Radar mounting bracket for aircraft

Abstract

The radar mounting support comprises a support body and a plurality of insertion modules, the top of each insertion module is provided with a plurality of insertion strips, the support body is provided with a plurality of insertion grooves, and each insertion strip is connected with each insertion groove in an insertion mode; each plug-in module is provided with a fitting cambered surface matched with the outer surface of the aircraft; meanwhile, a locking module is further arranged on the frame body, and the locking module is used for fixedly installing the inserting strips in the inserting grooves; the frame body is also connected with a pull rod; the other end of the pull rod is connected with the aircraft; according to the radar mounting rack, the inserting strips and the inserting grooves are matched with one another, so that detachable mounting between the rack body and the inserting modules is realized, that is, when the radar mounting rack is mounted on aircrafts of different models, the rack body is of a universal structure, and matching with the aircrafts can be realized by matching different inserting modules according to different models of the aircrafts; therefore, different use requirements are met, and the universality of the radar mounting rack is improved as much as possible.

Description

Technical Field

[0001] The present application relates to the technical field of aviation equipment, and in particular to a radar mounting bracket for an aircraft. Background Art

[0002] Aircraft play an important role in rescue and other aspects. In order to improve the communication and search capabilities of aircraft, the existing technology generally sets a mounting frame on the surface of the aircraft and installs corresponding auxiliary equipment on the mounting frame. However, the mounting frame in the existing technology has a simple structure and needs to be customized according to different installation points and aircraft models. The mounting frames between different aircraft are not interchangeable, and the versatility of the mounting frame is poor. Utility Model Content

[0003] The main purpose of this application is to provide a radar mounting bracket for an aircraft, aiming to solve the defect of poor versatility in the prior art.

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

[0005] A radar mounting bracket for an aircraft, comprising a frame body;

[0006] A plurality of plug-in modules, each of which is provided with a plurality of plug-in strips on the top, a plurality of plug-in slots on the frame, each of which is plug-in connected to each of the plug-in slots; each of which is provided with a fitting arc surface adapted to the outer surface of the aircraft;

[0007] A locking module, used for fixing the plug strip in the plug slot;

[0008] A pull rod, one end of which is connected to the frame, and the other end of which is connected to the aircraft.

[0009] Optionally, the frame includes a first main beam and a second main beam, the second main beam is arranged parallel to the first main beam, and a plurality of cross beams are arranged between the first main beam and the second main beam, and the two ends of each cross beam are respectively connected to the first main beam and the second main beam.

[0010] Optionally, the plug-in module includes a plug-in beam, and a plug-in strip is integrally connected to the top of the plug-in beam along the length direction of the plug-in beam, the cross-section of the plug-in strip is T-shaped or dovetail-shaped, and the plug-in slot is adapted to the plug-in strip.

[0011] Optionally, two L-shaped plug-in strips are provided on the plug-in beam along the length direction of the plug-in beam, and two plug-in slots are provided on the frame, and the two plug-in slots are respectively adapted to the two plug-in strips.

[0012] Optionally, a buffer rubber strip is further provided on the side of each of the splicing beams that is in contact with the surface of the aircraft, and the contact arc surface is provided on the buffer rubber strip.

[0013] Optionally, a plurality of mutually engaged limiting teeth are provided between the buffer rubber strip and the splicing beam; and an adhesive layer is provided between two of the limiting teeth.

[0014] Optionally, a mounting groove is further provided on the splicing beam, the buffer rubber strip is embedded in the mounting groove, and an adhesive layer is further provided between the buffer rubber strip and the mounting groove.

[0015] Optionally, the radar mounting bracket further includes a plurality of auxiliary beams, each of the auxiliary beams being respectively connected to two adjacent splicing beams.

[0016] Optionally, the locking module includes a plurality of limit blocks, and both ends of each of the plug-in slots are open; each of the limit blocks is respectively inserted into the open end of the plug-in slot; and the limit blocks are provided with fastening screws for fixing them in the plug-in slot.

[0017] Optionally, the radar mounting bracket further includes a reinforcement plate, which is connected to the aircraft and is provided with a plug hole adapted to the pull rod.

