CN219339704U

CN219339704U - Quick detach formula aircraft radome

Info

Publication number: CN219339704U
Application number: CN202320293408.7U
Authority: CN
Inventors: 吴彬; 王�琦
Original assignee: Changzhou Yuxiangyuan Aviation Technology Co ltd
Current assignee: Changzhou Yuxiangyuan Aviation Technology Co ltd
Priority date: 2023-02-23
Filing date: 2023-02-23
Publication date: 2023-07-14
Anticipated expiration: 2033-02-23

Abstract

The utility model discloses a quick-dismantling type aircraft radome, which comprises a machine body and a radome, wherein an outer ring is arranged outside the machine body, symmetrically arranged convex blocks are distributed on the outer ring in a circumferential array manner, threaded holes are formed in the convex blocks, threaded locking pins are connected in the threaded holes in a rotating manner, a mounting cavity is further formed in the side wall of the machine body, a limiting part is arranged in the mounting cavity, connecting blocks are distributed on the outer circumferential array manner of the radome, U-shaped openings are formed in the end parts of the connecting blocks, and stop blocks are connected in the U-shaped openings in a rotating manner through torsion spring rotating shafts. According to the utility model, the screw lock pin is only required to be unscrewed, the stop dog rotates into the U-shaped opening under the reset action of the torsion spring rotating shaft, the external locking of the radar housing and the engine body is released, then the radar housing is reversely rotated, so that the arc-shaped fixing strip is separated from the arc-shaped strip, and then the radar housing is taken down, thereby facilitating the rapid disassembly of the radar housing and improving the disassembly and assembly efficiency of the radar housing.

Description

Quick detach formula aircraft radome

Technical Field

The utility model relates to the technical field of aircraft radomes, in particular to a quick-release aircraft radome.

Background

The radome is a window of electromagnetic waves, and is used for protecting the antenna and preventing the influence and interference of the environment on the working state of the radar antenna, so that the running power of the driving antenna is reduced, the working reliability of the driving antenna is improved, and the all-weather working of the radar antenna is ensured.

The existing aircraft radome needs to use a specific dismounting tool when being mounted and dismounted, the mounting and dismounting processes are time-consuming and labor-consuming, the maintenance of the internal elements of the radome is inconvenient, and the dismounting efficiency of the aircraft radome is reduced.

Disclosure of Invention

The utility model aims at: in order to solve the above problems, a quick-release aircraft radome is provided.

In order to achieve the above purpose, the present utility model adopts the following technical scheme:

the utility model provides a quick detach formula aircraft radome, includes organism and radome, the outside of organism is provided with the outer loop, circumference array distributes and has the lug that the symmetry set up on the outer loop, have the screw hole on the lug, the screwed connection has the screw lock pin in the screw hole, the lateral wall of organism still has the installation cavity, the inside of installation cavity is provided with spacing part, the outside circumference array of radome distributes and has the connecting block, the tip of connecting block has the U type mouth, the inside dog that is connected with through torsional spring pivot rotation of U type mouth, the inner wall of radome is provided with fixed part.

Preferably, the limiting component comprises two arc-shaped strips and a stop block which are symmetrically arranged, the arc-shaped strips are arranged on the side wall of the installation cavity, and the stop block is arranged at the end part of the arc-shaped strips and is connected with the cavity wall of the installation cavity.

Preferably, the fixing part comprises two arc-shaped fixing strips, and the end parts of the two arc-shaped fixing strips are bent and fixedly connected with the inner wall of the radar housing.

Preferably, the arc-shaped fixing strip is in running fit with the arc-shaped strip.

In summary, due to the adoption of the technical scheme, the beneficial effects of the utility model are as follows:

in this application, during the dismantlement, only need unscrew the screw lock pin, the dog rotates to U type mouth under the reset action of torsional spring pivot in, releases the outside locking of radome and organism, then reverse rotation radome for arc fixed strip breaks away from the arc strip, then take off the radome can, the quick dismantlement of radome of being convenient for has improved the dismouting efficiency of radome.

Drawings

Fig. 1 shows a schematic perspective view of a quick-release aircraft radome according to an embodiment of the present utility model;

fig. 2 shows a schematic diagram of a left view explosion structure of a quick-release aircraft radome according to an embodiment of the present utility model;

fig. 3 shows a schematic diagram of a right view explosion structure of a quick-release aircraft radome according to an embodiment of the present utility model;

fig. 4 shows an enlarged schematic view of a portion a in fig. 1 of a quick-release aircraft radome according to an embodiment of the present utility model.

