Aircraft limiting mechanism and storage and transportation box using same

Abstract

The invention relates to a limiting mechanism for an aircraft and a storage and transportation box using the limiting mechanism. The aircraft limiting mechanism and the storage and transportation box using the aircraft limiting mechanism are simple in structure, low in cost, capable of achieving automatic unlocking, safe, reliable and high in adaptability. The aircraft limiting mechanism comprises a limiting assembly and a telescopic assembly, the limiting assembly comprises a limiting plate, one end of the limiting plate is provided with a first rotating connecting piece rotationally connected with the limiting plate, the limiting plate is positioned through the first rotating connecting piece, and the other end of the limiting plate is provided with a limiting block; the telescopic assembly comprises a telescopic rod with the adjustable length, one end of the telescopic rod is provided with a second rotating connecting piece rotationally connected with the telescopic rod, the other end of the telescopic rod is rotationally connected with the end, provided with the limiting block, of the limiting plate, and the inclination of the limiting plate is adjusted by adjusting the length of the telescopic rod so that the aircraft can be limited.

Description

Technical Field

[0001] The present invention relates to a limiting mechanism, in particular to a limiting mechanism for an aircraft and a storage and transportation box using the same. Background Art

[0002] When unlocking a common aircraft limiting mechanism, usually two unlocking methods, manual operation unlocking or electrical control unlocking, are adopted to unlock the aircraft.

[0003] When unlocking by manual operation, due to the large volume of the storage and transportation box, the relatively high installation position of the limiting mechanism or the relatively narrow space at the installation position, it is necessary to operate in a narrow space or work at height during unlocking, which poses certain safety hazards.

[0004] When unlocking by electrical control, it is necessary to unlock through a relatively complex electrical circuit and a mechanical structure controlled by it. Since mechanical equipment such as motors and hydraulic cylinders is relatively expensive and requires regular maintenance and repair, and various mechanical failures may occur in the long-term use of the complex structure, the reliability is relatively low. Summary of the Invention

[0005] To overcome the above technical problems, the present invention provides an aircraft limiting mechanism with a simple structure, low cost, automatic unlocking, high safety and reliability, and strong adaptability, and a storage and transportation box using the same.

[0006] In one embodiment, an aircraft limiting mechanism of the present invention includes a limiting component and a telescopic component. The limiting component includes a limiting plate. One end of the limiting plate is provided with a first rotating connector rotatably connected thereto, and the limiting plate is positioned through the first rotating connector. The other end of the limiting plate is provided with a limiting block, and the head of the aircraft is limited by the limiting block. The telescopic component includes a telescopic rod whose length can be adjusted. One end of the telescopic rod is provided with a second rotating connector rotatably connected thereto, and the telescopic rod is positioned through the second rotating connector. The other end of the telescopic rod is rotatably connected to the end of the limiting plate where the limiting block is provided, and the inclination of the limiting plate is adjusted by adjusting the length of the telescopic rod to limit the aircraft.

[0007] In an aircraft limiting mechanism of the present invention, a third rotating connector is further provided on the limiting plate, and the telescopic rod is rotatably connected to the third rotating connector.

[0008] In an aircraft limiting mechanism of the present invention, the telescopic rod includes a first threaded rod, a second threaded rod and an adjusting sleeve. The two ends of the adjusting sleeve are respectively provided with internal threads with opposite rotation directions. One end of the first threaded rod is rotatably connected to the third rotating connector, and the other end of the first threaded rod is threadedly connected to one end of the adjusting sleeve. One end of the second threaded rod is rotatably connected to the second rotating connector, and the other end of the second threaded rod is threadedly connected to the other end of the adjusting sleeve.

[0009] An aircraft limiting mechanism of the present invention, wherein the first rotating connecting member, the second rotating connecting member, and the third rotating connecting member are all hinge seats.

[0010] An aircraft limiting mechanism of the present invention, wherein the limiting plate is of a U-shaped structure, and the limiting block is fixed in the U-shaped groove of the limiting plate.

[0011] An aircraft limiting mechanism of the present invention, wherein the first threaded rod and the third rotating connecting member, the second threaded rod and the second rotating connecting member, and the limiting plate and the first rotating connecting member are all rotationally connected by pin shafts.

