A luggage case hinge for a civil aircraft

Abstract

The utility model provides a kind of civil aircraft suitcase hinge, comprising: rocker arm and base, rocker arm below is provided with mounting hole and camshaft, base below is rotatably installed with threaded adjusting shaft, another end of threaded adjusting shaft is rotatably installed in the middle of camshaft, the middle part of base is fixedly installed by rocker arm pivot through mounting hole, rocker arm forms four-bar linkage by camshaft and connecting rod, limiting block is integrated in base, set the minimum opening angle of case door.The hinge system of the utility model is through the innovative "axial compression+radial decoupling" design concept, combined with modular adjustable structure, while ensuring high reliability, realizes the accurate control of case door movement and the convenience of installation and maintenance, breaks through the technical bottleneck that aviation level hinge high reliability and small size are difficult to be compatible, has been successfully applied to multiple civil aircraft luggage compartment system, and has the technical versatility of extending to spacecraft hatch mechanism.

Description

Technical Field

[0001] This utility model relates to the field of aircraft structural cabin interior technology, and in particular to a civil aircraft luggage hinge. Background Technology

[0002] Currently, the most similar product for airplane luggage hinges is the tension spring hinge, which has the following disadvantages:

[0003] 1. Tension springs have high requirements for material properties, and the springs are in a tensile state during operation, resulting in a short fatigue life;

[0004] 2. The internal spring of the tension spring hinge is directly connected to the door bracket, and the force is transmitted solely by the spring itself. The spring bears both axial and radial forces at the same time, and fatigue accumulates at the connection between the spring and the door bracket, making it prone to breakage.

[0005] 3. The maximum opening angle of the cabinet door is adjusted by using an eccentric adjustment sleeve, but the internal adjustment space of the hinge is limited, and the adjustment range of the maximum opening angle of the cabinet door is small.

[0006] While existing technologies have attempted to utilize linear springs, these solutions often fail to meet the stringent operational requirements of aviation due to structural redundancy (such as multi-stage linkages), off-center wear, or complex adjustments. Therefore, there is an urgent need for a lightweight, highly reliable hinge solution adapted to the unique aviation environment to balance durability, space efficiency, and dynamic stability. Utility Model Content

[0007] (a) Technical problems to be solved

[0008] To address the shortcomings of existing technologies, this utility model provides a civil aircraft luggage hinge that solves the technical problem of luggage hinge connection stability.

[0009] (II) Technical Solution

[0010] To achieve the above objectives, this utility model provides the following technical solution:

[0011] A civilian aircraft luggage compartment hinge, including

[0012] The rocker arm and base have mounting holes and a camshaft at the bottom. A threaded adjustment shaft is rotatably mounted on the bottom of the base. The threaded adjustment shaft is a set of axially telescopic sleeve structures. The other end of the threaded adjustment shaft is rotatably mounted in the middle of the camshaft. The rocker arm is fixedly mounted in the middle of the upper part of the base by passing through the mounting hole via the rocker arm pivot. The rocker arm forms a four-bar linkage with the connecting rod via the camshaft. The limit block is integrated into the base to set the minimum opening angle of the cabinet door.

[0013] Preferably, the rocker arm shaft includes a connecting rod, a piston rod, a pressure cap, and a cylinder. The tail end of the cylinder forms a rotating pair with the base. The upper end of the connecting rod is hinged to the camshaft of the rocker arm to form a motion transmission hub. The piston rod is slidably installed inside the connecting rod and the cylinder, and the piston rod passes through the guide connecting rod and the cylinder to form a sliding pair.

[0014] Preferably, a pressure cap is provided in the middle of the piston rod, a spring is installed between the connecting rod and the cylinder, and a nut is used to connect the piston rod to the cylinder. The spring seat is fixedly installed, and the nut is fitted onto the outer periphery of the piston rod. The preload is transmitted through the spring seat, and the nut is connected to the cylinder. Thread This combination enables stepless adjustment of the spring preload.

