spline surface.

[0014] In any embodiment, the biasing fitting has an oval shape.

[0015] In any embodiment, the biasing fitting is coupled to a first end of a rod that is slidingly disposed within the ball screw for translational movement along a centerline of the ball screw.

[0016] In any embodiment, an actuation element is coupled to the second end of the rod, the actuation element being configured to move the biasing fitting from the connected position to the disconnected position.

[0017] In any embodiment, the actuation element is a cable.

[0018] In any embodiment, the disconnect mechanism further includes a biasing element that biases the fitting toward the connected position.

[0019] In any embodiment, the disconnect mechanism further includes a locking feature configured to resist the biasing element to maintain the biasing fitting in the disconnected position.

[0020] In any embodiment, the locking feature includes a locking fitting slidably received within an aperture formed in the rod when the biasing fitting is in the isolated position.

[0021] This Summary is provided to introduce a selection of concepts in a simplified form that are further described below in the Detailed Description. This Summary is not intended to identify key features of the claimed subject matter, nor is it intended to be used as an aid in determining the scope of the claimed subject matter. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The foregoing aspects and many of the attendant advantages of the invention will become more readily understood as they become better understood by reference to the following detailed description when taken in conjunction with the accompanying drawings, wherein:

[0023] Figure 1 A front elevation view showing an exemplary embodiment of a landing gear assembly for an aircraft according to aspects of the present invention, wherein the landing gear assembly is in a stowed position;

[0024] Figure 2 A front elevation view thereof is shown with the landing gear assembly in a deployed position;

[0025] Figure 3 Shows Figure 1 A schematic partial view of a landing gear assembly of , wherein the disconnect mechanism is in a connected state;

[0026] Figure 4 A partial schematic diagram thereof is shown, wherein the disconnection mechanism is in a disconnected state;

[0027] Figure 5 Shows Figure 3 a schematic diagram of a disconnect mechanism; and

[0028] Figure 6 Shows Figure 4 Schematic diagram of the disconnect mechanism. DETAILED DESCRIPTION

[0029] refer to Figure 1 and Figure 2 , shows a retractable landing gear assembly 50 for an aircraft 40 according to aspects of the present invention. The landing gear assembly 50 includes a main beam 52 coupled to the aircraft 40 for retracting the landing gear assembly 50. Figure 1 The collapsed position and Figure 2 The main beam 52 is rotatably coupled to the aircraft 40 about an axis 402 at one end. The axle 54 is disposed on the other end of the main beam 52 and has a pair of wheels rotatably mounted thereto about the axis 400. When the aircraft 40 is on the ground, i.e., during takeoff, landing, and taxiing, the landing gear assembly 50 is in the extended position and the wheels 56 rollingly engage the ground to support the aircraft. When the aircraft 40 is in flight, the landing gear assembly 50 is retracted upward into the aircraft to reduce drag.

[0030] The landing gear assembly 50 includes an actuator 100 that drives the main beam 52 through an extension and retraction motion. In the illustrated embodiment, the actuator 100 is a linear actuator that is rotatably coupled to the aircraft 40 at one end about an axis 404. The other end of the actuator 100 is rotatably coupled to the main beam 52 of the landing gear assembly 50 about an axis 406. Extension of the actuator drives the landing gear assembly 40 toward the deployed position, while retraction of the actuator drives the landing gear assembly toward the stowed position.

[0031] Reference now Figure 3 and Figure 4 , an exemplary embodiment of a linear actuator 100 according to aspects of the present invention will be described. In the illustrated embodiment, the actuator 100 is a ball screw actuator, which includes a ball screw 140 threadedly engaged with a ball nut 180. The ball screw 140 is selectively rotatable about a centerline 408, and the ball nut 180 is fixed to rotate about a central axis. Therefore, rotation of the ball screw 140 in a first direction drives the ball nut 180 in a first linear direction, and rotation of the ball screw in a second direction drives the ball nut in a second linear direction.

[0032] The ball screw 140 is a known ball screw having an elongated body 142 having an external thread 144 formed thereon. One end of the ball screw 140 is mounted to a ball screw fitting 160. Figure 3 and Figure 4 As shown, a radial flange 146 extends from the end of the body 142 of the ball screw 140. A plurality of bearings 166 are mounted within the body 162 of the ball screw assembly 160 and engage the body 142 and flange 146 of the ball screw 140 to allow the ball screw to rotate relative to the ball screw assembly about the centerline 408 while limiting translation of the ball screw 140 relative to the ball screw assembly 160 along the centerline 408.