[0012] An aircraft limiting mechanism of the present invention, wherein the outer periphery of the adjusting sleeve is provided with anti-slip threads.

[0013] In another embodiment, a storage and transportation box using the aircraft limiting mechanism, wherein an openable box door is provided on the storage and transportation box, the aircraft is installed in the storage and transportation box, and the limiting mechanism is provided on the box door.

[0014] A storage and transportation box using the aircraft limiting mechanism, wherein the first rotating connecting member and the second rotating connecting member are arranged at intervals in the vertical direction on the inner wall of the box door, the limiting block is pressed against the head of the aircraft, when the box door is opened, the limiting mechanism is separated from the aircraft, and when the box door is closed, the limiting mechanism completes the limiting of the aircraft.

[0015] The difference between the present invention and the prior art is that the present invention omits complex electrical circuits and expensive mechanical equipment, and adopts a telescopic rod with adjustable length and a limiting plate which are rotatably connected through three rotating connecting members to form a stable triangular structure. A limiting block is provided on the limiting plate, and the head of the aircraft is effectively pressed by the limiting block. When this limiting mechanism is applied to the storage and transportation box, the automatic separation and limiting of the aircraft are completed through the opening and closing of the box door. It not only has simple operation and low cost, but also improves the efficiency and convenience of aircraft loading and unloading, and has certain popularization value.

[0016] An aircraft limiting mechanism of the present invention and an automatically unlocked storage and transportation box using the same have at least the following beneficial effects:

[0017] (1) Simple structure, convenient operation, easy to install, can be quickly and accurately installed on the aircraft, with stable and reliable performance, can maintain good performance under different environmental conditions, easy for later maintenance, and is beneficial to cost saving.

[0018] (2) Through the design of the triangular stable structure, the bending moment generated by the head load of the aircraft is effectively dispersed, the shear force continuously borne by the connection between the front and rear cabin sections of the aircraft is avoided, and the safety of the aircraft is enhanced.

[0019] (3) According to different types of aircraft, not only can the inclination of the limit plate be adjusted to achieve the purpose of limiting the head of the aircraft, but also different types of telescopic rods and limit plates can be replaced to adapt to different types of aircraft, with strong adaptability.

[0020] (4) Without complex electrical circuits and expensive mechanical equipment, the automatic separation and limitation of the aircraft are completed when the control system opens and closes the box door, with simple operation and low cost, and has the significance of popularization.

[0021] The present invention will be further described below with reference to the accompanying drawings. Description of the Drawings

[0022] Figure 1 is a three-dimensional structural schematic diagram of the aircraft limiting mechanism in the present invention;

[0023] Figure 2 is a front view of the aircraft limiting mechanism in the present invention;

[0024] Figure 3 is a three-dimensional structural schematic diagram of the storage and transportation box in the present invention;

[0025] Figure 4 is a schematic diagram of the internal structure of the storage and transportation box in the present invention Figure 1 ;

[0026] Figure 5 is a schematic diagram of the internal structure of the storage and transportation box in the present invention Figure 2 .

[0027] Reference Signs:

[0028] 01 - Limit Component; 11 - Limit Plate; 12 - Limit Block; 13 - First Rotating Connector; 14 - Second Rotating Connector; 15 - Third Rotating Connector; 02 - Telescopic Component; 21 - Telescopic Rod; 22 - Adjusting Sleeve; 23 - First Threaded Rod; 24 - Second Threaded Rod; 03 - Storage and Transportation Box; 31 - Box Door; 04 - Aircraft. Detailed Embodiment

[0029] As Figure 1As shown in the figure, the aircraft limiting mechanism in the present invention includes a limiting component 01 and a telescopic component 02. The limiting component 01 includes a limiting plate 11. One end of the limiting plate 11 is provided with a first rotating connector 13 which is rotatably connected thereto, and the limiting plate 11 is positioned by the first rotating connector 13. The other end of the limiting plate 11 is provided with a limiting block 12, and the head of the aircraft 04 is limited by the limiting block 12. The telescopic component 02 includes a telescopic rod 21 whose length can be adjusted. One end of the telescopic rod 21 is provided with a second rotating connector 14 which is rotatably connected thereto, and the telescopic rod 21 is positioned by the second rotating connector 14. The other end of the telescopic rod 21 is rotatably connected to the end of the limiting plate 11 where the limiting block 12 is provided. The inclination of the limiting plate 11 is adjusted by adjusting the length of the telescopic rod 21 to limit the aircraft 04.