[0015] Preferably, a placement platform is provided below the base, and a limiting block is installed by rotating the placement platform. The limiting block is a limiting plate structure with one side curved and the other side straight.

[0016] Preferably, the rocker arm is a C-shaped structural plate, with the tail of the rocker arm contacting the outside of the limiting block. The limiting block limits the rotation position (open state) of the rocker arm, limits the maximum sliding amount between the connecting rod and the cylinder, and limits the minimum sliding amount between the connecting rod and the cylinder by the pressure cap.

[0017] Preferably, the threaded adjustment shaft includes a pressure cap and a rotating shaft. A protruding rod is provided above the base. Both the pressure cap and the rotating shaft are sleeved on the outside of the protruding rod. The mounting hole is a long, narrow groove structure. A cut-edge stop is provided on the outside of the rotating shaft. The outer dimensions of the cut edge of the rotating shaft are the same as the dimensions of the groove in the mounting hole for engagement. When the rocker arm rotating shaft extends or retracts axially, the corresponding rotating shaft can slide in the mounting hole to allow for the extension or retraction of the rocker arm rotating shaft.

[0018] Preferably, a bushing is provided at the position where the rotating shaft contacts the base to reduce friction loss. A screw is rotatably installed in the middle of the rotating shaft, and a pressure cap is rotatably installed at the other end of the screw to rotate the rocker arm between the pressure cap and the rotating shaft. In addition, a washer is provided between the screw and the rotating shaft to level the installation position of the rotating shaft, which facilitates installation.

[0019] Preferably, the hinge cover is fixed to the outside of the base by bolts.

[0020] (III) Beneficial Effects

[0021] 1. Low material requirements and long life design:

[0022] By replacing the traditional torsion spring with a compression spring, the spring only bears the axial compression load, avoiding stress concentration caused by torsional deformation, significantly reducing the requirements for the fatigue resistance of the spring material. The precision sliding pair design of the piston rod and cylinder ensures that the spring is always compressed in a straight line, eliminating off-center wear and extending the spring life by more than 30% compared to traditional hinges.

[0023] 2. Space optimization and assembly flexibility:

[0024] The spring-loaded hinges can be installed laterally inside the side panel of the trunk, avoiding taking up space on top of the trunk and increasing loading capacity by about 15%. The angle of the limit block is adjustable through the rotating platform, allowing for fine-tuning of the minimum opening angle during assembly according to the trunk structure, adapting to different car models or trunk tolerances and improving compatibility.

[0025] 3. Dynamic performance controllability:

[0026] By adjusting the initial compression of the spring by rotating the nut, the opening speed and holding force of the door can be precisely controlled. If the opening force needs to be reduced under lightweight design, or the fixation reliability needs to be enhanced under heavy load requirements, the sleeve structure of the threaded adjustment shaft, together with the sliding design of the rotating shaft waist groove, provides dynamic clearance space for the rocker arm rotating shaft when the door moves, ensuring smooth and jam-free hinge movement.

[0027] 4. Maintenance and Reliability Enhancement:

[0028] The optimized friction pair design of the bushing and gasket reduces the wear rate between the rocker arm and the shaft, reducing maintenance frequency. The bidirectional limiting structure of the pressure cap and spring seat prevents the spring from being over-compressed or relaxed, ensuring the long-term stability of the system.

[0029] This hinge system, through its innovative "axial compression + radial decoupling" design concept and modular adjustable structure, achieves precise control of door movement and ease of installation and maintenance while ensuring high reliability. It overcomes the technical bottleneck of the difficulty in compatibility between high reliability and small size in aerospace-grade hinges, and has now been successfully applied to baggage compartment systems of multiple civil aircraft, and has the technical versatility to be extended to spacecraft door mechanisms. Attached Figure Description

[0030] The above description is only an overview of the technical solution of this utility model. In order to better understand the technical means of this utility model and to implement it in accordance with the contents of the specification, the preferred embodiments of this utility model are described in detail below with reference to the accompanying drawings.

[0031] Figure 1 This is an exploded structural diagram of a civil aircraft luggage compartment hinge according to the present invention.

