Single-actuation control landing gear retraction and locking system

Abstract

The application belongs to the technical field of aircraft landing gear, and specifically discloses a single-actuating control landing gear retraction and locking system, which comprises a first support rod, a second support rod, a third support rod, a retraction actuating cylinder and a multi-link mechanism; one end of the first support rod is connected with a hinge joint of a landing gear cabin body, and the other end is provided with a wheel; one end of the second support rod is connected with a hinge joint of a landing gear cabin body, and the other end is connected with the third support rod through a hinge joint, and one end of the third support rod, which is far away from the second support rod, is connected with the middle part of the first support rod; an upper locking mechanism is arranged on the second support rod, and a lower locking mechanism is arranged on the end close to the third support rod; the retraction actuating cylinder is connected between the hinge joint and the hinge joint of the landing gear cabin body, and is in transmission connection with the lower locking mechanism through the multi-link mechanism. The application has the advantages of compact structure and simple operation, can synchronously complete the retraction and locking of the landing gear through the single-actuating cylinder driving the multi-link mechanism, simplifies the operation process, improves the structural stability, and prolongs the service life of the landing gear.

Description

Technical Field

[0001] This invention relates to the field of aircraft landing gear technology, and in particular to a landing gear retraction and locking system with single-actuator control. Background Technology

[0002] In the aviation field, landing gear, as the core load-bearing system for aircraft takeoff, landing, and taxiing, is closely linked to flight safety in terms of reliability. The performance of the landing gear directly affects the safety of takeoff and landing and the stability of ground operations. Therefore, landing gear design has always been one of the important directions in aviation technology research.

[0003] Currently, many aircraft landing gears employ multiple actuators to handle retraction, extension, and locking. While this design achieves basic landing gear functionality, it also presents several problems: First, the arrangement of multiple actuators requires significant internal space, posing a major challenge to the already compact aircraft layout and severely limiting the installation space for other critical equipment, thus impacting the optimization of overall aircraft performance. Second, the weight of multiple actuators undoubtedly increases the overall weight of the aircraft. This increased weight not only leads to higher fuel consumption and reduced flight efficiency but may also adversely affect maneuverability, range, and other performance characteristics. Furthermore, in actual operation, the coordinated control of multiple actuators is quite challenging, and inconsistencies in movement during retraction, extension, and locking can easily occur, leading to landing gear malfunctions and, in severe cases, even jeopardizing normal takeoff and landing.

[0004] In summary, existing landing gear systems have many shortcomings in terms of structural complexity, weight, space occupation, and reliability. Therefore, it is particularly important to develop a landing gear retraction and locking mechanism that is simple in structure, highly reliable, and can effectively cope with landing impacts. Summary of the Invention

[0005] The purpose of this invention is to provide a landing gear retraction and locking system with single-actuator control. Through innovative structural design, it achieves efficient retraction, locking, and locking of the landing gear, while solving the problems of large space occupation, increased weight, high difficulty in coordinated control, and low reliability in the prior art.

[0006] To achieve the above objectives, the present invention provides the following solution: a landing gear retraction and locking system with single-actuation control, comprising a first strut and a second strut rotatably connected to different positions on the landing gear bay; the first strut is hinged to a connector at one end connected to the landing gear bay, and a wheel is mounted at the other end; the second strut is hinged to a steering knuckle at one end connected to the landing gear bay, and a third strut at the other end, the end of the third strut away from the second strut being hinged to the middle of the first strut; an upper locking mechanism is provided on the body of the second strut, and a lower locking mechanism is provided at the end of the second strut near the third strut; a retraction actuating cylinder is connected between the connector and the steering knuckle, and the steering knuckle is drivenly connected to the lower locking mechanism through a multi-link mechanism; the movement of the retraction actuating cylinder forms a complete power transmission system through the steering knuckle and the multi-link mechanism, used to drive the unlocking or locking of the upper and lower locking mechanisms.

[0007] When the retraction actuator extends, it pushes the steering knuckle to move. The steering knuckle drives the multi-link mechanism to pull the lower locking mechanism to unlock, and drives the first, second, and third struts to retract. The upper locking mechanism then locks, maintaining the landing gear in the retracted state.

