Radar mounting rack with self-adaptive function

Abstract

The utility model discloses a radar mounting rack with a self-adaptive function, which comprises a rack body, a plurality of mutually independent adjusting cavities are arranged on the rack body, a flexible skin is arranged on each adjusting cavity, a self-adaptive support module is further arranged in each adjusting cavity, and the working end of the self-adaptive support module is attached to the flexible skin; a fixing module is further arranged on the frame body, and the fixing module is used for fixing the frame body on the aircraft; compared with the prior art, through cooperation of the flexible skin and the self-adaptive supporting module, the mounting frame can deform according to the shape of the outer surface of the aircraft, so that the mounting frame is tightly attached to the surface of the aircraft, and the mounting stability and reliability of the frame body are improved; and secondly, the mounting requirements of various different mounting point positions can be met, the frame body does not need to be independently designed according to the curved surface shapes of the different point positions of the aircraft, the mounting efficiency of the equipment is improved, and meanwhile, the design procedure of the frame body is simplified.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft auxiliary equipment, and in particular to a radar mounting bracket with adaptive function. Background Art

[0002] Aircraft play an important role in rescue and other aspects. In the prior art, in order to improve the communication and search capabilities of aircraft, a mounting frame is generally set on the surface of the aircraft, and corresponding auxiliary equipment is installed on the mounting frame; however, the mounting frame in the prior art has a simple structure, and its shape is fixed after processing. The surface of the aircraft is generally curved, and the curved surface on the mounting frame may not be able to completely fit the aircraft surface, resulting in poor fit between the mounting frame and the aircraft surface. Utility Model Content

[0003] The main purpose of this application is to provide a radar mounting bracket with adaptive function, aiming to solve the defect of poor fit with the outer surface of the aircraft in the prior art.

[0004] This application achieves the above objectives through the following technical solutions:

[0005] A radar mounting bracket with adaptive function, comprising:

[0006] A frame body is provided with a plurality of independent adjustment cavities, each of which is provided with a flexible skin, and each of which is further provided with an adaptive support module, wherein a working end of the adaptive support module is in contact with the flexible skin;

[0007] A fixed module is provided on the frame and is used to fix the frame on the aircraft.

[0008] Optionally, the frame includes a first main beam and a second main beam, the first main beam and the second main beam are arranged in parallel, and the first main beam and the second main beam are connected by a plurality of cross beams.

[0009] Optionally, the flexible skin includes a skeleton layer made of steel wire mesh, and the surface of the skeleton layer is wrapped with a rubber buffer layer; connecting plates are provided on all four sides of the flexible skin, and the connecting plates are connected to the frame through rivets.

[0010] Optionally, the adaptive support module includes a high-pressure airbag, which is arranged in the adjustment cavity; an inflation nozzle connected to the high-pressure airbag is provided on the frame; a plurality of fixing straps are provided on the high-pressure airbag, and each fixing strap is connected to the adjustment cavity by a mutually cooperating connecting buckle.

[0011] Optionally, the adaptive support module includes several independent adjustment boxes, each of which has a support rod slidably arranged therein, and a reset assembly is arranged in the adjustment box, the reset assembly abuts against one end of the support rod, and the other end of the support rod abuts against the flexible skin.

[0012] Optionally, the reset assembly includes a reset spring, a telescopic hole is provided at one end of the adjustment box, and a sealing plate is threadedly connected to the other end thereof, a step surface is provided on the support rod, one end of the support rod abuts against the reset spring, and the other end thereof extends through the telescopic hole; the step surface abuts against the end face of the telescopic hole.

[0013] Optionally, the free end of the support rod is further rotatably connected to a support sheet, and the support sheet and the flexible skin abut against each other.

[0014] Optionally, a connecting sleeve is provided at the free end of the support rod, an adjusting ball is provided on the support plate, a rotating cavity adapted to the connecting sleeve is provided on the adjusting ball, and a limiting cover is also provided on the support rod.

[0015] Optionally, a retaining frame is further provided in the adjustment cavity, and a plurality of plug-in slots are provided on the retaining frame, and each of the adjustment boxes is inserted into each of the plug-in slots respectively.

[0016] Optionally, the fixing module includes a plurality of patches, each of which is arranged in the cabin of the aircraft, and each of the patches is connected to the frame via rivets.

