Interchangeable connecting structure for large-size radome of airplane

Abstract

The utility model belongs to the technical field of aviation structure design, and particularly relates to an interchangeable connecting structure for a large-size radome of an airplane, which comprises the radome and a fuselage mounting end frame, and the radome and the fuselage mounting end frame are both provided with positioning reference holes. The reference hole is used for positioning the initial positions of the antenna housing and the fuselage mounting end frame; the radome and the fuselage mounting end frame are also provided with a plurality of connecting holes, and fixed connection is realized through cooperation of bolts and nuts. According to the technical scheme of the utility model, the unified positioning reference is arranged on the antenna housing and the fuselage installation end frame, the assembly compensation allowance is reserved on the fuselage installation end frame, and the bolt connection mode of the antenna housing and the end frame is optimized, so that the technical difficulty of the interchangeability of the large-scale antenna housing is solved, and the technical requirement of the interchangeability of the antenna housing is met.

Description

Technical Field

[0001] The utility model belongs to the technical field of aviation structure design and relates to an interchangeable connection of large-size radomes of aircraft. Background Art

[0002] The radome is an important component of the aircraft radar system. It is mainly used to protect the radar antenna to work normally in harsh environments. It is an integrated aerodynamic / structural / wave-transmitting component.

[0003] In recent years, with the continuous upgrading of airborne electronic equipment, the number and scale of airborne electronic equipment have increased, and the size and number of radomes have also increased accordingly. Usually, in order to meet the maintainability design requirements of the aircraft and ensure the aircraft's attendance rate, the same type of radomes installed in the same or different parts of the aircraft should meet the interchangeability requirements. For large-sized radomes, because their connection interfaces are more complex and assembly coordination is difficult, achieving the interchangeability of radomes is usually a technical difficulty.

[0004] A certain type of aircraft has multiple large radome structures installed on the outside of the fuselage. The appearance of the radome and the interface connected to the fuselage are exactly the same. During the design, a unified positioning reference is set on the radome and the fuselage mounting end frame, and assembly compensation margin is reserved on the fuselage mounting end frame. The bolt connection method between the radome and the end frame is optimized. This solves the technical difficulties of the interchangeability of large radomes and meets the technical requirements for the interchangeability of radomes. Utility Model Content

[0005] 1. Technical problems solved

[0006] The utility model overcomes the technical difficulties of the interchangeability of existing large-size radomes of aircraft and provides an interchangeable connection of large-size radomes of aircraft.

[0007] 2. Technical solution

[0008] In order to solve the above technical problems, the utility model is achieved through the following technical solutions:

[0009] An interchangeable connection structure for a large-size aircraft radome, the connection structure comprising: a radome and a fuselage mounting end frame, both the radome and the fuselage mounting end frame being provided with positioning reference holes, the reference holes being used to locate the initial positions of the radome and the fuselage mounting end frame; a plurality of connection holes are also arranged on the radome and the fuselage mounting end frame, and fixed connection is achieved by the cooperation of bolts and nuts.

[0010] Furthermore, a bushing is embedded in the connection hole of the antenna cover.

[0011] Furthermore, the fuselage mounting end frame and the radome docking area are elliptical or circular structures.

[0012] Furthermore, the butt joint area of ​​the fuselage mounting end frame is symmetrically provided with sunken areas.

[0013] Furthermore, the positioning reference hole on the fuselage mounting end frame is used as a unified positioning reference when the interchangeable radomes are interchanged.

[0014] Furthermore, a floating carriage nut is embedded in the fuselage mounting end frame. While the floating carriage nut realizes the processability of the closed space butt-jointed bolt connection, the nut also has an adjustment amount of 0.5mm in the direction of the hole axis.

[0015] 3. Beneficial technical effects

[0016] The utility model provides an interchangeable connection for a large-sized radome of an aircraft, which solves the technical difficulties of the interchangeability of large radomes and realizes the technical requirements for the interchangeability of radomes by setting a unified positioning reference on the radome and a fuselage mounting end frame, reserving an assembly compensation margin on the fuselage mounting end frame, and optimizing the bolt connection method between the radome and the end frame. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The utility model includes 4 drawings, and the drawings and the descriptions of the drawings are as follows:

[0018] Figure 1 Schematic diagram of the connection of the end frame for the radome and fuselage;

[0019] Figure 2 This is a cross-sectional view of the butt bolt hole of the utility model;

[0020] Figure 3 This is a schematic diagram of the location of the positioning holes of the utility model;

[0021] Figure 4 This is a cross-sectional view of the locating hole position of the utility model;

[0022] Figure 5 This is a schematic diagram of the end face of the interchangeable connection structure of the utility model;

[0023] Figure 6 for Figure 5 Middle CC view;

[0024] Figure 7 Schematic diagram of the end frame end sinking structure.

