An aircraft handling device based on a main landing gear strut and a main load frame

Abstract

The application belongs to the technical field of aircraft hoisting design, and particularly relates to an aircraft hoisting tool based on a main landing gear support and a main bearing frame, which comprises a hoisting frame, a top hoisting ring, a bottom front bearing crossbeam, and a bottom main landing gear connecting clamp. The hoisting frame is isosceles triangular and horizontally arranged. The top hoisting ring is above the hoisting frame and above the gravity center of the hoisting frame, and is connected to three corner parts of the hoisting frame through a diagonal cable. The bottom front bearing crossbeam is below the hoisting frame and is connected to the top corner of the hoisting frame through a front hoisting cable to bear below the main bearing front frame part of the aircraft. The bottom landing gear connecting clamp has two and is used to be clamped to two main landing gear supports of the aircraft. The two bottom landing gear connecting clamps are below the hoisting frame and are connected to the bottom edges of the hoisting frame through rear hoisting cables.

Description

Technical Field

[0001] This application belongs to the field of aircraft hoisting design technology, specifically relating to an aircraft hoisting tool based on the main landing gear strut and the main load-bearing frame. Background Technology

[0002] During field operations, shipborne aircraft may suffer structural or system damage that cannot be repaired on board, preventing them from taking off. In such cases, the aircraft needs to be lifted off the ship and transported to an onshore repair facility for maintenance.

[0003] However, currently, shipborne aircraft are often designed without considering the need to be lifted off ships. There are no dedicated lifting points or specialized lifting tools. When it is necessary to lift an aircraft off a ship, temporary tools and emergency measures are often used, which involves great uncertainty and danger. Therefore, this application is made.

[0004] This application is made in view of the aforementioned technical deficiencies. Utility Model Content

[0005] The purpose of this application is to provide an aircraft hoisting tool based on the main landing gear strut and the main load-bearing frame, so that when needed, it can be used conveniently to safely and reliably lift the aircraft off the ship quickly.

[0006] The technical solution of this application is:

[0007] An aircraft hoisting tool based on a main landing gear strut and a main load-bearing frame includes a hoisting frame, a top hoisting ring, a bottom front load-bearing crossbeam, and a bottom main landing gear connecting clamp.

[0008] The hanging frame is an isosceles triangle and is installed horizontally.

[0009] The top lifting ring is located above the lifting frame, above the center of gravity of the lifting frame, and is connected to the three corners of the lifting frame by diagonal steel cables;

[0010] The bottom front load-bearing crossbeam is located below the lifting frame and is connected to the front sling at the top corner of the lifting frame to provide support below the main load-bearing front frame of the aircraft.

[0011] There are two bottom landing gear connecting clamps, which are used to fasten the aircraft to the two main landing gear struts;

[0012] The two bottom landing gear connecting clamps are located below the lifting frame and are connected to the rear slings between the bottom edges of the lifting frame and the two ends of the lifting frame.

[0013] According to at least one embodiment of this application, in the above-mentioned aircraft hoisting tool based on the main landing gear strut and the main load-bearing frame, the hoisting frame is internally connected with longitudinal, transverse and diagonal reinforcing beams, and the longitudinal, transverse and diagonal reinforcing beams are integrally formed with the hoisting frame.

[0014] The top hanging ring is shaped like a racetrack.

[0015] According to at least one embodiment of this application, in the above-mentioned aircraft hoisting tool based on the main landing gear strut and the main load-bearing frame, two pull rings are provided below the top lifting ring, wherein one pull ring is connected to the connecting joint on the top end of the inclined steel cable at the top corner of the connecting frame, and the two pull rings are connected to the connecting joints on the top end of the inclined steel cable at the two bottom corners of the connecting frame.

[0016] Pull rings are installed above the three corners of the suspension frame, and these three pull rings are connected to the connecting joints at the bottom of the three inclined steel cables.

[0017] According to at least one embodiment of this application, in the above-mentioned aircraft hoisting tool based on the main landing gear strut and the main load-bearing frame, two pull rings are provided below the top corner of the hoisting frame, and the two pull rings are connected to the connecting joints on the top of the two front slings.

