Lift-imitating hanging cross beam of airplane structure
By designing an aircraft structure-simulated lift suspension beam and utilizing the wing-fuselage joint to transfer loads and prevent roll, the problems of simulated lift application and structural strength were solved, achieving a combination of stability and economy.
Patent Information
- Application Number
- CN202423046706.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-10
- Publication Date
- 2025-10-28
- Estimated Expiration
- 2034-12-10
AI Technical Summary
It is difficult to effectively apply simulated lift without damaging the structural strength of the aircraft with existing technologies, and the aircraft is prone to rolling when subjected to simulated lift loads.
An aircraft structure simulated lift suspension beam is designed. Through the combination of the main beam, connecting fork ears, ear plate connection holes, sling connection points and counterweight sections, the wing-fuselage joint is used to transfer loads and prevent roll, thereby achieving simulated lift application.
At the same time, it meets the requirements of imitation lift application and structural strength, prevents rolling, has a simple structure, low production cost, a wide range of applications, and is easy to promote.
Smart Images
Figure CN223479355U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of aircraft design technology, and in particular to an aircraft structural imitation lifting suspension beam. Background Technology
[0002] To ensure safe landing, aircraft typically float to a landing at a certain descent speed Vy. At this time, the lift of the wing is generally equal to the landing weight of the aircraft. To simulate the effect of the wing lift on the landing load of the aircraft during landing, it is necessary to conduct a structural lift simulation test.
[0003] The methods of applying simulated lift to aircraft structures vary. The form of applying simulated lift can be determined according to the characteristics of the aircraft structural design. The common method is to apply loads by using existing structural components of the aircraft, but this places high demands on the structural strength, which is usually difficult to meet. Utility Model Content
[0004] The purpose of this invention is to provide an aircraft structural lift-simulating suspension beam. This invention can simultaneously meet the requirements for applying lift force and structural strength.
[0005] The technical solution of this utility model is: an aircraft structural imitation lifting suspension beam, including a main beam, a front connecting fork lug at the lower front end of the main beam, and a rear connecting fork lug at the lower rear end. Both the front and rear connecting forks lugs are provided with upper lug connection holes and lower lug connection holes along the vertical direction. The upper and lower lug connection holes of the front and rear connecting forks lugs are aligned with the connection holes of the wing-body joint of the aircraft structure. A sling connection point is also provided on the upper part of the main beam between the front and rear connecting forks lugs.
[0006] In the aforementioned aircraft structure imitation lifting suspension beam, a counterweight section is provided at the rear end of the main beam.
[0007] In the aforementioned aircraft structural imitation lifting beam, the openings of the upper and lower lug connection holes are all provided with reinforcing steps.
[0008] In the aforementioned aircraft structure imitation lifting suspension beam, the main beam is provided with weight reduction holes.
[0009] In the aforementioned aircraft structure imitation lifting beam, vertical force transmission ribs are provided inside the weight reduction holes.
[0010] In the aforementioned aircraft structure imitation lifting suspension beam, one of the vertical force transmission ribs passes through the suspension cable connection point.
[0011] The advantages of this utility model are: In order to realize the addition of the device on the outside of the aircraft to achieve the simulated lift loading, this utility model provides an aircraft structural simulated lift suspension beam, which can simultaneously meet the requirements of simulated lift application and structural strength requirements.
[0012] This utility model pertains to an external design attachment for aircraft. It does not impose high strength requirements on the aircraft structure, significantly reducing design redundancy. Simultaneously, it effectively utilizes the strong load-bearing capacity of the wing-body joint. Furthermore, the suspension beam connects to the wing-body joint via multiple forked lugs, preventing the aircraft from rolling around its center of gravity while under simulated lift loads, thus improving stability during suspension. The counterweight section at the rear of the suspension beam allows for easy adjustment of the structural center of gravity by adding or removing counterweights, making the process relatively simple and reliable.
