Aircraft radar pod support and aircraft

Abstract

The present application relates to an aircraft radar compartment support and an aircraft. The aircraft radar compartment support comprises a mounting plate, a first reinforcing rib and a second reinforcing rib; wherein the mounting plate is used to be connected with system equipment arranged in the radar compartment, the first reinforcing rib and the second reinforcing rib each comprise an end panel and a bottom panel, the bottom panel is substantially perpendicular to the end panel, the end panel of each of the first reinforcing rib and the second reinforcing rib is mounted on a front end panel of the radar compartment, the bottom panel of each of the first reinforcing rib and the second reinforcing rib is connected with a top surface of the mounting plate, and the bottom panel of the first reinforcing rib and the bottom panel of the second reinforcing rib are respectively arranged near two opposite side edges of the mounting plate. According to the above technical scheme, the present application can achieve the following beneficial technical effects: the system equipment in the radar compartment is stably mounted, the radome and the system equipment and the cable thereof are not damaged, and the increasing weight of the system equipment and the requirement for mounting stability can be met.

Description

Technical Field

[0001] The present invention relates to an aircraft radar compartment support and an aircraft including the aircraft radar compartment support. Background Technology

[0002] In existing technologies, the connection between system equipment and radomes in systems such as visual enhancement systems is often based solely on ease of placement, resulting in direct slinging onto the radome. Consequently, the radome directly bears the entire weight of the system equipment, leading to deformation due to the constant strain from the equipment's weight during operation. Furthermore, opening the radome can easily pull on the cables connecting the system equipment, causing damage. Additionally, this slinging method limits the weight of the system equipment and hinders the expansion and enhancement of its functionality. Summary of the Invention

[0003] One object of the present invention is to provide an aircraft radar compartment bracket that overcomes at least some of the defects of the prior art, ensures stable installation of system equipment inside the radar compartment, does not damage the radome and system equipment and their cables, and meets the increasing weight of system equipment and the requirements for installation stability.

[0004] The above-mentioned objectives of the present invention are achieved by an aircraft radar compartment bracket, which includes a mounting plate, a first reinforcing rib, and a second reinforcing rib.

[0005] The mounting plate is used to connect with system equipment arranged in the radar compartment. The first reinforcing rib and the second reinforcing rib each include an end panel and a bottom panel. The bottom panel is substantially perpendicular to the end panel. The end panel of each of the first reinforcing ribs and the second reinforcing ribs is mounted on the front end plate of the radar compartment. The bottom panel of each of the first reinforcing ribs and the second reinforcing ribs is connected to the top surface of the mounting plate. The bottom panels of the first reinforcing rib and the second reinforcing rib are respectively located near two opposite sides of the mounting plate.

[0006] According to the above technical solution, the aircraft radar compartment bracket of the present invention can achieve the following beneficial technical effects: the system equipment inside the radar compartment is installed stably, without damaging the radar dome and system equipment and their cables, and can meet the increasing weight of the system equipment and the requirements for installation stability.

[0007] Preferably, the aircraft radar compartment bracket further includes a third reinforcing rib, which is disposed between the first reinforcing rib and the second reinforcing rib. The third reinforcing rib also includes an end panel and a bottom panel, with the bottom panel being substantially perpendicular to the end panel. The end panel of the third reinforcing rib is mounted on the front end plate of the radar compartment, and the bottom panel of the third reinforcing rib is connected to the top surface of the mounting plate.

[0008] Preferably, the aircraft radar bay bracket further includes a first adjusting bolt, a second adjusting bolt, a third adjusting bolt, and a fourth adjusting bolt;

[0009] The bottom panel of the first reinforcing rib is provided with a first internal thread component and a second internal thread component. The first internal thread component is located near the front end of the bottom panel of the first reinforcing rib, and the second internal thread component is located near the rear end of the bottom panel of the first reinforcing rib.

[0010] The bottom panel of the second reinforcing rib is provided with a third internal thread component and a fourth internal thread component. The third internal thread component is located near the rear end of the bottom panel of the second reinforcing rib, and the fourth internal thread component is located near the front end of the bottom panel of the second reinforcing rib.

[0011] The first adjusting bolt, the second adjusting bolt, the third adjusting bolt, and the fourth adjusting bolt are respectively inserted into holes in the first internal thread component, the second internal thread component, the third internal thread component, the fourth internal thread component, and the corresponding reinforcing rib bottom panel, thereby pressing against the top surface of the mounting plate.