Legend description:

1. a body; 2. a radome; 3. a connecting block; 4. a U-shaped opening; 5. a torsion spring rotating shaft; 6. a stop block; 7. an outer ring; 8. a bump; 9. a threaded locking pin; 10. an arc-shaped fixing strip; 11. a mounting cavity; 12. an arc-shaped strip; 13. a gear block.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

Referring to fig. 1-4, the present utility model provides a technical solution:

the utility model provides a quick detach formula aircraft radome, including organism 1 and radome 2, the outside of organism 1 is provided with outer loop 7, circumference array distribution has the lug 8 that the symmetry set up on the outer loop 7, have the screw hole on the lug 8, the screw hole internal rotation is connected with screw lock pin 9, the lateral wall of organism 1 still has installation cavity 11, the inside of installation cavity 11 is provided with spacing part, the outside circumference array distribution of radome 2 has connecting block 3, the tip of connecting block 3 has U type mouth 4,U type mouth 4 inside to rotate through torsional spring pivot 5 and be connected with dog 6, when not receiving external force effect, dog 6 is the horizontality with U type mouth 4 under torsional force of torsional spring pivot 5, when receiving external force oppression, can be the vertical state with U type mouth 4, the inner wall of radome 2 is provided with fixed part.

Specifically, as shown in fig. 3, the limiting component comprises two arc strips 12 and a gear block 13 which are symmetrically arranged, the arc strips 12 are arranged on the side wall of the installation cavity 11, the gear block 13 is arranged at the end part of the arc strips 12 and is connected with the cavity wall of the installation cavity 11, so that a limiting space is formed among the arc strips 12, the gear block 13 and the installation cavity 11, and the radar housing 2 is convenient to install and limit from the inside.

Specifically, as shown in fig. 2, the fixing component includes two arc fixing strips 10, the ends of the two arc fixing strips 10 are all bent and fixedly connected with the inner wall of the radar housing 2, and the arc fixing strips 10 are matched with the arc fixing strips 12.

Specifically, as shown in fig. 1, the arc-shaped fixing strip 10 is in running fit with the arc-shaped strip 12, so that the arc-shaped fixing strip 10 can rotate below the arc-shaped strip 12, and the arc-shaped fixing strip 10 is blocked and limited through the arc-shaped strip 12.

In summary, in the quick-dismantling type aircraft radar cover provided in this embodiment, during installation, the arc fixing strip 10 is inserted into the installation cavity 11 from the gap between the two arc strips 12, and the radar cover 2 is rotated, the radar cover 2 drives the arc fixing strip 10 to move into the limit space formed by the arc strip 12, the gear block 13 and the installation cavity 11, when the arc fixing strip 10 contacts with the gear block 13, the radar cover 2 stops rotating, then the stop block 6 is stirred, under the action of the torsion spring rotating shaft 5, the stop block 6 enters the space formed by the two projections 8, then the threaded lock pin 9 is rotated to enable the end part of the stop block 6 to abut against the stop block 6, so that the radar cover 2 is installed on the machine body 1, and during disassembly, only the threaded lock pin 9 is required to be unscrewed, the stop block 6 rotates into the U-shaped opening 4 under the reset action of the torsion spring rotating shaft 5, the external locking of the radar cover 2 and the machine body 1 is released, then the arc fixing strip 10 is reversely rotated, the radar cover 2 is separated from the arc strip 12, and then the radar cover 2 is removed, the quick disassembly of the radar cover 2 is facilitated, and the efficiency of the radar cover is improved.

The previous description of the embodiments is provided to enable any person skilled in the art to make or use the present utility model. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the utility model. Thus, the present utility model is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. The utility model provides a quick detach formula aircraft radome, includes organism (1) and radome (2), its characterized in that, the outside of organism (1) is provided with outer loop (7), circumference array distributes and has lug (8) that the symmetry set up on outer loop (7), have the screw hole on lug (8), the screw hole internal rotation is connected with screw lock pin (9), the lateral wall of organism (1) still has installation cavity (11), the inside of installation cavity (11) is provided with spacing part, the outside circumference array of radome (2) distributes and has connecting block (3), the tip of connecting block (3) has U type mouth (4), U type mouth (4) inside is connected with dog (6) through torsional spring pivot (5) rotation, the inner wall of radome (2) is provided with fixed part.

2. The quick release aircraft radar cover according to claim 1, wherein the limiting component comprises two symmetrically arranged arc-shaped strips (12) and a stop block (13), the arc-shaped strips (12) are arranged on the side wall of the installation cavity (11), and the stop block (13) is arranged at the end part of the arc-shaped strips (12) and is connected with the cavity wall of the installation cavity (11).

3. The quick release aircraft radar cover according to claim 1, characterized in that the fixing part comprises two arc-shaped fixing strips (10), and the ends of the two arc-shaped fixing strips (10) are bent and fixedly connected with the inner wall of the radar housing (2).

4. A quick release aircraft radar cover according to claim 3, characterized in that the arcuate fixing strip (10) is in a running fit with the arcuate strip (12).