[0033] The ball screw assembly 160 includes a lug 164 extending from the body 162. In the illustrated embodiment, the lug 164 has a bushing hole 168 formed therein so that the ball screw assembly 160 can be rotatably coupled to the aircraft about the axis 404. In any embodiment, a spherical bearing is mounted in the hole 168 to provide a pivotal mounting of the ball screw assembly 160 to the aircraft. In any embodiment, the ball screw assembly 160 is rotatably or pivotally coupled to the aircraft in any suitable manner.

[0034] Still reference Figure 3 and Figure 4, the ball nut 180 is fixedly mounted to a ball nut fitting 190. The ball nut fitting 190 has an elongated body 192 having a cavity 194 formed at the end to which the ball nut 180 is mounted. The cavity is sized and configured to accommodate at least a portion of the ball screw 140 during extension and retraction of the actuator 100.

[0035] A lug 196 is formed on the ball nut fitting 190 opposite the ball nut 180. In the illustrated embodiment, a bushing hole 198 is formed in the lug 196 so that the ball nut fitting can be rotatably coupled to the main beam 52 about the axis 406. In any embodiment, a spherical bearing is installed in the hole 198 to provide a pivotal mounting of the ball nut fitting 190 to the main beam. In any embodiment, the ball nut fitting 190 is rotatably or pivotally coupled to the main beam in any suitable manner.

[0036] The linear actuator 100 includes a motor 110 connected to a ball screw 140 through a transmission 120 and a disconnect mechanism 300. As will be described in further detail, the motor 110 selectively drives the rotation of the ball screw 140. The motor 110 includes an output shaft 112 that is selectively rotatable in a first direction and a second direction. In any embodiment, the motor 110 is an electric motor. In any embodiment, the motor 110 may include a brake 114. In any embodiment, the motor is any motor suitable for providing a rotational force to drive actuation of the actuator.

[0037] The output shaft 112 of the motor 110 is coupled to the ball screw 140 through the transmission 120, such that rotation of the output shaft 112 in a first direction and a second direction respectively drives the ball screw 140 to rotate in the first direction and the second direction about the centerline 408 of the ball screw. In any embodiment, the transmission 120 is configured such that rotation of the output shaft 112 drives the ball screw 140 to rotate in the same direction as the output shaft. In any embodiment, the transmission 120 is configured such that rotation of the output shaft 112 drives the ball screw 140 to rotate in a direction opposite to the direction of the output shaft.

[0038] The transmission 120 includes an input gear 122 coupled to the output shaft 112 of the motor 110 and an output gear 126 that selectively engages the ball screw 140. In the illustrated embodiment, the input gear 122 and the output gear 126 are connected by a planetary gear assembly 124. In any embodiment, the transmission 120 transforms the input torque and speed provided by the motor 110 to the input gear 122 into a suitable output torque and speed provided by the output gear 126 to the ball screw 140.

[0039] The ball screw 140 includes a disconnect mechanism 300 that selectively Figure 3 and Figure 5 The connection status shown is the same as Figure 4 and Figure 6 In the connected state, the disconnect mechanism 300 engages the output gear 126 of the transmission 120, so that the rotation of the output shaft 112 of the motor 110 drives the rotation of the ball screw 140. When the disconnect mechanism 300 is in the disconnect state, the disconnect mechanism is disengaged from the output gear 126 of the transmission 120, so that the ball screw 140 is isolated from the transmission 120, and the ball screw 140 can rotate independently of the output shaft 112 of the motor 110.

[0040] Reference now Figures 3 to 6 , the disconnect mechanism 300 will now be described. The disconnect mechanism 300 includes a biasing fitting 302 and one or more disconnect fittings 330 disposed within a cavity 148 formed within the body 142 of the ball screw 140. The one or more disconnect fittings 330 are positioned circumferentially around the centerline 408 of the ball screw. Figure 5 and Figure 6 , each disconnect fitting 330 includes an arm 332 rotatably coupled to the ball screw 140 about an axis 410. In any embodiment, the disconnect mechanism 300 includes four disconnect fittings 330 evenly spaced about a centerline 408 of the ball screw 140. In any embodiment, the disconnect mechanism 300 includes any suitable number of disconnect fittings 330 positioned within the cavity 148 of the ball screw 140 in any suitable configuration.

