An onboard equipment vibration-damping mounting structure
Patent Information
- Application Number
- CN202522622911.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-12-10
- Publication Date
- 2026-10-20
- Estimated Expiration
- 2035-12-10
AI Technical Summary
[0003]机载设备在飞机平台上的集成面临一系列苛刻且相互制约的挑战：首先，飞机宽频带、高强度的振动与冲击环境，对机载设备的减振抗冲保护提出了极高要求；其次，飞机内部空间极为有限且形态复杂，要求安装结构必须具备极高的空间利用率与布局适应性；再次，飞机对重量极度敏感，安装方案必须遵循严格的轻量化设计准则
[0025]本申请的机载设备减振安装结构，能够有效降低振动对机载设备的影响，极大提高了机上的空间利用率，减轻重量，方便安装维护。
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Figure CN224868606U_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the field of aircraft airborne equipment installation design, and specifically relates to an airborne equipment vibration reduction installation structure. Background Technology
[0002] The various airborne equipment on an aircraft are core components for ensuring flight safety and enabling its functions. These devices are typically fixed in the cabin or equipment bay using specialized mounting brackets or structures.
[0003] The integration of airborne equipment onto aircraft platforms faces a series of stringent and mutually constraining challenges: First, the wide-bandwidth, high-intensity vibration and shock environment of aircraft places extremely high demands on the vibration reduction and shock resistance protection of airborne equipment; second, the extremely limited and complex internal space of aircraft requires the installation structure to have extremely high space utilization and layout adaptability; third, aircraft are extremely sensitive to weight, and the installation scheme must follow strict lightweight design principles. Traditional airborne equipment installation methods cannot synergistically optimize vibration reduction performance, space utilization, and overall weight, and also generally suffer from complex and time-consuming installation and maintenance procedures.
[0004] Therefore, there is an urgent need for a technical solution to overcome or mitigate at least one of the aforementioned defects in the existing technology. Utility Model Content
[0005] The purpose of this application is to provide an airborne equipment vibration damping mounting structure to solve at least one problem existing in the prior art.
[0006] The technical solution of this application is:
[0007] A vibration damping mounting structure for airborne equipment includes:
[0008] An interior panel, wherein there is a space between the interior panel and the cabin wall panel, and an opening is provided on the interior panel;
[0009] A door body, which is installed at the opening of the interior panel;
[0010] Mounting plate, which is located in the accommodating space and is connected to the interior panel and the cabin wall panel respectively, and the mounting plate is provided with slide rails;
[0011] The support base includes a lower support plate and an upper support plate. The lower support plate is provided with a slider that cooperates with the slide rail. The lower support plate and the upper support plate are connected by an elastic component. The upper support plate has mounting holes for installing airborne equipment.
[0012] In at least one embodiment of this application, a linkage handle is installed on the door.
[0013] In at least one embodiment of this application, the door body is provided with a device identifier.
[0014] In at least one embodiment of this application, the mounting plate is connected to the load-bearing beams of the interior panel and the cabin wall panel, respectively.
[0015] In at least one embodiment of this application, the mounting plate is provided with reinforcing ribs.
[0016] In at least one embodiment of this application, two slide rails are arranged in parallel on the mounting plate, and two sliders are arranged on the lower support plate.
[0017] In at least one embodiment of this application, a limiting member is provided between the slide rail and the slider.
[0018] In at least one embodiment of this application, the resilient component includes:
[0019] The support rod is V-shaped and includes a first diagonal brace, a second diagonal brace, and an intermediate connecting rod connecting the first diagonal brace and the second diagonal brace. The first diagonal brace and the second diagonal brace are connected to the lower support plate.
[0020] The spring seat includes a lower bushing, an upper bushing, and a spring. The lower bushing is connected to the intermediate connecting rod, and the upper bushing is connected to the upper support plate. The lower bushing and the upper bushing are nested together. The spring is sleeved on the outside of the lower bushing and the upper bushing, and the lower bushing and the upper bushing limit the two ends of the spring.
[0021] In at least one embodiment of this application, the resilient component includes:
[0022] The support rod is claw-shaped and includes a first diagonal brace, a second diagonal brace, a third diagonal brace, and an intermediate connecting plate connecting the first diagonal brace, the second diagonal brace, and the third diagonal brace. The first diagonal brace, the second diagonal brace, and the third diagonal brace are connected to the lower support plate.