[0012] Preferably, each of the first internal threaded component, the second internal threaded component, the third internal threaded component, and the fourth internal threaded component is a nut.

[0013] Preferably, each of the first internal threaded component, the second internal threaded component, the third internal threaded component, and the fourth internal threaded component is a threaded hole in the bottom panel of the corresponding reinforcing rib.

[0014] Preferably, when it is necessary to adjust the pitch angle of the system equipment, the first adjusting bolt, the fourth adjusting bolt, or the second adjusting bolt and the third adjusting bolt are adjusted in pairs.

[0015] Preferably, when it is necessary to adjust the roll angle of the system equipment, the first adjusting bolt, the second adjusting bolt, or the third adjusting bolt and the fourth adjusting bolt are adjusted in pairs.

[0016] Preferably, the mounting plate is connected to the system device by means of fasteners provided in fastener holes in the mounting plate.

[0017] Preferably, the fastener hole is an oblong hole, and when it is necessary to adjust the yaw angle of the system device, the system device is rotated along the direction of the oblong hole.

[0018] The above-mentioned objectives of the present invention are also achieved by an aircraft comprising an aircraft radar bay support as described in any of the above aspects.

[0019] According to the above technical solution, the aircraft of the present invention can achieve the following beneficial technical effects: the installation of the system equipment in the radar compartment is stable, it will not damage the radar dome and system equipment and their cables, and it can meet the increasing weight of the system equipment and the requirements for installation stability. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the installation of an aircraft radar compartment bracket according to an embodiment of the present invention.

[0021] Figure 2 This is a schematic diagram of the position of the adjusting bolts in the aircraft radar compartment bracket according to an embodiment of the present invention.

[0022] Figure 3 This is a schematic diagram illustrating the use of adjusting bolts in an aircraft radar compartment bracket according to an embodiment of the present invention.

[0023] Figure 4 This is a schematic diagram of yaw angle adjustment in an aircraft radar compartment support according to an embodiment of the present invention.

[0024] List of reference numerals

[0025] 10: Mounting plate;

[0026] 11: First reinforcing rib;

[0027] 12: Second reinforcing rib;

[0028] 13: Third reinforcing rib;

[0029] 20: System equipment;

[0030] 21: End panel;

[0031] 22: Bottom panel;

[0032] 30: Front panel of the radar compartment;

[0033] 31: First adjusting bolt;

[0034] 32: Second adjusting bolt;

[0035] 33: Third adjusting bolt;

[0036] 34: Fourth adjusting bolt;

[0037] 41: First internal thread component;

[0038] 42: Second internal thread component;

[0039] 43: Third internal thread component;

[0040] 44: Fourth internal thread component;

[0041] 51: Fastener hole;

[0042] 52: Fasteners. Detailed Implementation

[0043] The following describes specific embodiments of the present invention. It should be noted that, in order to provide a concise description, this specification cannot exhaustively describe all features of the actual embodiments. It should be understood that, in the actual implementation of any embodiment, just as in any engineering or design project, various specific decisions are often made to achieve the developer's specific goals and to meet system-related or business-related constraints, and this can change from one embodiment to another. Furthermore, it is understood that although the efforts made in this development process may be complex and lengthy, for those skilled in the art related to the content disclosed in this invention, some design, manufacturing, or production modifications based on the technical content disclosed herein are merely conventional technical means and should not be construed as insufficient content of this disclosure.

[0044] Unless otherwise defined, the technical or scientific terms used in the claims and description shall have the ordinary meaning understood by one of ordinary skill in the art to which this invention pertains. The terms "first," "second," and similar terms used in the patent application description and claims of this invention do not indicate any order, quantity, or importance, but are merely used to distinguish different components. The terms "an" or "a" and similar terms do not indicate a quantity limitation, but rather indicate the presence of at least one. The terms "comprising" or "including" and similar terms mean that the element or object preceding "comprising" or "including" encompasses the element or object listed following "comprising" or "including" and its equivalents, and do not exclude other elements or objects. The terms "connected" or "linked" and similar terms are not limited to physical or mechanical connections, nor are they limited to direct or indirect connections.