[0041] Each arm 332 includes a first end 334 and a second end 336 that form an angle. In the illustrated embodiment, the angle is approximately 135°. In any embodiment, the angle is between 130° and 140°, between 100° and 150°, or has any other suitable value. In the illustrated embodiment, the axis 408 about which the arm 332 rotates is located at the apex of the angle. In any embodiment, the axis can be located on the first end 334 or the second end 336 of the arm 332 so that the apex of the angle is offset therefrom.

[0042] Each disconnect fitting 330 has an engagement element 338 positioned on the second end 336. The engagement element 330 is sized and configured to extend through a corresponding aperture 150 formed in the body 142 of the ball screw 140 when the disconnect mechanism 300 is in the connected state. In the illustrated embodiment, each engagement element 338 includes one or more splines. Figure 5As shown, when the disconnect mechanism 300 is in the connected state, the engagement element 338 cooperates to form an external spline surface on the ball screw 140, which engages the internal spline surface 128 formed on the output gear 126 of the transmission 120. With the engagement element 338 engaged with the spline surface 330 of the output gear, the rotation of the output gear 126 driven by the motor drives the rotation of the ball screw 140.

[0043] When the disconnect mechanism 300 is in the disconnected state, Figure 6 As shown, the engagement element 338 is disengaged from the internal spline surface 128 of the output gear 126 of the transmission 120. With the engagement element 338 disengaged from the output gear 126, the ball screw 140 is isolated from the motor 110 and can be freely back-driven without being restricted by the motor.

[0044] The disconnect mechanism 300 includes a biasing fitting 302 located within the cavity 148 and engaging a disconnect fitting 330. The biasing fitting 302 is mounted to one end of a rod 304 disposed within the ball screw 140 for sliding movement along the centerline 408 of the ball screw 140. The second end of the rod 304 extends through a recess 152 formed in an end of the ball screw 140 proximate to the ball screw fitting 160. In the illustrated embodiment, the biasing fitting 302 has an oval shape. In any embodiment, the biasing fitting 302 has a spherical shape, a cylindrical shape, or any other suitable shape.

[0045] refer to Figure 5 and Figure 6 , the ball housing 308 is slidably disposed within the recess 152 and is securely secured to the rod 304. The biasing element 310 is disposed within the recess 152 and engages the ball housing 308 to urge the biasing element in the direction of the biasing fitting 302. In any embodiments, the biasing element 310 is a compression spring configured to urge the ball housing 308 in the direction of the biasing fitting 302. In any embodiments, the biasing element is an extension spring, a gas spring, a torsion spring, or any other suitable biasing element configured to urge the ball housing 308 in the direction of the biasing fitting 302.

[0046] The disconnect mechanism 300 also includes an actuating element 312 configured to selectively drive the biasing fitting 302 toward the cavity 148, ie, from the disconnect mechanism 300 in the connected state ( Figure 5 When the disconnect mechanism 300 is in the disconnected state ( Figure 6 In any embodiment, the actuating element 312 is a cable connected at one end to the rod 304 and at the other end to a joystick accessible from within the aircraft (e.g., within the cockpit). When the joystick is pulled, the cable pulls the rod 304 and the biasing fitting 302 to the left, as shown. Figure 5 and Figure 6 As shown, that is, to overcome the biasing force of the biasing element 310. In any embodiment, the actuating element can be an electric actuator (e.g., a solenoid) or a hydraulic actuator configured to drive the rod 304 and the biasing accessory 302 to overcome the biasing force of the biasing element 310. In any embodiment, the actuating element is any suitable element that is configured to manually or automatically overcome the biasing force of the biasing element 310 to drive the rod 304 and the biasing accessory 302.

[0047] When the actuating element 312 moves the rod 304 and the biasing fitting 302 to Figure 6 After the position shown, the locking feature 350 engages the rod 304 to maintain the rod and the biasing fitting in place. That is, when the biasing fitting 302 has reached the isolation position, the locking feature 350 maintains the disconnect mechanism in the disconnected state.

