Thrust reverser synchronization shaft lock system and method of thrust reverser synchronization shaft locking

Abstract

The subject matter of this specification can be embodied in a thrust reverser synchronous axle lock system that includes a rotatable axle including at least one radial prong extending radially from the axle, a hydraulic lock assembly including a housing, a piston head having a lock recess, a piston rod extending radially away from the axle and configured to be urged by the piston head to move a first piston rod end out of engagement with the radial prong to selectively allow rotation of the axle, and a biasing member configured to urge the first piston rod end into engagement with the radial prong, and an electric lock assembly including a lock pin and an electric actuator configured to controllably extend and retract the lock pin into and out of engagement with the lock recess.

Description

[0001] Priority requirements

[0002] This application claims priority to U.S. Patent Application No. 16 / 919,854, filed July 2, 2020, the entire contents of which are incorporated herein by reference. Technical Field

[0003] This specification relates to an aircraft thrust reverser actuation locking system. Background Technology

[0004] Modern aircraft engines may include thrust reverser actuation systems to help reduce aircraft speed during landing. A typical thrust reverser includes a movable translation fairing that, when in the operating position, reverses at least a portion of the airflow passing through the engine.

[0005] Accidental or unintentional activation and deployment of thrust reversers at inappropriate times can be dangerous or fatal. Accidental deployment on the ground while ground crew are performing engine servicing can result in injury or death. Accidental activation during flight can lead to catastrophic loss of airspeed or airframe failure. Mechanical failures such as hydraulic losses can also allow the reverser to move out of its retracted position at inappropriate times.

[0006] To prevent accidental or unintentional deployment of the thrust reverser, a locking mechanism is used. The lock must be disengaged before the thrust reverser can be moved from its retracted position. Some existing reverser lock designs employ a rotating claw to engage the probe. This design can be heavy and mechanically complex, increasing the weight and maintenance requirements of the aircraft on which it is mounted. Some existing reverser lock designs implement a hydraulic actuation element, which requires additional hydraulic control lines no longer available in some newer aircraft designs, and therefore this type of lock cannot be used with such aircraft. Summary of the Invention

[0007] Overall, this document describes an aircraft thrust reverser actuation locking system.

[0008] In a first example, a thrust reverser synchronous shaft locking system includes: a rotatable shaft including at least one radial fork extending radially from the shaft; a hydraulic locking assembly including: a housing including a tubular inner wall defining a chamber; a piston head configured to contact the tubular inner wall and including a first piston face on a first longitudinal side of the piston head, a second piston face on a second longitudinal side of the piston head opposite the first piston face, and a locking recess, and configured to divide the chamber into a first fluid chamber defined by the tubular inner wall and the first piston face and a second fluid chamber defined by the tubular inner wall and the second piston face; and a piston rod. The piston rod extends radially away from the shaft from the end of the first piston rod and to the end of the second piston rod opposite the end of the first piston rod, and is configured to be driven by the piston head to move the end of the first piston rod out of engagement with the radial fork to selectively allow rotation of the shaft; and a biasing member configured to drive the end of the first piston rod into engagement with the radial fork to selectively prevent rotation of the shaft; and an electric locking assembly comprising: a locking pin; and an electric actuator configured to controllably extend and retract the locking pin to engage and disengage with the locking recess to selectively prevent and allow movement of the piston rod.

[0009] In the second example according to Example 1, the tubular inner wall includes: a first longitudinal wall portion configured to define the first fluid chamber having a first lateral cross-sectional area near the end of the first piston rod; and a second longitudinal wall portion configured to define the second fluid chamber having a second lateral cross-sectional area smaller than the first lateral cross-sectional area away from the end of the first piston rod; and the piston head includes: a first piston head portion sized to contact the tubular inner wall such that the first piston face substantially has the first lateral cross-sectional area; and a second piston head portion sized to contact the tubular inner wall such that the second piston face substantially has the second lateral cross-sectional area.

[0010] In the third example according to Example 2, the thrust reverser synchronous shaft lock system further includes a third fluid chamber configured to be in fluid communication with atmospheric gas at ambient pressure or with hydraulic return pressure, and defined by the first longitudinal wall portion and the second piston head portion.

[0011] In the fourth example according to any one of Examples 1 to 3, the first fluid chamber is configured to be in fluid communication with the thrust reverser retractable fluid pressure source, and the second fluid chamber is configured to be in fluid communication with the thrust reverser retractable fluid pressure source.

[0012] In the fifth example according to any one of Examples 1 to 4, the thrust reverser synchronous shaft lock system further includes a shaft housing disposed around the shaft and defining an axial fluid chamber configured to be in fluid communication with a thrust reverser deployment fluid source.

[0013] In the sixth example according to Example 5, the thrust reverser synchronous shaft lock system further includes a fluid conduit configured to fluidly connect the first fluid chamber and the second fluid chamber.

[0014] In the seventh example according to Example 6, the fluid conduit is a tubular conduit defined by the piston rod.

[0015] In the eighth example according to any one of Examples 1 to 7, the thrust reverser synchronous shaft lock system further includes a pivotable cam configured to engage a cam recess defined in the piston head and pivot to drive longitudinal movement of the piston head and disengage the first piston rod end from the radial fork.

[0016] In the ninth example according to any one of Examples 1 to 8, the thrust reverser synchronous shaft lock system further includes a drive assembly configured to removably couple torque from a removable rotary power source to the shaft.

[0017] In a tenth example, a method for locking a thrust reverser synchronizing shaft includes: removing or equalizing hydraulic retraction fluid pressure in a first fluid chamber, wherein the hydraulic lock assembly includes a housing, a piston head, a piston rod coupled to the piston head, the first fluid chamber in the housing at a first longitudinal end of the piston head, and a second fluid chamber in the housing at a second longitudinal end of the piston head opposite the first longitudinal end; driving longitudinal movement of the piston rod in a first direction by a biasing member, the piston rod including a first piston rod end and a second piston rod end opposite the first piston rod end; driving the first piston rod end to engage with a radial fork extending radially from a rotatable shaft by the longitudinal movement of the piston rod in the first direction; de-energizing the electric lock assembly; and extending a locking pin to engage with a recess defined in the piston head based on de-energizing the electric lock assembly.

[0018] In the eleventh example according to Example 10, the method further includes preventing the first piston rod end from disengaging from the radial fork by engaging the locking pin with the recess.

[0019] In a twelfth example according to Example 10 or 11, the method further includes preventing rotation of the shaft by engaging the end of the first piston rod with the radial fork.

