Combined lifting appliance for airplane

Abstract

The utility model discloses a combined lifting appliance for an airplane, which relates to the technical field of airplane assembly and comprises a cross beam, two longitudinal beams which are horizontally arranged in parallel at an interval, two first hanging cables which are connected between the cross beam and the two longitudinal beams, and second hanging cables which are connected to the bottoms of the two ends of the two longitudinal beams, the two longitudinal beams are perpendicularly located under the two ends of the cross beam respectively. The cross beam comprises a first lifting plate, a first lifting beam integrally and symmetrically connected to the lower surface of the first lifting plate and two first lifting buckles, and the two first lifting buckles are symmetrically connected to the lower surface of the first lifting beam; the longitudinal beam comprises a second lifting plate, a second lifting beam integrally and symmetrically connected to the lower surface of the second lifting plate and two second lifting buckles, and the two second lifting buckles are symmetrically connected to the lower surface of the second lifting beam. The lifting appliance adopts a two-layer design and can avoid wings at the upper part of an airplane, and the longitudinal beams are arranged below the wings, so that possible damage to an airplane skin is avoided.

Description

Technical Field

[0001] The utility model relates to the technical field of lifting equipment, in particular to an aircraft combined lifting device. Background Art

[0002] The skid-type landing gear is a type of landing gear commonly used by small aircraft and drones. The part that bears the weight of the aircraft is also the location that can be used as a lifting point.

[0003] Chinese utility model patent publication number CN216272665U describes a sling that is mounted on a mounting plate with a mounting opening. The sling includes a mounting assembly and a lifting assembly. The mounting assembly can pass through the mounting opening and abut against the inner wall of the mounting plate, and the mounting assembly has a clearance opening that allows parts to pass through the mounting opening. The lifting assembly is mounted on the mounting assembly and can lift the part to be lifted. This sling can be installed in confined spaces without the need for support and fixation by a supporting device, and can also avoid parts passing through the mounting opening.

[0004] However, the above technical solution adopts a two-claw lifting method, and its oblique lifting rope will squeeze the upper fuselage, which may cause damage to the aircraft skin. Utility Model Content

[0005] In view of this, the main purpose of the present invention is to provide an aircraft combination sling to solve the technical problem that existing aircraft slings easily cause damage to the aircraft upper body skin.

[0006] To achieve the above-mentioned object, the present invention provides an aircraft combined sling, comprising a crossbeam, two horizontally parallel longitudinal beams spaced apart, two first hanging cables connected between the crossbeam and the two longitudinal beams, and second hanging cables connected to the bottoms of both ends of the two longitudinal beams, wherein the two longitudinal beams are respectively located vertically directly below the ends of the crossbeam;

[0007] The crossbeam includes a first hanging plate, a first hanging beam integrally and symmetrically connected to the lower surface of the first hanging plate, and two first hanging buckles, and the two first hanging buckles are symmetrically connected to the lower surface of the first hanging beam;

[0008] The longitudinal beam includes a second hanging plate, a second hanging beam integrally and symmetrically connected to the lower surface of the second hanging plate, and two second hanging buckles, and the two second hanging buckles are symmetrically connected to the lower surface of the second hanging beam.

[0009] Optionally, a first hanging hole is provided at the center of the first hanging plate, and a plurality of evenly distributed third hanging holes are provided at the center of the second hanging plate.

[0010] Optionally, the first suspension beam and the second suspension beam are both steel pipe structures with square hollow cross-sections.

[0011] Optionally, a plurality of evenly distributed second hanging holes are opened at the center of the surface of the first hanging buckle, and a plurality of evenly distributed fourth hanging holes are opened at the center of the surface of the second hanging buckle.

[0012] Optionally, the first hanging rope and the second hanging rope are any one of a steel rope and a soft rope with a hook.

[0013] Optionally, the soft rope with hook is a synthetic fiber lifting belt structure.

[0014] Optionally, the length of the cross beam is smaller than the length of the longitudinal beam.

[0015] Optionally, the length of the first hanging rope is greater than the length of the second hanging rope.

[0016] Optionally, the length of the first hanging buckle is greater than the length of the second hanging buckle.

