Undercarriage down lock mechanism

Abstract

The utility model relates to the technical field of down lock mechanisms, in particular to an undercarriage down lock mechanism, which comprises an actuating cylinder, a locking mechanism, a locking mechanism and a locking mechanism, the hydraulic oil nozzle is arranged at the oil inlet hole of the actuating cylinder; the piston rod is arranged in the through cavity of the actuating cylinder, and a positioning groove is formed in the piston rod; the locking ring is arranged in the through cavity of the actuating cylinder, is matched with the positioning groove of the piston rod and is used for locking the piston rod; the auxiliary mechanism is arranged at one end of the through cavity of the actuating cylinder and is used for carrying out auxiliary support on the piston rod; the lock hoop is arranged on the auxiliary mechanism and is installed in a sliding mode in the direction of the through cavity, and the lock hoop and the lock ring are installed in a matched mode; one end of the first spring is arranged on the lock hoop, and the other end is arranged on the auxiliary mechanism; the sensing mechanism is arranged on the actuating cylinder, and the sensing mechanism and the lock hoop are installed in a matched mode; the positioning mechanism is arranged in the through cavity of the actuating cylinder and is used for limiting the position of the locking ring; the structure is simple, the failure rate is low, and space is saved.

Description

Technical Field

[0001] This utility model relates to the technical field of lower locking mechanisms, and in particular to a landing gear lower locking mechanism. Background Technology

[0002] The function of the landing gear lower position lock is to secure the landing gear strut in the lowered position. Therefore, ensuring smooth locking and preventing loosening due to interference is a primary design consideration. The lower position lock is typically located inside the retraction / extension actuator, i.e., an internal lock. Once locked, it determines the length of the actuator rod, thus securing the landing gear in the lowered position and functioning as the lower position lock.

[0003] With the continuous development of aviation technology and the improvement of user needs, especially in the field of civil aircraft, higher requirements have been put forward for the intuitive confirmation of the landing gear locking status. Traditional internal lock designs are often difficult to observe their locking status directly due to their concealed structure, which increases the uncertainty of flight operations to a certain extent. In order to meet this requirement, the aviation industry has begun to explore more intuitive and reliable landing gear lower lock solutions. Utility Model Content

[0004] To solve the above-mentioned technical problems, this utility model provides a landing gear lower position locking mechanism that is simple in structure, has a low failure rate, and saves space.

[0005] This utility model discloses a landing gear lower position locking mechanism, comprising:

[0006] The actuator is independently and fixedly installed, and a through cavity is provided on the actuator.

[0007] The hydraulic nozzle is located at the oil inlet of the actuator and is connected to the oil passage inside the actuator.

[0008] The piston rod is located in the cavity of the actuator cylinder and is slidably installed along the length of the cavity. A positioning groove is provided on the piston rod.

[0009] The locking ring is located inside the cavity of the actuator cylinder and engages with the positioning groove of the piston rod to lock the piston rod.

[0010] An auxiliary mechanism, located at one end of the cavity of the actuator cylinder, is used to provide auxiliary support for the piston rod;

[0011] The locking clamp is installed on the auxiliary mechanism and slides along the direction of the cavity. The locking clamp and the locking ring are installed together.

[0012] The first spring has one end attached to the locking clamp and the other end attached to the auxiliary mechanism;

[0013] The sensing mechanism is mounted on the actuator cylinder and is installed in conjunction with the locking clamp to transmit signals of unlocking or locking status to the cockpit.

[0014] The positioning mechanism, located in the through cavity of the actuating cylinder, is used to limit the position of the locking ring.

[0015] Furthermore, the sensing mechanism includes:

[0016] The sensor is installed in the through hole of the actuator cylinder and is connected to the cockpit via a signal.

[0017] The second spring is located on the sensor's trigger.

[0018] The steel ball is located in the through hole of the actuator cylinder and is connected to the second spring and the locking clamp.

[0019] Preferably, the contact end between the locking clamp and the steel ball has a beveled structure, which is used to drive the steel ball to its position in the through hole of the actuator cylinder.

[0020] Furthermore, the auxiliary mechanisms include:

[0021] An auxiliary component is installed in the through cavity of the actuator cylinder, and the first spring is installed in conjunction with the auxiliary component. The locking clamp is slidably installed on the auxiliary component, and the piston rod is slidably connected to the inner cavity of the auxiliary component.

[0022] A locking element is located at one end of the actuator cylinder cavity to determine the installation position of the auxiliary component, and the locking element is installed with the actuator cylinder by threads.

[0023] As a preferred option, the positioning mechanism includes:

[0024] The unlocking baffle is installed in the through cavity of the actuator cylinder, and the locking ring is installed in conjunction with the unlocking baffle;

[0025] The connector is located in the cavity of the actuator cylinder, with one end connected to the unlocking baffle and the other end connected to the auxiliary component.