[0020] In a thirteenth example according to any one of Examples 10 to 12, the method further includes: energizing the electric lock assembly; retracting the locking pin from engagement with the recess based on the energization; applying the hydraulic retraction fluid pressure to the first fluid chamber; driving the piston head longitudinally in a second direction opposite to the first direction by the hydraulic retraction fluid pressure in the first fluid chamber; driving the piston rod longitudinally in the second direction by the longitudinal movement of the piston head in the second direction; and driving the end of the first piston rod to disengage from engagement with the radial fork by the longitudinal movement of the piston rod in the second direction.

[0021] In a fourteenth example according to Example 13, the method further includes: applying the hydraulic retraction fluid pressure to the second fluid chamber, wherein a first piston face of the piston head has a first lateral cross-sectional area; applying a first hydraulic pressure to the piston head in the first direction based on the first lateral cross-sectional area; applying the hydraulic retraction fluid pressure to the first fluid chamber, wherein a second piston face of the piston head has a second lateral cross-sectional area greater than the first lateral cross-sectional area; and applying a second hydraulic pressure to the piston head in the second direction based on the second lateral cross-sectional area, wherein the second lateral cross-sectional area is configured such that the second hydraulic pressure is greater than the first hydraulic pressure and the biasing force of the biasing member.

[0022] In the fifteenth example according to any one of Examples 10 to 14, removing or equalizing the hydraulic retraction fluid pressure in the first fluid chamber includes: removing the hydraulic retraction fluid pressure from a first piston face on a first longitudinal side of the piston head, the first piston face defining a first fluid chamber in fluid communication with a thrust reverser retraction fluid pressure source of the jet engine thrust reverser system; and removing the hydraulic retraction fluid pressure from a second piston face on a second longitudinal side of the piston head opposite the first piston face, the second piston face defining a second fluid chamber in fluid communication with the thrust reverser retraction fluid pressure source of the jet engine thrust reverser system.

[0023] In a sixteenth example according to any one of Examples 10 to 15, the method further includes: driving rotation of a pivotable cam engaged with a cam recess defined in the piston rod; driving longitudinal movement of the piston rod in a second longitudinal direction opposite to the first longitudinal direction based on the rotation; and disengaging the end of the first piston rod from the radial fork based on the longitudinal movement of the piston rod in the second longitudinal direction.

[0024] In a seventeenth example according to Example 16, the method further includes: connecting a removable rotary power source to an input of a drive assembly; driving rotation of the input via the removable rotary power source; and driving rotation of the shaft via the drive assembly based on the rotation of the input.

[0025] In one example, a thrust reverser synchronous shaft locking system includes: a rotatable shaft including at least one radial fork extending radially from the shaft; a hydraulic locking assembly including: a housing having a tubular inner wall defining a chamber; a piston head configured to contact the tubular inner wall and having a first piston face on a first longitudinal side of the piston head, a second piston face on a second longitudinal side of the piston head opposite the first piston face, and a locking recess, and configured to divide the chamber into a first fluid chamber defined by the tubular inner wall and the first piston face and a second fluid chamber defined by the tubular inner wall and the second piston face; and a piston rod. The piston rod extends radially away from the shaft from the end of the first piston rod and to the end of the second piston rod opposite the end of the first piston rod, and is configured to be driven by the piston head to move the end of the first piston rod out of engagement with the radial fork to selectively allow rotation of the shaft; and a biasing member configured to drive the end of the first piston rod into engagement with the radial fork to selectively prevent rotation of the shaft; and an electric locking assembly comprising: a locking pin; and an electric actuator configured to controllably extend and retract the locking pin to engage and disengage with the locking recess to selectively prevent and allow movement of the piston rod.

[0026] Various embodiments may include some, all, or none of the following features. The tubular inner wall may include: a first longitudinal wall portion configured to define the first fluid chamber having a first lateral cross-sectional area near the end of the first piston rod; and a second longitudinal wall portion configured to define the second fluid chamber having a second lateral cross-sectional area smaller than the first lateral cross-sectional area away from the end of the first piston rod; and the piston head may include: a first piston head portion sized to contact the tubular inner wall such that the first piston face substantially has the first lateral cross-sectional area; and a second piston head portion sized to contact the tubular inner wall such that the second piston face substantially has the second lateral cross-sectional area. The thrust reverser synchronous shaft lock system may also include a third fluid chamber configured to be in fluid communication with atmospheric gas at ambient pressure or having hydraulic return pressure, and defined by the first longitudinal wall portion and the second piston head portion. The first fluid chamber may be configured to be in fluid communication with the thrust reverser retractable fluid pressure source, and the second fluid chamber may be configured to be in fluid communication with the thrust reverser retractable fluid pressure source. The thrust reverser synchronous shaft locking system may further include a shaft housing disposed around the shaft and defining a shaft fluid chamber configured to be in fluid communication with a thrust reverser deployment fluid source. The thrust reverser synchronous shaft locking system may further include a fluid conduit configured to fluidly connect the first fluid chamber and the second fluid chamber. The fluid conduit may be a tubular conduit defined by the piston rod. The thrust reverser synchronous shaft locking system may further include a pivotable cam configured to engage a cam recess defined in the piston head and pivot to drive longitudinal movement of the piston head and disengage the end of the first piston rod from the radial fork. The thrust reverser synchronous shaft locking system may further include a drive assembly configured to removably connect torque from a removable rotational power source to the shaft.

[0027] In another example aspect, a method for locking a thrust reverser synchronizing shaft includes: removing or equalizing hydraulic retraction fluid pressure in a first fluid chamber, wherein the hydraulic lock assembly includes a housing, a piston head, a piston rod coupled to the piston head, the first fluid chamber in the housing at a first longitudinal end of the piston head, and a second fluid chamber in the housing at a second longitudinal end of the piston head opposite the first longitudinal end; driving longitudinal movement of the piston rod in a first direction by a biasing member, the piston rod having a first piston rod end and a second piston rod end opposite the first piston rod end; driving the first piston rod end to engage with a radial fork extending radially from a rotatable shaft by the longitudinal movement of the piston rod in the first direction; de-energizing the electric lock assembly; and, based on the de-energizing of the electric lock assembly, extending a locking pin to engage with a recess defined in the piston head.

