An aerial radar radome support frame

Abstract

The utility model relates to radar cover installation technical field, concretely is an aviation radar cover support frame, including radar cover and organism, one side inside the radar cover is fixedly connected with the mounting ring, the mounting ring side wall is fixedly connected with the symmetry of a plurality of installation rods that set up, all are equipped with the installation slot on the installation rod, the organism one side inside rotationally connected with the connecting ring, the connecting ring all are equipped with the connecting groove on the position department of installation rod, the organism inside and the connecting ring adjacent position department are fixedly connected with the symmetry of the limit ring that sets up, the organism inside corresponding installation rod position department all are fixedly connected with the support rod, the utility model's beneficial effect is: from the structure completely avoids the support part to the radar main detection beam's shelter, ensures radar signal transceiving without obstruction, guarantees the detection accuracy and the detection distance not to be influenced, also has shortened radar cover installation time -consuming, has improved operation convenience and assembly efficiency remarkably.

Description

TECHNICAL FIELD

[0001] The utility model relates to radar cover installation technical field, concretely is an aviation radar cover support frame. BACKGROUND

[0002] The radar cover is mainly to maintain the aerodynamics appearance of the whole aircraft, reduce the resistance, and protect the radar antenna inside. The material of the radar cover must be easy to penetrate by radar electromagnetic waves, which is generally composed of special glass fiber, high-silica glass fiber, aramid fiber and quartz fiber.

[0003] The patent document with the Chinese patent publication number CN219339703U was published on July 14, 2023, and disclosed a kind of airplane radar cover with locking structure, including machine body connecting shell, radar cover, the inside of machine body connecting shell is provided with inner plate, the center of inner plate has through-hole, the rear wall of inner plate and located at through-hole has symmetrically distributed recess, the rear wall of inner plate is also provided with unlocking assembly, the inside of radar cover is provided with connecting rod, in the utility model, lock rod is passed through through-hole, under the action of spring, lock block is abutted with inner plate, then through electric control button control electric telescopic rod elongation, electric telescopic rod drives snap ring to abut with the other side of inner plate, so as to lock radar cover on machine body connecting shell, at the same time, the clamping hook outside radar cover turns into card block and is clamped with it, to fix radar cover from outside again, so that it is closely fixed with machine body connecting shell as a whole, in turn, make radar cover and machine body connecting shell installation adjustment fast, maintenance is convenient, and applicability is strong;Although the above application has many beneficial effects, but still has the following shortcomings: the current installation assembly layout is concentrated in the center point of radar cover, and this position just overlaps with the main detection beam path of the front end radar of machine body, this layout will make the installation assembly directly block the core detection area of radar, form detection blind area, not only lead to the recognition accuracy of radar to target decline, detection distance shorten, but also may interfere with the normal reception and transmission of radar signal, seriously affect the detection performance and use convenience of radar system. UTILITY MODEL CONTENTS

[0004] The utility model aims at providing an aviation radar cover support frame to solve the problems raised in the above background technology.

[0005] To achieve the above object, the utility model provides the following technical scheme: An aviation radar cover support frame, including radar cover and machine body, the inside one side of radar cover is fixedly connected with the mounting ring, the mounting ring side wall is fixedly connected with a plurality of installation rods of symmetry setting, the installation rod all is equipped with the installation groove, the inside one side of machine body is rotatably connected with the connecting ring, the connecting ring all is equipped with the connecting groove in position department of installation rod, the inside position department of machine body and connecting ring is fixedly connected with the limit ring of symmetry setting, the inside position department of machine body and installation rod all is fixedly connected with the support rod, the inside of support rod all is slidably connected with the moving rod, the one side of moving rod all is fixedly connected with the limit seat, the one side of limit seat all is fixedly connected with the spring.

[0006] Preferably, the installation rod one side all slide through corresponding connecting groove.

[0007] Preferably, the limit ring all with corresponding multiple installation grooves sliding connection.