[0030] The limiting plate 11 is fixed on a fixed base (such as the cabin wall or the cabin chamber wall of the aircraft 04) through the first rotating connector 13 at the left end, providing a supporting force for the limiting plate 11 and allowing the limiting plate 11 to rotate up and down relative to the first rotating connector 13. The limiting plate 11 is of a U-shaped structure. The limiting block 12 is firmly fixed in the U-shaped groove of the limiting plate 11 by bolts, and the limiting block 12 is limited and fixed through the U-shaped groove to ensure that it does not move under pressure. A limiting block 12 is provided below the right end of the limiting plate 11. In view of the conical shape of the head of the aircraft 04, the limiting block 12 is designed to be an arch shape or an inverted cone shape matching it. The limiting block 12 is pressed against the head of the aircraft 04 to limit it, so that the head of the aircraft 04 will not bounce up and down, ensuring the stability of the aircraft 04.

[0031] The limiting block 12 is machined and formed from polyurethane foam material. A buffer sponge is bonded to the contact surface between the lower surface of the limiting block 12 and the head of the aircraft 04 to ensure that the surface of the head of the aircraft 04 is not damaged. A metal block with a threaded hole is embedded at the top of the limiting block 12, and the limiting block 12 and the limiting plate 11 are fixedly connected into one body by screws (the screws pass through the limiting plate and are screwed into the threaded hole of the metal block), ensuring a firm connection between the two.

[0032] The left end of the telescopic rod 21 is fixed to the same fixed base (such as the bulkhead of the aircraft 04 or the wall of the aircraft 04 cabin) through the second rotating connector 14, providing support for the telescopic rod 21 and allowing the telescopic rod 21 to rotate up and down relative to the second rotating connector 14. The left end of the telescopic rod 21 is rotatably connected to the upper surface of the limit plate 11 and can rotate relative to each other, thus forming a stable and adjustable triangular limit mechanism. This limit mechanism has many advantages. On the one hand, it ensures that the limit block 12 is always pressed against the head of the aircraft 04, eliminating the downward deviation of the head of the aircraft 04 due to its own weight and manufacturing process, with high reliability. On the other hand, for different types of aircraft 04, according to the position of the aircraft 04, the inclination of the limit plate 11 can be adjusted by adjusting the length of the telescopic rod 21, so that the limit block 12 can be adapted to the heads of different types of aircraft 04, improving the adaptability of the limit mechanism. On the other hand, the structure of this limit mechanism is simple and easy to install, without the need to additionally increase expensive mechanical equipment such as electrical circuits, motors, and hydraulic cylinders, which is convenient for cost savings.

[0033] During use, the limit plate 11 is positioned through the first rotating connector 13 according to the position of the head of the aircraft 04. The first rotating connector 13 is fixed to the fixed base by bolts, and then the left end of the limit plate 11 is connected to the first rotating connector 13, so that the limit block 12 is pressed against the head of the aircraft 04. Then, the telescopic rod 21 is positioned through the second rotating connector 14. The second rotating connector 14 is fixed above the first rotating connector 13 (i.e., on the same central axis), and there is a certain distance between the two. The specific value of this distance is not particularly limited here and can be set according to the actual situation. Finally, the length of the telescopic rod 21 is adjusted, and the left and right ends of the telescopic rod 21 are respectively installed on the limit plate 11 and the second rotating connector 14, and the limit plate 11 is fixed (i.e., the limit block 12 is fixed at a position where it is pressed against the head of the aircraft 04). It is also possible to first connect the two ends of the telescopic rod 21 to the second rotating connector 14 and the limit plate 11 respectively, and then adjust the inclination of the limit plate 11 by adjusting the length of the telescopic rod 21, so as to fix the limit block 12 at a position where it is pressed against the head of the aircraft 04. If the installation space is large enough, preferably, the limit plate 11 is arranged horizontally (i.e., the limit mechanism forms a right triangle structure) to enhance the stability of the limit mechanism for limiting the aircraft 04.