[0013] The suspension beam has a clear principle, simple structure, strong load-bearing capacity, and high reliability. It can effectively solve the problem of applying simulated lift force, meet the structural strength requirements, and has a wide range of applications. At the same time, the structure is easy to produce, has low production cost, good practicality, and is easy to promote and apply. Attached Figure Description
[0014] Figure 1 This is a schematic diagram of the structure of this utility model;
[0015] Figure 2 This is a diagram showing the usage state of this utility model. Detailed Implementation
[0016] The present invention will be further described below with reference to the accompanying drawings and embodiments, but this should not be construed as limiting the present invention.
[0017] Example 1. An aircraft structural imitation lifting suspension beam, see [reference needed]. Figures 1-2 The main beam 1 includes a front connecting fork lug 2 at the lower front end and a rear connecting fork lug 3 at the lower rear end. Both the front and rear connecting forks are provided with upper lug connecting holes 4 and lower lug connecting holes 5 along the vertical direction. The upper and lower lug connecting holes of the front and rear connecting forks are aligned with the connecting holes of the wing-body joint of the aircraft structure. The main beam 1 between the front and rear connecting forks is also provided with a sling connection point 6.
[0018] The aforementioned main beam 1 has a counterweight section 7 at its rear end.
[0019] The openings of the aforementioned upper and lower ear-shaped connecting holes are all provided with reinforcing steps 8.
[0020] The aforementioned main beam 1 is provided with weight reduction holes 9.
[0021] The aforementioned weight-reducing hole 9 is provided with a vertical force-transmitting rib 10.
[0022] One of the vertical force transmission bars, 10, passes through the cable connection point 6.
[0023] This structure is an external design attachment for aircraft. The simulated lift application device is connected to the fuselage via symmetrically arranged suspension beams. The load application point (lifting point) passes through the aircraft's center of gravity section, such as... Figure 2 As shown. The suspension beam is connected to the fuselage-wing docking joint (wing-fuselage joint) via two sets of lugs, enabling load transfer while preventing the aircraft from rolling around its center of gravity while bearing simulated lift loads, as... Figure 2 As shown, the design of the counterweight section at the rear of the suspended crossbeam allows for adjustment of the structure's center of gravity.
[0024] The design principle of this suspended crossbeam is clear, the structure is simple, the load-bearing capacity is strong, the reliability is high, it can effectively solve the problem of simulated lift application, and it can also meet the structural strength requirements, making it widely applicable. At the same time, the structure is easy to produce, has low production cost, good practicality, and is easy to promote and apply.
[0025] The suspension beam is primarily connected to the aircraft wing-body joint via lugs. As a crucial load-bearing component of the aircraft structure, the wing-body joint can transmit significant concentrated loads. The suspension beam's connection to the wing-body joint through multiple lugs prevents the aircraft from rolling around its center of gravity while under simulated lift loads, thus improving stability during suspension. Additionally, a counterweight section is located at the rear of the suspension beam to accommodate counterweights, allowing for adjustment of the structure's center of gravity. Furthermore, the upper limit of its load-bearing capacity can be altered by selecting different materials for the suspension beam.
Claims
1. An aircraft structural imitation lifting suspension beam, characterized in that, The main beam (1) is provided with a front connecting fork lug (2) at the lower front end and a rear connecting fork lug (3) at the lower rear end. Both the front and rear connecting forks are provided with an upper lug connecting hole (4) and a lower lug connecting hole (5) in the vertical direction. The upper and lower lug connecting holes of the front and rear connecting forks are aligned with the connecting holes of the wing-body joint of the aircraft structure. The main beam (1) between the front and rear connecting forks is also provided with a sling connection point (6).
2. The aircraft structural imitation lifting suspension beam according to claim 1, characterized in that, The rear end of the main beam (1) is equipped with a counterweight section (7).
3. The aircraft structural imitation lifting suspension beam according to claim 1, characterized in that, The openings of the connecting holes for the upper and lower ear pieces are provided with reinforcing steps (8).
4. The aircraft structural imitation lifting suspension beam according to claim 1, characterized in that, The main beam (1) is provided with weight reduction holes (9).
5. The aircraft structural imitation lifting suspension beam according to claim 4, characterized in that, The weight reduction hole (9) is provided with a vertical force transmission rib (10).
6. The aircraft structural imitation lifting suspension beam according to claim 5, characterized in that, One of the vertical force transmission bars (10) passes through the cable connection point (6).