[0008] When the retraction actuator retracts, it pulls the steering knuckle, which drives the multi-link mechanism to unlock the upper locking mechanism. The landing gear then unfolds under the action of gravity and aerodynamic force. The multi-link mechanism then locks the lower locking mechanism, maintaining the landing gear in the unfolded state.

[0009] Optionally, the multi-link mechanism includes a first link, a second link, a sleeve, and a third link. One end of the first link is connected to the connector, and the other end is connected to the second link. The end of the second link away from the first link slides inside the sleeve. One end of the third link is rotatably connected to the sleeve, and the other end is rotatably connected to the lower locking hook for transmitting power.

[0010] Optionally, the sleeve is provided with a limiting mechanism.

[0011] Optionally, the upper locking mechanism includes an upper locking hook and an upper locking tongue fixed on the landing gear bay, and the upper locking hook is connected to the retraction and extension actuator via a first link and a second link.

[0012] Optionally, the lower locking mechanism includes a lower locking hook and a lower locking tongue fixed to the side of the third support rod. The lower locking hook is connected to the retraction and extension actuation cylinder through a third connecting rod and a sleeve. The retraction and extension actuation cylinder controls the separation or locking of the lower locking hook and the lower locking tongue by driving a multi-link mechanism.

[0013] Optionally, the lower locking hook is connected to the extension of the second support rod.

[0014] Optionally, the first strut has a Y-shaped structure.

[0015] Optionally, a clamping mechanism is installed in the middle of the first support rod, and one end of the third support rod is hinged to the second support rod, and the other end is hinged to the clamping mechanism, forming a multi-link transmission chain.

[0016] Optionally, the clamping mechanism includes a clamping body and fastening bolts.

[0017] Optionally, the retraction actuator is an electrically operated actuator.

[0018] Compared with the prior art, the present invention discloses at least the following beneficial effects:

[0019] The landing gear retraction and extension system of this invention has a compact structure and is simple to operate. Driven by a single actuator, a multi-link mechanism can simultaneously complete the retraction, extension, and locking functions of the landing gear, simplifying the landing gear operation process. In the extended state, the transmission chain forms a stable triangular structure, improving structural stability. This structural design ensures that the transmission linkage of the locking mechanism only bears the working force during the retraction and extension phase, while the landing impact load is directly transmitted by the main load-bearing component, thereby improving system reliability, reducing the risk of landing gear damage during use, and extending the service life of the landing gear. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1 This is a front view of the landing gear retraction and locking system of the present invention, which features single-actuator control for retraction, extension, and locking.

[0022] Figure 2 for Figure 1 A magnified view of a section at point A in the middle;

[0023] Figure 3 This is a top view of the landing gear retraction and locking system of the present invention, which features single-actuator control for retraction, extension, and locking.

[0024] Figure 4 This is a right view of the landing gear retraction and locking system of the present invention, which features single-actuator control for retraction, extension, and locking.

[0025] Figure 5 This is an isometric view of the landing gear retraction and locking system of the present invention, which features single-actuator control for retraction, extension, and locking.

[0026] Figure 6 for Figure 5 A magnified view of a section at point B in the middle;

[0027] Figure 7 This is a schematic diagram of the landing gear retraction system of the present invention in the retracted state;

[0028] Figure 8 This is a schematic diagram of the upper lock in the locking state of the landing gear retraction system of the present invention;

[0029] Figure 9 This is a schematic diagram of the upper lock in the landing gear retraction system of the present invention in the unlocked state;

[0030] Figure 10 This is a schematic diagram of the landing gear retraction and extension system of the present invention in the extended state;

[0031] Figure 11 This is a schematic diagram of the lower lock in the locking state of the landing gear retraction system of the present invention;

[0032] Figure 12 This is a schematic diagram of the lower lock in the landing gear retraction system of the present invention in the unlocked state.