[0028] Various implementations may include some, all, or none of the following features. The method may also include preventing disengagement of the first piston rod end from the radial fork by engaging the locking pin with the recess. The method may also include preventing rotation of the shaft by engaging the first piston rod end with the radial fork. The method may further include: energizing the electric locking assembly; retracting the locking pin from engagement with the recess based on the energization; applying hydraulic retraction fluid pressure to the first fluid chamber; driving the piston head longitudinally in a second direction opposite to the first direction by the hydraulic retraction fluid pressure in the first fluid chamber; driving the piston rod longitudinally in the second direction by the longitudinal movement of the piston head in the second direction; and driving the first piston rod end to disengage from the radial fork by the longitudinal movement of the piston rod in the second direction. The method may further include: applying the hydraulic retraction fluid pressure to the second fluid chamber, wherein the first piston face of the piston head has a first lateral cross-sectional area; applying a first hydraulic pressure to the piston head in the first direction based on the first lateral cross-sectional area; applying the hydraulic retraction fluid pressure to the first fluid chamber, wherein the second piston face of the piston head has a second lateral cross-sectional area larger than the first lateral cross-sectional area; and applying a second hydraulic pressure to the piston head in the second direction based on the second lateral cross-sectional area, wherein the second lateral cross-sectional area is configured such that the second hydraulic pressure is greater than the first hydraulic pressure and the biasing force of the biasing member. Removing or equalizing the hydraulic retraction fluid pressure in the first fluid chamber may include: removing the hydraulic retraction fluid pressure from a first piston face on a first longitudinal side of the piston head, the first piston face defining a first fluid chamber in fluid communication with a thrust reverser retraction fluid pressure source of the jet engine thrust reverser system; and removing the hydraulic retraction fluid pressure from a second piston face on a second longitudinal side of the piston head opposite the first piston face, the second piston face defining a second fluid chamber in fluid communication with the thrust reverser retraction fluid pressure source of the jet engine thrust reverser system. The method may further include: driving rotation of a pivotable cam engaged with a cam recess defined in the piston rod; driving longitudinal movement of the piston rod in a second longitudinal direction opposite to the first longitudinal direction based on the rotation; and disengaging the end of the first piston rod from the radial fork based on the longitudinal movement of the piston rod in the second longitudinal direction. The method may further include: connecting a removable rotary power source to an input end of a drive assembly; driving rotation of the input end via the removable rotary power source; and driving rotation of the shaft via the drive assembly based on the rotation of the input end.

[0029] The system and technology described herein offer one or more of the following advantages. First, the system replaces the conventional two-piece jaw lock mechanism with a much simpler rotary design. Second, the system uses a rotary mechanism that is smaller and less complex than the large and heavy moving jaws of a jaw lock mechanism. Third, the system uses a single moving part mechanism instead of the complex slot and bearing mechanism used to swing the jaws of a jaw lock. Fourth, the system is lighter and more reliable than a jaw lock mechanism.

[0030] Details of one or more implementations are set forth in the accompanying drawings and the description below. Other features and advantages will be apparent from the specification, drawings, and claims. Attached Figure Description

[0031] Figure 1 This is a schematic diagram of an example turbofan jet engine assembly, in which a portion of the external nacelle has been removed for clarity.

[0032] Figure 2 shows an example thrust reverser. Figure 1 A schematic diagram of an example engine component.

[0033] Figure 3 shows an exemplary thrust reverser with alternatives. Figure 1 A schematic diagram of an example engine component.

[0034] Figure 4 This is a schematic diagram of an example thrust reverser system.

[0035] Figure 5A and Figure 5B This is an isometric view of an example thrust reverser synchronous shaft lock system.

[0036] Figures 6A to 6C It is in a locked structure Figure 5A and Figure 5B A cross-sectional view of an example thrust reverser synchronous shaft lock system.

[0037] Figure 7A and Figure 7B It is in a fluid unlocking structure Figure 5A and Figure 5B A cross-sectional view of an example thrust reverser synchronous shaft lock system.

[0038] Figure 8 It is in the manual unlocking configuration. Figure 5A and Figure 5B A cross-sectional view of an example thrust reverser synchronous shaft lock system.

[0039] Figure 9 It is used for locking Figure 5A and Figure 5B The flowchart shows an example process for a thrust reverser synchronous shaft lock system. Detailed Implementation

[0040] This document describes systems and techniques for reversing airflow from an aircraft turbine engine. A thrust reverser having at least one movable element can be used to change the direction of bypass airflow, the element being capable of moving to and from a reversed position. In the reversed position, the movable element can be configured to reverse at least a portion of the bypass airflow.

[0041] The locking mechanism engages the thrust reverser to prevent accidental activation or deployment (e.g., during flight or during ground maintenance operations). The following paragraphs describe a mechanism that provides this locking in a relatively lighter and less complex component than existing designs, and without requiring dedicated hydraulic lines for locking as some existing designs do.

[0042] Figure 1 An example turbofan jet engine assembly 10 with a turbine engine 12, a fan assembly 13, and a nacelle 14 is illustrated. For clarity, a portion of the nacelle 14 has been cut away. The nacelle 14 surrounds the turbine engine 12 and defines an annular airflow path or annular bypass duct 16 through the jet engine assembly 10 to define a generally front-to-back bypass airflow path, as schematically illustrated by arrow 18. The combustion airflow is schematically illustrated by arrow 19.

[0043] A thrust reverser having at least one movable element can be used to change the direction of bypass airflow, the element being capable of moving to and from a reversed position. In the reversed position, the movable element can be configured to reverse at least a portion of the bypass airflow. Several methods exist for obtaining reverse thrust on turbofan jet engine assemblies. Figure 2 schematically illustrates an example of a thrust reverser 20 that can be used for a turbofan jet engine assembly 10. The thrust reverser 20 includes a movable element 22. The movable element 22 has been illustrated as a cowl section capable of axial movement relative to the forward portion of the nacelle 14. A hydraulic actuator 24 can be coupled to the movable element 22 to move the movable element 22 into and out of the reversed position. In the reversed position, as illustrated, the movable element 22 restricts an annular bypass region between the movable element 22 and the turbine engine 12, and it also opens a portion 26 between the movable element 22 and the forward portion of the nacelle 14, allowing the airflow path to be reversed as illustrated by arrow 28. Optional deflectors or flaps 29 may be included to help guide the airflow path between the movable element 22 and the front portion of the nacelle 14.

[0044] Figure 3 schematically illustrates an alternative example of a thrust reverser 30. The thrust reverser 30 includes a movable element 32. The movable element 32, illustrated as a deflector, may be incorporated into a portion of the nacelle 14. A hydraulic actuator 34 may be coupled to the movable element 32 to move it into and out of the reversed position. In the reversed position, shown in dashed lines and indicated by 36, the movable element 32 deflects the air outward and forward to reverse its direction, as illustrated by arrow 38. Optional deflectors or baffles 39 may be included to help guide the airflow path outward.