[0045] In the following description, in order to clearly demonstrate the structure and operation of the present invention, a number of directional terms will be used. However, terms such as "front," "rear," "left," "right," "outer," "inner," "outward," "inward," "up," and "down" should be understood as convenient terms and not as limiting terms. In particular, it should be noted that "front" and "rear" are determined according to the heading of the aircraft.

[0046] Figure 1 This is a schematic diagram of the installation of an aircraft radar compartment bracket according to an embodiment of the present invention. Figure 2This is a schematic diagram of the position of the adjusting bolts in the aircraft radar compartment bracket according to an embodiment of the present invention. Figure 3 This is a schematic diagram illustrating the use of adjusting bolts in an aircraft radar compartment bracket according to an embodiment of the present invention. Figure 4 This is a schematic diagram of yaw angle adjustment in an aircraft radar compartment support according to an embodiment of the present invention.

[0047] like Figure 1 As shown, an aircraft radar bay bracket according to an embodiment of the present invention includes a mounting plate 10, a first reinforcing rib 11, and a second reinforcing rib 12;

[0048] The mounting plate 10 is used to connect with system equipment 20 (e.g., a vision enhancement system) arranged in the radar compartment. The first reinforcing rib 11 and the second reinforcing rib 12 each include an end panel 21 and a bottom panel 22. The bottom panel 22 is substantially perpendicular to the end panel 21. The end panel 21 of each of the first reinforcing ribs 11 and the second reinforcing rib 12 is mounted on the front end plate 30 of the radar compartment, thereby forming a fixed base for the bracket installation. The bottom panel 22 of each of the first reinforcing ribs 11 and the second reinforcing rib 12 is connected to the top surface of the mounting plate 10, thereby forming a stable triangular mounting support structure. The bottom panels 22 of the first reinforcing rib 11 and the second reinforcing rib 12 are respectively located near two opposite sides (e.g., the left side and the right side) of the mounting plate 10.

[0049] According to the above technical solution, the aircraft radar compartment bracket of the present invention can achieve the following beneficial technical effects: the system equipment inside the radar compartment is installed stably, without damaging the radar dome and system equipment and their cables, and can meet the increasing weight of the system equipment and the requirements for installation stability.

[0050] Specifically, this invention utilizes a combined bracket installation scheme of reinforcing ribs and mounting plates to connect the system equipment to the fuselage (radar compartment front panel), avoiding direct connection between the system equipment and the radome. This ensures safe separation of the system equipment from the radome, stable installation of the system equipment within the radar compartment, and prevents damage to the radome. Furthermore, because the system equipment is not connected to the radome, opening the radome will not pull on the cables connecting the system equipment, thus preventing damage to the system equipment and its cables. This enhances the safety of system equipment operation without altering the fuselage structural design. Moreover, this invention overcomes the weight limitations of hoisting methods on system equipment and meets the increasing weight and installation stability requirements of system equipment.

[0051] It should be noted that "near the side" here refers to the side of the mounting plate 10 (e.g., the left or right side), for example, within 20%, 10%, or 5% of the lateral (i.e., substantially perpendicular to the heading) length of the mounting plate from the side of the mounting plate.

[0052] In some embodiments, such as Figure 1As shown, the aircraft radar compartment support also includes a third reinforcing rib 13, which is disposed between the first reinforcing rib 11 and the second reinforcing rib 12. The third reinforcing rib 13 also includes an end panel 21 and a bottom panel 22. The bottom panel 22 is substantially perpendicular to the end panel 21. The end panel 21 of the third reinforcing rib 13 is mounted on the front end plate 30 of the radar compartment, and the bottom panel 22 of the third reinforcing rib 13 is connected to the top surface of the mounting plate 10.

[0053] Preferably, such as Figure 1 As shown, the first reinforcing rib 11 and the second reinforcing rib 12 are arranged parallel to each other. Preferably, as shown... Figure 1 As shown, the third reinforcing rib 13 is also arranged parallel to the first reinforcing rib 11 and the second reinforcing rib 12.

[0054] Preferably, the spacing between two adjacent reinforcing ribs is substantially equal. For example, as shown... Figure 1 As shown, the distance between the first reinforcing rib 11 and the third reinforcing rib 13 is basically equal to the distance between the second reinforcing rib 12 and the third reinforcing rib 13.

[0055] Of course, the number of reinforcing ribs mentioned above (two or three) is only a preferred form of the aircraft radar compartment support frame of this application. Those skilled in the art can understand, based on the disclosure of this application, that other suitable numbers of reinforcing ribs (e.g., four, five, etc.) can also be used without departing from the protection scope of the claims of this application.