[0017] Compared with the prior art, this application has the following beneficial effects:

[0018] The present application includes a frame, which is provided with a plurality of mutually independent adjustment cavities, each of which is provided with a flexible skin, and each of which is further provided with an adaptive support module, wherein the working end of the adaptive support module is in contact with the flexible skin; the frame is further provided with a fixing module, and the fixing module is used to fix the frame to the aircraft;

[0019] When in use, the frame is mounted on the outer surface of the aircraft through the fixed module. The flexible skin has a certain deformation ability. The flexible skin is squeezed and lowered on the outer surface of the aircraft to undergo elastic deformation, thereby ensuring the fit between the flexible skin and the outer surface of the aircraft and improving the stability and reliability of the connection. At the same time, the adaptive support module located in the adjustment cavity elastically yields when the flexible skin is pushed down. The adaptive support module will provide stable support for the flexible skin, ensuring that it can fit tightly with the surface of the aircraft.

[0020] Compared with the existing technology, the present application can deform according to the shape of the outer surface of the aircraft, thereby closely fitting with the aircraft surface, improving the stability and reliability of the frame installation;

[0021] Secondly, the present application can adapt to the installation requirements of various installation points, eliminating the need to design the frame separately according to the curved surface shape of different points on the aircraft, which is conducive to improving the installation efficiency of the equipment and simplifying the design process of the frame;

[0022] Finally, the present application can be transferred and installed between different points. It not only has strong adaptability but can also be reused, effectively reducing the cost of the frame. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 A schematic structural diagram of a radar mounting bracket with adaptive function provided in embodiment 1 of the present application;

[0024] Figure 2 An exploded view of a radar mounting bracket with adaptive function provided in embodiment 1 of the present application;

[0025] Figure 3 An exploded view of another optional embodiment of the adaptive support module provided in this application;

[0026] Figure 4 This is the exploded view of the adaptive support module;

[0027] Figure 5 is a cross-sectional view of the adaptive support module;

[0028] Figure 6 is a cross-sectional view of the flexible skin;

[0029] Figure markings: 1-frame, 2-adjusting cavity, 3-flexible skin, 4-high-pressure airbag, 5-inflating nozzle, 6-adjusting box, 7-support rod, 8-return spring, 9-telescopic hole, 10-sealing plate, 11-step surface, 12-support plate, 13-connecting sleeve, 14-adjusting ball, 15-rotating cavity, 16-limiting cover, 17-retaining frame, 18-plug-in slot, 19-patch, 101-first main beam, 102-second main beam, 103-cross beam, 301-skeleton layer, 302-rubber buffer layer, 303-connecting plate.

[0030] The purpose, features and advantages of this application will be further explained in conjunction with embodiments and with reference to the accompanying drawings. 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 all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention 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 this utility model, unless otherwise specified or limited, the terms "connection" and "fixation" should be understood in a broad sense. For example, "fixation" can mean fixed connection, detachable connection, or integration; mechanical connection or electrical connection; direct connection or indirect connection through an intermediate medium; internal communication between two elements or interaction between two elements, unless otherwise specified. For those skilled in the art, the specific meanings of the above terms in this utility model can be understood according to specific circumstances.

[0034] 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 suggesting their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of such features. In addition, the meaning of "and / or" appearing throughout the text includes three parallel schemes. Taking "A and / or B" as an example, it includes scheme A, or scheme B, or a scheme in which A and B are satisfied at the same time. In addition, the technical solutions between the various embodiments can be combined with each other, but it must be based on the ability of ordinary technicians in this field to implement. When the combination of technical solutions is mutually 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.

[0035] Implementation Method 1

[0036] Reference Figures 1 to 6This embodiment, as an optional embodiment of the present application, discloses a radar mounting frame with an adaptive function, including a frame body 1, wherein the frame body 1 includes a first main beam 101 and a second main beam 102, wherein the first main beam 101 and the second main beam 102 are in a long strip structure, and the first main beam 101 and the second main beam 102 are arranged in parallel, and a plurality of cross beams 103 are arranged in parallel between the first main beam 101 and the second main beam 102, wherein one end of each cross beam 103 is connected to the first main beam 101 by a connecting bolt or rivet 304, and the other end thereof is connected to the second main beam 102 by a connecting bolt or rivet 304;

[0037] The structures of the first main beam 101 and the second main beam 102 are identical. An adjustment cavity 2 is provided on the side of the first main beam 101 and the second main beam 102 that is in contact with the aircraft surface. The adjustment cavity 2 is opened on one side facing the aircraft surface.

[0038] The first main beam 101 and the second main beam 102 are both provided with a flexible skin 3, and the flexible skin 3 includes a skeleton layer 301 and a rubber buffer layer 302, wherein the skeleton layer 301 is made of steel mesh, and the rubber buffer layer 302 is attached to the skeleton layer 301;

[0039] The flexible skin 3 has an overall long strip shape, with rubber strips integrally connected along the edge of the flexible skin 3, and the ends of the rubber strips are connected; a connecting plate 303 is also provided on the rubber strip, and the connecting plate 303 is connected to the frame 1 via rivets 304;

[0040] When in use, the flexible skin 3 is plugged and connected to the open end of the adjustment cavity 2 through the connecting plate 303. The inner wall of the connecting plate 303 is tightly fitted with the outer wall of the first main beam 101 or the second main beam 102, and the connection is achieved by rivets 304.