[0048] In the illustrated embodiment, the locking feature 350 includes a locking fitting 354 slidably mounted perpendicular to the centerline 408 of the rod 304. The biasing element 356 is configured to urge the end of the locking fitting 354 to maintain sliding contact with the rod. Figure 5 As shown, the aperture 352 is formed in the rod 304 and is sized and configured to be in a closed position when the disconnect mechanism 300 is in the Figure 6 The disconnected state of the locking member 354 is received. In order to move the disconnecting member 300 back to Figure 5 In the connected state, the locking fitting 354 is disengaged from the aperture 352, and then the biasing element 310 drives the ball housing 308, the rod 304 and the biasing fitting 302 back to the connected position.

[0049] In the illustrated embodiment, the locking accessory 354 is a rod and the biasing element 356 is a compression spring. In any embodiment, the locking accessory 354 is a latch. In any embodiment, the locking accessory 354 is a ratchet and pawl combination. In any embodiment, the biasing element is a compression spring, an extension spring, a torsion spring, or any other suitable element configured to apply a biasing force to the locking accessory. In any embodiment, the locking feature is any suitable configuration that releasably secures the disconnect mechanism 300 in an engaged state.

[0050] The disclosed embodiment of the disconnect mechanism 300 enables the landing gear assembly 50 to be manually deployed in the event of a drive system failure. Figure 3 and Figure 5 When the disconnect mechanism 300 is in the connected state, the motor 110 is operably connected to the ball screw 140 so that the actuator 100 can drive the landing gear assembly 50 through extension and retraction movements.

[0051] When the disconnect mechanism 300 is in the connected state, the biasing fitting 302 engages the second end 336 of the arm 332 so that each engagement element 338 extends through a corresponding aperture 150 in the ball screw 140 to maintain engagement with the spline surface 128 of the output gear 126 of the transmission 120. Thus, when the disconnect mechanism 300 is in the connected state, rotation of the ball screw 140 is limited by the output shaft 112 of the motor 110.

[0052] In the event of a system failure that prevents the landing gear assembly 50 from extending, the disconnect mechanism 300 may be moved to Figure 4 and Figure 6 This allows the landing gear assembly to extend under gravity. Figure 3 and Figure 5 To move the connected state of the controller to disconnected, the user activates the actuation element 312. In the illustrated embodiment, activating the actuation element 312 includes pulling a cable.

[0053] Activating the actuating element 312 drives the biasing assembly 302, the rod 304 and the ball housing 308 against the force of the biasing element 310, i.e., Figures 3 to 6 304 is driven leftward as shown until the locking feature 350 engages to lock the rod 304 in place. As the biasing fitting 302 moves leftward, the biasing fitting engages the first end 334 of each arm 332 of the disconnect fitting 330, which causes each arm to rotate about its respective axis 410. The rotation of the arm 332 causes the second end 336 of each arm to move, thereby causing the corresponding engagement element 338 to move away from the spline surface 128 of the output gear 126 until the disconnect fitting 330 is separated from the output gear 126.

[0054] With the locking feature engaged, the biasing fitting 302, rod 304, and ball housing 308 are prevented from translating in either direction along the centerline 408 of the ball screw 140, and the disconnect fitting 330 is locked in the disengaged state. Because the ball screw 140 is isolated from the transmission 120 and the motor 110, the ball screw 140 is free to backdrive under external loads. More specifically, the weight of the landing gear assembly 50 pushes the landing gear assembly toward the deployed position, and the ball screw 140, which is not restricted by the motor, backdrives until the landing gear assembly 50 reaches the deployed position.

[0055] When the landing gear reaches the deployed position, the user can disengage the locking fitting 350. With the locking fitting 350 disengaged, the biasing fitting 302, the rod 304 and the ball housing 308 return to the Figure 3 and Figure 5In the connected state, the ball screw 140 is again connected to the motor 110 through the transmission 120, and the motor provides resistance against the rotation of the ball screw 140, thereby assisting the landing gear to lock downward to lock the landing gear in the deployed position.

[0056] While illustrative embodiments have been illustrated and described, it will be appreciated that various changes can be made therein without departing from the spirit and scope of the invention.

[0057] It should be understood that the disclosed embodiments are exemplary only and should not be considered restrictive. In some embodiments, the landing gear configuration, motor and transmission may vary within the scope of the present invention. These and other variations are contemplated and should be considered within the scope of the present invention.