[0032] Figure 2 This is an opening structure diagram of a civil aircraft luggage compartment hinge according to the present invention;

[0033] Figure 3 This is a closing structure diagram of a civil aircraft luggage compartment hinge according to the present invention;

[0034] Figure 4 This is a structural diagram of a civil aircraft luggage compartment hinge without a rocker arm, according to the present invention.

[0035] Figure 5 This is a top view of the hinge structure of a civil aircraft luggage compartment according to the present invention.

[0036] Legend:

[0037] 1. Rocker arm; 2. Shaft; 3. Rocker arm shaft; 31. Connecting rod; 32. Piston rod; 33. Pressure cap; 34. Spring; 35. Spring seat; 36. Nut; 37. Cylinder; 4. Base; 5. Threaded adjusting shaft; 51. Pressure cap; 52. Screw; 53. Washer; 54. Shaft; 55. Bushing; 6. Placement platform; 7. Hinge cover; 8. Mounting hole; 9. Camshaft. Detailed Implementation

[0038] This application provides a civil aircraft luggage hinge that solves the problem of connection stability in the prior art. It uses a compression spring instead of a traditional torsion spring, so that the spring only bears the axial compression load, avoiding stress concentration caused by torsional deformation and significantly reducing the requirements for the fatigue resistance of the spring material.

[0039] Example 1

[0040] The technical solution in this application embodiment is to solve the problem of the stability of the luggage hinge connection mentioned above. The general idea is as follows:

[0041] To address the problems existing in the prior art, this utility model provides a civil aircraft luggage compartment hinge, comprising:

[0042] like Figure 1-5 As shown, there is a rocker arm 1 and a base 4. The rocker arm 1 is provided with a mounting hole 8 and a camshaft 9 below it. A threaded adjusting shaft 5 is rotatably mounted below the base 4. The threaded adjusting shaft 5 is a set of axially telescopic sleeve structures. The other end of the threaded adjusting shaft 5 is rotatably mounted in the middle of the camshaft 9. The rocker arm 1 is fixedly mounted in the middle of the upper part of the base 4 by the rocker arm rotating shaft 3 passing through the mounting hole 8.

[0043] The rocker arm shaft 3 includes a connecting rod 31, a piston rod 32, a pressure cap 33, and a cylinder 37. The tail of the cylinder 37 forms a rotating pair with the base 4. The upper end of the connecting rod 31 is hinged to the camshaft 9 of the rocker arm 1, forming a motion transmission hub. The piston rod 32 is slidably installed inside the connecting rod 31 and the cylinder 37. The piston rod 32 passes through the connecting rod 31 and the cylinder 37 to form a sliding pair. The pressure cap 33 is provided in the middle of the piston rod 32. A spring 34 is installed between the connecting rod 31 and the cylinder 37. The spring seat 35 is fixedly installed below the cylinder 37 by a nut 36. The nut 36 is sleeved around the piston rod 32. The preload is transmitted through the spring seat 35. The nut 36 and the cylinder 37 are threaded together to realize stepless adjustment of the spring preload.

[0044] A placement platform 6 is provided below the base 4. A limiting block 2 is rotatably mounted on the placement platform 6. The limiting block 2 is a limiting plate structure with one side arc-shaped and the other side straight. The rocker arm 1 is a C-shaped structure plate. The tail of the rocker arm 1 contacts the outer side of the limiting block 2. The limiting block 2 limits the rotational position of the rocker arm 1 to the open state. The limiting block 2 also limits the maximum sliding amount between the connecting rod 31 and the cylinder 37 (e.g., ...). Figure 2 As shown), the minimum sliding amount between the connecting rod 31 and the cylinder 37 is limited by the pressure cap 33 (e.g., Figure 3 (As shown).