[0017] Compared with the prior art, the beneficial effects of the present invention are:

[0018] In the technical solution of the present invention, the aircraft combination sling includes a crossbeam, two first hanging cables, two longitudinal beams and a second hanging cable, wherein the crossbeam is used to provide a stable support structure so that the sling remains stable during the lifting process; the two longitudinal beams are arranged horizontally and parallel at intervals, and are arranged across the two sides of the skid-type landing gear device, and are spaced a certain distance from the skid-type landing gear device; the use of the first hanging cable and the second hanging cable increases the overall rigidity and torsion resistance of the sling through different connection methods; the two longitudinal beams and the two first hanging cables are symmetrically installed and connected about the vertical center axis of the crossbeam, ensuring the balance of the sling when subjected to force, reducing structural deformation or damage caused by asymmetric force, and allowing the sling to evenly distribute the weight when lifting the aircraft, reducing the pressure on a single connection point. Therefore, through reasonable structural design and material selection, the safety of the sling during the lifting process can be ensured, reducing the risk of accidents caused by structural failure, or damage to the aircraft skin caused by contact and compression between the hanging cables and the fuselage. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying any creative work.

[0020] Figure 1 Schematic diagram of the three-dimensional structure of the aircraft combined sling provided in the embodiment of the utility model Figure 3

[0021] Figure 2 A schematic diagram of the main structure of an aircraft combined sling provided by an embodiment of the utility model;

[0022] Figure 3 A schematic diagram of the top view of the aircraft combined sling provided by an embodiment of the utility model;

[0023] Figure 4 The present invention is a schematic side structural diagram of an aircraft combined sling provided in an embodiment of the present invention.

[0024] Description of Figure Numbers:

[0025] 1- beam;

[0026] 11-first hanging plate; 111-first hanging hole; 12-first hanging beam; 13-first hanging buckle; 131-second hanging hole;

[0027] 2-First lanyard;

[0028] 3-longitudinal beam;

[0029] 31-second hanging plate; 311-third hanging hole; 32-second hanging beam; 33-second hanging buckle; 331-fourth hanging hole;

[0030] 4- Second lanyard. DETAILED DESCRIPTION

[0031] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0032] It should be noted that if the embodiments of the present invention involve directional indications (such as up, down, left, right, front, back, etc.), such directional indications are only used to explain the relative position relationship, movement status, etc. between the various components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0033] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the present invention, the descriptions of "first", "second", etc. are only for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features specified as "first" or "second" may explicitly or implicitly include at least one of such features. In addition, the technical solutions between the various embodiments can be combined with each other, but this must be based on the fact that ordinary technicians in this field can implement them. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such a combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0034] See also Figure 1-4 As shown, an embodiment of the present invention provides an aircraft combined sling, which includes a crossbeam 1, two first hanging cables 2, two longitudinal beams 3 and a second hanging cable 4, wherein:

[0035] The two longitudinal beams 3 are arranged horizontally and parallelly at intervals. The two first hanging ropes 2 are used to connect between the cross beam 1 and the two longitudinal beams 3. The second hanging rope 4 is connected to the bottom of both ends of the two longitudinal beams 3. The two longitudinal beams 3 are vertically located directly below the two ends of the cross beam 1.

[0036] The crossbeam 1 includes a first hanging plate 11 , a first hanging beam 12 and a first hanging buckle 13 . The first hanging beam 12 is integrally and symmetrically connected to the lower surface of the first hanging plate 11 , and two first hanging buckles 13 are symmetrically connected to the lower surface of the first hanging beam 12 .

[0037] The longitudinal beam 3 includes a second hanging plate 31 , a second hanging beam 32 and two second hanging buckles 33 . The second hanging beam 32 is integrally and symmetrically connected to the lower surface of the second hanging plate 31 , and the two second hanging buckles 33 are symmetrically connected to the lower surface of the second hanging beam 32 .

[0038] Specifically in the embodiment of the present invention, the crossbeam 1 is used to provide a stable support structure so that the sling remains stable during the lifting process; the two longitudinal beams 3 are arranged horizontally and parallel to each other, and are arranged across the two sides of the skid-type landing gear device, and are separated by a certain distance from the skid-type landing gear device; the use of the first hanging rope 2 and the second hanging rope 4 increases the overall rigidity and torsion resistance of the sling through different connection methods.