[0033] In the diagram: 1. Connector; 2. First strut; 3. Clamping mechanism; 4. Wheel; 5. Landing gear bay; 6. Retraction / extension actuator; 7. First link; 8. Steering knuckle; 9. Second strut; 10. Second link; 11. Upper locking hook; 12. Sleeve; 13. Third link; 14. Lower locking hook; 15. Third strut; 16. Lower locking tongue; 17. Upper locking tongue. Detailed Implementation

[0034] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0035] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0036] Reference Figures 1 to 12As shown, this embodiment of the invention provides a single-actuator control system for retraction, extension, and locking of landing gear, connected to the landing gear bay 5. It mainly includes a first support rod 2, a second support rod 9, and a third support rod 15. The first support rod 2 and the second support rod 9 are rotatably connected to different positions on the landing gear bay 5. The second support rod 9 is movably connected to the first support rod 2 via a connector 1 and a retraction / extension actuator 6. One end of the third support rod 15 is hinged to the end of the second support rod 9 away from the landing gear bay 5, and the other end is hinged to the middle of the first support rod 2. These key components work together through specific connections to achieve the retraction, extension, and locking functions of the landing gear.

[0037] Specifically, such as Figures 1 to 6 As shown, connector 1 is rotatably connected to landing gear bay 5, and its front end is rotatably connected to the piston rod of retraction / extension actuator 6, serving as the basic connection between landing gear bay 5 and retraction / extension actuator 6. First strut 2 is rigidly connected to connector 1, bearing the wheel 4 assembly, and has a Y-shaped structure; it is a key component of the landing gear supporting the aircraft's weight. Second strut 9 is rotatably connected to landing gear bay 5 and forms a transmission chain with third strut 15 via a series hinge. Second strut 9 has an extension for connecting to lower locking hook 14 when the landing gear is deployed. The end of third strut 15 is rotatably connected to first strut 2 via clamping mechanism 3. Clamping mechanism 3 includes a clamp body and fastening bolts, ensuring a stable connection between third strut 15 and first strut 2. The retraction / extension actuator 6 is an electrically operated actuator that provides power for the retraction and extension of the landing gear. It drives the upper locking hook 11 and the lower locking hook 14 to separate or lock via components such as the steering knuckle 8, the first connecting rod 7, the second connecting rod 10, the sleeve 12, and the third connecting rod 13. When the landing gear is deployed, the lower locking hook 14 connects to the extension of the second support rod 9. When locked, it forms a cross-shaped structure with the extension to lock the landing gear. When the landing gear is retracted, the upper locking hook 11 acts on a protrusion on the inner wall of the landing gear bay. When locked, it forms a cross-shaped structure with the protrusion to lock the landing gear. One end of the first connecting rod 7 is rotatably connected to the second connecting rod 10, and the other end is rotatably connected to the steering knuckle 8, serving as part of the power transmission system. The sleeve 12 is slidably connected to the second connecting rod 10 and contains a limit mechanism to restrict the sliding distance of the second connecting rod 10. One end of the third connecting rod 13 is rotatably connected to the sleeve 12, and the other end is rotatably connected to the lower locking hook 14, for transmitting power. One end of the steering knuckle 8 is rotatably connected to the retraction actuator 6, and the other end is rotatably connected to the first connecting rod 7. The middle part is rotatably connected to the second support rod 9. A limit mechanism is provided between the steering knuckle 8 and the second support rod 9 to realize steering and limit functions.

[0038] In the above embodiment, the first link 7, the second link 10, the sleeve 12, and the third link 13 form a multi-link mechanism. When the retraction actuator 6 extends, it pushes the steering knuckle 8 to move. The steering knuckle 8 drives the multi-link mechanism to pull the lower locking hook 14 to unlock, and drives the first support rod 2, the second support rod 9, and the third support rod 15 to retract. The upper locking hook 11 is locked, maintaining the landing gear in the retracted state. When the retraction actuator 6 retracts, it pulls the steering knuckle 8 to move. The steering knuckle 8 drives the multi-link mechanism to push the upper locking hook 11 to unlock. The landing gear unfolds under the action of gravity and aerodynamic force. The multi-link mechanism pushes the lower locking hook 14 to lock, maintaining the landing gear in the unfolded state.