[0056] Preferably, such as Figure 1 As shown, the ratio of the bottom panel length to the end panel length of the reinforcing rib is 1 to 2:1. By using this suitable ratio range, the radar cabin system equipment can be stably installed while providing sufficient installation space and leeway. Even better, as... Figure 1 As shown, the ratio between the length of the bottom panel and the length of the end panel of the reinforcing rib is 1.2 to 1.8:1.

[0057] In some embodiments, such as Figures 1 to 3 As shown, the aircraft radar bay support also includes a first adjusting bolt 31, a second adjusting bolt 32, a third adjusting bolt 33, and a fourth adjusting bolt 34;

[0058] The bottom panel 22 of the first reinforcing rib 11 is provided with a first internal thread component 41 and a second internal thread component 42. The first internal thread component 41 is located near the front end of the bottom panel 22 of the first reinforcing rib 11, and the second internal thread component 42 is located near the rear end of the bottom panel 22 of the first reinforcing rib 11.

[0059] The bottom panel 22 of the second reinforcing rib 12 is provided with a third internal thread component 43 and a fourth internal thread component 44. The third internal thread component 43 is located near the rear end of the bottom panel 22 of the second reinforcing rib 12, and the fourth internal thread component 44 is located near the front end of the bottom panel 22 of the second reinforcing rib 12.

[0060] The first adjusting bolt 31, the second adjusting bolt 32, the third adjusting bolt 33 and the fourth adjusting bolt 34 are respectively inserted into the holes in the first internal thread component 41, the second internal thread component 42, the third internal thread component 43 and the fourth internal thread component 44 and the corresponding reinforcing rib bottom panel 22, thereby pressing against the top surface of the mounting plate 10.

[0061] It should be noted that "near the front (rear) end" here refers to the end of the bottom panel (e.g., the front or rear end), such as within 20%, 10%, or 5% of the bottom panel length from the end of the bottom panel.

[0062] In some embodiments, such as Figure 3 As shown, each of the first internal threaded component 41, the second internal threaded component 42, the third internal threaded component 43, and the fourth internal threaded component 44 is a nut. Preferably, the nut is pre-fixed to the reinforcing rib as a whole, for example, the nut may be a plate nut or the nut may be welded to the reinforcing rib.

[0063] In some embodiments, each of the first internal threaded component 41, the second internal threaded component 42, the third internal threaded component 43, and the fourth internal threaded component 44 is a threaded hole in the corresponding reinforcing rib bottom panel 22. That is, the first adjusting bolt 31, the second adjusting bolt 32, the third adjusting bolt 33, and the fourth adjusting bolt 34 are respectively inserted through the threaded holes in the corresponding reinforcing rib bottom panel 22 (without the need for additional nuts), thereby pressing against the top surface of the mounting plate 10.

[0064] In some embodiments, such as Figures 1 to 3 As shown, when it is necessary to adjust the pitch angle of the system equipment 20, the first adjusting bolt 31 and the fourth adjusting bolt 34 or the second adjusting bolt 32 and the third adjusting bolt 33 are adjusted in pairs.

[0065] In some embodiments, such as Figures 1 to 3 As shown, when it is necessary to adjust the roll angle of the system equipment 20, the first adjusting bolt 31, the second adjusting bolt 32 or the third adjusting bolt 33, and the fourth adjusting bolt 34 are adjusted in pairs.

[0066] In some embodiments, such as Figure 4 As shown, the mounting plate 10 is connected to the system device 20 via fasteners 52 provided in the fastener holes 51 of the mounting plate 10.

[0067] In some embodiments, such as Figure 4 As shown, the fastener hole 51 is an oblong hole. When it is necessary to adjust the yaw angle of the system device 20, the system device 20 is rotated along the direction of the oblong hole.

[0068] In some embodiments, after the adjustment is completed, the bolts are injected with glue or locked with fuses before the system equipment can be installed.

[0069] The main innovations of the aircraft radar compartment bracket of this invention are as follows:

[0070] (1) The installation of the system equipment inside the radar cabin is stable and will not damage the radar dome and system equipment and their cables, and can meet the increasing weight of the system equipment and the requirements for installation stability.

