A high-precision adjustable stabilizing support plate assembly for aircraft

Abstract

This utility model relates to the technical field of support plate assemblies, and more particularly to a high-precision adjustable and stable support plate assembly for aircraft. It includes an inner fixing block, with middle connecting plates fixedly connected to both sides of the inner fixing block, and outer connecting plates fixedly connected to opposite sides of the two middle connecting plates. This utility model has the advantages of achieving a secure lock and resisting vibrations and impacts in the aviation environment. In actual use, through the coordinated use of the inner fixing block, middle connecting plates, outer connecting plates, first fixing block, sliding rod, slider, first rotating plate, and fixing frame, when vibration acts on the outer connecting plate, it can effectively increase the connection effect, ensuring that the device is firmly fixed to the fuselage mounting block and preventing detachment. This achieves a stable connection between the two fuselage mounting blocks. The vibration damping structure enhances the vibration damping effect, effectively preventing damage to the device in the event of a large impact.

Description

Technical Field

[0001] This utility model relates to the technical field of support plate assembly, specifically a high-precision adjustable and stable support plate assembly for aircraft. Background Technology

[0002] In the manufacturing, assembly and maintenance of aircraft, it is often necessary to install support plates between two or more structural components (such as between skin and frame, between door and door frame, between movable wing surface and fixed structure) to precisely control assembly gaps, ensure structural rigidity, transfer loads or compensate for tolerances. The fuselage, wings, engines and other components of an aircraft are subjected to a large number of complex mechanical loads during flight, and the mechanical loads change constantly with different flight conditions. Traditional support structures are often unable to adapt to these changes, resulting in unstable or inaccurate support effects.

[0003] Currently, many aircraft support components still use simple shim stacking or coarse-threaded bolt adjustment methods, which are difficult to meet the stringent requirements of modern aircraft for high precision, high reliability, and high performance. Traditional support methods often cannot provide sufficient locking force after adjustment, and the structural design is usually relatively simple, failing to consider strain changes under various dynamic working conditions. In addition, rigid fixed structures often cannot adapt to the diverse assembly requirements of different specifications of components, limiting their application in complex assembly environments. In the long-term high-frequency vibration flight environment, these traditional support components are prone to failure due to mechanical loosening, thereby affecting the stability of the support and the overall safety of the aircraft. Especially in environments with high vibration, severe impact, and large temperature changes, support components are prone to loosening or displacement, leading to a decrease in reliability, which in turn affects the precise fit of various aircraft components and the overall structural performance. Moreover, traditional stacking methods and bulky structures often bring unnecessary weight increases, affecting the aircraft's fuel efficiency and performance. Utility Model Content

[0004] The purpose of this invention is to provide a high-precision adjustable stabilizing support plate assembly for aircraft, which has the advantages of being able to lock firmly and resist vibration and impact in the aviation environment, thus solving the problems mentioned in the background art.

[0005] To achieve the above objectives, this utility model provides the following technical solution: a high-precision adjustable stable support plate assembly for aircraft, comprising an inner fixing block, with middle connecting plates fixedly connected to both sides of the inner fixing block, outer connecting plates fixedly connected to opposite sides of the two middle connecting plates, and fuselage mounting blocks provided on opposite sides of the two outer connecting plates. A plurality of first fixing blocks are fixedly connected to the surface of the inner fixing block, and two sliding rods are slidably connected to the inner cavities of the plurality of first fixing blocks. One end of each sliding rod passes through the outer connecting plate and is slidably connected to the inner cavity of the fuselage mounting block. Two sliders are slidably connected to the inner cavities of the plurality of first fixing blocks, with one end of each slider contacting the two sliding rods. Two first rotating plates are rotatably connected to the other end of each slider. A fixing frame is rotatably connected to one end of each of the two first rotating plates, with one side of the fixing frame fixedly connected to the surface of the outer connecting plate. Two vibration damping structures are fixedly connected to the opposite surfaces of the two outer connecting plates.

[0006] Furthermore, as a preferred embodiment of this utility model, the vibration damping structure includes a fixing plate fixedly connected to the surface of the outer connecting plate. Grooves are provided on both sides of the surface of the fixing plate. A first fixing rod is fixedly connected to the inner cavity of the groove. A first spring is sleeved on the surface of the first fixing rod. A second fixing block is fixedly connected to one end of each of the two first springs. The second fixing block is fixedly connected to the surface of another outer connecting plate, and the first fixing rod is slidably connected to the inner cavity of the second fixing block. A second fixing rod is fixedly connected to the opposite side of each of the two second fixing blocks. A sliding frame is slidably connected to the surfaces of both ends of the second fixing rod. A second spring is fixedly connected to the opposite side of each of the two sliding frames, and the second spring is sleeved on the surface of the second fixing rod. A second rotating plate is rotatably connected to the inner cavity of the sliding frame, and the other end of the second rotating plate is rotatably connected to the inner cavity of the fixing plate.

