Full-machine lifting sling based on bearing of main force bearing frame and method of full-machine lifting sling

Abstract

The invention belongs to the technical field of aircraft lifting design, and particularly relates to a full-aircraft lifting sling based on bearing of a main force bearing frame and a method thereof.The full-aircraft lifting sling based on bearing of the main force bearing frame comprises a lifting frame, a top lifting ring, a bottom front sling and a bottom rear bracket; the hanging frame is in an isosceles triangle shape and is horizontally arranged. The top lifting ring is connected with lifting equipment; the top lifting ring is positioned above the lifting frame, is positioned above the gravity center of the lifting frame, and is connected with three corner parts of the lifting frame through cable-stayed steel cables; the two ends of the bottom front sling are connected below the vertex angle part of the lifting frame and used for sleeving the main force-bearing front frame part of the airplane; the bottom rear bracket is used for supporting the bottom of a main force-bearing rear frame part of the airplane, and a rubber plate is laid on the bottom rear bracket; the bottom rear bracket is located below the hanging frame and below the bottom edge of the hanging frame, and the two ends are connected with the two ends of the bottom edge of the hanging frame through vertical steel cables.

Description

Technical Field

[0001] This application belongs to the technical field of aircraft hoisting design, and particularly relates to a full-aircraft hoisting sling based on the main load-bearing frame and its method. Background Art

[0002] During the outfield use of shipborne aircraft, structural or system damage may occur, and repairs cannot be completed on the ship, resulting in the inability to fly away from the ship. At this time, it is necessary to lift the aircraft off the ship and transport it to an onshore repair factory for repair.

[0003] However, currently, shipborne aircraft often lack consideration for the problems of lifting off the ship during design, do not design dedicated lifting points, and lack dedicated lifting tools. When it is necessary to lift the aircraft off the ship, temporary tools and temporary emergency measures are mostly used to lift the aircraft off the ship, which has great uncertainty and danger. In view of this, this application is proposed.

[0004] This application is proposed in view of the existence of the above technical defects. Summary of the Invention

[0005] The purpose of this application is to provide a full-aircraft hoisting sling based on the main load-bearing frame and its method, so as to be conveniently used when needed and quickly lift the aircraft off the ship safely and reliably.

[0006] The technical solution of this application is as follows:

[0007] On the one hand, a full-aircraft hoisting sling based on the main load-bearing frame is provided, including a sling frame, a top sling ring, a front bottom sling, and a rear bottom bracket;

[0008] The sling frame is in the shape of an isosceles triangle and is horizontally arranged;

[0009] The top sling ring is used to connect the lifting equipment;

[0010] The top sling ring is above the sling frame, above the center of gravity of the sling frame, and is connected to the three corner parts of the sling frame by diagonal steel cables;

[0011] Both ends of the front bottom sling are connected below the top corner parts of the sling frame and are used to be sleeved on the front part of the main load-bearing frame of the aircraft;

[0012] The rear bottom bracket is used to support the bottom of the rear part of the main load-bearing frame of the aircraft, and a rubber plate is laid on it;

[0013] The rear bottom bracket is below the sling frame, below the bottom edge of the sling frame, and both ends are connected to both ends of the bottom edge of the sling frame by vertical steel cables.

[0014] According to at least one embodiment of the present application, in the above-mentioned full-aircraft hoisting sling based on the main load-bearing frame, longitudinal strengthening beams are connected between the inner top corners and the bottom sides of the sling frame, and multiple transverse strengthening beams are connected between the two side edges. The longitudinal strengthening beams and each transverse strengthening beam intersect at right angles, and the longitudinal strengthening beams and each transverse strengthening beam are integrally formed with the sling frame;

[0015] The top sling ring is in a runway shape.

[0016] According to at least one embodiment of the present application, in the above-mentioned full-aircraft hoisting sling based on the main load-bearing frame, two sling rings are hung below the top sling ring. Among them, one sling ring is connected to the connection joint at the top of the diagonal stay cable at the corner part of the connection sling frame, and the two sling rings are connected to the connection joints at the top of the diagonal stay cables at the two bottom corner parts of the connection sling frame;

[0017] Above the three corner parts of the sling frame, upper sling rings are provided, and the three upper sling rings are connected to the connection joints at the bottom ends of the three diagonal stay cables.