[0018] Compared with the prior art, this application has the following beneficial effects:

[0019] The present application includes a frame and several plug-in modules, each of which is provided with several plug-in strips on the top, and a plurality of plug-in slots on the frame, each of which is plug-in connected to each of the plug-in slots; each of the plug-in modules is provided with a fitting arc surface adapted to the outer surface of the aircraft; a locking module is also provided on the frame, and the locking module is used to fix the plug-in strip in the plug-in slot; the frame is also connected to a pull rod, and the other end of the pull rod is connected to the aircraft;

[0020] Compared with the prior art, the present application realizes detachable installation between the frame and each plug-in module by the mutual cooperation between the plug-in strip and the plug-in slot. That is, when the radar mounting bracket is installed on different models of aircraft, the frame has a universal structure and only needs to match different plug-in modules according to different aircraft models to achieve matching with the aircraft, thereby meeting different usage requirements and maximizing the versatility of the radar mounting bracket.

[0021] Secondly, due to the large number of aircraft models and the fixed structure of the mounting frame, the existing technology usually adopts a fixed-value radar mounting bracket, which is relatively expensive. The technical solution described in this application only requires replacing the plug-in module to achieve switching between different aircraft, which is conducive to reducing the cost of the mounting frame. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 A schematic structural diagram of a radar mounting bracket for an aircraft provided in Embodiment 1 of the present application;

[0023] Figure 2 An exploded view of a radar mounting bracket for an aircraft provided in embodiment 1 of the present application;

[0024] Figure 3 A side view of a radar mounting bracket for an aircraft provided in embodiment 1 of the present application;

[0025] Figure 4 A cross-sectional view of another optional embodiment of the radar mounting bracket provided in this application;

[0026] Figure markings: 1-frame, 2-connecting strip, 3-connecting groove, 4-fitting arc surface, 5-pull rod, 6-connecting beam, 7-buffer rubber strip, 8-limiting tooth, 9-adhesive layer, 10-installation groove, 11-auxiliary beam, 12-limiting block, 13-fastening screw, 14-reinforcement plate, 15-connecting hole, 101-first main beam, 102-second main beam, 103-cross beam.

[0027] 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

[0028] 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.

[0029] 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.

[0030] 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.

[0031] 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.

[0032] Implementation Method 1

[0033] Reference Figures 1 to 4 This embodiment is an optional embodiment of the present application, which discloses a radar mounting bracket for an aircraft, wherein the frame 1 includes a first main beam 101 and a second main beam 102, the second main beam 102 is arranged parallel to the first main beam 101, and a plurality of cross beams 103 are arranged between the first main beam 101 and the second main beam 102, and the two ends of each cross beam 103 are respectively connected to the first main beam 101 and the second main beam 102.

[0034] The radar mounting bracket further includes a pull rod 5 and a reinforcement plate 14, wherein the reinforcement plate 14 is provided with a plug hole 15; when in use, a connection hole is opened on the surface of the aircraft, and the reinforcement plate 14 covers the connection hole and reinforces the connection hole to ensure the stability and safety of the aircraft;

[0035] One end of the pull rod 5 is connected to the cross beam 103, and the other end thereof passes through the plug hole 15 and is connected to the internal structure of the aircraft;

[0036] The arrangement of the tie rod 5 enables the radar mounting bracket to be tightly connected to the internal structure of the aircraft, thereby effectively improving the stability and reliability of the connection. The reinforcement plate 14 is used to structurally reinforce the area where the tie rod 5 penetrates, which is beneficial to improving the structural strength of the aircraft.

[0037] The radar mounting bracket further includes a plurality of plug-in modules, the number of which is two, corresponding to the first main beam 101 and the second main beam 102 respectively. That is, if three or more main beams are provided, additional plug-in modules can be provided as needed;

[0038] The radar mounting bracket further includes a plurality of auxiliary beams 11, each of the auxiliary beams 11 being disposed between two adjacent plug-in beams 6, and each of the auxiliary beams being connected to two adjacent plug-in beams 6;

[0039] If two splicing beams 6 are provided, each auxiliary beam 11 is connected to the two auxiliary beams 11 respectively. If three splicing beams 6 are provided, each auxiliary beam 11 is divided into two groups, each connected to the adjacent splicing beams 6 respectively.