[0008] Preferably, the installation rod corresponding limit seat position department all is spherical, and the spherical part of installation rod all is movably clamped in the inside of corresponding limit seat.

[0009] Preferably, the edge of limit seat and installation rod clamping part is arc-shaped, and the edge of limit seat one side is arc-shaped, and the one side of spring is fixedly connected with corresponding support rod.

[0010] Compared with the prior art, the utility model has the beneficial effects that: the support frame composed of various components adopts edge type layout, is installed in the inside edge position of the side end of radar cover and machine body, makes the central area between radar cover and machine body keep completely empty, completely avoids the shielding of support component to radar main detection beam from structure, ensures radar signal receiving and transmitting without obstruction, guarantees that detection precision and detection distance are not influenced, simultaneously, this layout design makes the installation process of radar cover greatly simplify, does not need staff to repeatedly disassemble, fastens bolt, only through external mechanical rotating mechanism can drive radar cover to complete alignment and installation, not only reduces manual operation step, but also shortens installation time consumption, significantly improves operation convenience and assembly efficiency. BRIEF DESCRIPTION OF DRAWINGS

[0011] Figure 1 It is the front view structure schematic diagram of the utility model;

[0012] Figure 2 It is the radar cover and machine body separation structure schematic diagram of the utility model;

[0013] Figure 3 It is the machine body upper structure schematic diagram of the utility model;

[0014] Figure 4The internal structure schematic diagram when the machine body is cut along the connecting ring of the utility model;

[0015] Figure 5 The support rod and the limiting seat of the utility model are shown in the sectional structure schematic diagram.

[0016] In the figure: 1, radar cover; 2, machine body; 3, mounting ring; 4, mounting rod; 5, mounting groove; 6, connecting ring; 7, connecting groove; 8, limiting ring; 9, support rod; 10, moving rod; 11, limiting seat; 12, spring. DETAILED DESCRIPTION

[0017] The technical solutions in the embodiments of the utility model will be clearly and completely described below with reference to the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the protection scope of the utility model.

[0018] Please refer to Figures 1-5 The utility model provides the following technical schemes:

[0019] An aviation radar cover support frame, including radar cover 1 and machine body 2, radar cover 1 inside one side is fixedly connected with mounting ring 3, the sidewall of mounting ring 3 is fixedly connected with the multiple mounting rods 4 of symmetrical arrangement, is all set with mounting groove 5 on mounting rod 4, machine body 2 one side inside rotationally connected with connecting ring 6, all set with connecting groove 7 on connecting ring 6 position corresponding mounting rod 4, machine body 2 inside and connecting ring 6 adjacent position is fixedly connected with the limiting ring 8 of symmetrical arrangement, machine body 2 inside corresponding mounting rod 4 position is all fixedly connected with support rod 9, and the inside of support rod 9 is all slidably connected with moving rod 10, and moving rod 10 one side is all fixedly connected with limiting seat 11, and limiting seat 11 one side is all fixedly connected with spring 12.

[0020] Mounting rod 4 one side is all slidably penetrated through corresponding connecting groove 7, and limiting ring 8 is all slidably connected with the multiple mounting grooves 5, and limiting ring 8 is convenient for through mounting groove 5 fixed mounting rod 4, the position of mounting ring 3 and radar cover 1, and the position corresponding limiting seat 11 of mounting rod 4 is all spherical, and the spherical part of mounting rod 4 is all movably clamped in the inside of corresponding limiting seat 11, and the edge and corner of the clamping part of limiting seat 11 and mounting rod 4 is all arc-shaped, and the edge and corner of limiting seat 11 one side is all arc-shaped, and spring 12 one side is all fixedly connected with corresponding support rod 9, and the spherical mounting rod 4 and the arc-shaped setting position of limiting seat 11 are convenient for extruding limiting seat 11 and being extruded by mounting rod 4.