[0023] The spring seat includes a lower bushing, an upper bushing, and a spring. The lower bushing is connected to the intermediate connecting plate, and the upper bushing is connected to the upper support plate. The lower bushing and the upper bushing are nested together. The spring is sleeved on the outside of the lower bushing and the upper bushing, and the lower bushing and the upper bushing limit the two ends of the spring.
[0024] The utility model has at least the following beneficial technical effects:
[0025] The airborne equipment vibration damping installation structure of this application can effectively reduce the impact of vibration on airborne equipment, greatly improve the space utilization rate on the aircraft, reduce weight, and facilitate installation and maintenance. Attached Figure Description
[0026] Figure 1 This is a schematic diagram of an airborne equipment vibration damping installation structure according to one embodiment of this application;
[0027] Figure 2 This is a schematic diagram of a support base according to one embodiment of this application.
[0028] in:
[0029] 1-Navy wall panel; 2-Interior panel; 3-Door body; 4-Mounting plate; 5-Slide rail; 6-Lower support plate; 7-Upper support plate; 8-Slider; 9-Elastic component. Detailed Implementation
[0030] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.
[0031] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this application.
[0032] The following is in conjunction with the appendix Figures 1 to 2 This application will be described in further detail.
[0033] This application provides an airborne equipment vibration damping mounting structure, including: interior panel 2, door 3, mounting plate 4, and support base.
[0034] Specifically, such as Figure 1As shown, there is a space between the interior panel 2 and the cabin wall panel 1, and the interior panel 2 has an opening. The interior panel 2 also has wiring holes for onboard equipment. A door 3 is installed at the opening of the interior panel 2 and is hinged to one side of the interior panel 2. A linkage handle is installed on the door 3, and a locking tongue that is linked to the linkage handle is provided on the inner side of the door 3. The door 3 is opened and closed by rotating the linkage handle. Preferably, the door 3 has an equipment label recording equipment information. A mounting plate 4 is located in the space and is connected to both the interior panel 2 and the cabin wall panel 1. A slide rail 5 is provided on the mounting plate 4. In a preferred embodiment of this application, the mounting plate 4 is connected to the load-bearing beams of both the interior panel 2 and the cabin wall panel 1 by fasteners to ensure stable assembly. The mounting plate 4 also has reinforcing ribs.
[0035] like Figure 2 As shown, the support base includes a lower support plate 6 and an upper support plate 7. The lower support plate 6 is provided with a slider 8 that cooperates with the slide rail 5. The lower support plate 6 and the upper support plate 7 are connected by an elastic component 9. The upper support plate 7 is provided with mounting holes for installing airborne equipment.
[0036] It is understandable that the number of slide rails 5 and sliders 8 can be set to multiple. In this embodiment, two slide rails 5 are arranged in parallel on the mounting plate 4, and two sliders 8 are arranged on the lower support plate 6. A limiting component is provided between the slide rails 5 and the sliders 8. The limiting component can be in the form of a screw. Screw holes are opened on the slide rails 5 and the sliders 8. When the slide rails 5 and the sliders 8 are assembled in place, they are fixed by the limiting component.
[0037] Multiple elastic components 9 are arranged between the lower support plate 6 and the upper support plate 7. These elastic components 9 can be arranged in a multi-row, multi-column array, and have various structural forms. In one embodiment of this application, the elastic component 9 includes a V-shaped support rod and an elastic seat. In this embodiment, the support rod is V-shaped and includes a first diagonal brace, a second diagonal brace, and an intermediate connecting rod connecting the first and second diagonal braces. The first and second diagonal braces are connected to the lower support plate 6. The spring seat includes a lower bushing, an upper bushing, and a spring. The lower bushing is connected to the intermediate connecting rod, and the upper bushing is connected to the upper support plate 7. The lower and upper bushings are nested together, and the spring is sleeved on the outside of the lower and upper bushings, limiting the two ends of the spring through the lower and upper bushings. In another embodiment of this application, the elastic component 9 includes a claw-shaped support rod and an elastic seat. The support rod is claw-shaped and includes a first diagonal brace, a second diagonal brace, a third diagonal brace, and an intermediate connecting plate connecting the first diagonal brace, the second diagonal brace, and the third diagonal brace. The first diagonal brace, the second diagonal brace, and the third diagonal brace are connected to the lower support plate 6. The spring seat includes a lower bushing, an upper bushing, and a spring. The lower bushing is connected to the intermediate connecting plate, and the upper bushing is connected to the upper support plate 7. The lower bushing and the upper bushing are nested together. The spring is sleeved on the outside of the lower bushing and the upper bushing, and the lower bushing and the upper bushing limit the two ends of the spring.