[0007] Furthermore, as a preferred embodiment of this utility model, dampers are provided on both sides of the two vibration reduction structures, and the two ends of the dampers are fixedly connected to the surface of the outer connecting plate.

[0008] Furthermore, as a preferred embodiment of this utility model, the end of the slide bar that contacts the mounting block of the body is configured as an inclined surface.

[0009] Furthermore, as a preferred embodiment of this utility model, the middle connecting plate is configured as a honeycomb-shaped vibration damping layer, and the outer connecting plate is made of, but is not limited to, a vibration damping soft material.

[0010] Beneficial effects: The technical solution of this application has the following advantages: This utility model has the advantage of being able to achieve a firm lock and resist vibration and impact in the aviation environment. In actual use, through the coordinated use of the inner fixing block, the middle connecting plate, the outer connecting plate, the first fixing block, the slide rod, the slider, the first rotating plate, and the fixing frame, when vibration acts on the outer connecting plate, it can effectively increase the connection effect, ensuring that the device is firmly fixed on the fuselage body mounting block and preventing detachment, thereby achieving a stable connection between the two fuselage body mounting blocks. Through the setting of the vibration damping structure, the vibration damping effect is enhanced, and the device is effectively prevented from being damaged when encountering a large impact. In order to further improve the impact resistance, the coordinated use of the middle connecting plate and the outer connecting plate improves the vibration damping effect, enhances the stability of the device on the fuselage body mounting block under high impact conditions, ensures reliability under complex and extreme conditions, improves the service life and stability of the device, and adapts to the requirements of complex working environments.

[0011] It should be understood that all combinations of the foregoing concepts and the additional concepts described in more detail below can be considered as part of the utility model subject matter of this disclosure, provided that such concepts do not contradict each other. Attached Figure Description

[0012] The accompanying drawings are provided to further illustrate the present invention and form part of the specification. They are used together with the embodiments of the present invention to explain the present invention, but do not constitute a limitation thereof. In the drawings:

[0013] Figure 1 This is a schematic diagram of the structure of this utility model;

[0014] Figure 2 This is a cross-sectional schematic diagram of the mounting block of the fuselage body of this utility model;

[0015] Figure 3 This is a schematic cross-sectional view of the outer connecting plate of this utility model;

[0016] Figure 4 This is a cross-sectional schematic diagram of the middle layer connecting plate of this utility model;

[0017] Figure 5 This is a schematic cross-sectional view of the vibration reduction structure of this utility model;

[0018] Figure 6 This is a cross-sectional schematic diagram of the first fixing block of this utility model.

[0019] In the figure, the meanings of the various reference numerals are as follows: 1. Inner fixing block; 2. Middle connecting plate; 3. Outer connecting plate; 4. Body mounting block; 5. First fixing block; 6. Slide rod; 7. Slider; 8. First rotating plate; 9. Fixing frame; 10. Vibration damping structure; 101. Fixing plate; 102. Groove; 103. First fixing rod; 104. First spring; 105. Second fixing block; 106. Second fixing rod; 107. Sliding frame; 108. Second spring; 109. Second rotating plate; 11. Damper. Detailed Implementation

[0020] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings. To better understand the technical content of the present utility model, specific embodiments are provided and described in conjunction with the accompanying drawings. Various aspects of the present utility model are described in this disclosure with reference to the accompanying drawings, which show many illustrative embodiments. It should be understood that the various concepts and embodiments described above, as well as those described in more detail below, can be implemented in any of many ways. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model without creative effort are within the scope of protection of the present utility model.

[0021] As attached Figure 1 To be continued Figure 6 As shown: This embodiment provides a high-precision adjustable stabilizing support plate assembly for aircraft, including an inner fixing block 1. Middle connecting plates 2 are fixedly connected to both sides of the inner fixing block 1. Outer connecting plates 3 are fixedly connected to opposite sides of the two middle connecting plates 2. A fuselage mounting block 4 is provided on opposite sides of the two outer connecting plates 3. A plurality of first fixing blocks 5 are fixedly connected to the surface of the inner fixing block 1. Two sliding rods 6 are slidably connected to the inner cavities of the plurality of first fixing blocks 5. The opposite ends of the two sliding rods 6 penetrate the outer connecting plates 3 and are slidably connected to the inner cavities of the fuselage mounting blocks 4. Two sliders 7 are slidably connected to the inner cavities of the plurality of first fixing blocks 5. One end of each slider 7 contacts the two sliding rods 6. Two first rotating plates 8 are rotatably connected to the other ends of the sliders 7. A fixing frame 9 is rotatably connected to one end of each of the two first rotating plates 8. One side of the fixing frame 9 is fixedly connected to the surface of the outer connecting plate 3. Two vibration damping structures 10 are fixedly connected to the opposite surfaces of the two outer connecting plates 3.