[0058] The application can quote quantity and number. Unless otherwise specified, these quantity and number should not be considered as restrictive, but examples of possible quantities or numbers associated with the application. Also in this regard, the application can use the term "multiple" to quote quantity or number. In this regard, the term "multiple" refers to any number more than one, such as two, three, four, five, etc. The terms "approximately", "approximately", "close to" etc. refer to the positive or negative 5% of the value. For purposes of the present invention, the phrase "at least one of A, B and C" for example means (A), (B), (C), (A and B), (A and C), (B and C) or (A, B and C), including all other possible arrangements when listing more than three elements.

[0059] The principles, representative embodiments and operating modes of the present invention have been described in the foregoing description. However, the aspects of the present invention that are intended to be protected should not be interpreted as being limited to the specific embodiments disclosed. Further, the embodiments described herein should be considered to be illustrative rather than restrictive. It should be understood that changes and modifications may be made by others without departing from the spirit of the present invention, and equivalents may be adopted. Therefore, it is expressly intended that all such changes, modifications and equivalents fall within the spirit and scope of the present invention as claimed.

Claims

1. An aircraft landing device, comprising: a main beam coupled to the aircraft for reciprocating movement between a stowed position and a deployed position; as well as an actuator, configured to drive the reciprocating movement of the main beam, the actuator comprising: Ball screw; a motor having an output shaft operably coupled to the ball screw and configured to drive selective rotation of the ball screw; and Disconnect mechanism, including: a disconnect fitting rotatably mounted to the ball screw; and A biasing accessory engages the disconnect accessory to rotate the disconnect accessory between a first position and a second position, wherein when the disconnect accessory is in the first position, the disconnect accessory transmits rotation of the output shaft to the ball screw, and when the disconnect accessory is in the second position, the ball screw is isolated from the output shaft.

2. The aircraft landing gear according to claim 1, wherein: The motor drives a gear having a splined surface to rotate, and the disconnect fitting includes an engagement element disposed on an elongated member, wherein rotation of the disconnect fitting causes the engagement element to engage and disengage with the splined surface.

3. The aircraft landing gear according to claim 2, wherein: The elongated member has a first end and a second end, the first end and the second end defining an angle therebetween.

4. The aircraft landing gear according to claim 3, wherein: The angle is between 100° and 150°.

5. The aircraft landing gear according to claim 3, wherein: The biasing accessory is configured for sliding translation along the centerline of the ball screw between a connected position and a disconnected position, wherein translation of the biasing accessory from the disconnected position to the connected position causes the biasing accessory to engage the first end of the elongated member to rotate the disconnecting accessory.

6. The aircraft landing gear according to claim 5, wherein: Engagement of the biasing fitting with the elongated member maintains engagement of the engagement element with the spline surface when the biasing fitting is in the connected position.

7. The aircraft landing gear according to claim 6, wherein: Translation of the biasing fitting from the connected position to the disconnected position engages the biasing fitting with the second end of the elongated member to rotate the disconnect fitting.

8. The aircraft landing gear according to claim 7, wherein: Engagement of the biasing fitting with the second end of the elongated member when the biasing fitting is in the isolated position prevents engagement of the engagement element with the spline surface.

9. The aircraft landing gear according to claim 5, wherein: The offset fitting has an oval shape.

10. The aircraft landing gear according to claim 5, wherein: The biasing fitting is coupled to a first end of a rod that is slidingly disposed within the ball screw for translational movement along the centerline of the ball screw.

11. The aircraft landing gear according to claim 10, wherein: An actuation element is coupled to the second end of the rod, the actuation element being configured to move the biasing fitting from the connected position to the disconnected position.

12. The aircraft landing gear according to claim 11, wherein: The actuating element is a cable.

13. The aircraft landing gear according to claim 11, wherein: The disconnect mechanism also includes a biasing element that urges the biasing fitting toward the connected position.

14. The aircraft landing gear according to claim 13, wherein: The disconnect mechanism also includes a locking feature configured to act against the biasing element to maintain the biasing fitting in the isolated position.

15. The aircraft landing gear according to claim 14, wherein: The locking feature includes a locking fitting slidably received within an aperture formed in the rod when the biasing fitting is in the isolated position.

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