Aircraft four-point semi-rigid sling capable of adjusting the lifting center of gravity position

Abstract

The utility model discloses a four point half hard hoist of aircraft in the field of aircraft production technology can adjust the position of lifting the center of gravity, including main crossbeam, be provided with main longitudinal beam on the main crossbeam, the main crossbeam with main longitudinal beam is vertically arranged, is welded between the main crossbeam and main longitudinal beam, be provided with extension assembly on the main crossbeam, be provided with connecting assembly on the main crossbeam, the main crossbeam with main longitudinal beam all are provided with the hoisting body. The utility model discloses through setting up extension assembly, connecting assembly and point concrete etc. structure, makes hoist can according to the size of different aircraft and the free adjustment of the change of center of gravity, significantly enhances the versatility of equipment, through adjustable sling and evenly distributed connecting hole, system can accurately match the hoisting demand of all kinds of aircraft, ensures that the stress is balanced, effectively reduces the operation complexity, simultaneously is convenient for transportation, storage and maintenance, and the efficiency of aviation support operation is greatly promoted.

Description

Technical Field

[0001] This utility model relates to the field of aircraft manufacturing technology, and in particular to a rigid four-and-a-half-point lifting device for aircraft that can adjust the lifting center of gravity position. Background Technology

[0002] Aircraft lifting equipment, as a key piece of equipment in the maintenance and assembly process of the aviation equipment industry, is mainly used for the lifting, transfer, and attitude adjustment of aircraft. In traditional designs, the lifting center of gravity of the lifting equipment is usually fixed, which has significant limitations. Because the center of gravity of an aircraft can shift due to dynamic factors such as fuel level, load distribution, and landing gear retraction / extension, its actual center of gravity can fluctuate within a considerable range. When the lifting point of the lifting equipment cannot be adjusted, it can cause unexpected tilting or deflection of the aircraft during lifting, increasing the difficulty for operators to adjust the balance and potentially leading to uneven structural stress. For example, in a tilted state, critical components such as the wings and fuselage may bear additional torsional loads, which can lead to structural fatigue or even damage over time; simultaneously, the unbalanced state can also cause localized overload of the lifting cables, posing a risk of breakage.

[0003] Furthermore, unstable attitudes during hoisting significantly reduce operational efficiency, requiring operators to repeatedly attempt balancing and even forcing work interruptions to manually adjust the lifting point positions, severely impacting the timeliness and safety of aviation support. Therefore, traditional fixed lifting rigs are no longer sufficient to meet the diverse and high-precision hoisting needs of modern aircraft, necessitating the development of intelligent hoisting solutions with adaptive center of gravity adjustment capabilities. Consequently, we propose a rigid four-and-a-half-point lifting rig for aircraft capable of adjusting the lifting center of gravity. Utility Model Content

[0004] To address the shortcomings of existing technologies, this utility model provides a rigid four-and-a-half-point lifting device for aircraft that can adjust the lifting center of gravity. By setting up extension components, connecting components, and point bodies, the lifting device can be freely adjusted according to the size and center of gravity changes of different aircraft, significantly enhancing the versatility of the equipment.

[0005] The purpose of this utility model is achieved as follows: A rigid four-and-a-half-point lifting device for aircraft capable of adjusting the lifting center of gravity includes a main crossbeam, on which a main longitudinal beam is provided. The main crossbeam and the main longitudinal beam are arranged perpendicularly and welded together. An extension assembly is provided on the main crossbeam, and there are two sets of extension assemblies symmetrically distributed. A connecting assembly is provided on the main crossbeam for adjusting the center of gravity of the lifting device. A lifting body is provided on both the main crossbeam and the main longitudinal beam for lifting and connecting the aircraft.

[0006] Optionally, the extension assembly includes a first side beam and a second side beam, one end of the first side beam being bolted to the main crossbeam, and the other end of the first side beam being bolted to the second side beam.

[0007] Optionally, the connecting assembly includes a lifting ring located directly above the junction of the main crossbeam and the main longitudinal beam. A first lifting strap is provided between the lifting ring and the main crossbeam, and a second lifting strap is provided between the lifting ring and the main longitudinal beam. The lengths of the first and second lifting straps are adjustable.

[0008] Optionally, the main longitudinal beam, the main transverse beam, the first side beam, and the second side beam are all provided with connection holes. The first sling and the second sling are both fixedly connected to the lifting ring. The first sling is connected to the main transverse beam and the extension assembly, and the second sling is connected to the main longitudinal beam.

[0009] Optionally, the number of connecting holes is multiple, and the multiple connecting holes are evenly distributed.

[0010] Optionally, the lifting body includes a belt, one end of which is provided with a shackle, one set of the shackles is attached to the first side beam, and the other set of the shackles is attached to the main longitudinal beam. The other end of the belt is provided with a suspension screw, which is threadedly connected to the aircraft.