[0018] According to at least one embodiment of the present application, in the above-mentioned full-aircraft hoisting sling based on the main load-bearing frame, a bottom front sling ring is provided below the corner part of the sling frame, and the bottom front sling ring is connected to the connection joints at both ends of the bottom front sling.

[0019] According to at least one embodiment of the present application, in the above-mentioned full-aircraft hoisting sling based on the main load-bearing frame, there are multiple bottom front slings, which are wound around each other and wrapped with a sling.

[0020] According to at least one embodiment of the present application, in the above-mentioned full-aircraft hoisting sling based on the main load-bearing frame, bottom rear sling rings are provided below both ends of the bottom side of the sling frame, and the two bottom rear sling rings are connected to the connection joints at the top ends of the two vertical stay cables;

[0021] Upper sling rings are provided above both ends of the bottom rear bracket, and the two upper sling rings are connected to the connection joints at the bottom ends of the two vertical stay cables, and are detachable therebetween.

[0022] On the other hand, a hoisting method based on the above-mentioned full-aircraft hoisting sling based on the main load-bearing frame is provided for hoisting an aircraft off a ship, including:

[0023] Connect the top sling ring to the hoisting equipment, hang the full-aircraft hoisting sling based on the main load-bearing frame above the aircraft, and adjust the top sling ring to be above the center of gravity of the aircraft;

[0024] Put the bottom front sling over the front part of the main load-bearing frame of the aircraft;

[0025] Place the bottom rear bracket under the bottom of the rear part of the main load-bearing frame of the aircraft;

[0026] Use a lifting device to lift the aircraft and lift it off the ship.

[0027] The present application has at least the following beneficial technical effects:

[0028] Provide a whole-aircraft lifting sling based on the load-bearing of the wing root. Design with the main load-bearing front frame and rear frame parts of the aircraft with high strength as the lifting points, without the need for special modification of the aircraft, and the overall structure is simple, facilitating application, and can ensure the stability of lifting the aircraft, and can realize the safe and reliable rapid lifting of the aircraft off the ship. Description of the Drawings

[0029] Figure 1 is a schematic diagram of the whole-aircraft lifting sling based on the load-bearing of the main load-bearing frame provided by the embodiment of the present application;

[0030] Figure 2 is a schematic diagram of lifting the aircraft with the whole-aircraft lifting sling based on the load-bearing of the main load-bearing frame provided by the embodiment of the present application;

[0031] Among them:

[0032] 1 - lifting frame; 2 - top lifting ring; 3 - front bottom sling; 4 - rear bottom bracket; 5 - pull ring; 6 - upper lifting ring; 7 - front bottom lifting ring; 8 - vertical pulling steel cable; 9 - rear bottom lifting ring; 10 - upper lifting ring; 11 - diagonal pulling steel cable.

[0033] For better illustration of this embodiment, some contents of the drawings will be omitted, enlarged or reduced, and are only used for exemplary illustration and cannot be construed as a limitation to the present application. Detailed Embodiments

[0034] To make the technical solutions and their advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in detail below with reference to the drawings. It can be understood that the specific embodiments described herein are only part of the embodiments of the present application, which are only used to explain the present application and are not a limitation to the present application. It should be noted that for the convenience of description, only the parts related to the present application are shown in the drawings, and other related parts can refer to the general design.

[0035] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of the present application should be the ordinary meanings understood by those of ordinary skill in the art to which the present application belongs. The "including" used in the description of the present application means that the concept appearing before this word covers the concepts listed after this word and their equivalents, without excluding other related concepts.

[0036] In addition, the terms indicating directions used in the description of this application are only used to represent relative directions or positional relationships. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. It should also be noted that unless otherwise clearly specified and limited, terms such as "installation" and "connection" used in the description of this application should be understood in a broad sense. For example, 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 situation.

[0037] A full-aircraft hoisting sling based on the load-bearing of the main load-bearing frame, as Figure 1 shown, includes a hoisting frame 1, a top lifting ring 2, a front bottom sling 3, and a rear bottom bracket 4.