[0018] Pull rings are installed above both ends of the bottom front load-bearing crossbeam, and these two pull rings are connected to the connecting joints at the bottom of the two front slings.

[0019] According to at least one embodiment of this application, in the above-mentioned aircraft hoisting tool based on the main landing gear strut and the main load-bearing frame, the bottom ends of the two rear slings pass around from the front of the wing root of the two wings, pass through the external mounting points under the wings, connect to the two bottom landing gear connecting clamps, and are fitted with protective sleeves at the contact points with the wing roots.

[0020] According to at least one embodiment of this application, in the above-mentioned aircraft hoisting tool based on the main landing gear strut and the main load-bearing frame, pull rings are provided at both ends of the bottom edge of the hoisting frame, and the two pull rings are connected to the connecting joints at the top of the two rear slings.

[0021] Pull rings are installed above the two bottom landing gear connecting clamps, and these two pull rings are connected to the connecting joints at the bottom of the two rear slings.

[0022] According to at least one embodiment of this application, the aircraft hoisting tool based on the main landing gear strut and the main load-bearing frame described above further includes a front main load-bearing frame connecting ring.

[0023] The front main load-bearing frame connecting ring is connected above the bottom front load-bearing crossbeam, located in the middle of the bottom front load-bearing crossbeam, and is used to fit onto the front main load-bearing frame of the aircraft.

[0024] According to at least one embodiment of this application, in the above-described aircraft hoisting tool based on the main landing gear strut and the main load-bearing frame, a plurality of connectors are provided circumferentially on the front main load-bearing frame connecting ring, such as fasteners like bolts, for connecting to the aircraft's main load-bearing front frame.

[0025] This application has at least the following beneficial technical effects:

[0026] The aircraft hoisting tool based on the main landing gear strut and main load-bearing frame disclosed in the above embodiments is designed with the aircraft's main load-bearing front frame and main landing gear strut, which have high strength, as the hoisting points. It does not require special modifications to the aircraft, and the overall structure is simple and easy to use. It can also ensure the stability of the aircraft hoisting and can achieve the safe, reliable and rapid hoisting of the aircraft off the ship. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of an aircraft hoisting tool based on the main landing gear strut and main load-bearing frame provided in an embodiment of this application;

[0028] Figure 2 This is a schematic diagram of an aircraft hoisting tool based on the main landing gear strut and main load-bearing frame, provided in an embodiment of this application, for hoisting an aircraft.

[0029] in:

[0030] 1- Lifting frame; 2- Top lifting ring; 3- Bottom front load-bearing crossbeam; 4- Front main load-bearing frame connecting ring; 5- Bottom main landing gear connecting clamp; 6- Cable tie; 7- Front sling; 8- Rear sling; 9- Protective sleeve.

[0031] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual product dimensions. Furthermore, the drawings are for illustrative purposes only and should not be construed as limiting this application. Detailed Implementation

[0032] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings, and other related parts can be referred to the general design.

[0033] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms indicating direction used in this application description are used only to indicate relative direction or positional relationship; when the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "comprising" as used in this application description indicates that the element or object preceding the word encompasses the elements or objects listed following the word and their equivalents, but does not exclude other elements or objects.

[0034] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as "installation" and "connection" used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0035] An aircraft hoisting tool based on the main landing gear strut and main load-bearing frame, such as Figure 1 As shown, it includes a lifting frame 1, a top lifting ring 2, a bottom front load-bearing crossbeam 3, and a bottom main landing gear connecting clamp 5.

[0036] The hanging frame 1 is an isosceles triangle, horizontally set, and internally connected with longitudinal, transverse, and diagonal reinforcing beams, which are integrally formed with the hanging frame 1.

[0037] The top lifting ring 2 is used to connect the lifting equipment and can be designed in the shape of a racetrack.

[0038] The top lifting ring 2 is located above the lifting frame 1, above the center of gravity of the lifting frame 1, and is connected to the three corners of the lifting frame 1 by inclined steel cables 6.