[0041] In the above structure, the skeleton layer 301 can effectively improve the structural strength of the flexible skin 3, while improving the adhesion of the rubber buffer layer 302, thereby extending the service life of the flexible skin 3; secondly, the skeleton layer 301 can effectively increase the deformation pressure of the flexible skin 3, which is beneficial to improving the tightness of the fit between the frame 1 and the aircraft.

[0042] Secondly, the provision of the rubber strips can maintain sufficient adjustment deformation on the first main beam 101 and the second main beam 102, thereby meeting the adjustment requirements;

[0043] Furthermore, an adaptive support module is provided in the regulating chamber 2, and the adaptive support module includes a high-pressure airbag 4. An inflation nozzle 5 is provided on each of the first main beam 101 and the second main beam 102, and the inflation nozzle 5 is respectively connected to the corresponding high-pressure airbag 4;

[0044] During use, the high-pressure airbag 4 is inflated through the inflation nozzle 5. After the inflation is completed, the high-pressure airbag 4 is tightly fitted to the flexible skin 3, thereby providing stable support for the flexible skin 3 through the high-pressure airbag 4. The high-pressure airbag 4 also has a certain elastic deformation ability, ensuring that the flexible skin 3 can be tightly fitted to the surface of the aircraft.

[0045] As another feasible embodiment, the adaptive support module includes a plurality of independent adjustment boxes 6, each of which has the same structure and is cylindrical. Along the axis direction of the adjustment box 6, one end is open and the other end is provided with a telescopic hole 9. It should be noted that the inner diameter of the telescopic hole 9 is smaller than the inner diameter of the adjustment box 6.

[0046] A support rod 7 is slidably provided in the regulating box 6. The support rod 7 is in a T-shaped structure as a whole, and a step surface 11 is provided in the middle thereof. The small end of the support rod 7 extends through the telescopic hole 9, and the large end thereof is located in the regulating box 6. The step surface 11 abuts against the end surface of the telescopic hole 9.

[0047] At the same time, a reset assembly is also provided in the regulating box 6, and the reset assembly includes a reset spring 8, one end of the reset spring 8 and the end surface of the large end of the support rod 7 abut against each other; the open end of the regulating box 6 is also threadedly connected to a sealing plate 10, and the sealing plate 10 abuts against the reset spring 8; at the same time, the sealing plate 10 is also provided with an inner six holes, through which the sealing plate 10 can be easily disassembled and assembled;

[0048] The free end of the support rod 7 is also rotatably provided with a support piece 12, and the support piece 12 and the flexible skin 3 are in contact with each other; a connecting sleeve 13 is provided at the free end of the support rod 7, and a rotating cavity 15 is provided on the connecting sleeve 13;

[0049] The back of the support piece 12 is integrally connected with a plug-in sleeve, and a connecting rod is inserted into the plug-in sleeve. The connecting rod is provided with an adjustment ball 14, and the adjustment ball 14 is adapted to the rotation cavity 15. At the same time, the support rod 7 is also provided with a limit cover 16; the limit cover 16 is also provided with a limit spherical surface, and the limit spherical surface cooperates with the rotation cavity 15 to fix the adjustment ball 14;

[0050] The above structure can give the support sheet 12 a certain rotation margin, thereby adjusting the posture of the support sheet 12 so that it can better fit with the flexible skin 3;

[0051] At the same time, the above structure is combined with the telescopic movement of the support rod 7, so that the support piece 12 has telescopic freedom and rotational freedom, which can better adapt to the curved surface structure of the aircraft and improve the adaptability of the equipment to complex curved surfaces;

[0052] Furthermore, a holder 17 is provided in the adjustment cavity 2, and a plurality of insertion slots 18 are provided on the holder 17, and each of the adjustment boxes 6 is inserted into each of the insertion slots 18;

[0053] The holder 17 can better define the position of each adjustment box 6 to prevent it from sliding under external pressure, thereby improving the stability of the device;

[0054] Furthermore, the mounting frame further includes a fixing module, which includes a plurality of patches 19. Each patch 19 is disposed in the cabin of the aircraft. Each patch 19 is connected to the frame 1 via a rivet 304, thereby fixing the mounting frame to the aircraft via the fixing module.