[0026] Furthermore, the unlocking baffle is equipped with an oil passage hole to allow hydraulic oil to pass through.

[0027] Preferably, the connection end between the lock clamp and the lock ring is chamfered, and the connection end between the lock ring and the lock clamp is also chamfered.

[0028] Furthermore, sealing components are provided at the connection points of the piston rod and the actuator cylinder, the connection points of the connecting piece and the locking clamp, the connection points of the locking clamp and the auxiliary piece, the connection points of the piston rod and the auxiliary piece, and the connection points of the locking piece and the piston rod.

[0029] A landing gear lower position locking mechanism was designed: the landing gear lower position locking mechanism adopts hydraulic and mechanical unlocking, and is equipped with a locking-unlocking sensor mechanism 8. It has a simple structure, low failure rate, and saves space. The unlocking of the actuator cylinder 1 and the retraction of the piston rod 3 adopt a unified hydraulic system. Attached Figure Description

[0030] Figure 1 This is a schematic diagram of the structure of a landing gear lower locking mechanism in the first angle according to the present invention;

[0031] Figure 2 This is a schematic diagram of the locked state structure of a landing gear lower position locking mechanism in this utility model;

[0032] Figure 3 This is a schematic diagram of the unlocking state structure of a landing gear lower position lock mechanism in this utility model;

[0033] Figure 4 This utility model relates to a landing gear lower position locking mechanism. Figure 3 Enlarged structural diagram of section A in the middle;

[0034] The following components are labeled in the attached diagram: 1. Actuating cylinder; 2. Hydraulic nozzle; 3. Piston rod; 4. Locking ring; 5. Auxiliary mechanism; 51. Auxiliary component; 52. Locking component; 6. Locking clamp; 7. First spring; 8. Sensing mechanism; 81. Sensor; 82. Second spring; 83. Steel ball; 9. Positioning mechanism; 91. Unlocking baffle; 92. Connecting component; 10. Sealing assembly. Detailed Implementation

[0035] The specific embodiments of this utility model will be described in further detail below with reference to the accompanying drawings and examples. The following examples are used to illustrate this utility model, but are not intended to limit its scope.

[0036] This utility model relates to a landing gear lower position locking mechanism, such as Figures 1 to 4 As shown, it includes:

[0037] Actuating cylinder 1 is independently and fixedly installed, serving as the basic structure of the entire locking mechanism, and a through cavity is provided on actuating cylinder 1;

[0038] The hydraulic nozzle 2 is located at the oil inlet of the actuator cylinder 1 and is connected to the oil passage inside the actuator cylinder 1.

[0039] The piston rod 3 is disposed in the through cavity of the actuating cylinder 1 and is slidably installed along the length of the through cavity. The piston rod 3 is provided with a positioning groove.

[0040] Locking ring 4 is set in the through cavity of actuator cylinder 1 and cooperates with the positioning groove of piston rod 3 to lock piston rod 3;

[0041] Auxiliary mechanism 5 is located at one end of the through cavity of actuator cylinder 1 and is used to provide auxiliary support for piston rod 3;

[0042] The locking clamp 6 is mounted on the auxiliary mechanism 5 and is slidably installed along the cavity direction. The locking clamp 6 is installed in conjunction with the locking ring 4.

[0043] The first spring 7 has one end mounted on the locking clamp 6 and the other end mounted on the auxiliary mechanism 5;

[0044] The sensing mechanism 8 is mounted on the actuator cylinder 1 and is installed in conjunction with the locking clamp 6 to transmit signals of unlocking or locking status to the cockpit.

[0045] The positioning mechanism 9 is located in the through cavity of the actuating cylinder 1 and is used to limit the position of the locking ring 4;

[0046] The working principle of the lower landing gear locking mechanism is as follows:

[0047] When the landing gear retracts, the actuator 1 unlocks first, and then the piston rod 3 retracts to retract the landing gear. During this process, hydraulic oil is introduced into the hydraulic nozzle 2, and the pressure of the hydraulic oil increases. When the pressure is greater than the pressure of the first spring 7, the locking ring 6 displaces the pressure of the spring 7 and disengages from the locking ring 4. The locking ring 4 automatically expands, and the unlocked state is reached. The sensor mechanism 8 transmits the unlocking information to the outside. At this time, the piston rod 3 is in a free state and retracts under the action of hydraulic oil to achieve the purpose of retracting the landing gear.

[0048] When the landing gear is lowered again, the piston rod 3 of the actuator cylinder 1 extends. When the piston rod 3 is extended to its maximum length, the spring 7 pushes the locking clamp 6 to lock the locking ring 4, and the sensing mechanism 8 transmits the locking information to the outside.