[0039] Specifically, the top hanging ring 2 can be designed with two pull rings below it. One pull ring is connected to the connecting joint at the top of the inclined steel cable 6 at the top corner of the connecting frame 1, and the two pull rings are connected to the connecting joints at the top of the inclined steel cable 6 at the two bottom corners of the connecting frame 1.

[0040] Pull rings are installed above the three corners of the suspension frame 1, and these three pull rings are connected to the connecting joints at the bottom of the three inclined steel cables 6.

[0041] The bottom front load-bearing crossbeam 3 is located below the suspension frame 1 and is connected to the front suspension cable 7 at the top corner of the suspension frame 1 to provide support below the main load-bearing front frame of the aircraft.

[0042] Specifically, two pull rings can be designed below the top corner of the lifting frame 1, and these two pull rings are connected to the connecting joints at the top of the two front lifting cables 7.

[0043] Pull rings are provided above both ends of the bottom front load-bearing crossbeam 3. These two pull rings are connected to the connecting joints at the bottom of the two front slings 7, and can be detached.

[0044] A front main load-bearing frame connecting ring 4 can be further installed above the bottom front load-bearing crossbeam 3. The front main load-bearing frame connecting ring 4 is connected to the middle position of the bottom front load-bearing crossbeam 3 and is used to fit onto the main load-bearing front frame of the aircraft, such as the first main load-bearing front frame. The first main load-bearing front frame is an integral machined frame that can withstand the lifting load.

[0045] Multiple connectors, such as bolts or other fasteners, are provided circumferentially along the front main load-bearing frame connecting ring 4 to connect to the aircraft's main load-bearing front frame.

[0046] When connecting the front main load-bearing frame 4, the bottom front load-bearing crossbeam 3 and its front main load-bearing frame connecting ring 4 can be removed from the bottom of the two front slings 7, and then fitted onto the front main load-bearing frame of the aircraft. Then, the bottom front load-bearing crossbeam 3 and its front main load-bearing frame connecting ring 4 can be connected to the bottom of the two front slings 7.

[0047] There are two bottom landing gear connecting clamps 5, which are used to clamp onto the two main landing gear struts of the aircraft. The two main landing gear struts are the key load-bearing components that support the hoisting of the entire aircraft.

[0048] The two bottom landing gear connecting clamps 5 are located below the lifting frame 1 and are connected to the two ends of the bottom edge of the lifting frame 1 by the rear suspension cables 8.

[0049] The bottom ends of the two rear slings 8 pass in front of the wing roots of the aircraft, through the external mounting points under the wings, and connect to the two bottom landing gear connecting clamps 5. Protective sleeves 9 are fitted at the contact points with the wing roots.

[0050] Specifically, the bottom of the frame 1 can be designed with pull rings at both ends, and these two pull rings can be connected to the connecting joints at the top of the two rear slings 8.

[0051] Pull rings are provided above the two bottom landing gear connecting clamps 5. These two pull rings are connected to the connecting joints at the bottom of the two rear slings 8, and can be detached.

[0052] When attaching the two bottom landing gear connecting clamps 5 to the two main landing gear struts of the aircraft, the two bottom landing gear connecting clamps 5 can be removed from the bottom ends of the two rear slings 8 first, then attached to the two main landing gear struts of the aircraft, and then the two bottom landing gear connecting clamps 5 can be connected to the bottom ends of the two rear slings 8.

[0053] The aircraft hoisting tool based on the main landing gear strut and main load-bearing frame disclosed in the above embodiments can be used to lift the aircraft off the ship, and the following method can be referred to:

[0054] Connect the top lifting ring 2 to the lifting equipment, hoist the aircraft hoisting tool based on the main landing gear strut and main load-bearing frame above the aircraft, and adjust the top lifting ring 2 to be above the aircraft's center of gravity.

[0055] Attach the four front main load-bearing frame connecting rings to the front main load-bearing frame of the aircraft.

[0056] Secure the two bottom landing gear connecting clamps 5 to the two main landing gear struts of the aircraft;

[0057] The aircraft was lifted using hoisting equipment and removed from the ship, such as... Figure 2 As shown, the connecting ring 4 of the front main load-bearing frame is not shown.