[0040] The plug-in module includes a plug-in beam 6, and a plug-in strip 2 is integrally connected to the top of the plug-in beam 6 along the length direction of the plug-in beam 6. The plug-in strip 2 is provided with at least one, and preferably, 2-3 plug-in strips 2 are provided;

[0041] At the same time, the same number of plug-in slots 3 are provided on the bottom surfaces of the first main beam 101 and the second main beam 102, and each of the plug-in slots 3 is adapted to each of the plug-in strips 2;

[0042] It should be noted that the cross section of the plug strip 2 is T-shaped or dovetail-shaped, and the shape of the plug slot 3 is adapted to the shape of the plug strip 2;

[0043] Furthermore, along the length direction of the splicing beam 6, two splicing strips 2 are provided on the top surface of the splicing beam 6, the cross-sections of the two splicing strips 2 are L-shaped, and the two splicing strips 2 are symmetrically provided with respect to the length direction of the splicing beam 6;

[0044] At the same time, corresponding plug-in slots 3 are provided on the first main beam 101 and the second main beam 102;

[0045] The above-mentioned structural arrangement effectively improves the connection strength between the splicing beam 6 and the first main beam 101 or the second main beam 102, thereby ensuring the stability and reliability of the connection;

[0046] Secondly, the above connection can be achieved by pushing and pulling the splicing beam 6, which is easy to remove and install, thereby improving the convenience of using the equipment.

[0047] Furthermore, a locking module is provided between the plug strip 2 and the plug slot 3. The locking module includes a plurality of limit blocks 12. The number of the limit blocks 12 is set according to the number of open ends of the plug slot 3.

[0048] It should be pointed out that the length of the plug-in slot 3 is greater than the length of the plug-in strip 2. Along the axial direction of the plug-in slot 3, both ends of the plug-in slot 3 can be set to an open structure, or one open end can be set. Each limit block 12 is inserted into the open end of each plug-in slot 3 respectively. At the same time, a fastening screw 13 is provided on each limit block 12. Mutually matching screw holes are provided on the plug-in slot 3 and the limit block 12. The fastening screw 13 passes through the screw hole, thereby fixing the limit block 12 in the plug-in slot 3.

[0049] The locking module has a simple structure and can achieve stable positioning in the plug-in direction, thereby preventing the plug-in beam 6 from separating from the main beam.

[0050] Furthermore, a buffer rubber strip 7 is provided on each of the splicing beams 6, and the buffer rubber strip 7 is provided on the side of the splicing beam 6 facing the aircraft; a side of each of the buffer rubber strips 7 that is in contact with the aircraft is provided with a fitting cambered surface 4, and the fitting cambered surface 4 is in close contact with the surface of the aircraft;

[0051] A plurality of limiting teeth 8 are provided on the side of the buffer rubber strip 7 that contacts the splicing beam 6. A plurality of limiting teeth 8 are also provided on the bottom surface of the splicing beam 6. The two groups of limiting teeth 8 are engaged with each other. An adhesive layer 9 is provided between the two limiting teeth 8.

[0052] The adhesive layer 9 can ensure the stability and reliability of the connection between the case punching strip and the plug-in beam 6. At the same time, the mutual engagement of the limiting teeth 8 can effectively limit the displacement between the buffer strip 7 and the plug-in beam 6 while increasing the area of ​​the adhesive layer 9, thereby further improving the stability of the connection.

[0053] Furthermore, a mounting groove 10 is provided on the splicing beam 6, and the buffer rubber strip 7 is embedded in the mounting groove 10, and an adhesive layer 9 is provided between the buffer rubber strip 7 and the mounting groove 10;

[0054] The installation groove 10 can effectively limit the displacement between the buffer rubber strip 7 and the plug-in beam 6; it should be pointed out that mutually engaging limiting teeth 8 can also be provided between the bottom surface of the installation groove 10 and the buffer rubber strip 7 to further improve the stability and reliability of the connection.