[0049] The lower landing gear locking mechanism uses a combination of hydraulic and mechanical unlocking, and is equipped with a locking-unlocking sensor mechanism 8. It has a simple structure, low failure rate, and saves space. The unlocking of the actuator cylinder 1 and the retraction of the piston rod 3 adopt a unified hydraulic system.

[0050] As a preferred option, such as Figure 1 Figure 4 As shown, the sensing mechanism 8 includes:

[0051] Sensor 81 is installed in the through hole of actuator cylinder 1, and sensor 81 is in signal communication with the cockpit;

[0052] The second spring 82 is disposed on the trigger of the sensor 81;

[0053] The steel ball 83 is located in the through hole of the actuator cylinder 1 and is connected to the second spring 82 and the locking clamp 6. The function of the steel ball 83 is to act as a transmission element to convert the displacement of the locking clamp 6 into a pressure change on the trigger of the sensor 81.

[0054] The contact end between the locking clamp 6 and the steel ball 83 is a beveled structure, which is used to drive the steel ball 83 to the position in the through hole of the actuator cylinder 1;

[0055] The working principle of the sensing mechanism 8 in this device is as follows:

[0056] The inclined structure of the locking clamp 6 causes the steel ball 83 to compress the second spring 82 when the locking clamp 6 is displaced, causing the trigger to activate and activate the sensor 81 to send a signal. When the locking clamp 6 is reset, the second spring 82 returns to its original state, driving the trigger back to the initial position, ready for the next action.

[0057] As a preferred option, such as Figures 1 to 3 As shown, the auxiliary mechanism 5 includes:

[0058] The auxiliary component 51 is installed in the through cavity of the actuator cylinder 1, and the first spring 7 is installed in cooperation with the auxiliary component 51. The locking clamp 6 is slidably installed on the auxiliary component 51, and the piston rod 3 is slidably connected to the inner cavity of the auxiliary component 51.

[0059] Locking element 52 is provided at one end of the through cavity of actuator cylinder 1 and is used to fix the installation position of auxiliary component 51. Locking element 52 is installed with actuator cylinder 1 by thread.

[0060] The auxiliary component 51 is precisely installed in the cavity of the actuator cylinder 1, which not only provides a solid assembly base for the first spring 7, ensuring the stability and reliability of the spring during compression and release, but also provides a stable and smooth sliding track for the locking clamp 6, greatly reducing frictional resistance and improving the response speed and efficiency of the locking mechanism. The sliding connection design between the piston rod 3 and the inner cavity of the auxiliary component 51 ensures the smooth extension and retraction of the piston rod under the action of hydraulic oil, which is crucial for the precise control of the landing gear. In addition, the locking component 52 is threadedly installed at one end of the cavity of the actuator cylinder 1, which not only achieves precise positioning of the installation position of the auxiliary component 51, but also facilitates installation and disassembly, optimizing the overall layout and performance of the locking mechanism.

[0061] As a preferred option, such as Figures 1 to 3 As shown, the positioning mechanism 9 includes:

[0062] The unlocking baffle 91 is installed in the through cavity of the actuator cylinder 1, and the locking ring 4 is installed in conjunction with the unlocking baffle 91. The unlocking baffle 91 is provided with an oil passage hole to allow hydraulic oil to pass through.

[0063] The connector 92 is disposed in the through cavity of the actuator cylinder 1, with one end connected to the unlocking baffle 91 and the other end connected to the auxiliary component 51;

[0064] The unlocking baffle 91 is precisely installed in the cavity of the actuating cylinder 1 and fits tightly with the locking ring 4, ensuring the stability and reliability of the locking mechanism during the unlocking and locking process. The connecting piece 92 not only strengthens the connection between the unlocking baffle 91 and the auxiliary piece 51, but also effectively limits the position of the locking ring 4 through its structural characteristics, preventing the locking ring from moving accidentally in the non-operating state. This design not only improves the overall rigidity and durability of the locking mechanism, but also optimizes the movement trajectory of the locking ring, making the unlocking and locking actions smoother and more efficient.

[0065] As a preferred option, such as Figures 1 to 3 As shown, the connection end between the locking clamp 6 and the locking ring 4 is chamfered, and the connection end between the locking ring 4 and the locking clamp 6 is also chamfered;

[0066] The chamfer at the connection end between the locking clamp 6 and the locking ring 4 not only optimizes the fit between the locking clamp 6 and the locking ring 4, allowing them to slide and separate more smoothly when in contact, reducing frictional resistance, but also improves the efficiency and reliability of the locking mechanism during unlocking and locking.