[0058] The aircraft hoisting tool based on the main landing gear strut and main load-bearing frame disclosed in the above embodiments is designed with the aircraft's main load-bearing front frame and main landing gear strut, which have high strength, as the hoisting points. It does not require special modifications to the aircraft, and the overall structure is simple and easy to use. It can also ensure the stability of the aircraft hoisting and can achieve the safe, reliable and rapid hoisting of the aircraft off the ship.

[0059] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. Similar or identical parts between embodiments can be referred to mutually. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined to obtain new embodiments.

[0060] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. An aircraft hoisting tool based on the main landing gear strut and the main load-bearing frame, characterized in that, Includes a lifting frame (1), a top lifting ring (2), a bottom front load-bearing crossbeam (3), and a bottom main landing gear connecting clamp (5); The hanging frame (1) is an isosceles triangle and is set horizontally; The top lifting ring (2) is located above the lifting frame (1), above the center of gravity of the lifting frame (1), and is connected to the three corners of the lifting frame (1) by inclined steel cables (6); The bottom front load-bearing crossbeam (3) is located below the suspension frame (1) and is connected to the front sling (7) at the top corner of the suspension frame (1) to provide load support below the main load-bearing front frame of the aircraft. There are two bottom landing gear connecting clamps (5), which are used to clamp onto the two main landing gear struts of the aircraft; The two bottom landing gear connecting clamps (5) are located below the lifting frame (1) and are connected to the two ends of the bottom edge of the lifting frame (1) by the rear slings (8).

2. The aircraft hoisting tool based on the main landing gear strut and main load-bearing frame according to claim 1, characterized in that, The hanging frame (1) is internally connected with longitudinal, transverse and diagonal reinforcing beams, which are integrally formed with the hanging frame (1); The top hanging ring (2) is shaped like a racetrack.

3. The aircraft hoisting tool based on the main landing gear strut and main load-bearing frame according to claim 2, characterized in that, Two pull rings are provided below the top lifting ring (2). One pull ring is connected to the connecting joint at the top of the inclined steel cable (6) at the top corner of the connecting frame (1), and the two pull rings are connected to the connecting joints at the top of the inclined steel cable (6) at the two bottom corners of the connecting frame (1). Pull rings are provided above the three corners of the hanging frame (1), and the three pull rings are connected to the connecting joints at the bottom of the three inclined steel cables (6).

4. The aircraft hoisting tool based on the main landing gear strut and main load-bearing frame according to claim 3, characterized in that, Two pull rings are provided below the top corner of the lifting frame (1), and these two pull rings are connected to the connecting joints at the top of the two front lifting cables (7); Pull rings are provided above both ends of the bottom front load-bearing crossbeam (3), and these two pull rings are connected to the connecting joints at the bottom of the two front slings (7).

5. The aircraft hoisting tool based on the main landing gear strut and main load-bearing frame according to claim 4, characterized in that, The bottom ends of the two rear slings (8) go around the front of the wing root of the aircraft, pass through the external mounting points under the wing, connect to the two bottom landing gear connecting clamps (5), and are fitted with protective sleeves (9) at the contact points with the wing root.

6. The aircraft hoisting tool based on the main landing gear strut and main load-bearing frame according to claim 5, characterized in that, Pull rings are provided at both ends of the bottom edge of the lifting frame (1), and these two pull rings are connected to the connecting joints at the top of the two rear lifting cables (8); Pull rings are provided above the two bottom landing gear connecting clamps (5), and the two pull rings are connected to the connecting joints at the bottom of the two rear slings (8).

7. The aircraft hoisting tool based on the main landing gear strut and main load-bearing frame according to claim 6, characterized in that, It also includes the front main load-bearing frame connecting ring (4); The front main load-bearing frame connecting ring (4) is connected above the bottom front load-bearing crossbeam (3) and is located in the middle of the bottom front load-bearing crossbeam (3) to be fitted onto the front main load-bearing frame of the aircraft.

8. The aircraft hoisting tool based on the main landing gear strut and main load-bearing frame according to claim 7, characterized in that, Multiple connectors, such as bolts or other fasteners, are provided along the circumferential direction of the front main load-bearing frame connecting ring (4) to connect to the aircraft's main load-bearing front frame.

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