[0034] As Figure 1 、 2 As shown in the figure, a third rotating connector 15 is also provided on the limit plate 11, and the telescopic rod 21 is rotatably connected to the third rotating connector 15. The first rotating connector 13, the second rotating connector 14, and the third rotating connector 15 are all hinge seats.

[0035] All three rotating connectors adopt hinge seats. The third rotating connector 15 is fixed to the upper surface of the right end of the limit plate 11 by screws. The right end of the telescopic rod 21 is rotatably connected to the third rotating connector 15 by a pin shaft. The left end of the telescopic rod 21 is rotatably connected to the second rotating connector 14 by a pin shaft. The left end of the limit plate 11 is rotatably connected to the first rotating connector 13 by a pin shaft. The telescopic rod 21 and the limit plate 11 can rotate in the up and down directions by means of three hinge seats. By adjusting the length of the telescopic rod 21, the inclination of the limit plate 11 in the up and down directions can be adjusted to ensure that the limit block 12 is pressed against the head of the aircraft 04. Through the design of the triangular stable structure, while ensuring the rotational flexibility of the limit plate 11, it is ensured that the head of the aircraft 04 will not bounce up and down, effectively dispersing the bending moment and shear force generated by the load at the head of the aircraft 04, avoiding continuous shear force on the connection between the front and rear cabin sections of the aircraft 04, and enhancing the safety of the aircraft 04.

[0036] As Figure 1 shown, the telescopic rod 21 includes a first threaded rod 23, a second threaded rod 24, and an adjustment sleeve 22. The two ends of the adjustment sleeve 22 are respectively provided with internal threads with opposite helix directions. One end of the first threaded rod 23 is rotatably connected to the third rotating connector 15, and the other end of the first threaded rod 23 is threadedly connected to one end of the adjustment sleeve 22; one end of the second threaded rod 24 is rotatably connected to the second rotating connector 14, and the other end of the second threaded rod 24 is threadedly connected to the other end of the adjustment sleeve 22. The first threaded rod 23 and the third rotating connector 15, the second threaded rod 24 and the second rotating connector 14, and the limit plate 11 and the first rotating connector 13 are all rotatably connected by pin shafts.

[0037] Threads are provided at the left end of the first threaded rod 23 and the right end of the second threaded rod 24. The left and right ends inside the adjustment sleeve 22 are respectively provided with internal threads with opposite helix directions. The left end of the first threaded rod 23 and the right end of the second threaded rod 24 are respectively threadedly connected to the left and right ends of the adjustment sleeve 22. The right end of the first threaded rod 23 is rotatably connected to the third rotating connector 15 by a pin shaft, and the left end of the second threaded rod 24 is rotatably connected to the second rotating connector 14 by a pin shaft. By rotating the adjustment sleeve 22, the length of the telescopic rod 21 can be adjusted, thereby achieving the purpose of adjusting the inclination of the limit plate 11.

[0038] During use, the limiting mechanism is positioned according to the position of the aircraft 04 through the first rotating connector 13 and the second rotating connector 14. The adjusting sleeve 22 is rotated clockwise or counterclockwise, and the telescopic rod 21 extends or contracts. When the telescopic rod 21 extends, the limiting plate 11 rotates clockwise (i.e., rotates downward) as the telescopic rod 21 extends until the limiting block 12 is tightly pressed against the head of the aircraft 04. When the telescopic rod 21 contracts, the limiting plate 11 rotates counterclockwise (i.e., rotates upward) as the telescopic rod 21 contracts until the limiting block 12 on the limiting plate 11 is pressed against the head of the aircraft 04, ensuring that when the head of the aircraft 04 is in the pressed state, the axis of the limiting block 12 and the axis of the aircraft 04 are on the same straight line, so that the upper surface of the head of the aircraft 04 is perfectly fitted with the limiting block 12 to ensure the limiting effect.