[0067] As a preferred option, such as Figures 1 to 3 As shown, sealing components 10 are provided at the connection points of piston rod 3 and actuator cylinder 1, connector 92 and locking clamp 6, locking clamp 6 and auxiliary component 51, piston rod 3 and auxiliary component 51, and locking component 52 and piston rod 3.

[0068] The sealing components 10 effectively prevent the leakage of hydraulic oil and other potential contaminants, ensuring the cleanliness of the internal environment of the locking mechanism and the unobstructed flow of hydraulic oil circuits, thereby significantly improving the operational stability and durability of the locking mechanism. Secondly, these sealing components also significantly enhance the sealing performance of each connection part, avoiding performance degradation or failure risks caused by poor sealing, and further ensuring the safety and reliability of the lower landing gear locking mechanism.

[0069] The landing gear lower locking mechanism of this utility model can be installed, connected or set in a common mechanical way, and can be implemented as long as it can achieve its beneficial effect.

[0070] The above are merely preferred embodiments of this utility model. It should be noted that, for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of this utility model, and these improvements and modifications should also be considered within the protection scope of this utility model.

Claims

1. A landing gear lower position locking mechanism, characterized in that, include: The actuator (1) is independently fixed and has a through cavity. The hydraulic nozzle (2) is located at the oil inlet of the actuator (1) and is connected to the oil passage inside the actuator (1). The piston rod (3) is disposed in the cavity of the actuating cylinder (1) and is slidably installed along the length of the cavity. The piston rod (3) is provided with a positioning groove. A locking ring (4) is provided in the through cavity of the actuating cylinder (1) and cooperates with the positioning groove of the piston rod (3) to lock the piston rod (3); An auxiliary mechanism (5) is provided at one end of the cavity of the actuating cylinder (1) to provide auxiliary support for the piston rod (3); A locking clamp (6) is provided on the auxiliary mechanism (5) and is slidably installed along the cavity direction. The locking clamp (6) is installed in conjunction with the locking ring (4). The first spring (7) has one end set on the locking clamp (6) and the other end set on the auxiliary mechanism (5); The sensing mechanism (8) is disposed on the actuating cylinder (1), and the sensing mechanism (8) is installed in conjunction with the locking clamp (6) to transmit the signal of unlocking or locking status to the cockpit; The positioning mechanism (9) is located in the cavity of the actuating cylinder (1) and is used to limit the position of the locking ring (4).

2. The landing gear lower position locking mechanism as described in claim 1, characterized in that, The sensing mechanism (8) includes: The sensor (81) is installed in the through hole of the actuator (1), and the sensor (81) is in signal communication with the cockpit; The second spring (82) is disposed on the trigger of the sensor (81); The steel ball (83) is located in the through hole of the actuating cylinder (1) and is connected to the second spring (82) and the locking clamp (6).

3. The landing gear lower locking mechanism as described in claim 2, characterized in that, The contact end between the locking clamp (6) and the steel ball (83) is a beveled structure, which is used to drive the steel ball (83) in the through hole of the actuating cylinder (1).

4. The landing gear lower position locking mechanism as described in claim 1, characterized in that, The auxiliary mechanism (5) includes: An auxiliary component (51) is installed in the through cavity of the actuating cylinder (1), and the first spring (7) is installed in cooperation with the auxiliary component (51). The locking clamp (6) is slidably installed on the auxiliary component (51), and the piston rod (3) is slidably connected to the inner cavity of the auxiliary component (51). A locking element (52) is provided at one end of the cavity of the actuating cylinder (1) for fixing the installation position of the auxiliary component (51), and the locking element (52) is threadedly installed with the actuating cylinder (1).

5. The landing gear lower position locking mechanism as described in claim 4, characterized in that, The positioning mechanism (9) includes: The unlocking baffle (91) is installed in the through cavity of the actuating cylinder (1), and the locking ring (4) is installed in conjunction with the unlocking baffle (91); The connector (92) is disposed in the through cavity of the actuating cylinder (1), with one end connected to the unlocking baffle (91) and the other end connected to the auxiliary component (51).

6. The landing gear lower position locking mechanism as described in claim 5, characterized in that, The unlocking baffle (91) is provided with an oil passage hole to allow hydraulic oil to pass through.

7. A landing gear lower position locking mechanism as described in claim 1, characterized in that, The connection end between the locking clamp (6) and the locking ring (4) is chamfered, and the connection end between the locking ring (4) and the locking clamp (6) is also chamfered.

8. The landing gear lower position locking mechanism as described in claim 5, characterized in that, Sealing components (10) are provided at the connection points of the piston rod (3) and the actuating cylinder (1), the connection points of the connecting member (92) and the locking clamp (6), the connection points of the locking clamp (6) and the auxiliary member (51), the connection points of the piston rod (3) and the auxiliary member (51), and the connection points of the locking member (52) and the piston rod (3).

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