[0038] In use, the airborne equipment vibration damping installation structure of this application involves installing the airborne equipment onto the upper support plate 7 of the support base using fasteners, opening the door 3 by rotating the linkage handle, placing the support base into the receiving space, and connecting the slider 8 on the support base with the slide rail 5 of the mounting plate 4. After the slider 8 slides into place, it is fixed by a limiting component. The lead wire of the airborne equipment is led out through the lead wire hole on the interior panel 2, and the door 3 is locked by rotating the linkage handle. Equipment identification with equipment information is affixed to the door 3.
[0039] The airborne equipment vibration damping installation structure of this application, through the design of a support base with vibration damping effect, can effectively reduce the impact of vibration on airborne equipment; the airborne equipment is installed in the accommodation space between the interior panel 2 and the cabin wall panel 1, which greatly improves the space utilization rate on the aircraft; the overall structure is simple, with fewer parts, effectively reducing weight; the airborne equipment is installed externally, which facilitates installation and maintenance.
[0040] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.
Claims
1. A vibration damping installation structure for airborne equipment, characterized in that, include: Interior panel (2), there is a space between the interior panel (2) and the cabin wall panel (1), and the interior panel (2) has an opening; Door body (3), said door body (3) is installed at the opening of said interior panel (2); Mounting plate (4), which is located in the accommodating space and is connected to the interior panel (2) and the cabin wall panel (1) respectively. The mounting plate (4) is provided with a slide rail (5). The support base includes a lower support plate (6) and an upper support plate (7). The lower support plate (6) is provided with a slider (8) that cooperates with the slide rail (5). The lower support plate (6) and the upper support plate (7) are connected by an elastic component (9). The upper support plate (7) is provided with mounting holes for installing airborne equipment.
2. The airborne equipment vibration damping installation structure according to claim 1, characterized in that, A linkage handle is installed on the door body (3).
3. The airborne equipment vibration damping installation structure according to claim 2, characterized in that, The door (3) is equipped with equipment markings.
4. The airborne equipment vibration damping installation structure according to claim 1, characterized in that, The mounting plate (4) is connected to the load-bearing beams of the interior panel (2) and the cabin wall panel (1), respectively.
5. The airborne equipment vibration damping installation structure according to claim 4, characterized in that, The mounting plate (4) is provided with reinforcing ribs.
6. The airborne equipment vibration damping installation structure according to claim 5, characterized in that, Two slide rails (5) are arranged in parallel on the mounting plate (4), and two sliders (8) are arranged on the lower support plate (6).
7. The airborne equipment vibration damping installation structure according to claim 6, characterized in that, A limiting element is provided between the slide rail (5) and the slider (8).
8. The airborne equipment vibration damping installation structure according to claim 1, characterized in that, The elastic component (9) includes: The support rod is V-shaped and includes a first diagonal brace, a second diagonal brace, and an intermediate connecting rod connecting the first diagonal brace and the second diagonal brace. The first diagonal brace and the second diagonal brace are connected to the lower support plate (6). The spring seat includes a lower bushing, an upper bushing, and a spring. The lower bushing is connected to the intermediate connecting rod, and the upper bushing is connected to the upper support plate (7). The lower bushing and the upper bushing are nested together. The spring is sleeved on the outside of the lower bushing and the upper bushing, and the two ends of the spring are limited by the lower bushing and the upper bushing.
9. The airborne equipment vibration damping installation structure according to claim 1, characterized in that, The elastic component (9) includes: The support rod is claw-shaped and includes a first diagonal brace, a second diagonal brace, a third diagonal brace, and an intermediate connecting plate connecting the first diagonal brace, the second diagonal brace, and the third diagonal brace. The first diagonal brace, the second diagonal brace, and the third diagonal brace are connected to the lower support plate (6). The spring seat includes a lower bushing, an upper bushing, and a spring. The lower bushing is connected to the intermediate connecting plate, and the upper bushing is connected to the upper support plate (7). The lower bushing and the upper bushing are nested together. The spring is sleeved on the outside of the lower bushing and the upper bushing, and the two ends of the spring are limited by the lower bushing and the upper bushing.