[0045] The threaded adjusting shaft 5 includes a pressure cap 51 and a rotating shaft 54. A protruding rod is provided above the base 4. Both the pressure cap 51 and the rotating shaft 54 ​​are sleeved on the outside of the protruding rod. The mounting hole 8 is a long, narrow groove structure. A cut-edge stop is provided on the outside of the rotating shaft 54. The outer dimensions of the cut edge of the rotating shaft 54 ​​are the same as the dimensions of the groove in the mounting hole 8 for engagement. When the rocker arm rotating shaft 3 extends and retracts axially, the corresponding rotating shaft 54 ​​can slide in the mounting hole 8 to allow for the extension and retraction of the rocker arm rotating shaft 3. A bushing 55 is provided at the position where the rotating shaft 54 ​​contacts the base 4 to reduce friction loss. A screw 52 is rotatably installed in the middle of the rotating shaft 54. The pressure cap 51 is rotatably installed at the other end of the screw 52 to rotatably install the rocker arm 1 between the pressure cap 51 and the rotating shaft 54. In addition, a washer 53 is provided between the screw 52 and the rotating shaft 54 ​​to level the mounting position of the rotating shaft 54 ​​for easy installation.

[0046] The rocker arm 1 forms a four-bar linkage with the connecting rod 31 via the camshaft 9. The limit block 2 is integrated into the base 4 to set the minimum opening angle of the door.

[0047] The hinge cover 7 is fixed to the outside of the base 4 by bolts to protect the internal structure.

[0048] The workflow is as follows:

[0049] Door closing: The rocker arm 1 rotates downward around the rocker arm pivot 3, causing the connecting rod 31 and piston rod 32 to move downward, compressing the spring 34 until the door is completely closed. At this time, the pressure cover 33 abuts against the end of the cylinder 37 to ensure that the spring compression reaches the set minimum value and closes in place.

[0050] When the door opens: the spring 34 releases its elastic potential energy, pushing the piston rod 32 and the connecting rod 31 back to their original positions, driving the rocker arm 1 to rotate upwards, causing the door to open smoothly. During the opening process, the straight side of the limit block 2 contacts the tail of the rocker arm 1, limiting its maximum opening angle and preventing overshoot.

[0051] Beneficial effects:

[0052] 1. Low material requirements and long life design:

[0053] By replacing the traditional torsion spring with a compression spring 34, the spring only bears the axial compression load, avoiding stress concentration caused by torsional deformation, and significantly reducing the requirements for the fatigue resistance of the spring material. The precision sliding pair design of the piston rod 32 and the cylinder 37 ensures that the spring 34 is always compressed in a straight line, eliminating off-center wear and extending the spring life by more than 30% compared with traditional hinges.

[0054] 2. Space optimization and assembly flexibility:

[0055] The spring-loaded hinge can be installed laterally inside the side panel of the trunk, avoiding taking up space on top of the trunk and increasing the loading capacity by about 15%. The angle of the limit block 2 is adjustable through the rotating placement platform 6, allowing for fine-tuning of the minimum opening angle during assembly according to the trunk structure, adapting to different car models or trunk tolerances and improving compatibility.

[0056] 3. Dynamic performance controllability:

[0057] By adjusting the initial compression of the spring 34 by rotating the nut 36, the opening speed and holding force of the door can be precisely controlled. If the opening force needs to be reduced under lightweight design, or the fixing reliability needs to be enhanced under heavy load requirements, the sleeve structure of the threaded adjustment shaft 5, together with the waist groove sliding design of the rotating shaft 54, provides dynamic clearance space for the rocker arm rotating shaft 3 when the door moves, ensuring smooth and unhindered hinge movement.

[0058] 4. Maintenance and Reliability Enhancement:

[0059] The optimized friction pair design of bushing 55 and gasket 53 reduces the wear rate between rocker arm 1 and shaft 54, reducing maintenance frequency. The bidirectional limiting structure of pressure cap 33 and spring seat 35 prevents excessive compression or relaxation of spring 34, ensuring long-term system stability.