[0045] In both illustrative examples, the thrust reverser changes the direction of the thrust. Both thrust reverser 20 and thrust reverser 30 have been described as hydraulic operating systems, and the hydraulic actuators have been schematically shown. In some embodiments, thrust reverser 20 and / or thrust reverser 30 may be powered by other fluids (e.g., pneumatic), electromechanical actuators, or any other suitable power source or actuator type.

[0046] Figure 4 This is a schematic diagram of an example thrust reverser system 400. In some embodiments, the thrust reverser system 400 may include some or all of the example thrust reverser 20 of FIG. 2 and / or the example thrust reverser 30 of FIG. 3. In some embodiments, Figure 1 The example turbofan jet engine assembly 10 of Figure 3 may include an example thrust reverser system 400.

[0047] A movable translation fairing portion 410a is attached to the rod end 411 of a set of synchronizing actuators 430a. A movable translation fairing portion 410b is attached to the rod end 411 of a set of synchronizing actuators 430b. In the illustrated example, the movable translation fairing portions 410a and 410b are shown as flat (e.g., planar) for ease of observation only. In their intended form, both the movable translation fairing portions 410a and 410b have a semi-tubular (e.g., semi-cylindrical) shape, such that when joined together in a closed configuration, the movable translation fairing portions 410a and 410b form a generally tubular, cylindrical, or conical cross-section that can surround a portion of the turbine engine. For example, the movable translation fairing portions 410a and 410b could be example movable element 22 or movable element 32.

[0048] The movable translation fairing section 410a is attached to the aircraft wing, fuselage, or other structural components. The movable translation fairing section 410b is also attached to the aircraft wing, fuselage, or other structural components.

[0049] Synchronizing actuators 430a and 430b each have a proximal end 431 attached to the engine nacelle or other substantially stationary portion, and a movable end 438 (e.g., a piston rod end) directly or indirectly coupled at its respective rod end 411 to one or both of the movable translation fairing portions 410a or 410b. A mechanical synchronizing system 470 (e.g., a cable or shaft interconnection device) interconnects the synchronizing actuators 430a-430b to transmit a locking load between opposite sides of the thrust reverser system 400. The mechanical synchronizing system 470 provides multiple functions. In the illustrated example, the mechanical synchronizing system 470 also provides a fluid conduit that delivers pressurized fluid to the synchronizing actuators 430a-430b (e.g., a cable or shaft extending through the interior of the fluid conduit, in which a housing can transmit mechanical torque and also allow fluid flow through its interior). Synchronous actuator 430a is configured to primarily actuate the movable translation fairing section 410a. Synchronous actuator 430b is configured to primarily actuate the movable translation fairing section 410b.

[0050] The movable translation fairing sections 410a and 410b are operated by controllably directing pressurized fluid (e.g., hydraulic fluid) from fluid supply line 482 through isolation valve 487 to synchronizer actuators 430a-430b and back to fluid return line 483. Pressurized fluid is supplied to directional control valve 488. Directional control valve 488 is a hydraulic valve operable to direct fluid flow to synchronizer actuators 430a-430b, thereby actuating synchronizer actuators 430a-430b and driving the movable translation fairing sections 410a and 410b to move between retracted and deployed configurations. For example, in one configuration of the directional control valve 488, pressurized fluid can be directed through fluid conduit 495 to flow to synchronizer actuators 430a-430b and return through fluid conduit 494 to deploy movable translation fairing portions 410a and 410b, and in another configuration of the directional control valve 488, pressurized fluid can be directed through fluid conduit 494 to flow to synchronizer actuators 430a-430b and return through fluid conduit 495 to retract movable translation fairing portions 410a and 410b.

[0051] In some embodiments, the directional control valve 488 may be a regenerative valve. For example, in a regenerative valve, pressure may be applied simultaneously to the deploy line 495 and the retract line 494 to deploy actuators 430a-430b.

[0052] Although the illustrated example has been described in terms of deployment, the thrust reverser system 400 can operate in a retracted mode. For example, the directional control valve 488 can be configured to allow pressurized fluid to flow out through fluid conduit 494 and receive returned fluid through fluid conduit 495, causing the synchronizing actuators 430a-430b to retract the movable translation fairing portions 410a and 410b.

[0053] System 400 includes a pair of thrust reverser synchronizing shaft locking systems 440. Each thrust reverser synchronizing shaft locking system 440 is coupled to an end of a mechanical synchronizing system 470 (e.g., to a rotational motion provided by a synchronizing shaft). The thrust reverser synchronizing shaft locking systems 440 are configured to selectively allow intentional rotation of the synchronizing system 470 and prevent unintentional rotation, and thus selectively allow intentional movement of movable translation fairing portions 410a and 410b and prevent unintentional movement based on fluid pressure provided by fluid conduits 494 and 495 and electrical signals provided by controller 441 via a set of electrical signal lines 442. The construction and operation of the thrust reverser synchronizing shaft locking systems 440 will be determined by... Figures 5A to 9 Further discussion will follow in the description.

[0054] Figure 5A and Figure 5B This is an isometric view of an example thrust reverser synchronous shaft locking system 500. In some implementations, the thrust reverser synchronous shaft locking system 500 may be... Figure 4 Example thrust reverser synchronizing shaft locking system 440. Thrust reverser synchronizing shaft locking system 500 includes a synchronizing system interface 510 configured to be fluidly coupled to a thrust reverser deployment fluid pressure source (e.g., pressure provided by example fluid conduit 495 through example synchronizing system 470) and has a synchronizing shaft input 512 configured to be rotatably coupled to a synchronizing shaft (e.g., the synchronizing shaft of example synchronizing system 470). Thrust reverser synchronizing shaft locking system 500 includes a fluid port 520 configured to be fluidly coupled to a thrust reverser retraction fluid pressure source (e.g., fluid pressure such as that provided by example fluid conduit 495). Thrust reverser synchronizing shaft locking system 500 includes an electrically operated locking assembly 530 having an electrical input port 532 configured to be electrically connected to an electrically activated signal (e.g., an electrically activated signal from controller 441 via electrical signal line 442). The thrust reverser synchronizer shaft locking system 500 includes a manual unlocking assembly 540 with a manual input terminal 542. The thrust reverser synchronizer shaft locking system 500 also includes a manual drive assembly 550. These components of the thrust reverser synchronizer shaft locking system 500 will... Figures 6A to 9 This will be discussed in more detail in the description.

[0055] Figures 6A to 6C It is in a locked structure Figure 5A and Figure 5B A cross-sectional view of an example thrust reverser synchronous shaft lock system 500. Figure 4 The mechanical synchronization system 470 is connected to the synchronization system interface 510 via a synchronization shaft input 512. When the mechanical synchronization system 470 is connected to the synchronization system interface 510, the shaft fluid chamber 602 is defined. The synchronization shaft input 512 is connected to the shaft 610, and rotation of the mechanical synchronization system 470 drives rotation of the shaft 610. The shaft 610 includes radial forks 612 extending radially away from the shaft 610. In some embodiments, a plurality of radial forks, such as radial forks 612, may extend radially away from the shaft 610.