[0038] The hoisting frame 1 is in the shape of an isosceles triangle and is horizontally arranged. There is a longitudinal strengthening beam connected between the inner top angle and the bottom edge, and multiple transverse strengthening beams are connected between the two side edges. The longitudinal strengthening beam and each transverse strengthening beam cross each other, and the longitudinal strengthening beam and each transverse strengthening beam are integrally formed with the hoisting frame 1.

[0039] The top lifting ring 2 is used to connect the hoisting equipment and can be designed in a runway shape.

[0040] The top lifting ring 2 is located above the hoisting frame 1 and above the center of gravity of the hoisting frame 1, and is connected to the three corner parts of the hoisting frame 1 by diagonal steel cables 11.

[0041] Specifically, two pulling rings 5 can be designed to be hung below the top lifting ring 2. Among them, one pulling ring 5 is connected to the connection joint at the top of the diagonal steel cable 11 at the top corner part of the hoisting frame 1, and the two pulling rings 5 are connected to the connection joints at the top of the diagonal steel cables 11 at the two bottom corner parts of the hoisting frame 1.

[0042] Above the three corner parts of the hoisting frame 1, upper lifting rings 6 are provided, and the three upper lifting rings 6 are connected to the connection joints at the bottom ends of the three diagonal steel cables 11.

[0043] Both ends of the front bottom sling 3 are connected below the top corner parts of the hoisting frame 1 and are used to be sleeved on the front part of the main load-bearing frame of the aircraft, for example, it can be the fourth front main load-bearing frame part.

[0044] Specifically, a front bottom lifting ring 7 can be designed to be provided below the top corner parts of the hoisting frame 1, and the front bottom lifting ring 7 is connected to the connection joints at both ends of the front bottom sling 3.

[0045] To ensure the load-bearing capacity of the front bottom sling 3, multiple front bottom slings 3 can be designed, which are wound around each other and wrapped with a sling to prevent the front bottom sling 3 from directly contacting the main load-bearing front frame part of the aircraft and causing damage to the main load-bearing front frame part of the aircraft.

[0046] The rear bottom bracket 4 is used to support the bottom of the main load-bearing rear frame part of the aircraft. For example, it can be at the 38th main load-bearing front frame part. Its shape is designed to fit the bottom of the main load-bearing rear frame part of the aircraft. For an aircraft with two engines installed at the rear, two positioning ports can be provided on the rear bottom bracket 4 to be stuck under the two engine parts, and a rubber plate can be laid on it to prevent the rear bottom bracket 4 from directly contacting the main load-bearing rear frame part of the aircraft and causing damage to the main load-bearing rear frame part of the aircraft.

[0047] The rear bottom bracket 4 is located below the lifting frame 1, under the bottom edge of the lifting frame 1, and is connected to both ends of the bottom edge of the lifting frame 1 by vertical tension cables 8.

[0048] Specifically, it can be designed that there are rear bottom lifting rings 9 below both ends of the bottom edge of the lifting frame 1, and the two rear bottom lifting rings 9 are connected to the connection joints at the top ends of the two vertical tension cables 8.

[0049] There are upper lifting rings 10 above both ends of the rear bottom bracket 4, and the two upper lifting rings 10 are connected to the connection joints at the bottom ends of the two vertical tension cables 8, and they are detachable therebetween.

[0050] For the full-aircraft lifting sling based on the main load-bearing frame load disclosed in the above embodiments, to lift the aircraft off the ship, the following method can be referred to:

[0051] Connect the top lifting ring 2 to the lifting equipment, hang the full-aircraft lifting sling based on the main load-bearing frame load above the aircraft, and adjust the top lifting ring 2 above the center of gravity of the aircraft;

[0052] Put the front bottom sling 3 around the main load-bearing front frame part of the aircraft;

[0053] Put the rear bottom bracket 4 under the bottom of the main load-bearing rear frame part of the aircraft;

[0054] Use the lifting equipment to lift the aircraft and lift the aircraft off the ship, as Figure 2 shown.