[0060] This hinge system, through its innovative "axial compression + radial decoupling" design concept and modular adjustable structure, achieves precise control of door movement and ease of installation and maintenance while ensuring high reliability. It overcomes the technical bottleneck of the difficulty in compatibility between high reliability and small size in aerospace-grade hinges, and has now been successfully applied to baggage compartment systems of multiple civil aircraft, and has the technical versatility to be extended to spacecraft door mechanisms.

[0061] Finally, it should be noted that the above embodiments are merely examples for clearly illustrating the present invention and are not intended to limit the implementation. Those skilled in the art can make other variations or modifications based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations. However, obvious variations or modifications derived therefrom are still within the protection scope of this invention.

Claims

1. A civil aircraft luggage bin hinge, characterized in that, Include: The rocker arm (1) is provided with mounting hole (8) and camshaft (9) below, the base (4) is rotatably mounted with threaded adjusting shaft (5) below, the threaded adjusting shaft (5) is a set of axial telescopic sleeve structure, the other end of threaded adjusting shaft (5) is rotatably installed in the middle of camshaft (9), the rocker arm (1) is fixedly installed through rocker arm pivot (3) passing through mounting hole (8) in the middle of the upper side of base (4), the rocker arm (1) forms a four-bar linkage mechanism with connecting rod (31) through camshaft (9), limit block (2) is integrated in base (4), and the minimum opening angle of the box door is set.

2. A carry-on luggage hinge for a civil aircraft according to claim 1, characterized in that, The rocker arm pivot (3) includes connecting rod (31), piston rod (32), gland (33) and cylinder barrel (37), the tail of cylinder barrel (37) forms a rotary pair with base (4), the upper end of connecting rod (31) is hinged with camshaft (9) of rocker arm (1), wherein piston rod (32) is slidably installed inside connecting rod (31) and cylinder barrel (37), and piston rod (32) penetrates connecting rod (31) and cylinder barrel (37) to form a sliding pair.

3. A carry-on luggage hinge for a civil aircraft according to claim 2, characterized in that, The middle of piston rod (32) is provided with gland (33), spring (34) is installed between connecting rod (31) and cylinder barrel (37), spring seat (35) is fixedly installed below cylinder barrel (37) through nut (36), nut (36) is sleeved on the periphery of piston rod (32), and the pre-tightening force is transmitted through spring seat (35), the nut (36) is screwed with the cylinder barrel (37).

4. A carry-on luggage hinge for a civil aircraft according to claim 3, characterized in that, The lower side of base (4) is provided with a placing table (6), and the limit block (2) is rotatably installed through the placing table (6), the limit block (2) is a limit plate structure with one side arc and one side straight plate.

5. A carry-on luggage hinge for a civil aircraft according to claim 4, characterized in that, The rocker arm (1) is a C-shaped structure plate, the tail of rocker arm (1) contacts the outer side of limit block (2), and the rotating position (open state) of rocker arm (1) is limited by limit block (2).

6. A carry-on luggage hinge for a civil aircraft according to claim 5, characterized in that, The threaded adjusting shaft (5) includes gland (51) and pivot (54), the upper side of base (4) is provided with a protruding rod, the gland (51) and the pivot (54) are both sleeved outside the protruding rod, the mounting hole (8) is a long waist groove structure, the outer side of the pivot (54) is provided with a cutting edge stopper, the outer dimension of the cutting edge of the pivot (54) is the same as the waist groove dimension of the mounting hole (8) for clamping, and the corresponding pivot (54) can slide in the mounting hole (8).

7. A carry-on luggage hinge for a civil aircraft according to claim 6, characterized in that, The side of pivot (54) contacting base (4) is provided with a bushing (55), screw (52) is rotatably installed in the middle of pivot (54), the other end of screw (52) is rotatably installed with gland (51), the rocker arm (1) is rotatably installed between the gland (51) and the pivot (54), and the spacer (53) is arranged between the screw (52) and the pivot (54), and the installation position of the pivot (54) is padded flat by the spacer (53).

8. A carry-on luggage hinge for a civil aircraft according to claim 1, characterized in that, The outer side of base (4) is fixed with hinge cover (7) by bolts.

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