[0056] As the shaft rotates, the radial fork 612 rotates to contact the rod end 622 of the piston rod 620 in the locked configuration. The mechanical interference between the first rod end 622 and the radial fork 612 prevents further rotation of the shaft 610, which in turn prevents further rotation of the mechanical synchronization system 470. In the illustrated example, rotation of the mechanical synchronization system 470 is limited to less than one revolution in the locked configuration. The gear ratios of the synchronizing actuators 430a and 430b are configured such that a single revolution or less of rotation of the mechanical synchronization system 470 does not result in significant movement of the movable translation fairing portions 410a and 410b, thereby substantially locking the movable translation fairing portions 410a and 410b in place and substantially preventing unintentional deployment of the thrust reverser 400.

[0057] The piston rod 620 is moved into and out of the locking configuration via a hydraulic locking assembly 630. The hydraulic locking assembly 630 includes a housing 632 having a tubular inner wall 634 defining a chamber 636. A piston head 638 is configured to contact the tubular inner wall 634 and has a first piston surface 640 on a first longitudinal side of the piston head 638 and a second piston surface 642 on a second longitudinal side of the piston head 638 opposite to the first piston surface 640.

[0058] A piston rod 620 extends through a cavity 621 defined by a piston head 638 and is configured to move radially within the cavity 621. The piston rod 620 extends radially from a first piston rod end 622 away from the shaft 610 to a second piston rod end 624 opposite the first piston rod end 622. The piston rod 620 includes a stop 623 configured to contact a second piston face 642. As the piston head 638 moves radially away from the shaft 610, the second piston face 642 contacts the stop 623 and also drives the piston rod 620 radially outward. The piston rod 620 is configured to be driven by the contact between the stop 623 and the piston head 638 to move the first piston rod end 622 out of engagement with the radial fork 612, thereby optionally allowing rotation of the shaft 610, as will be... Figure 7A and Figure 7B This is discussed in more detail in the description.

[0059] A biasing member 660 (e.g., a spring) is configured to force a stop 623 into engagement with a piston head 638, and a biasing member 662 is configured to force the piston head 638 in the direction of the shaft 610. The combined action of biasing members 660 and 662 forces a first piston rod end 622 into a locking configuration in which the first piston rod end 622 can contact and interfere with the movement of the radial fork 612 to selectively prevent rotation of the shaft 610.

[0060] refer to Figure 6B and Figure 6C The electrically operated locking assembly 530 includes a locking pin 672 and an electrically operated actuator 674 configured to controllably extend and retract the locking pin 672 to engage and disengage from a locking recess 670 defined in a piston head 638. The locking recess 670 is configured to receive a portion of the locking pin 672. In some embodiments, the electrically operated locking assembly 530 may be an electric solenoid or any other suitable form of electrically operated actuator. The electrically operated locking assembly 530 is configured by default to drive the locking pin 672 toward extension and to retract the locking pin 672 in response to an electrically controlled signal.

[0061] When the locking pin 672 is driven toward the extension, the locking pin 672 will abut the piston head 638 until the locking recess 670 is aligned with the locking pin 672. Once aligned, the locking pin 672 will extend into the locking recess 670 and prevent longitudinal movement of the piston head 638. This prevents movement of the piston head 638 when driven by hydraulic pressure, which prevents the first piston rod end 622 from disengaging from the radial fork 612, thus preventing rotation of the shaft 610.

[0062] refer to Figure 7B The locking pin 672 is shown in a retracted (e.g., unlocked) configuration. When the locking pin 672 retracts from the locking recess 670, the piston head 638 moves freely to its unlocked configuration, as shown in the diagram. Figures 7A to 9 This is discussed in more detail in the description. In use, the electric lock assembly 530 can be controlled to activate and deactivate to selectively allow and disable the movement of the piston head 638.

[0063] Figure 7A and Figure 7B It is in a fluid-unlocking configuration (e.g., unlocked by hydraulic pressure). Figure 5A and Figure 5B A cross-sectional view of an example thrust reverser synchronous shaft locking system 500. The piston head 638 is configured to divide the chamber 636 into a first fluid chamber 650 defined by a tubular inner wall 634 and a first piston face 640, and a second fluid chamber 652 defined by a tubular inner wall 634 and a second piston face 642.

[0064] The first fluid chamber 650 is in fluid communication with the fluid port 520 (e.g., under retraction pressure). A tubular fluid conduit 654 is defined in length through the piston rod 620 and configured to fluidly connect the first fluid chamber 650 to the second fluid chamber 652. When retraction pressure is applied at the fluid port 520, both the first fluid chamber 650 and the second fluid chamber 652 receive the retraction pressure. Although the tubular fluid conduit 654 is defined within the piston rod 620 in the illustrated example, in some embodiments, the fluid conduit may have any suitable form, such as a dedicated conduit extending through or formed within the housing 632 (e.g., a separate tube connecting chambers 650 and 652) or a conduit defined between the piston rod 620 and the piston head 638.

[0065] The hydraulic lock assembly 630 is configured to force the first piston rod end 622 out of the locked position (e.g., engaging with the radial fork 612) when the example thrust reverser synchronous shaft lock system 500 is subjected to retraction and / or deployment fluid pressure (e.g., during the intentional retraction and / or deployment of the thrust reverser 400). Figure 6A and Figure 6B (as shown) and enter the unlocking configuration (e.g., disengage from the radial fork 612, as ...). Figure 7A and Figure 7B (As shown in the diagram). The tubular inner wall 634 includes a first longitudinal outer wall portion 710 configured to define a first fluid chamber 650 having a first lateral cross-sectional area (indicated by arrow 712) near the end of the first piston rod 622. The tubular inner wall 634 also includes a second longitudinal outer wall portion 720 configured to define a second fluid chamber 652 having a second lateral cross-sectional area (indicated by arrow 722) smaller than the first lateral cross-sectional area 712, away from the end of the first piston rod 622.

[0066] Piston head 638 includes a first piston head portion 724 sized to contact a tubular inner wall 634 such that a first piston face 640 substantially has a first lateral cross-sectional area 712. Piston head 638 also includes a second piston head portion 726 sized to contact the tubular inner wall 634 such that a second piston face 642 substantially has a second lateral cross-sectional area 722. A variable-volume axial fluid chamber 730 is defined by chamber 638 between a first longitudinal outer wall portion 710 and a second piston head portion 726. The axial fluid chamber 730 is configured to be in fluid communication with atmospheric gas at ambient pressure or with hydraulic return pressure to prevent pressure or vacuum buildup within the axial fluid chamber 730 as piston head 638 moves.