[0022] Specifically, the vibration damping structure 10 includes a fixing plate 101 fixedly connected to the surface of the outer connecting plate 3. Grooves 102 are provided on both sides of the surface of the fixing plate 101. A first fixing rod 103 is fixedly connected to the inner cavity of the groove 102. A first spring 104 is sleeved on the surface of the first fixing rod 103. A second fixing block 105 is fixedly connected to one end of each of the two first springs 104. The second fixing block 105 is fixedly connected to the surface of another outer connecting plate 3. The first fixing rod 103 is slidably connected to the inner cavity of the second fixing block 105. A second fixing rod 106 is fixedly connected to the opposite side of the two second fixing blocks 105. A sliding frame 107 is slidably connected to the surfaces of both ends of the second fixing rod 106. A second spring 108 is fixedly connected to the opposite side of the two sliding frames 107. The second spring 108 is sleeved on the surface of the second fixing rod 106. A second rotating plate 109 is rotatably connected to the inner cavity of the sliding frame 107. The other end of the second rotating plate 109 is rotatably connected to the inner cavity of the fixing plate 101.

[0023] In this embodiment, the vibration damping structure 10 effectively achieves the vibration damping function, which can reduce the impact of vibration and impact generated during use, and ensure the tight cooperation between components. Especially in the aviation environment, the vibration damping structure 10 can effectively resist high-intensity vibration and external impact, provide stable and reliable support, and ensure normal operation in harsh environments. It not only improves the anti-interference ability, but also extends its service life and ensures continuous and efficient operation in complex environments.

[0024] Specifically, dampers 11 are provided on both sides of the two vibration reduction structures 10, and the two ends of the dampers 11 are fixedly connected to the surface of the outer connecting plate 3.

[0025] In this embodiment, by setting the damper 11, excessive vibration and impact generated during equipment operation can be effectively suppressed, and the vibration amplitude can be reduced. The damper 11 absorbs and dissipates vibration energy, reducing the transmission of vibration to other components and preventing the negative impact of vibration on the stability, accuracy and life of the equipment.

[0026] Specifically, the end of the slide bar 6 that contacts the mounting block 4 of the fuselage body is set as an inclined surface.

[0027] In this embodiment: the inclined surface allows for a smoother locking action. The angle of the inclined surface enables the slide bar 6 to generate an adaptive force when it contacts the mounting block 4 of the main body, helping the two to lock smoothly and avoiding the tedious manual pressing operation, thus improving the convenience of locking.

[0028] Specifically, the middle connecting plate 2 is set as a honeycomb vibration damping layer, and the outer connecting plate 3 is made of, but is not limited to, a vibration damping soft material.

[0029] In this embodiment: by using a honeycomb damping layer in the middle connecting plate 2, the honeycomb structure design not only has excellent damping performance, but also disperses vibration energy and reduces the impact of vibration on the overall structure, thereby improving the stability and service life of the equipment. The honeycomb damping layer can also maintain strong load-bearing capacity while being lightweight. The outer connecting plate 3 uses a damping soft material, which provides a more flexible and precise vibration absorption function. The soft material can effectively absorb external impacts and vibrations, reduce external interference to the internal system of the equipment, and improve the anti-interference ability and operational stability of the equipment.