[0071] (2) The installation angle of the system equipment is adjusted by combining different bolts with internal threaded components, thereby solving the problem that the existing technology cannot accurately adjust the installation angle of the system equipment.

[0072] According to one embodiment of the present invention, the aircraft includes an aircraft radar bay support as described in any of the above aspects. Based on the above technical solution, the aircraft of the present invention can achieve the following beneficial technical effects: the system equipment inside the radar bay is installed stably, without damaging the radome and system equipment and their cables, and can meet the increasing weight of the system equipment and the requirements for installation stability.

[0073] The specific embodiments of the present invention have been described above. However, those skilled in the art will understand that the above specific embodiments do not constitute a limitation on the present invention. Those skilled in the art can make various modifications based on the above disclosure without exceeding the scope of the present invention.

Claims

1. An aircraft radar compartment support, the aircraft radar compartment support comprising a mounting plate, a first reinforcing rib, and a second reinforcing rib; in, The mounting plate is used to connect with system equipment arranged in the radar compartment. The first reinforcing rib and the second reinforcing rib each include an end panel and a bottom panel. The bottom panel is substantially perpendicular to the end panel. The end panel of each of the first reinforcing ribs and the second reinforcing ribs is mounted on the front end plate of the radar compartment. The bottom panel of each of the first reinforcing ribs and the second reinforcing ribs is connected to the top surface of the mounting plate. The bottom panels of the first reinforcing rib and the second reinforcing rib are respectively located near two opposite sides of the mounting plate. The first reinforcing rib and the second reinforcing rib are arranged parallel to each other. The aircraft radar compartment support also includes a first adjusting bolt, a second adjusting bolt, a third adjusting bolt, and a fourth adjusting bolt; The bottom panel of the first reinforcing rib is provided with a first internal thread component and a second internal thread component. The first internal thread component is located near the front end of the bottom panel of the first reinforcing rib, and the second internal thread component is located near the rear end of the bottom panel of the first reinforcing rib. The bottom panel of the second reinforcing rib is provided with a third internal thread component and a fourth internal thread component. The third internal thread component is located near the rear end of the bottom panel of the second reinforcing rib, and the fourth internal thread component is located near the front end of the bottom panel of the second reinforcing rib. The first adjusting bolt, the second adjusting bolt, the third adjusting bolt, and the fourth adjusting bolt are respectively inserted into holes in the first internal thread component, the second internal thread component, the third internal thread component, the fourth internal thread component, and the corresponding reinforcing rib bottom panel, thereby pressing against the top surface of the mounting plate.

2. The aircraft radar bay support as described in claim 1, characterized in that, The aircraft radar compartment support also includes a third reinforcing rib, which is disposed between the first reinforcing rib and the second reinforcing rib. The third reinforcing rib also includes an end panel and a bottom panel. The bottom panel is substantially perpendicular to the end panel. The end panel of the third reinforcing rib is mounted on the front end plate of the radar compartment, and the bottom panel of the third reinforcing rib is connected to the top surface of the mounting plate.

3. The aircraft radar bay support as described in claim 1, characterized in that, Each of the first internal threaded component, the second internal threaded component, the third internal threaded component, and the fourth internal threaded component is a nut.

4. The aircraft radar bay support as described in claim 1, characterized in that, Each of the first internal threaded component, the second internal threaded component, the third internal threaded component, and the fourth internal threaded component is a threaded hole in the bottom panel of the corresponding reinforcing rib.

5. The aircraft radar bay support as described in claim 1, characterized in that, When it is necessary to adjust the pitch angle of the system equipment, the first adjusting bolt, the fourth adjusting bolt, or the second adjusting bolt and the third adjusting bolt are adjusted in pairs.

6. The aircraft radar bay support as described in claim 1, characterized in that, When it is necessary to adjust the roll angle of the system equipment, the first adjusting bolt, the second adjusting bolt, or the third adjusting bolt and the fourth adjusting bolt are adjusted in pairs.

7. The aircraft radar bay support as described in claim 1, characterized in that, The mounting plate is connected to the system equipment via fasteners provided in fastener holes in the mounting plate.

8. The aircraft radar bay support as described in claim 7, characterized in that, The fastener hole is an oblong hole. When it is necessary to adjust the yaw angle of the system device, the system device is rotated along the direction of the oblong hole.

9. An aircraft comprising an aircraft radar bay support as claimed in any one of claims 1-8.

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