[0067] During deployment, the electric lock assembly 530 is activated to move the locking pin 672. Figure 7A and Figure 7B The retraction (e.g., unlocking) configuration is shown. When the locking pin 672 retracts from the locking recess 670, the piston rod 620 can move away from the locking configuration. Retraction pressure is then provided to the first fluid chamber 650 and subsequently to the second fluid chamber 652 (e.g., via the tubular fluid conduit 654), such that the fluid pressures in the first and second fluid chambers 650 and 652 are substantially equalized. However, due to the unequal sizes of the cross-sectional areas 712 and 722, the mechanical effects of the equal pressures acting on the first piston face 640 and the second piston face 642 will be unequal. This resulting imbalance in hydraulic pressure will drive the piston head 638 radially away from the axis 610.

[0068] As the piston head 638 moves away from the shaft 610, the second piston surface 642 contacts the stop 623, causing the piston rod 620 to also move radially away from the shaft 610. The radial outward movement of the piston rod 620 forces the first piston rod end 622 to retract from its interference with the radial fork 612, which unlocks the shaft 610.

[0069] During deployment, the electric lock assembly 530 is activated to move the locking pin 672. Figure 7A and Figure 7BThe retraction (e.g., unlocking) configuration is shown. When the locking pin 672 retracts from the locking recess 670, the piston rod 620 is able to move away from the locking configuration. Deployment pressure is applied to the first piston rod end 622 via the synchronization system interface 510. Deployment fluid pressure drives the piston head 638 with a force sufficient to overcome the biasing forces of the biasing members 662 and 663 and cause the first piston rod end 622 to move into the retraction configuration. In some embodiments, the retraction and deployment pressures may be provided as part of a regenerative hydraulic system, wherein fluid pressures may be present simultaneously on both the retraction and deployment sides of the actuator 431 (e.g., deployment pressure 495 and retraction pressure 494 are equal). In such an example system, the retraction pressure, which is also present during the deployment operation, may act on the piston head 638 to also drive the piston rod 620 into the unlocking configuration.

[0070] Figure 8 It is in the manual unlocking configuration. Figure 5A and Figure 5B A cross-sectional view of an example thrust reverser synchronous shaft locking system 500. The thrust reverser synchronous shaft locking system 500 includes a manual input terminal 542 (not visible here, but...). Figure 5A , Figure 5B and Figure 6B The manual unlocking component 540 (shown in the figure) is used to place the example thrust reverser synchronizing shaft lock system 500 into an unlocked configuration in the absence of electrical or hydraulic power (e.g., during ground maintenance of the aircraft).

[0071] The manual input 542 is coupled to the pivotable cam 810. The pivotable cam 810 includes a fork 812 that engages with a recess 814 formed in the piston rod 620.

[0072] In use, the manual input 542 rotates (e.g., by an aircraft mechanic). When the manual input 542 rotates (e.g., counterclockwise in the example view), the pivotable cam 810 and the fork 812 also rotate. The rotation of the fork 812, which engages with the recess 814, drives the piston rod 620 to move against the force of the biasing member 660 and retracts the first piston rod end 622 away from interference with the radial fork 612. Since the piston rod 620 is not attached to the piston head 638, the piston rod 620 can retract while the piston head 638 remains locked by the electric locking assembly 530.

[0073] With the first piston rod end 622 in the unlocked configuration, shaft 610 is free to rotate. Manual drive assembly 550 is configured to connect shaft 610 to a removable rotary torque power source (e.g., a socket wrench, power or manual rotary tool, such as a manual crank, portable drill or pneumatic wrench) to actuate actuators 430a-430b.

[0074] The manual drive assembly 550 includes a coupling 850 connected to a gear head 852 via a clutch mechanism 854. When not in use, the clutch mechanism 854 forces the gear head 852 out of engagement with a set of gear teeth 860 extending from the shaft 610, thus disengaging the manual drive assembly from the shaft 610. In use, a rotary tool is rotatably engaged with the coupling 850, and a longitudinal force is applied to the coupling 850 to force the gear head 852 to engage with the gear teeth 860. The coupling 850 can then be rotated to drive rotation of the shaft 610.

[0075] Figure 9 It is used for locking Figures 5A to 8 The flowchart of the example process 900 for the example thrust reverser synchronous shaft lock system 500.

[0076] At 910, the hydraulic retraction fluid pressure in the first fluid chamber is removed or equalized (e.g., relative to atmospheric pressure), wherein the hydraulic lock assembly includes a housing, a piston head, a piston rod coupled to the piston head, a first fluid chamber in the housing at a first longitudinal end of the piston head, and a second fluid chamber in the housing at a second longitudinal end of the piston head opposite the first longitudinal end. For example, an example thrust reverser synchronizing shaft lock system 500 may be provided, and the retraction pressure may be removed from or otherwise released from the first fluid chamber 650.

[0077] At 920, a biasing member drives longitudinal movement of the piston rod in a first direction, the piston rod having a first piston rod end and a second piston rod end opposite the first piston rod end. For example, biasing member 660 can drive piston rod 620 toward axis 610.

[0078] At 930, longitudinal movement of the piston rod in the first direction forces the end of the first piston rod to engage with a radial fork extending radially from the rotatable axis. For example, the piston rod 620 may be movable such that the end of the first piston rod 622 enters a position that results in engagement with the radial fork 612.

[0079] At 940, the electric lock assembly is de-energized. For example, the electric actuator 674 of the electric lock assembly 530 can be de-energized or otherwise deactivated.

[0080] At 950, based on de-energizing the electric lock assembly, the locking pin extends to engage with a recess defined in the piston head. For example, when the electric actuator 674 of the electric lock assembly 530 is de-energized, the locking pin 672 is allowed to extend into the locking recess 670.

[0081] In some implementations, process 900 may also include preventing disengagement of the first piston rod end from the radial fork by engaging the locking pin with the recess. For example, when the locking pin 672 engages with the locking recess 670, longitudinal movement of the piston rod 620 is substantially suppressed.

[0082] In some implementations, process 900 may also include preventing rotation of the shaft by engaging the end of the first piston rod with the radial fork. For example, when the piston rod 620 is in the locked configuration, the shaft 610 is prevented from rotating more than about one revolution due to mechanical interference between the end of the first piston rod 622 and the radial fork 612.