[0039] In one specific embodiment, the connector 1 is rotatably connected to the landing gear bay 5, and its front end is rotatably connected to the piston rod of the retraction / extension actuator 6. The connector 1 serves to connect the landing gear bay 5 and the retraction / extension actuator 6, providing a basic connection structure for the retraction and extension of the landing gear. The connector 1 is a key connecting component between the landing gear bay 5 and the retraction / extension actuator 6, transmitting the power of the retraction / extension actuator 6 to other components of the landing gear.

[0040] In one specific embodiment, the first strut 2 is connected to the landing gear housing 5 via a connector 1, and is also connected to the second strut 9 and the third strut 15 via a clamping mechanism 3, forming the main support structure of the landing gear. The first strut 2 is rigidly connected to the connector 1, supports the aircraft wheel 4, and has a Y-shaped structure. The first strut 2 is a key component of the landing gear that supports the weight of the aircraft and enables takeoff and landing.

[0041] In one specific embodiment, one end of the second strut 9 is connected to the landing gear bay 5, and the other end is connected in series with the third strut 15 via a hinge. The strut 9 is connected to the power transmission system of the retraction / extension actuator 6 via a steering knuckle 8. The strut 9, rotatably connected to the landing gear bay 5 and connected in series with the third strut 15 to form a transmission chain, has an extension portion. It transmits power during landing gear retraction / extension and locking, achieving landing gear state switching via the second strut 9. Together with the third strut 15, it forms a "two-force bar" structure, which, in conjunction with the lower locking hook 14, ensures stable landing gear support.

[0042] In one specific embodiment, one end of the third support rod 15 is connected in series with the second support rod 9 and the other end is connected to the first support rod 2 through a clamping mechanism 3, forming a support and transmission structure for the landing gear. The end of the third support rod 15 is rotatably connected to the first support rod 2 through the clamping mechanism 3, and at the same time, it forms a transmission chain with the second support rod 9 through a series hinge, transmitting power during the landing gear retraction, extension, and locking process, thereby realizing the switching of the landing gear state.

[0043] In one specific embodiment, the piston rod of the retraction / extension actuator 6 is rotatably connected to the connector 1, and is connected to components such as the first connecting rod 7, the second connecting rod 10, the sleeve 12, and the third connecting rod 13 via the steering knuckle 8, forming a complete power transmission system. The retraction / extension actuator 6 can be an electrically driven actuator to provide power for the retraction and extension of the landing gear. Through components such as the steering knuckle 8, connecting rod, and sleeve 12, it drives the upper locking hook 11 and the lower locking hook 14 to separate or lock, thereby realizing the retraction, extension, and locking functions of the landing gear.

[0044] In one specific embodiment, the lower locking hook 14 is connected to the sleeve 12 via the third connecting rod 13, and its connection and separation with the lower locking tongue 16 are controlled by the retraction actuator 6 through a power transmission system. The lower locking tongue 16 is fixed to the side of the third support rod 15. When the landing gear is deployed, the lower locking hook 14 and the lower locking tongue 16 lock together to lock the landing gear and ensure its stability during landing.

[0045] In one specific embodiment, the upper locking hook 11 is connected to the retraction / extension actuation cylinder 6 via components such as the first connecting rod 7, the second connecting rod 10, the sleeve 12, and the third connecting rod 13. The retraction / extension actuation cylinder 6 controls the connection and separation between the upper locking hook 11 and the upper locking tongue 17. Specifically, the upper locking tongue 17 is a protrusion located on the inner wall of the landing gear bay. When the landing gear is retracted, the upper locking hook 11 and the upper locking tongue 17 lock together to secure the landing gear and ensure its stability during flight.

[0046] In one specific embodiment, the first link 7 connects the steering knuckle 8 and the second link 10, and is a key connecting component between the retractable actuator 6 and the locking hook. One end of the first link 7 is rotatably connected to one end of the second link 10, and the other end is rotatably connected to the steering knuckle 8. As part of the power transmission system, the first link 7 transmits the power of the retractable actuator 6 to the upper locking hook 11 and the lower locking hook 14.