[0039] According to different types of aircraft 04, not only can the inclination of the limiting plate 11 be adjusted to meet the purpose of limiting the head of the aircraft 04, but also different types of telescopic rods 21 and limiting plates 11 can be replaced to adapt to different types of aircraft 04, with strong adaptability. To prevent the telescopic rod 21 from automatically extending and contracting under the shaking of the aircraft 04, a locking screw or a locking part with the same effect can be set on the adjusting sleeve 22 of the telescopic rod 21. Through such a design, the telescopic rod 21 can be effectively locked to ensure that the adjusted limiting mechanism is always tightly pressed against the head of the aircraft 04, and no loosening or overpressure and other adverse conditions will occur.

[0040] The outer circumference of the adjusting sleeve 22 is provided with anti-slip lines to increase friction, which is convenient for adjusting the length of the telescopic rod 21, especially in extreme weather conditions.

[0041] This limiting mechanism has a simple structure, is easy to operate and install, and can be quickly and accurately installed on the aircraft 04; it has stable and reliable performance and can maintain good performance under different environmental conditions; it is convenient for later maintenance and is beneficial to cost savings.

[0042] As Figure 3 、 4 、shown in Figure 5, the storage and transportation box 03 in the present invention is provided with an openable box door 31. The aircraft 04 is installed in the storage and transportation box 03, and the limiting mechanism is arranged on the box door 31. The first rotating connector 13 and the second rotating connector 14 are arranged at intervals along the vertical direction on the inner wall of the box door 31, and the limiting block 12 is pressed against the head of the aircraft 04. When the box door 31 is opened, the limiting mechanism is separated from the aircraft 04, and when the box door 31 is closed, the limiting mechanism completes the limiting of the aircraft 04.

[0043] The storage and transportation box 03 is used to transport the aircraft 04. The box door 31 is arranged on the left or right side of the storage and transportation box 03, or one box door 31 is arranged on both sides, so as to facilitate the loading and unloading of the aircraft 04. When one box door 31 is arranged, the aircraft 04 is loaded into the storage and transportation box 03 with its head facing the box door 31, and the limiting mechanism is installed on the inner wall of the box door 31. When two box doors 31 are arranged, the limiting mechanism is installed on the inner wall of the box door 31 with the head of the aircraft 04 facing, and the aircraft 04 is limited by the limiting mechanism to ensure the stability of the aircraft 04 in the storage and transportation box 03.

[0044] According to the actual situation such as the position of the aircraft 04, the limiting mechanism is fixed to the inner wall of the door 31 through the first rotating connector 13 and the second rotating connector 14. First, the limiting plate 11 is positioned through the first rotating connector 13. Preferably, the limiting plate 11 and the door 31 are perpendicular to each other. When the door 31 is closed, the limiting block 12 is just pressed against the head of the aircraft 04. Then, according to the force analysis results of the aircraft 04, the telescopic rod 21 is positioned through the second rotating connector 14. The second rotating connector 14 is located above the first rotating connector 13 (that is, the two are separated by a certain distance), and the two are located on the same central axis. Then, the adjusting sleeve 22 is rotated to adjust the length of the telescopic rod 21, and the adjusted telescopic rod 21 is connected to the third rotating connector 15 and the second rotating connector 14 through a pin shaft, and finally the adjusting sleeve 22 is locked by a locking screw to ensure that the limiting mechanism limits the head of the aircraft 04 in the up and down directions, prevents the head of the aircraft 04 from jumping up and down, and ensures that the aircraft 04 is not deflected by the lateral force. Of course, the telescopic rod 21 can also be connected to the second rotating connector 14 and the third rotating connector 15 through a pin shaft first, and then the length of the telescopic rod 21 is adjusted to adjust the inclination of the limiting plate 11 until the limiting block 12 is pressed against the head of the aircraft 04.

[0045] The door 31 of the storage and transportation box 03 is opened and closed by an external control system. When the door 31 is opened, the limiting mechanism automatically disengages from the head of the aircraft 04 as the door 31 is opened. When the door 31 is fully opened, the limiting mechanism gives way to the aircraft 04 to facilitate the removal of the aircraft 04. When the door 31 is closed, the limiting mechanism automatically presses against the head of the aircraft 04 as the door 31 is closed. In this way, the automatic separation and limiting of the aircraft 04 are respectively completed when the door 31 is opened and closed, without the need for complex electrical circuits and mechanical equipment. Not only is the operation simple and the cost low, but the efficiency and convenience of loading and unloading the aircraft 04 are also improved, which has certain promotion value.

