Conformal antenna disassembly and assembly method and structure for invisible platform

Abstract

The invention provides a stealth platform conformal antenna disassembly and assembly method and structure, and belongs to the technical field of stealth aircraft antenna installation structures.The method comprises the steps that S10, at least two disassembly and assembly threaded process holes are formed in a conformal area of an aircraft skin structure opening frame and an antenna aperture; s20, at least two handles matched with the disassembly and assembly threaded process holes are arranged; s30, when the antenna aperture needs to be disassembled, the handle is installed in the disassembly and assembly threaded process hole in a threaded mode, and the antenna aperture is disassembled from the aircraft skin by pulling the handle outwards; when the antenna aperture is installed on the aircraft skin and does not need to be dismounted, the dismounting threaded process hole is blocked by a process screw. According to the conformal antenna aperture disassembly and assembly method for the stealth platform, the repeatability and safety of conformal antenna aperture disassembly and assembly are guaranteed in design, meanwhile, the unified method for full-machine antenna aperture disassembly and assembly is standardized, the antenna aperture disassembly and assembly time is shortened, and the consistency of stealth performance after disassembly and assembly is guaranteed.

Description

Technical Field

[0001] The present application belongs to the technical field of stealth aircraft antenna installation structures, and in particular, relates to a stealth platform conformal antenna disassembly and assembly method and structure. Background Art

[0002] The stealth platform is equipped with a variety of sensors such as communication, navigation, surveillance, and detection. In order to ensure the continuity of the aircraft's stealth appearance, the antenna aperture of the general sensor is installed conformally with the aircraft skin. At the same time, in order to reduce the scattering characteristics of the antenna aperture, there are strict requirements for the gap between it and the aircraft skin, and sealant will be filled in the gap. When the antenna aperture fails and needs to be replaced, it is usually necessary to lift it from the inside of the fuselage to the outside to separate it from the skin. Due to the limitations of the aircraft structure frame beams, internal equipment, cables, and pipeline layout and direction, most of the installation areas are actually inaccessible, which makes the installation and removal of the antenna aperture inconvenient.

[0003] At present, there are two general methods for antenna apertures: direct disassembly or suction cup disassembly. Direct disassembly is to pry up the antenna from the outside through the gap, which will inevitably cause certain damage to the antenna aperture and the aircraft skin, and will also affect the stealth performance after installation; suction cup disassembly requires the antenna aperture surface to be smooth, and the antenna aperture is pulled out by suction. Generally, this method can be used for lighter antennas, but during the disassembly process, there is a risk of damaging the stealth coating on the antenna aperture surface and the antenna aperture falling and being damaged due to insufficient suction, or even hitting the surface of the fuselage.

[0004] In view of this, in order to achieve repeatability and safety in the disassembly and assembly of the stealth platform conformal antenna aperture from the outside and to ensure that no damage is caused to the aircraft skin and antenna aperture before and after disassembly and assembly, a stealth platform conformal antenna disassembly and assembly method or structure is needed. Summary of the invention

[0005] The purpose of the present application is to provide a method and structure for disassembling and assembling a conformal antenna of a stealth platform to solve or alleviate at least one problem in the background technology.

[0006] The technical solution of the present application is: a method for disassembling and assembling a conformal antenna of a stealth platform, comprising:

[0007] S10, setting at least two disassembly thread process holes in the conformal area between the aircraft skin structure frame and the antenna aperture;

[0008] S20, providing at least two handles adapted to the disassembly threaded process holes;

[0009] S30, when the antenna aperture needs to be disassembled, the handle thread is installed in the disassembly thread process hole, and the antenna aperture is removed from the aircraft skin by pulling the handle outward; when the antenna aperture is installed on the aircraft skin and does not need to be disassembled, the disassembly thread process hole is sealed with a process screw.

[0010] In a preferred embodiment of the present application, there are two disassembly threaded process holes, and the two disassembly threaded process holes are arranged at diagonal positions of the antenna aperture 22.

[0011] In a preferred embodiment of the present application, the handle is a C-shaped handle, which is convenient for applying pulling force.

[0012] In a preferred embodiment of the present application, the art screw is a countersunk screw.