[0039] The two longitudinal beams 3 and the two first slings 2 are symmetrically mounted and connected about the vertical center axis of the crossbeam 1, ensuring balanced loads on the spreader and reducing structural deformation or damage caused by asymmetric loads. Furthermore, this arrangement allows the spreader to evenly distribute the weight of the aircraft being hoisted, reducing stress on individual connection points.

[0040] It should be noted that the spreader can be adapted to different types of skid-type landing gear devices (such as aircraft, etc.) because the main components of the spreader (crossbeam, longitudinal beam, hanging rope) can be adjusted in length and position as needed.

[0041] Therefore, through reasonable structural design and material selection, the safety of the sling during the lifting process can be ensured, reducing the risk of accidents caused by structural failure, or damage to the aircraft skin caused by contact and extrusion between the hanging cable and the fuselage.

[0042] For further information, see Figure 1 、 2 As shown in FIG. 4 , a first hanging hole 111 is opened at the center of the first hanging plate 11 , and a plurality of evenly distributed third hanging holes 311 are opened at the center of the second hanging plate 31 .

[0043] Specifically, the first lifting hole 111 is located at the center of the first lifting plate 11 and is mainly used to connect the lifting equipment on the crane to ensure that the lifting equipment can effectively concentrate the force during the lifting process and enhance the stability of the lifting.

[0044] The third lifting hole 311 is located at the center of the second lifting plate 31. In this embodiment, preferably, a plurality of third lifting holes 311 are provided, allowing for flexible adjustment based on the lifting object and the operating environment. For example, different lifting holes can be selected for connection based on the center of gravity of the object, thereby optimizing the balance of the lifting operation. This allows for a variety of lifting methods to accommodate different lifting requirements. Furthermore, the uniform distribution of the third lifting holes 311 allows for a more even distribution of force to multiple points during the lifting process, reducing the risk of excessive force at a single point and the possibility of structural damage.

[0045] For further information, see Figure 1 As shown, the first suspension beam 12 and the second suspension beam 32 are both steel pipe structures with square hollow cross-sections.

[0046] As a result, the hollow steel tube structure can reduce material usage while maintaining strength, thereby reducing the weight of the overall spreader. This design is more economical in material use while maintaining sufficient structural strength.

[0047] For further information, see Figure 2 、 4 As shown, a plurality of evenly spaced second hanging holes 131 are formed in the center of the surface of the first hanging buckle 13, and a plurality of evenly spaced fourth hanging holes 331 are formed in the center of the surface of the second hanging buckle 33. The even distribution of the second hanging holes 131 and the fourth hanging holes 331 allows the hanging buckle to more evenly distribute the force when subjected to stress, reducing local stress concentration, thereby improving the durability and reliability of the hanging buckle and enhancing its structural strength.

[0048] In addition, the evenly distributed hanging holes can reduce stress concentration, thereby improving the fatigue resistance of the hanging buckle, so that the first hanging buckle 13 and the second hanging buckle 33 can maintain their performance under long-term repeated loading and reduce the risk of fatigue failure.

[0049] In summary, the lifting hole design of the first hanging plate 11 and the second hanging plate 31 further optimizes the performance of the aircraft combination lifting equipment by enhancing force uniformity, improving flexibility and adaptability, and improving safety and ease of operation, thereby ensuring the efficiency and safety of lifting operations.

[0050] Furthermore, as a preferred embodiment of the present invention, the first hanging rope 2 and the second hanging rope 4 are both any one of a steel rope and a soft rope with a hook.

[0051] Among them, steel cables usually require less maintenance and have a longer service life due to their material properties.

[0052] The flexible hooked rope, due to its flexibility, can be used more easily in complex lifting environments, especially when navigating obstacles or operating in confined spaces. It offers greater flexibility and adaptability, especially when bending or tackling irregularly shaped loads. The hook design allows for easy securing and release, making it suitable for a variety of lifting operations. Made of high-strength alloy steel, it offers excellent wear and high-temperature resistance. It provides stable lifting support and a high safety factor, ensuring safe operation.