[0046] Generally speaking, the design of the storage and transportation box 03 of the aircraft 04 and its limiting mechanism, while meeting the loading and unloading requirements of the aircraft 04 and the automatic crimping and separation of the limiting mechanism, realizes an efficient, convenient and stable transportation and loading / unloading process through ingenious structural design and control methods. In practical applications, appropriate adjustments and optimizations can be made according to different types of aircraft 04 and loading / unloading requirements to better play its role.

[0047] It should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "front", "rear", "left", "right", "middle", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention.

[0048] In the description of the present invention, it should be noted that unless otherwise clearly specified and limited, the terms "connected" and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0049] The above-described embodiments are only used to describe the preferred embodiments of the present invention, and do not limit the scope of the present invention. Without departing from the design spirit of the present invention, various deformations and improvements made by those of ordinary skill in the art to the technical solutions of the present invention shall fall within the protection scope determined by the claims of the present invention.

Claims

1. An aircraft limiting mechanism, characterized in that: The telescopic assembly comprises a limit assembly and a telescopic assembly, wherein the limit assembly comprises a limit plate, a first rotating connection member rotatably connected thereto is provided at one end of the limit plate, the limit plate is positioned by means of the first rotating connection member, a limit block is provided at the other end of the limit plate, the head of the aircraft is limited by means of the limit block; the telescopic assembly comprises a telescopic rod with adjustable length, a second rotating connection member rotatably connected thereto is provided at one end of the telescopic rod, the telescopic rod is positioned by means of the second rotating connection member, the other end of the telescopic rod is rotatably connected to one end of the limit plate provided with the limit block, the inclination of the limit plate is adjusted by adjusting the length of the telescopic rod to limit the aircraft.

2. The aircraft limiting mechanism according to claim 1, characterized in that: The limiting plate is also provided with a third rotating connecting piece, and the telescopic rod is rotatably connected to the third rotating connecting piece.

3. The aircraft limiting mechanism according to claim 2, characterized in that: The telescopic rod comprises a first threaded rod, a second threaded rod and an adjusting sleeve, and both ends of the adjusting sleeve are respectively provided with internal threads with opposite rotation directions, one end of the first threaded rod is rotatably connected to the third rotating connecting piece, and the other end of the first threaded rod is threadedly connected to one end of the adjusting sleeve; one end of the second threaded rod is rotatably connected to the second rotating connecting piece, and the other end of the second threaded rod is threadedly connected to the other end of the adjusting sleeve.

4. The aircraft limiting mechanism according to claim 3, characterized in that: The first rotating connection member, the second rotating connection member and the third rotating connection member are all hinged seats.

5. The aircraft limiting mechanism according to claim 4, characterized in that: The limiting plate is a U-shaped structure, and the limiting block is fixed in the U-shaped groove of the limiting plate.

6. The aircraft limiting mechanism according to claim 5, characterized in that: The first threaded rod and the third rotating connecting member, the second threaded rod and the second rotating connecting member, and the limiting plate and the first rotating connecting member are all rotationally connected via a pin shaft.

7. The aircraft limiting mechanism according to claim 6, characterized in that: The outer periphery of the adjusting sleeve is provided with anti-slip grooves.

8. A storage and transportation box using the aircraft limiting mechanism according to any one of claims 1 to 7, characterized in that: The storage and transportation box is provided with an openable and closable box door, the aircraft is installed in the storage and transportation box, and the limiting mechanism is arranged on the box door.

9. The storage and transportation box according to claim 8, characterized in that: The first rotating connecting member and the second rotating connecting member are arranged on the inner wall of the door at intervals in the vertical direction, and the limit block is pressed on the head of the aircraft. When the door is opened, the limit mechanism is separated from the aircraft, and when the door is closed, the limit mechanism completes the limit of the aircraft.

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