[0055] The full-aircraft lifting sling based on the wing root load disclosed in the above embodiments is designed with the main load-bearing front frame and rear frame parts of the aircraft with relatively high strength as the lifting points, does not require special modification of the aircraft, has a simple overall structure, is convenient for application, and can ensure the stability of lifting the aircraft, and can realize quickly and safely lifting the aircraft off the ship.

[0056] So far, the technical solutions of the present application have been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle of the present 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 fall within the protection scope of the present application.

Claims

1. An all-aircraft lifting sling based on the load-bearing of the main load-bearing frame, characterized in that, It includes a hanging frame (1), a top hanging ring (2), a front bottom sling (3), and a rear bottom bracket (4); The hanging frame (1) is an isosceles triangle and is horizontally arranged; The top hanging ring (2) is used to connect the lifting equipment; The top hanging ring (2) is located above the hanging frame (1) and above the center of gravity of the hanging frame (1), and is connected to the three corner parts of the hanging frame (1) by diagonal steel cables (11); Both ends of the front bottom sling (3) are connected below the top corner parts of the hanging frame (1) and are used to be sleeved on the front part of the main load-bearing frame of the aircraft; The rear bottom bracket (4) is used to support the bottom of the rear part of the main load-bearing frame of the aircraft, and a rubber plate is laid on it; The rear bottom bracket (4) is located below the hanging frame (1) and below the bottom edge of the hanging frame (1), and both ends are connected to both ends of the bottom edge of the hanging frame (1) by vertical steel cables (8).

2. The full-aircraft lifting sling based on the main load-bearing frame as claimed in claim 1, characterized in that Longitudinal strengthening beams are connected between the top corners and the bottom edge inside the hanging frame (1), and multiple transverse strengthening beams are connected between the two side edges. The longitudinal strengthening beams and each transverse strengthening beam intersect at right angles, and the longitudinal strengthening beams and each transverse strengthening beam are integrally formed with the hanging frame (1); The top hanging ring (2) is in a runway shape.

3. The full-aircraft lifting sling based on the main load-bearing frame as claimed in claim 2, characterized in that Two pull rings (5) are hung below the top hanging ring (2). Among them, one pull ring (5) is connected to the connection joint at the top of the diagonal steel cable (11) connecting the top corner part of the hanging frame (1), and the two pull rings (5) are connected to the connection joints at the top of the diagonal steel cables (11) connecting the two bottom corner parts of the hanging frame (1); Above the three corner parts of the hanging frame (1), upper hanging rings (6) are provided, and the three upper hanging rings (6) are connected to the connection joints at the bottom ends of the three diagonal steel cables (11).

4. The full-aircraft lifting sling based on the main load-bearing frame as claimed in claim 3, characterized in that Below the top corner part of the hanging frame (1), a front bottom hanging ring (7) is provided, and the front bottom hanging ring (7) is connected to the connection joints at both ends of the front bottom sling (3).

5. The full-aircraft lifting sling based on the main load-bearing frame as claimed in claim 4, characterized in that There are multiple front bottom slings (3), which are wound around each other and are wrapped with a sling.

6. The full-aircraft lifting sling based on the main load-bearing frame as claimed in claim 5, characterized in that Below both ends of the bottom edge of the hanging frame (1), rear bottom hanging rings (9) are provided, and the two rear bottom hanging rings (9) are connected to the connection joints at the top ends of the two vertical steel cables (8); Above both ends of the rear bottom bracket (4), upper hanging rings (10) are provided, and the two upper hanging rings (10) are connected to the connection joints at the bottom ends of the two vertical steel cables (8), and they are detachable therebetween.

7. A lifting method for the full-aircraft lifting sling based on the main load-bearing frame as claimed in claim 6, used to lift an aircraft off a ship, characterized in that, It includes: Connect the top hanging ring (1) to the lifting equipment, hang the full-aircraft lifting sling based on the main load-bearing frame above the aircraft, and adjust the top hanging ring (2) to be above the center of gravity of the aircraft; Sleeve the front bottom sling (3) on the front part of the main load-bearing frame of the aircraft; support the rear bottom bracket (4) under the bottom of the rear part of the main load-bearing frame of the aircraft; Use a lifting device to lift the aircraft and hoist it off the ship.

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