[0030] The working principle and usage process of this utility model are as follows: During use, the device is aligned and placed between two body mounting blocks 4. A pushing operation causes the inclined surface of the slide rod 6 to press against the surface of the body mounting block 4, thereby guiding the other end of the slide rod 6 to slide within the inner cavity of the first fixed block 5. Simultaneously, the slide rod 6 contacts the surface of the slider 7, causing the slider 7 to slide within the inner cavity of the first fixed block 5. This allows the slide rod 6 to smoothly enter the inner cavity of the body mounting block 4, thus completing the installation of the device and ensuring the supporting connection between the two body mounting blocks 4. When the device is running... If vibration occurs, the two fuselage mounting blocks 4 will press against their surfaces through the outer connecting plates 3. A vibration damping structure 10 is provided between the two outer connecting plates 3 to effectively mitigate the impact of vibration. The outer connecting plates 3 drive the fixed plate 101 and the second fixed block 105 to move towards each other, thereby causing the second rotating plate 109 connected to the surface of the fixed plate 101 and the sliding frame 107 to rotate, thereby causing the sliding frame 107 to slide along the surface of the second fixed rod 106. At this time, the second spring 108 is compressed and subjected to its elastic recovery, which plays a role in vibration damping. At the same time, the fixed plate 101 has a vibration damping structure 10 at both ends. A groove 102 is provided, within which a first fixing rod 103 and a first spring 104 move. To ensure the stability of the first spring 104 during compression and prevent damage, a first fixing rod 103 is provided within the inner cavity of the first spring 104. The first fixing rod 103 serves as a guide and stabilizer, ensuring that the first spring 104 is not damaged due to excessive compression. When the outer connecting plate 3 is compressed, it also exerts a compressive force on the middle connecting plate 2. Furthermore, the outer connecting plate 3 and the middle connecting plate 2 further enhance the overall vibration damping effect. A first fixing block 5 is fixedly connected to the surface of the inner fixing block 1, and... It is placed between two outer connecting plates 3. When there is relative movement between the body mounting blocks 4, the outer connecting plates 3 will drive the fixing frame 9 to move together. One end of the fixing frame 9 is rotatably connected to the slider 7, thereby pushing the slider 7 to slide in the inner cavity of the first fixing block 5. At this time, the slider 7 will apply a squeezing force to the slide rod 6, so that the slide rod 6 slides in the inner cavity of the body mounting block 4, thereby enhancing the connection effect, ensuring a stable connection between the two body mounting blocks 4, reducing the risk of separation, ensuring the reliability and stability of the equipment in vibration and shock environments, and ensuring the efficient operation of the equipment in harsh environments.

[0031] It should be noted that in this paper, relational terms such as first and second are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations.

[0032] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Those skilled in the art to which this invention pertains can make various modifications and refinements without departing from the spirit and scope of the present invention. Therefore, the scope of protection of this invention shall be determined by the claims.

Claims

1. A high-precision adjustable stable support sheet assembly for an aircraft, comprising an inner fixed block (1), characterized in that: The inner fixing block (1) has a middle connecting plate (2) fixedly connected to both sides of its surface. An outer connecting plate (3) is fixedly connected to the opposite side of each of the two middle connecting plates (2). A fuselage mounting block (4) is provided on the opposite side of each of the two outer connecting plates (3). A plurality of first fixing blocks (5) are fixedly connected to the surface of the inner fixing block (1). Two sliding rods (6) are slidably connected to the inner cavity of each of the first fixing blocks (5). The opposite ends of the two sliding rods (6) penetrate the outer connecting plate (3) and are slidably connected to it. The inner cavity of the fuselage mounting block (4) and the inner cavities of several first fixing blocks (5) are slidably connected to two sliders (7), and the surface of one end of the two sliders (7) is in contact with two sliding rods (6). The other end of the sliders (7) is rotatably connected to two first rotating plates (8). One end of each of the two first rotating plates (8) is rotatably connected to a fixing frame (9). One side of the fixing frame (9) is fixedly connected to the surface of the outer connecting plate (3). The opposing surfaces of the two outer connecting plates (3) are fixedly connected to two vibration damping structures (10). ​ 2. A high-precision adjustable stable support sheet assembly for an aircraft according to claim 1, characterized in that: The vibration damping structure (10) includes a fixing plate (101) fixedly connected to the surface of the outer connecting plate (3). Grooves (102) are provided on both sides of the surface of the fixing plate (101). A first fixing rod (103) is fixedly connected to the inner cavity of the groove (102). A first spring (104) is sleeved on the surface of the first fixing rod (103). A second fixing block (105) is fixedly connected to one end of each of the two first springs (104). The second fixing block (105) is fixedly connected to the surface of another outer connecting plate (3), and the first fixing rod (103) is slidably connected to... The inner cavity of the second fixing block (105) is connected to the second fixing rod (106) on the opposite side of the two second fixing blocks (105). The surfaces of both ends of the second fixing rod (106) are slidably connected to the sliding frame (107). The opposite sides of the two sliding frames (107) are connected to the second spring (108), and the second spring (108) is sleeved on the surface of the second fixing rod (106). The inner cavity of the sliding frame (107) is rotatably connected to the second rotating plate (109), and the other end of the second rotating plate (109) is rotatably connected to the inner cavity of the fixing plate (101).

3. The high-precision adjustable stable support sheet assembly for an aerial aircraft according to claim 1, characterized in that: Both sides of the two vibration reduction structures (10) are provided with dampers (11), and the two ends of the dampers (11) are fixedly connected to the surface of the outer connecting plate (3).

4. The high-precision adjustable firm support sheet assembly for an aviation aircraft according to claim 1, characterized in that: The end of the slide bar (6) that contacts the fuselage mounting block (4) is set as an inclined surface.

5. The high-precision adjustable firm support sheet assembly for an aviation aircraft according to claim 1, characterized in that: The middle connecting plate (2) is configured as a honeycomb vibration damping layer, and the outer connecting plate (3) is made of, but is not limited to, a vibration damping soft material.

Images