[0013] In addition, the present application also provides a structure for implementing any of the above stealth platform conformal antenna disassembly and assembly methods, comprising: an aircraft skin, an antenna aperture, mounting bolts, process screws and a handle, wherein the aircraft skin has a structural opening frame, and the antenna aperture is conformally connected to the structural opening frame of the aircraft skin through mounting bolts;

[0014] Among them, no less than two disassembly threaded process holes are provided in the conformal area between the antenna aperture and the structural opening frame of the aircraft skin. When the antenna aperture needs to be disassembled, the handle is installed in the disassembly threaded process to serve as a load-bearing point for disassembly of the antenna aperture; when the antenna aperture is installed on the aircraft and does not need to be disassembled, the process screws are used to block the holes.

[0015] In a preferred embodiment of the present application, the disassembly thread process hole is a blind hole.

[0016] In a preferred embodiment of the present application, the disassembly threaded hole is a self-locking threaded hole.

[0017] In a preferred embodiment of the present application, there are two disassembly threaded process holes, and the two disassembly threaded process holes are arranged at diagonal positions of the antenna aperture 22.

[0018] In a preferred embodiment of the present application, the handle is a C-shaped handle, and the handle includes a threaded section threadedly connected to the disassembly threaded process hole and a curved section extending from the threaded section, and the curved section is C-shaped. In a preferred embodiment of the present application, the process screw is a countersunk screw.

[0019] The stealth platform conformal antenna aperture disassembly and assembly method and structure provided in the present application ensure the repeatability and safety of conformal antenna aperture disassembly and assembly from a design perspective, while standardizing a unified method for disassembly and assembly of the antenna aperture of the entire aircraft, shortening the antenna aperture disassembly and assembly time, and ensuring the consistency of stealth performance after disassembly and assembly. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0021] Figure 1 It is a schematic diagram of a conformal antenna aperture installation structure in the prior art.

[0022] Figure 2 This is a schematic diagram of the conformal antenna aperture installation structure of the present application.

[0023] Figure 3 This is a schematic diagram of the handle in this application. DETAILED DESCRIPTION

[0024] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0025] like Figure 1 The figure shows a schematic diagram of an existing conformal antenna aperture installation structure. In the conformal antenna aperture installation structure 10, the structural frame of the aircraft skin 11 is conformally designed with the antenna aperture 12. The center of the antenna aperture 12 is a wave-transmitting area 13. The radio waves sent by the antenna (not shown) are emitted from the wave-transmitting area 13, or the antenna receives radio signals through the wave-transmitting area 13. The antenna aperture 12 is fixed to the aircraft skin 11 by mounting screws 14.

[0026] In order to ensure that the stealth aircraft skin and antenna aperture are not damaged during the disassembly and assembly process without changing the shape of the conformal antenna aperture, and to achieve the repeatability and safety of the antenna aperture disassembly and assembly from the outside, the present application proposes a stealth platform conformal antenna aperture disassembly and assembly method and structure.

[0027] The stealth platform conformal antenna aperture disassembly and assembly method provided in this application includes:

[0028] S10, setting at least two disassembly thread process holes in the conformal area between the aircraft skin structure frame and the antenna aperture;

[0029] S20, providing at least two handles adapted to the disassembly threaded process holes;

[0030] S30, when the antenna aperture needs to be disassembled, the handle thread is installed in the disassembly thread process hole, and the antenna aperture is removed from the aircraft skin by pulling the handle outward; when the antenna aperture is installed on the aircraft skin and does not need to be disassembled, the disassembly thread process hole is sealed with a process screw.

[0031] like Figure 2The structure shown in the present application is used to implement the method for disassembling and assembling conformal antenna apertures of stealth platforms. The structure 20 includes: an aircraft skin 21, an antenna aperture 22, mounting bolts, process screws 23 and a handle 24. The aircraft skin 21 has a structural opening frame. The antenna aperture 22 is conformally connected to the structural opening frame of the aircraft skin 21 by mounting bolts 25, wherein no less than two disassembly threaded process holes are provided in the conformal region between the antenna aperture 22 and the structural opening frame of the aircraft skin 21. When the antenna aperture 22 needs to be disassembled, the handle is installed in the disassembly thread process to serve as a load-bearing point for disassembly and assembly of the antenna aperture 22; when the antenna aperture 22 is installed on the aircraft and does not need to be disassembled, the process screws 23 are used to block the hole; when the antenna aperture 22 needs to be disassembled, the process screws 23 are first removed, and then the handle 24 is screwed in to pull out the antenna aperture 22.