[0055] Compared with the prior art, the present application realizes detachable installation between the frame and each plug-in module by the mutual cooperation between the plug-in strip and the plug-in slot. That is, when the radar mounting bracket is installed on different models of aircraft, the frame has a universal structure and only needs to match different plug-in modules according to different aircraft models to achieve matching with the aircraft, thereby meeting different usage requirements and maximizing the versatility of the radar mounting bracket.

[0056] Secondly, due to the large number of aircraft models and the fixed structure of the mounting frame, the existing technology usually adopts a fixed-value radar mounting bracket, which is relatively expensive. The technical solution described in this application only requires replacing the plug-in module to achieve switching between different aircraft, which is conducive to reducing the cost of the mounting frame.

[0057] 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 for an aircraft, characterized in that: comprising a frame (1); A plurality of plug-in modules, each of which is provided with a plurality of plug-in strips (2) on the top, a plurality of plug-in slots (3) on the frame (1), each of which is plug-in connected to each of the plug-in slots (3); each of which is provided with a fitting arc surface (4) adapted to the outer surface of the aircraft; A locking module, the locking module being used to fix the plug strip (2) in the plug slot (3); A pull rod (5), one end of which is connected to the frame (1), and the other end of which is connected to the aircraft.

2. The radar mounting bracket for an aircraft according to claim 1, characterized in that: The frame (1) comprises a first main beam (101) and a second main beam (102), wherein the second main beam (102) is arranged parallel to the first main beam (101), and a plurality of cross beams (103) are arranged between the first main beam (101) and the second main beam (102), and the two ends of each cross beam (103) are respectively connected to the first main beam (101) and the second main beam (102).

3. The radar mounting bracket for an aircraft according to claim 1, characterized in that: The plug-in module comprises a plug-in beam (6), a plug-in strip (2) integrally connected to the top of the plug-in beam (6) along the length direction of the plug-in beam (6), the cross section of the plug-in strip (2) being T-shaped or dovetail-shaped, and the plug-in slot (3) being adapted to the plug-in strip (2).

4. The radar mounting bracket for an aircraft according to claim 3, characterized in that: Two L-shaped plug-in bars (2) are provided on the plug-in beam (6) along the length direction of the plug-in beam (6), and two plug-in slots (3) are provided on the frame (1), and the two plug-in slots (3) are respectively adapted to the two plug-in bars (2).

5. A radar mounting bracket for an aircraft according to claim 3 or 4, characterized in that: A buffer rubber strip (7) is also provided on the side of each of the splicing beams (6) that is in contact with the aircraft surface, and the contact cambered surface (4) is provided on the buffer rubber strip (7).

6. The radar mounting bracket for an aircraft according to claim 5, characterized in that: A plurality of mutually engaged limiting teeth (8) are provided between the buffer rubber strip (7) and the splicing beam (6); and an adhesive layer (9) is provided between two of the limiting teeth (8).

7. The radar mounting bracket for an aircraft according to claim 5, characterized in that: The splicing beam (6) is further provided with a mounting groove (10), the buffer rubber strip (7) is embedded in the mounting groove (10), and an adhesive layer (9) is further provided between the buffer rubber strip (7) and the mounting groove (10).

8. The radar mounting bracket for an aircraft according to claim 3, characterized in that: The radar mounting bracket further comprises a plurality of auxiliary beams (11), each of the auxiliary beams (11) being connected to two adjacent splicing beams (6).

9. The radar mounting bracket for an aircraft according to claim 1, characterized in that: The locking module comprises a plurality of limit blocks (12), both ends of each of the plug-in slots (3) are open; each of the limit blocks (12) is respectively inserted into the open end of the plug-in slot (3); and a fastening screw (13) is provided on the limit block (12) for fixing it in the plug-in slot (3).

10. The radar mounting bracket for an aircraft according to claim 1, characterized in that: The radar mounting bracket further comprises a reinforcing plate (14), the reinforcing plate (14) being connected to the aircraft, and a plug hole (15) adapted to the pull rod (5) being provided on the reinforcing plate (14).

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