[0053] Preferably, the hook and cord are constructed from synthetic fiber slings. These slings are primarily made from high-strength synthetic fibers such as nylon, polyester, and polypropylene. These materials provide the slings with exceptional strength and durability, enabling them to maintain stable performance in a variety of harsh environments.

[0054] Therefore, the synthetic fiber lifting belt structure provides high safety and efficiency in lifting operations due to its high strength, lightness, corrosion resistance, and aging resistance, while reducing the risk of damage to the lifted object. It is an ideal lifting tool.

[0055] For further information, see Figure 1 As shown, the length of the crossbeam 1 is shorter than that of the longitudinal beam 3. Through mechanical optimization, spatial adaptability, center of gravity adjustment, structural stability, operational convenience, safety considerations, versatility, and aesthetics, the overall performance of the spreader is improved, ensuring the efficiency and safety of lifting operations.

[0056] For further information, see Figure 2 、 4As shown, the length of the first hanging rope 2 is greater than that of the second hanging rope 4. By using hanging ropes of different lengths, the force during the lifting process can be better distributed. The longer first hanging rope 2 may bear the main lifting weight, while the shorter second hanging rope 4 may be used to assist in lifting or stabilize the load.

[0057] For further information, see Figure 2 、 4 As shown, the length of the first hanging buckle 13 is greater than the length of the second hanging buckle 33 .

[0058] Since different lengths of slings can adapt to different stress conditions and structural requirements, a more optimized tensioning plan can be formulated by using slings of different lengths. For example, the longer first sling 13 is used to bear greater forces or provide more mechanical stability, while the shorter second sling 33 may be used for auxiliary or smaller stress points.

[0059] The above description is only a preferred embodiment of the present invention and does not limit the patent scope of the present invention. All equivalent structural transformations made by using the contents of the present invention specification and drawings under the utility model concept, or direct / indirect application in other related technical fields are included in the patent protection scope of the present invention.

Claims

1. An aircraft combination sling, characterized in that: It comprises a crossbeam (1), two horizontally parallel longitudinal beams (3) spaced apart, two first hanging ropes (2) for connecting between the crossbeam (1) and the two longitudinal beams (3), and a second hanging rope (4) connected to the bottom of both ends of the two longitudinal beams (3), wherein the two longitudinal beams (3) are respectively located vertically directly below the two ends of the crossbeam (1); The crossbeam (1) comprises a first hanging plate (11), a first hanging beam (12) integrally and symmetrically connected to the lower surface of the first hanging plate (11), and two first hanging buckles (13), and the two first hanging buckles (13) are symmetrically connected to the lower surface of the first hanging beam (12); The longitudinal beam (3) comprises a second hanging plate (31), a second hanging beam (32) integrally and symmetrically connected to the lower surface of the second hanging plate (31), and two second hanging buckles (33), and the two second hanging buckles (33) are symmetrically connected to the lower surface of the second hanging beam (32).

2. The aircraft modular sling according to claim 1, characterized in that: A first hanging hole (111) is provided at the center of the first hanging plate (11), and a plurality of evenly distributed third hanging holes (311) are provided at the center of the second hanging plate (31).

3. The aircraft modular sling according to claim 1, wherein: The first suspension beam (12) and the second suspension beam (32) are both steel pipe structures with square hollow cross-sections.

4. The aircraft modular sling according to claim 1, wherein: A plurality of evenly distributed second hanging holes (131) are provided at the center of the surface of the first hanging buckle (13), and a plurality of evenly distributed fourth hanging holes (331) are provided at the center of the surface of the second hanging buckle (33).

5. The aircraft modular sling according to claim 1, wherein: The first hanging rope (2) and the second hanging rope (4) are either a steel rope or a soft rope with a hook.

6. The aircraft modular sling according to claim 5, characterized in that: The soft rope with hook is a synthetic fiber lifting belt structure.

7. The aircraft modular sling according to claim 1, wherein: The length of the cross beam (1) is smaller than the length of the longitudinal beam (3).

8. The aircraft modular sling according to claim 1, wherein: The length of the first hanging rope (2) is greater than the length of the second hanging rope (4).

9. The aircraft modular sling according to claim 1, wherein: The length of the first hanging buckle (13) is greater than the length of the second hanging buckle (33).

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