[0083] In some implementations, process 900 may include: energizing the electric lock assembly; retracting the locking pin from engagement with the recess based on the energization; applying hydraulic retraction fluid pressure to a first fluid chamber; driving a piston head longitudinally in a second direction opposite to a first direction by the hydraulic retraction fluid pressure in the first fluid chamber; driving a piston rod longitudinally in a second direction by the longitudinal movement of the piston head in the second direction; and driving the end of the first piston rod to disengage from engagement with the radial fork by the longitudinal movement of the piston rod in the second direction. For example, the example thrust reverser synchronous shaft lock system 500 may be activated by energizing the electric lock assembly 530 to retract the locking pin 672 from the lock recess 670. Figures 6A to 6C The locking construct shown is reconstructed as Figures 7A to 7B The unlocking configuration is shown in the diagram. Then, a retraction pressure can be applied to the hydraulic lock assembly 630 to retract the piston rod 620 away from the shaft 610 and remove the engagement between the first piston rod end 622 and the radial fork 612.

[0084] In some implementations, process 900 may further include: applying hydraulic retraction fluid pressure to a second fluid chamber, wherein the first piston face has a first lateral cross-sectional area; applying a first hydraulic pressure to a piston head in a first direction based on the first lateral cross-sectional area; applying hydraulic retraction fluid pressure to the first fluid chamber, wherein the second piston face has a second lateral cross-sectional area larger than the first lateral cross-sectional area; and applying a second hydraulic pressure to the piston head in a second direction based on the second lateral cross-sectional area, wherein the second lateral cross-sectional area is configured such that the second hydraulic pressure is greater than the first hydraulic pressure and the biasing force of the biasing member. For example, retraction pressure may be applied to the first fluid chamber 650 and the second fluid chamber 652. The difference between the first lateral cross-sectional area 712 and the second lateral cross-sectional area 722 results in an imbalance between the hydraulic pressure applied by the first piston head portion 724 (e.g., a relatively large force) and the hydraulic pressure applied by the second piston head portion 726 (e.g., a relatively small force).

[0085] In some implementations, removing the hydraulic retraction pressure in the first fluid chamber may include: removing the hydraulic retraction pressure from a first piston face on a first longitudinal side of the piston head, the first piston face defining a first fluid chamber in fluid communication with a thrust reverser retraction fluid pressure source of the jet engine thrust reverser system; and removing the hydraulic retraction fluid pressure from a second piston face on a second longitudinal side of the piston head opposite the first piston face, the second piston face defining a second fluid chamber in fluid communication with a thrust reverser retraction fluid pressure source of the jet engine thrust reverser system. For example, the first fluid chamber 650 and the second fluid chamber 652 are fluidly connected, and when the retraction pressure on the first piston face 640 is released, the corresponding retraction pressure on the second piston face 642 is also released.

[0086] In some implementations, process 900 may further include: driving rotation of a pivotable cam engaged with a cam recess defined in a piston rod; driving longitudinal movement of the piston rod in a second longitudinal direction opposite to the first longitudinal direction based on the rotation; and disengaging the end of the first piston rod from the radial fork based on the longitudinal movement of the piston rod in the second longitudinal direction. For example, the manual unlocking assembly 540 may be actuated to manually unlock the thrust reverser synchronous shaft lock system 500.

[0087] In some implementations, process 900 may further include: connecting a removable rotary power source to the input of a drive assembly; driving rotation of the input via the removable rotary power source; and driving rotation of the shaft based on the rotation of the input via the drive assembly. For example, shaft 610 can be rotated by connecting a rotary tool to a manual drive assembly 550 and applying torque.

[0088] While some implementations have been described in detail above, other modifications are possible. For example, the logical flow depicted in the figures does not require a specific order or sequence to achieve the desired result. Furthermore, other steps may be provided, or steps may be omitted from the described flow, and other components may be added to or removed from the described system. Therefore, other implementations are within the scope of the appended claims.

Claims

1. A thrust reverser synchronous shaft locking system, comprising: A rotatable shaft, comprising at least one radial fork extending radially from the shaft; Hydraulic lock assembly, comprising: A housing, comprising a tubular inner wall defining a chamber; A piston head configured to contact the tubular inner wall, and including a first piston face on a first longitudinal side of the piston head, a second piston face on a second longitudinal side of the piston head opposite to the first piston face, and a locking recess, and configured to divide the chamber into a first fluid chamber defined by the tubular inner wall and the first piston face and a second fluid chamber defined by the tubular inner wall and the second piston face; A piston rod extending radially away from the shaft from a first piston rod end to a second piston rod end opposite the first piston rod end, and configured to be driven by the piston head to move the first piston rod end out of engagement with the radial fork, selectively allowing rotation of the shaft; and A biasing member configured to force the end of the first piston rod to engage with the radial fork, selectively preventing rotation of the shaft; and Electric lock assembly, comprising: Locking pin; and An electric actuator configured to controllably extend and retract the locking pin to engage and disengage with the locking recess, selectively inhibiting and allowing movement of the piston rod.

2. The thrust reverser synchronous shaft locking system according to claim 1, wherein: The tubular inner wall includes: The first longitudinal wall portion is configured to define the first fluid chamber to have a first transverse cross-sectional area near the end of the first piston rod; and The second longitudinal wall portion is configured to define the second fluid chamber to have a second transverse cross-sectional area smaller than the first transverse cross-sectional area, located away from the end of the first piston rod; and The piston head includes: The first piston head portion is sized to contact the tubular inner wall such that the first piston surface substantially has the first lateral cross-sectional area; and The second piston head portion is sized to contact the tubular inner wall such that the second piston surface substantially has the second lateral cross-sectional area.

3. The thrust reverser synchronous shaft lock system of claim 2 further includes a third fluid chamber configured to be in fluid communication with atmospheric gas at ambient pressure or having hydraulic return pressure, and defined by the first longitudinal wall portion and the second piston head portion.

4. The thrust reverser synchronous shaft locking system according to any one of claims 1 to 3, wherein, The first fluid chamber is configured to be in fluid communication with the thrust reverser retracted fluid pressure source, and the second fluid chamber is configured to be in fluid communication with the thrust reverser retracted fluid pressure source.

5. The thrust reverser synchronous shaft locking system according to claim 4 further includes a shaft housing, the shaft housing being disposed around the shaft and defining an axial fluid chamber configured to be in fluid communication with the thrust reverser deployment fluid source.

6. The thrust reverser synchronous shaft locking system of claim 4 further includes a pivotable cam configured to engage a cam recess defined in the piston head and pivot to drive longitudinal movement of the piston head and disengage the first piston rod end from the radial fork.