[0047] In one specific embodiment, the second link 10 is a rigid rod with rotating connection points at both ends. One end is rotatably connected to one end of the first link 7, and the other end is slidably connected to the sleeve 12. This structure allows the second link 10 to slide and rotate within a certain range to adapt to the movement requirements during the landing gear retraction and extension process. The second link 10 is a key transmission component of the landing gear retraction and locking system. It transmits the power of the retraction actuator 6 to the sleeve 12 and the third link 13 through the first link 7, thereby driving the separation and locking of the upper locking hook 11 and the lower locking hook 14, realizing the landing gear retraction and locking functions.

[0048] In one specific embodiment, the sleeve 12 is connected to the first link 7 via the second link 10 and to the lower locking hook 14 via the third link 13, serving as a limit and connection mechanism to restrict the sliding distance of the second link 10 and ensure the accuracy and reliability of power transmission. Furthermore, the sleeve 12 contains a limit mechanism to further restrict the sliding distance of the second link 10, thereby ensuring the movement accuracy and stability of the landing gear during retraction and extension, and preventing excessive movement between components from causing system failure.

[0049] In one specific embodiment, the limiting mechanism inside the sleeve 12 is an annular boss provided on the inner wall of the sleeve 12. The annular boss extends axially along the sleeve 12 to form a guide groove. The end of the second connecting rod 10 is provided with a radial protrusion that cooperates with the guide groove. The axial length of the guide groove limits the movement stroke of the radial protrusion. When the second connecting rod 10 is driven to make axial displacement, its radial protrusion moves along the guide groove to the end of the annular boss and is blocked. At this time, the third connecting rod 13 and the lower locking hook 14 form a precise linkage to realize the stroke control of the opening and closing action of the lower lock.

[0050] In one specific embodiment, the third link 13 connects the sleeve 12 and the lower locking hook 14, and is a key connecting component between the retractable actuator 6 and the lower locking hook 14. One end of the third link 13 is rotatably connected to the other end of the sleeve 12, and the other end is rotatably connected to the middle of the lower locking hook 14. As part of the power transmission system, the third link 13 transmits the power of the retractable actuator 6 to the lower locking hook 14.

[0051] In one specific embodiment, one end of the steering knuckle 8 is rotatably connected to the retractable actuator 6, the other end is rotatably connected to the first connecting rod 7, and the middle part is rotatably connected to the second support rod 9. A limit mechanism is provided between the steering knuckle 8 and the second support rod 9. As a key component of the power transmission system, the steering knuckle 8 connects the retractable actuator 6, the first connecting rod 7, and the second support rod 9, transmitting the power of the retractable actuator 6 to the first connecting rod 7 and the second support rod 9, and realizing steering and limit functions through the limit mechanism.

[0052] In one specific embodiment, the clamping mechanism 3 has a clamping body and a fastening bolt. The clamping body clamps the first support rod 2, and the clamping force is adjusted by the fastening bolt. The clamping mechanism 3 connects the third support rod 15 and the first support rod 2, and plays a role in fixing and connecting, ensuring that the third support rod 15 and the first support rod 2 are firmly connected and that no relative displacement occurs during the operation of the landing gear.

[0053] The working process of this invention embodiment is as follows:

[0054] Landing gear retraction process: During takeoff, the retraction actuator 6 operates, extending the piston rod to push the steering knuckle 8. The steering knuckle 8 sequentially pulls the lower locking hook 14 away from the extension part via the first connecting rod 7, the second connecting rod 10, the sleeve 12, and the third connecting rod 13. Subsequently, the steering knuckle 8 is locked at the limit position. Under the action of the retraction actuator 6, the first support rod 2, the second support rod 9, and the third support rod 15 begin to rotate and slowly retract the landing gear until it is retracted to the upper locking hook 11. At this point, the retraction actuator 6 stops operating and maintains the current pressure to maintain the stable state of the retracted landing gear.