[0055] When in use, the frame 1 is mounted on the outer surface of the aircraft through the fixed module. The flexible skin 3 has a certain degree of deformation ability. The flexible skin 3 is squeezed and lowered on the outer surface of the aircraft to undergo elastic deformation, thereby ensuring the fit between the flexible skin 3 and the outer surface of the aircraft and improving the stability and reliability of the connection. At the same time, the adaptive support module located in the adjustment cavity 2 elastically yields when the flexible skin 3 is pushed down. The adaptive support module will provide stable support for the flexible skin 3, ensuring that it can fit tightly with the surface of the aircraft.

[0056] Compared with the existing technology, the present application can deform according to the shape of the outer surface of the aircraft, thereby closely fitting with the aircraft surface, improving the stability and reliability of the frame installation;

[0057] Secondly, the present application can adapt to the installation requirements of various installation points, eliminating the need to design the frame separately according to the curved surface shape of different points on the aircraft, which is conducive to improving the installation efficiency of the equipment and simplifying the design process of the frame;

[0058] Finally, the present application can be transferred and installed between different points. It not only has strong adaptability but can also be reused, effectively reducing the cost of the frame.

[0059] The above are only preferred embodiments of the present application and do not limit the patent scope of the present application. Any equivalent structure or equivalent process transformation made using the contents of the present application specification and drawings, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present application.

Claims

1. A radar mounting bracket with adaptive function, characterized in that: include: A frame (1), wherein the frame (1) is provided with a plurality of mutually independent adjustment cavities (2), each of the adjustment cavities (2) is provided with a flexible skin (3), and each of the adjustment cavities (2) is further provided with an adaptive support module, wherein a working end of the adaptive support module is in contact with the flexible skin (3); A fixing module is provided on the frame (1), and is used to fix the frame (1) on the aircraft.

2. The radar mounting bracket with adaptive function according to claim 1, characterized in that: The frame (1) comprises a first main beam (101) and a second main beam (102), wherein the first main beam (101) and the second main beam (102) are arranged in parallel, and the first main beam (101) and the second main beam (102) are connected via a plurality of cross beams (103).

3. The radar mounting bracket with adaptive function according to claim 1, characterized in that: The flexible skin (3) comprises a skeleton layer (301) made of a steel mesh, the surface of the skeleton layer (301) being wrapped with a rubber buffer layer (302); connecting plates (303) are provided on all four sides of the flexible skin (3), and the connecting plates (303) are connected to the frame (1) via rivets.

4. The radar mounting bracket with adaptive function according to claim 1, characterized in that: The adaptive support module comprises a high-pressure airbag (4), which is arranged in the regulating cavity (2); and an inflation nozzle (5) in communication with the high-pressure airbag (4) is provided on the frame (1).

5. The radar mounting bracket with adaptive function according to claim 1, characterized in that: The adaptive support module comprises a plurality of mutually independent adjustment boxes (6), each of which is slidably provided with a support rod (7), and a reset component is provided in the adjustment box (6), the reset component abuts against one end of the support rod (7), and the other end of the support rod (7) abuts against the flexible skin (3).

6. The radar mounting bracket with adaptive function according to claim 5, characterized in that: The reset assembly includes a reset spring (8), a telescopic hole (9) is provided at one end of the regulating box (6), and a sealing plate (10) is threadedly connected at the other end thereof; a step surface (11) is provided on the support rod (7), one end of the support rod (7) abuts against the reset spring (8), and the other end thereof extends through the telescopic hole (9); the step surface (11) and the end surface of the telescopic hole (9) abut against each other.

7. The radar mounting bracket with adaptive function according to claim 6, characterized in that: The free end of the support rod (7) is also rotatably connected to a support sheet (12), and the support sheet (12) and the flexible skin (3) are in contact with each other.

8. The radar mounting bracket with adaptive function according to claim 7, characterized in that: The free end of the support rod (7) is provided with a connecting sleeve (13), the support plate (12) is provided with an adjusting ball (14), the adjusting ball (14) is provided with a rotating cavity (15) adapted to the connecting sleeve (13), and the support rod (7) is also provided with a limiting cover (16) threadedly connected to the adjusting ball (14).

9. The radar mounting bracket with adaptive function according to claim 5, characterized in that: A retaining frame (17) is further provided in the regulating cavity (2), and a plurality of inserting slots (18) are provided on the retaining frame (17), and each regulating box (6) is inserted into each inserting slot (18) respectively.

10. The radar mounting bracket with adaptive function according to claim 1, characterized in that: The fixing module comprises a plurality of patches (19), each of the patches (19) is arranged in the cabin of the aircraft, and each of the patches (19) is connected to the frame (1) via rivets.

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