[0021] In use, the radome 1 is moved by external mechanical control, and the radome 1 is moved towards the body 2, the radome 1 drives the mounting ring 3 and the mounting rod 4 to move horizontally towards the body 2, at this time, the moving mounting rod 4 penetrates the connecting groove 7 on the connecting ring 6, and then the side end of the radome 1 abuts against the side end of the body 2, at this time, the radome 1 is rotated by 90° by external mechanical, the radome 1 rotates to drive the mounting ring 3 and the mounting rod 4 to rotate together, the mounting rod 4 drives the connecting ring 6 to rotate together through the connection with the connecting groove 7, when the mounting rod 4 rotates by 90° with the radome 1, the mounting grooves 5 on the plurality of mounting rods 4 are all in sliding connection with the corresponding limiting rings 8, at this time, the radome 1 cannot move away from the body 2, while the mounting rod 4 rotates with the radome 1, the spherical parts of the mounting rod 4 all extrude the arc-shaped position of the side end of the corresponding limiting seat 11, the limiting seat 11 is extruded to drive the moving rod 10 to retract into the inside of the supporting rod 9, the movement of the limiting seat 11 also extrudes and retracts the spring 12, all the limiting seats 11 all perform a retraction action in the process of the rotation of the mounting rod 4, after the radome 1 rotates by 90°, the spherical parts of the mounting rod 4 all correspond to the corresponding limiting seat 11, and the spring 12 also drives the limiting seat 11 to reset, at this time, the limiting seat 11 is clamped with the corresponding mounting rod 4, so as to prevent the radome 1 from rotating accidentally in use, the surface of the radome 1 is smooth, the wind pressure borne by the aircraft during operation cannot make the radome 1 rotate by itself, only the power of external mechanical can rotate the radome 1, not only the structure completely avoids the shielding of the supporting part to the radar main detection beam, but also the installation time is shortened, and the operation convenience and assembly efficiency are significantly improved.

[0022] Although the embodiments of the present application have been shown and described, it is to be understood that for the purpose of the present application, the changes, modifications, equivalents, substitutions and variations of the embodiments can be made by those skilled in the art without departing from the spirit and principles of the present application, and the scope of the present application is defined by the appended claims and their equivalents.

Claims

1. An aviation radar dome support frame, characterized in that: The device includes a radar dome (1) and a body (2). A mounting ring (3) is fixedly connected to one side of the radar dome (1). A plurality of mounting rods (4) are fixedly connected to the side wall of the mounting ring (3). Each mounting rod (4) has a mounting groove (5). A connecting ring (6) is rotatably connected to one side of the body (2). Each connecting ring (6) has a connecting groove (7) at the position corresponding to the mounting rod (4). A symmetrically arranged limiting ring (8) is fixedly connected to the body (2) at the position adjacent to the connecting ring (6). A support rod (9) is fixedly connected to the body (2) at the position corresponding to the mounting rod (4). Each support rod (9) has a sliding rod (10) slidably connected inside it. Each moving rod (10) has a limiting seat (11) fixedly connected to one side of it. Each limiting seat (11) has a spring (12) fixedly connected to one side of it.

2. The aviation radar dome support frame according to claim 1, characterized in that: The mounting rod (4) slides through the corresponding connecting groove (7) on one side.

3. The aviation radar dome support frame according to claim 1, characterized in that: Each of the limiting rings (8) is slidably connected to the corresponding multiple mounting slots (5).

4. The aviation radar dome support frame according to claim 1, characterized in that: The mounting rod (4) is spherically shaped at the corresponding position of the limiting seat (11), and the spherical part of the mounting rod (4) is movably engaged inside the corresponding limiting seat (11).

5. The aviation radar dome support frame according to claim 1, characterized in that: The corners of the engagement between the limiting seat (11) and the mounting rod (4) are all arc-shaped. The corners of one side of the limiting seat (11) are all arc-shaped. The spring (12) is fixedly connected to the corresponding support rod (9) on one side.

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