[0055] Landing gear deployment process: Before landing, the landing gear needs to be deployed. The retraction actuator 6 operates again, the piston rod retracts, and firstly, through the steering knuckle 8, it drives the first link 7 and the second link 10 to push the upper locking hook 11 past its dead center to unlock. Then, under the action of gravity and aerodynamic force, the landing gear slowly deploys, with the retraction actuator 6 providing auxiliary power. When the landing gear is deployed to the point where the second strut 9 and the third strut 15 are parallel, the retraction actuator 6 retracts, driving the steering knuckle 8 to rotate. The steering knuckle 8, through the first link 7, the second link 10, the sleeve 12, and the third link 13, pushes the lower locking hook 14 to lock, realizing the lower locking of the landing gear and providing stable support for the aircraft landing.

[0056] Throughout the landing gear retraction, extension, and locking process, the triangular structure formed by the retraction / extension actuator 6, the second strut 9, the third strut 15, and the first strut 2 exhibits strong stability in the deployed state. This effectively disperses the impact forces during aircraft landing and taxiing, ensuring the landing gear reliably supports the aircraft's weight. This system cleverly achieves synchronized control of landing gear retraction, extension, and locking through a single actuator driving a multi-link mechanism, simplifying the system structure and reducing operational complexity.

[0057] In the description of this invention, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this invention, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0058] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Various modifications and improvements made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.

Claims

1. A landing gear retraction and locking system with single-actuator control, characterized in that, The system includes a first strut (2) and a second strut (9) rotatably connected to different positions on the landing gear housing (5); the first strut (2) is hinged to a connector (1) at one end connected to the landing gear housing (5), and a wheel (4) is installed at the other end; the second strut (9) is hinged to a steering knuckle (8) at one end connected to the landing gear housing (5), and a third strut (15) at the other end, the third strut (15) being hinged to the middle of the first strut (2) via a clamping mechanism (3), the clamping mechanism (3) including a clamp body and a fastening bolt; an upper locking mechanism is provided on the body of the second strut (9), and a lower locking mechanism is provided on the end of the second strut (9) near the third strut (15); a connection is provided between the connector (1) and the steering knuckle (8). The retractable actuator (6) is connected to the lower locking mechanism via a multi-link mechanism. The multi-link mechanism includes a first link (7), a second link (10), a sleeve (12), and a third link (13). One end of the first link (7) is connected to the connector (1), and the other end is connected to the second link (10). The end of the second link (10) away from the first link (7) slides inside the sleeve (12). One end of the third link (13) is rotatably connected to the sleeve (12), and the other end is rotatably connected to the lower locking hook (14) for transmitting power. The retractable actuator (6) forms a complete power transmission system through the steering knuckle (8) and the multi-link mechanism for driving the unlocking or locking of the upper and lower locking mechanisms.

2. The landing gear retraction and locking system with single-actuator control according to claim 1, characterized in that, The sleeve (12) is provided with a limiting mechanism, which is an annular boss on the inner wall of the sleeve (12). The annular boss extends along the axial direction of the sleeve (12) to form a guide groove. The end of the second connecting rod (10) is provided with a radial protrusion that cooperates with the guide groove. The axial length of the guide groove limits the movement of the radial protrusion.

3. The landing gear retraction and locking system with single-actuator control according to claim 1, characterized in that, The upper locking mechanism includes an upper locking hook (11) and an upper locking tongue (17) fixed on the landing gear cabin (5). The upper locking hook (11) is connected to the retraction and extension actuator (6) through a first link (7) and a second link (10).

4. The landing gear retraction and locking system with single-actuator control according to claim 1, characterized in that, The lower locking mechanism includes a lower locking hook (14) and a lower locking tongue (16) fixed to the side of the third support rod (15). The lower locking hook (14) is connected to the retraction and extension actuation cylinder (6) through the third link (13) and the sleeve (12). The retraction and extension actuation cylinder (6) controls the separation or locking of the lower locking hook (14) and the lower locking tongue (16) through a multi-link mechanism.

5. The landing gear retraction and locking system with single-actuator control according to claim 4, characterized in that, The lower locking hook (14) is connected to the extension of the second support rod (9).

6. The landing gear retraction and locking system with single-actuator control according to claim 1, characterized in that, The first strut (2) has a Y-shaped structure.

7. The landing gear retraction and locking system with single-actuator control according to claim 1, characterized in that, The retraction and extension actuator (6) is an electrically operated actuator.

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