[0011] Compared with the prior art, the beneficial effects of this utility model are as follows: 1. By setting up extension components, connection components, and point-body structures, the spreader can be freely adjusted according to the size and center of gravity changes of different aircraft, significantly enhancing the versatility of the equipment. With adjustable slings and evenly distributed connection holes, the system can accurately match the lifting requirements of various aircraft, ensuring balanced force, effectively reducing operational complexity, and facilitating transportation, storage, and maintenance, thus greatly improving the efficiency of aviation support operations.

[0012] 2. Through the combined design of shackles, suspension screws and flexible belts, reliable fixation between the aircraft and the lifting equipment is achieved, avoiding loosening or displacement during the lifting process. The reasonable layout of the lifting rings and the main structure optimizes the load distribution and reduces stress concentration, while the flexible belts can buffer dynamic impacts and ensure that the lifting process is stable and controllable. Attached Figure Description

[0013] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0014] Figure 1This is a schematic diagram of the overall structure provided by this utility model.

[0015] Figure 2 This is a schematic diagram of the main crossbeam structure provided by this utility model.

[0016] Figure 3 This is a schematic diagram of the specific structure of the hoisting device provided by this utility model.

[0017] In the diagram: 1. Main crossbeam; 2. Main longitudinal beam; 3. Extension assembly; 31. First side beam; 32. Second side beam; 4. Connecting assembly; 41. Lifting ring; 42. First lifting strap; 43. Second lifting strap; 44. Connecting hole; 5. Lifting body; 51. Strap body; 52. Shackle; 53. Suspension screw. Detailed Implementation

[0018] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0019] like Figures 1 to 3 The invention illustrates a rigid four-and-a-half-point lifting device for aircraft capable of adjusting the lifting center of gravity. It includes a main crossbeam 1, on which a main longitudinal beam 2 is mounted. The main crossbeam 1 and the main longitudinal beam 2 are perpendicularly positioned and welded together. Two sets of extension components 3 are mounted on the main crossbeam 1 and are symmetrically distributed. A connecting component 4 is mounted on the main crossbeam 1 for adjusting the center of gravity of the lifting device. A lifting body 5 is mounted on both the main crossbeam 1 and the main longitudinal beam 2 for lifting and connecting the aircraft.

[0020] Furthermore, in the embodiments provided in this application, the adjustable connection component 4 can dynamically adapt to changes in the center of gravity of the aircraft, effectively solving the problem of lifting tilt caused by the fixed center of gravity of traditional lifting equipment. Its symmetrically distributed extension components 3 enhance structural stability, ensure uniform stress during hoisting, and avoid local overload or structural damage to the aircraft. The rigid connection between the main crossbeam 1 and the main longitudinal beam 2 provides high load-bearing strength, while the flexible adjustment function allows the spreader to adapt to the center of gravity shift caused by factors such as different fuel levels and landing gear status, thereby improving the safety and reliability of lifting operations.

[0021] In addition, the modular structure can reduce the need for manual intervention, simplify operating procedures, improve the efficiency of aircraft maintenance and assembly operations, and is suitable for the precision lifting needs of various aircraft.

[0022] Specifically, the extension component 3 includes a first side beam 31 and a second side beam 32. One end of the first side beam 31 is bolted to the main crossbeam 1, and the other end of the first side beam 31 is bolted to the second side beam 32.

[0023] Furthermore, the use of the extension assembly 3 with modular bolt connection allows the length and angle of the first side beam 31 and the second side beam 32 to be flexibly adjusted according to actual needs, thereby adapting to the hoisting requirements of aircraft of different sizes; Bolted connections not only facilitate disassembly and maintenance, but also provide the necessary degree of adjustment freedom while ensuring structural strength, enabling the spreader to more accurately match the changes in the aircraft's center of gravity. Furthermore, this segmented structure not only enhances the adaptability of the lifting equipment but also meets the wide span requirements of large aircraft. At the same time, it can be compactly configured for small aircraft, effectively improving the stability and controllability of the lifting process. In addition, the modular design facilitates transportation and storage, reduces the complexity of equipment deployment, and further optimizes the efficiency and safety of aviation support operations.

[0024] Specifically, the connecting component 4 includes a lifting ring 41, which is located directly above the junction of the main crossbeam 1 and the main longitudinal beam 2. A first lifting strap 42 is provided between the lifting ring 41 and the main crossbeam 1, and a second lifting strap 43 is provided between the lifting ring 41 and the main longitudinal beam 2. The lengths of the first lifting strap 42 and the second lifting strap 43 can be adjusted. Connecting holes 44 are provided on the main longitudinal beam 2, the main crossbeam 1, the first side beam 31, and the second side beam 32. The first lifting strap 42 and the second lifting strap 43 are fixedly connected to the lifting ring 41. The first lifting strap 42 is connected to the main crossbeam 1 and the extension component 3, and the second lifting strap 43 is connected to the main longitudinal beam 2. There are multiple connecting holes 44, which are evenly distributed.