[0025] Among them: 1. Radome, 2. Fuselage mounting end frame, 3. Docking bolts, 4. Floating drag plate nuts, 5. Embedded bushings, 6. Radome positioning holes, 7. Radome docking bolt initial holes, 8. End frame structure positioning holes, 9. End frame sunken area, 10. Docking bolt holes. DETAILED DESCRIPTION

[0026] Combined with the accompanying drawings, the utility model is described in detail about the interchangeable connection of a large-size aircraft radome:

[0027] The specific design process is as follows:

[0028] 1) Uniform positioning reference holes are set on the radomes and fuselage mounting end frames at different installation positions for alignment and positioning during the assembly of the radomes, and also to ensure the uniform positioning reference when the radomes are interchangeable.

[0029] 2) During the manufacturing process of the radome, the same set of standard tooling is used to drill the initial holes for the docking bolt holes in the radome connection area. When installing the radome, the initial holes on the radome are used as the positioning reference for the docking bolt holes, and the connection holes on the fuselage mounting end frame are drilled to ensure that the hole position information and reference of the docking bolt holes at different installation positions are completely consistent. At the same time, in order to prevent the composite material radome from delamination and fiber cutting during the drilling process, metal shoulder bushings are pressed into the initial holes for the docking bolts during the manufacturing of the radome.

[0030] 3) After the butt bolt holes are drilled, a floating carriage nut is embedded on the fuselage mounting end frame. While the floating carriage nut realizes the processability of the butt bolt connection in a closed space, the nut also has an adjustment amount of 0.5mm in the direction of the hole axis, which increases the compensation margin for the coaxiality deviation during the butt bolt connection after the antenna cover is interchanged.

[0031] 4) The fuselage mounting end frame is provided with structural depressions at both ends of the overlap area with the radome to provide a compensation margin for the tolerance accumulation during the assembly of the radome, so as to ensure the coordination of the assembly of the radome and the fuselage mounting end frame.

[0032] Uniform positioning reference holes 6 and 8 are provided on the radome 1 and the fuselage mounting end frame 2 at different mounting positions for alignment and positioning during assembly of the radome, and also ensure uniform positioning references when the radomes are interchanged.

[0033] During the manufacturing process of the radome 1, the same set of standard tooling is used to drill the initial holes 7 of the butt bolt holes in the connection area of ​​the radome. When the radome is installed, the initial holes 7 on the radome are used as the positioning reference for the butt bolt holes 10, and the connection holes on the fuselage mounting end frame are drilled to ensure that the hole position information and reference of the butt bolt holes at different installation positions are completely consistent. At the same time, in order to prevent the composite material radome from delamination and fiber cutting during the drilling process, a metal shoulder bushing 5 is pressed into the initial holes of the butt bolts when the radome is manufactured.

[0034] After the docking bolt hole 10 is drilled, a floating drag plate nut 4 is embedded on the fuselage mounting end frame 2. While the floating drag plate nut realizes the processability of the connection of the docking bolt 3 in a closed space, the nut also has an adjustment amount of 0.5mm in the direction of the hole axis, which increases the compensation margin for the coaxial deviation when the docking bolt 3 is connected after the antenna cover 1 is interchanged.

[0035] The fuselage mounting end frame 2 is provided with structural depressions 9 at both ends of the overlap area with the radome 1 to provide a compensation margin for tolerance accumulation during the assembly of the radome, so as to ensure coordination of the assembly of the radome and the fuselage mounting end frame.

[0036] Finally, it should be noted that the above implementation methods or implementation cases are only used to illustrate the technical solution of the utility model, and any incomplete details are regarded as conventional technical means or common knowledge in the field; it should be understood that the protection scope of the utility model is not limited to the above specific implementation forms, and any technician familiar with the field can easily think of various equivalent modifications or substitutions within the technical scope disclosed in the utility model, and these modifications or substitutions should be covered within the protection scope of the utility model.

Claims

1. An interchangeable connection structure for large-size aircraft radomes, characterized in that: The connection structure includes: an antenna cover and a fuselage mounting end frame. The antenna cover and the fuselage mounting end frame are both provided with positioning reference holes, and the reference holes are used to locate the initial positions of the antenna cover and the fuselage mounting end frame. The antenna cover and the fuselage mounting end frame are also provided with a plurality of connection holes, which are fixedly connected by bolts and nuts.

2. The aircraft large-size radome interchangeable connection structure according to claim 1, characterized in that: A bushing is embedded in the connection hole of the antenna cover.

3. The aircraft large-size radome interchangeable connection structure according to claim 1, characterized in that: The fuselage mounting end frame and the radome docking area are elliptical or circular structures.

4. The aircraft large-size radome interchangeable connection structure as claimed in claim 3, characterized in that: The butt joint area of ​​the fuselage mounting end frame is symmetrically provided with sunken areas.

5. The aircraft large-size radome interchangeable connection structure according to claim 1, characterized in that: The positioning reference hole on the fuselage mounting end frame serves as a unified positioning reference when interchangeable radomes are interchanged.

6. The aircraft large-size radome interchangeable connection structure according to claim 1, characterized in that: The floating carriage nut is embedded in the fuselage mounting end frame. While realizing the processability of the butt-bolt connection in a closed space, the nut also has an adjustment amount of 0.5mm in the direction of the hole axis.

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