[0032] In some embodiments of the present application, the disassembly threaded process hole is a blind hole. Further, the disassembly threaded process hole is a self-locking threaded hole.

[0033] In the present application, the process screw is a countersunk screw to reduce or eliminate unevenness of the conformal surface.

[0034] In a preferred embodiment of the present application, there may be two disassembly threaded process holes, and the two disassembly threaded process holes are arranged at diagonal positions of the antenna aperture 22, so as to facilitate the handle 24 to apply a disassembly pulling force to the antenna aperture 22.

[0035] like Figure 3 As shown, the handle 24 in the present application is a C-shaped handle, which includes a threaded section 241 threadedly connected to the disassembly threaded process hole and a curved section 242 extending from the threaded section 241, and the curved section 242 is C-shaped. After the handle 24 is threadedly matched with the antenna aperture 22 through the threaded section 241, the antenna aperture 22 can be separated from the structural opening frame of the aircraft skin 21 by applying a pulling force to the curved section 242, which is convenient for disassembly.

[0036] The stealth platform conformal antenna aperture disassembly and assembly method and structure provided in the present application ensure the repeatability and safety of conformal antenna aperture disassembly and assembly from a design perspective, while standardizing a unified method for disassembly and assembly of the antenna aperture of the entire aircraft, shortening the antenna aperture disassembly and assembly time, and ensuring the consistency of stealth performance after disassembly and assembly.

[0037] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A method for disassembling and assembling a conformal antenna of a stealth platform, characterized in that: include: S10, setting at least two disassembly thread process holes in the conformal area between the aircraft skin structure frame and the antenna aperture; S20, providing at least two handles adapted to the disassembly threaded process holes; S30, when the antenna aperture needs to be disassembled, the handle thread is installed in the disassembly thread process hole, and the antenna aperture is removed from the aircraft skin by pulling the handle outward; when the antenna aperture is installed on the aircraft skin and does not need to be disassembled, the disassembly thread process hole is sealed with a process screw.

2. The method for disassembling and assembling the conformal antenna of a stealth platform according to claim 1, characterized in that: There are two disassembly thread process holes, and the two disassembly thread process holes are arranged at the diagonal positions of the antenna aperture 22.

3. The method for disassembling and assembling the conformal antenna of a stealth platform according to claim 1, characterized in that: The handle is a C-shaped handle, which is convenient for applying pulling force.

4. The method for disassembling and assembling the conformal antenna of a stealth platform according to claim 1, characterized in that: The craft screws are countersunk screws.

5. A structure for implementing the method for disassembling and assembling the conformal antenna of a stealth platform as claimed in any one of claims 1 to 4, characterized in that: include: Aircraft skin, antenna aperture, mounting bolts, process screws and handles, wherein the aircraft skin has a structural opening frame, and the antenna aperture is conformally connected to the structural opening frame of the aircraft skin through mounting bolts; Among them, no less than two disassembly threaded process holes are provided in the conformal area between the antenna aperture and the structural opening frame of the aircraft skin. When the antenna aperture needs to be disassembled, the handle is installed in the disassembly threaded process to serve as a load-bearing point for disassembly of the antenna aperture; when the antenna aperture is installed on the aircraft and does not need to be disassembled, the process screws are used to block the holes.

6. The structure according to claim 5, characterized in that The threaded process holes for disassembly and assembly are blind holes.

7. The structure according to claim 6, characterized in that The disassembly threaded hole is a self-locking threaded hole.

8. The structure according to claim 6 or 7, characterized in that: There are two disassembly thread process holes, and the two disassembly thread process holes are arranged at the diagonal positions of the antenna aperture 22.

9. The structure according to claim 1, characterized in that The handle is a C-shaped handle, and the handle comprises a threaded section threadedly connected to the disassembly threaded process hole and a curved section extending from the threaded section, and the curved section is C-shaped.

10. The structure according to claim 1, characterized in that The process screw is a countersunk screw.

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