7. The thrust reverser synchronous shaft locking system according to any one of claims 1 to 3, further comprising a shaft housing, the shaft housing being disposed around the shaft and defining an axial fluid chamber configured to be in fluid communication with a thrust reverser deployment fluid source.

8. The thrust reverser synchronous shaft locking system of claim 7 further includes a pivotable cam configured to engage a cam recess defined in the piston head and pivot to drive longitudinal movement of the piston head and disengage the first piston rod end from the radial fork.

9. The thrust reverser synchronous shaft locking system of claim 7 further includes a fluid conduit configured to fluidly connect the first fluid chamber and the second fluid chamber.

10. The thrust reverser synchronous shaft locking system according to claim 9, wherein, The fluid conduit is a tubular conduit defined by the piston rod.

11. The thrust reverser synchronous shaft locking system according to any one of claims 1 to 3 and claim 5, further comprising a pivotable cam configured to engage a cam recess defined in the piston head and pivot to drive longitudinal movement of the piston head and disengage the end of the first piston rod from the radial fork.

12. The thrust reverser synchronous shaft locking system according to any one of claims 1 to 3, 5 to 6 and 8, further comprising a drive assembly configured to removably connect torque from a removable rotary power source to the shaft.

13. The thrust reverser synchronous shaft locking system of claim 4, further comprising a drive assembly configured to removably connect torque from a removable rotary power source to the shaft.

14. The thrust reverser synchronous shaft locking system of claim 7, further comprising a drive assembly configured to removably connect torque from a removable rotary power source to the shaft.

15. The thrust reverser synchronous shaft locking system of claim 11, further comprising a drive assembly configured to removably connect torque from a removable rotary power source to the shaft.

16. A method for locking the synchronous shaft of a thrust reverser, comprising: Remove or equalize the hydraulic retraction fluid pressure in the first fluid chamber, wherein the hydraulic lock assembly includes a housing, a piston head, a piston rod coupled to the piston head, the first fluid chamber in the housing at a first longitudinal end of the piston head, and a second fluid chamber in the housing at a second longitudinal end of the piston head opposite to the first longitudinal end; The piston rod is driven to move longitudinally in a first direction by a biasing member, the piston rod including a first piston rod end and a second piston rod end opposite to the first piston rod end; The longitudinal movement of the piston rod in the first direction forces the end of the first piston rod to engage with a radial fork extending radially from the rotatable shaft; De-energize the electric lock assembly; and Based on de-energizing the electric lock assembly, the locking pin extends to engage with a recess defined in the piston head.

17. The method of claim 16, further comprising preventing disengagement of the first piston rod end from the radial fork by engaging the locking pin with the recess.

18. The method of claim 17, further comprising preventing rotation of the shaft by engaging the end of the first piston rod with the radial fork.

19. The method of claim 16, further comprising preventing rotation of the shaft by engaging the end of the first piston rod with the radial fork.

20. The method according to any one of claims 16 to 19, further comprising: Power on the electric lock assembly; Based on the energization, the locking pin retracts from its engagement with the recess; The hydraulic retraction fluid pressure is applied to the first fluid chamber; The piston head is driven to move longitudinally in a second direction opposite to the first direction by the hydraulic retraction fluid pressure in the first fluid chamber; The piston rod is forced to move longitudinally in the second direction by the longitudinal movement of the piston head in the second direction; as well as The longitudinal movement of the piston rod in the second direction forces the end of the first piston rod to disengage from the radial fork.

21. The method of claim 20, further comprising: The hydraulic retraction fluid pressure is applied to the second fluid chamber, wherein the first piston surface of the piston head has a first lateral cross-sectional area; Based on the first transverse cross-sectional area, a first hydraulic pressure is applied to the piston head in the first direction; The hydraulic retraction fluid pressure is applied to the first fluid chamber, wherein the second piston face of the piston head has a second lateral cross-sectional area larger than the first lateral cross-sectional area; and Based on the second transverse cross-sectional area, a second hydraulic pressure is applied to the piston head in the second direction, wherein the second transverse cross-sectional area is configured such that the second hydraulic pressure is greater than the first hydraulic pressure and the biasing force of the biasing member.

22. The method according to any one of claims 16 to 19, wherein, Removing or equalizing the hydraulic retraction fluid pressure in the first fluid chamber includes: The hydraulic retraction fluid pressure is removed from a first piston face on a first longitudinal side of the piston head, the first piston face defining a first fluid chamber in fluid communication with a thrust reverser retraction fluid pressure source of the jet engine thrust reverser system; and The hydraulic retraction fluid pressure is removed from a second piston face on a second longitudinal side of the piston head opposite the first piston face, the second piston face defining a second fluid chamber in fluid communication with the thrust reverser retraction fluid pressure source of the jet engine thrust reverser system.

23. The method according to any one of claims 16 to 19, further comprising: Rotation of a pivotable cam that engages with a cam recess defined in the piston rod; The rotation drives the piston rod to move longitudinally in a second longitudinal direction opposite to the first longitudinal direction; as well as Based on the longitudinal movement of the piston rod in the second longitudinal direction, the end of the first piston rod is disengaged from the radial fork.

24. The method of claim 23, further comprising: Connect a removable rotary power source to the input of the drive assembly; The input terminal is rotated by the removable rotary power source; as well as The drive component drives the shaft to rotate based on the rotation at the input.

25. The method according to claim 20, wherein, Removing or equalizing the hydraulic retraction fluid pressure in the first fluid chamber includes: The hydraulic retraction fluid pressure is removed from a first piston face on a first longitudinal side of the piston head, the first piston face defining a first fluid chamber in fluid communication with a thrust reverser retraction fluid pressure source of the jet engine thrust reverser system; and The hydraulic retraction fluid pressure is removed from a second piston face on a second longitudinal side of the piston head opposite the first piston face, the second piston face defining a second fluid chamber in fluid communication with the thrust reverser retraction fluid pressure source of the jet engine thrust reverser system.

26. The method of claim 20, further comprising: Rotation of a pivotable cam that engages with a cam recess defined in the piston rod; The rotation drives the piston rod to move longitudinally in a second longitudinal direction opposite to the first longitudinal direction; as well as Based on the longitudinal movement of the piston rod in the second longitudinal direction, the end of the first piston rod is disengaged from the radial fork.

27. The method of claim 25, further comprising: Rotation of a pivotable cam that engages with a cam recess defined in the piston rod; The rotation drives the piston rod to move longitudinally in a second longitudinal direction opposite to the first longitudinal direction; as well as Based on the longitudinal movement of the piston rod in the second longitudinal direction, the end of the first piston rod is disengaged from the radial fork.

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