[0025] Furthermore, by using the adjustable length first sling 42 and second sling 43, along with the evenly distributed connecting holes 44, the center of gravity of the lifting device can be flexibly adjusted, ensuring that the aircraft remains in a balanced state during the lifting process. Furthermore, the lifting ring 41 is located directly above the junction of the main crossbeam 1 and the main longitudinal beam 2, which makes the force distribution more reasonable, avoids local stress concentration, and improves the load-bearing safety of the overall structure. The first lifting strap 42 is connected to the main crossbeam 1 or the extension component 3, and the second lifting strap 43 is connected to the main longitudinal beam 2, forming a stable multi-point support system that can effectively adapt to the center of gravity shift of the aircraft caused by factors such as fuel consumption and changes in landing gear status. Multiple evenly distributed connection holes 44 provide ample adjustment options, enabling the spreader to be precisely matched to the size and weight distribution of different aircraft, significantly reducing the risk of tilting during lifting. Furthermore, this application simplifies the operation process, reduces the need for manual intervention, improves lifting efficiency, and enhances the versatility and adaptability of the equipment, making it suitable for the safe lifting needs of various types of aircraft.

[0026] Specifically, the lifting body 5 includes a belt body 51, one end of which is provided with a shackle 52. One set of shackles 52 is hooked onto the first side beam 31, and the other set of shackles 52 is hooked onto the main longitudinal beam 2. The other end of the belt body 51 is provided with a suspension screw 53, which is threadedly connected to the aircraft.

[0027] Furthermore, the sling 51 structure of the lifting device 5, in conjunction with the shackle 52 and suspension bolt 53, achieves a stable connection between the aircraft and the lifting device, ensuring a safe and reliable lifting process. The shackle 52 is attached to the main longitudinal beam 2 or the extension assembly 3, ensuring even distribution of force and avoiding localized overload. The threaded connection between the suspension bolt 53 and the aircraft provides a secure fixation, preventing loosening or slippage during lifting. This not only facilitates quick installation and disassembly but also adapts to the connection interface requirements of different aircraft, improving the versatility of the lifting device. Simultaneously, the flexibility of the sling 51 effectively buffers dynamic loads during lifting, reducing impact on the aircraft structure and further ensuring the stability and safety of the lifting operation.

[0028] The above description of the embodiments is only for the purpose of helping to understand the method and core idea of ​​this utility model. It should be noted that for those skilled in the art, several improvements and modifications can be made to this utility model without departing from the principle of this utility model, and these improvements and modifications also fall within the protection scope of the claims of this utility model.

Claims

1. A rigid four-and-a-half-point lifting device for aircraft capable of adjusting the lifting center of gravity, comprising a main crossbeam (1), characterized in that: The main crossbeam (1) is provided with a main longitudinal beam (2), the main crossbeam (1) and the main longitudinal beam (2) are arranged perpendicularly, the main crossbeam (1) and the main longitudinal beam (2) are welded together, the main crossbeam (1) is provided with an extension component (3), the number of the extension components (3) is two sets, the two sets of extension components (3) are symmetrically distributed, the main crossbeam (1) is provided with a connecting component (4), the connecting component (4) is used to adjust the center of gravity position of the lifting device, the main crossbeam (1) and the main longitudinal beam (2) are both provided with a lifting body (5), the lifting body (5) is used to lift and connect the aircraft.

2. The four-and-a-half-point rigid lifting device for aircraft capable of adjusting the lifting center of gravity position according to claim 1, characterized in that: The extension assembly (3) includes a first side beam (31) and a second side beam (32), one end of the first side beam (31) is bolted to the main cross beam (1), and the other end of the first side beam (31) is bolted to the second side beam (32).

3. The four-and-a-half-point rigid lifting device for aircraft capable of adjusting the lifting center of gravity position according to claim 1, characterized in that: The connecting component (4) includes a lifting ring (41) located directly above the junction of the main crossbeam (1) and the main longitudinal beam (2). A first lifting strap (42) is provided between the lifting ring (41) and the main crossbeam (1), and a second lifting strap (43) is provided between the lifting ring (41) and the main longitudinal beam (2). The lengths of the first lifting strap (42) and the second lifting strap (43) can be adjusted.

4. The four-and-a-half-point rigid lifting device for aircraft capable of adjusting the lifting center of gravity position according to claim 3, characterized in that: The main longitudinal beam (2), the main transverse beam (1), the first side beam (31) and the second side beam (32) are all provided with connection holes (44). The first sling (42) and the second sling (43) are both fixedly connected to the lifting ring (41). The first sling (42) is connected to the main transverse beam (1) and the extension assembly (3). The second sling (43) is connected to the main longitudinal beam (2).

5. A rigid four-and-a-half-point lifting device for aircraft capable of adjusting the lifting center of gravity position according to claim 4, characterized in that: The number of the connecting holes (44) is multiple, and the multiple connecting holes (44) are evenly distributed.

6. The four-and-a-half-point rigid lifting device for aircraft capable of adjusting the lifting center of gravity position according to claim 1, characterized in that: The lifting body (5) includes a belt (51), one end of which is provided with a shackle (52). One set of the shackles (52) is hooked to the first side beam (31), and the other set of the shackles (52) is hooked to the main longitudinal beam (2). The other end of the belt (51) is provided with a suspension screw (53), which is threaded to the aircraft.

Images