CN219468010U

CN219468010U - Aircraft anti-icing and deicing integrated icing detector

Info

Publication number: CN219468010U
Application number: CN202223600787.4U
Authority: CN
Inventors: 徐业博; 李振硕; 彭汉元
Original assignee: Wuhan Aviation Instrument Co Ltd
Current assignee: Wuhan Aviation Instrument Co Ltd
Priority date: 2022-12-29
Filing date: 2022-12-29
Publication date: 2023-08-04
Anticipated expiration: 2032-12-29

Abstract

The utility model belongs to the technical field of ice control, and relates to an aircraft ice control integrated icing detector. Comprises a vibrator component, a base, a bracket, a circuit board, a socket and a rear cover; the vibrator component is connected with the base, and the clamping end of the bracket is embedded into the groove on the base to realize fastening; the circular ring end of the support is tightly attached to the socket, the socket is fixed on the rear cover by adopting a screw, the circuit board is fixed on the support by adopting a screw, and the rear cover is fastened with the base by adopting a screw. Further, the novel sealing device further comprises a sealing strip, wherein the sealing strip is arranged in a first concave groove arranged at the root of the flange surface of the base. The icing detector adopts a square circuit board and is vertically arranged in the detector, the transverse arrangement structural form of the existing circular circuit board is canceled, and the size of the circuit board is increased for arranging more complex circuits. The icing detector adopts the support in the truss structure form, the installation mode of the existing circular sleeve stacking circuit board is canceled, and the shock resistance of the icing detector is enhanced.

Description

Aircraft anti-icing and deicing integrated icing detector

Technical Field

The utility model belongs to the technical field of aircraft deicing, and relates to an integrated icing detector.

Background

The icing detector is used as a special detection and alarm device for detecting whether icing exists on the surface of the aircraft when the aircraft flies under icing meteorological conditions. The existing integrated icing detector adopts a pagoda type layout, adopts a round circuit board, and adopts a round sleeve to carry out a layer-by-layer superposition structure. Because the circuit board is circular, the space utilization rate is low, and the arrangement of electronic components is not facilitated, so that more circuits cannot be arranged to meet more complex functional requirements; meanwhile, the circuit boards are stacked by means of the round sleeves, and the sleeves between the sleeves and the circuit boards are tightly pressed by the sleeves at the uppermost layer to achieve the fastening effect, so that the anti-vibration effect is poor, and the anti-vibration device can only be used on the models of environments with small vibration values such as unmanned aerial vehicles, transportation machines and the like.

For the icing detector can meet the requirements of multiple models and multiple functions, the structural form inside the icing detector is optimally designed, and the integrated icing detector with the novel structural form is designed.

Disclosure of Invention

The integrated icing detector with the novel structural form is provided, the size of the circuit board is increased under the condition of changing the size of the detector, the circuit board is used for arranging more complex circuits, and meanwhile, the shock resistance of the detector is improved, so that the multifunctional and multi-model requirements of aircraft icing detection are met.

Technical proposal

An aircraft deicing and deicing integrated icing detector is characterized by comprising a vibrator assembly 1, a base 2, a bracket 3, a circuit board 4, a socket 8 and a rear cover 9;

the vibrator assembly 1 is connected with the base 2, and the clamping end of the bracket 3 is embedded into a groove on the base 2 to realize fastening; the circular ring end of the bracket 3 is tightly attached to the socket 8, the socket 8 is fixed on the rear cover 9 by adopting a screw, the circuit board 4 is fixed on the bracket 3 by adopting a screw, and the rear cover 9 is fastened with the base 2 by adopting a screw.

Further, still include sealing strip 5, sealing strip 5 sets up in the first concave groove that base 2 flange face root was arranged, plays waterproof sealing's effect.

Further, the electromagnetic sealing device also comprises a sealing ring 6, wherein the sealing ring 6 is arranged in a second concave groove arranged at the root of the flange surface of the base 2, and plays a role in electromagnetic sealing.

Further, the electromagnetic socket further comprises a sealing gasket 7, wherein the sealing gasket 7 covers the threaded mounting screw on the bracket 3, and the sealing gasket 7 is tightly pressed by the rear cover 9 to be tightly attached to the mounting surface of the socket 8, so that electromagnetic leakage is prevented.

Further, the bracket 3 is a truss structure.

Further, the circuit board 4 is vertically arranged, and the circuit board is rectangular in shape.

Technical effects

The icing detector adopts a square circuit board and is vertically arranged in the detector, the transverse arrangement structural form of the existing circular circuit board is canceled, and the size of the circuit board is increased for arranging more complex circuits. The icing detector adopts the support in the truss structure form, the installation mode of the existing circular sleeve stacking circuit board is canceled, and the shock resistance of the icing detector is enhanced.

Drawings

FIG. 1 is a schematic diagram of an integrated icing detector in a novel configuration;

fig. 2 is a schematic diagram of a stent structure.

Detailed Description

The utility model is further described below with reference to examples. The following description is of some, but not all embodiments of the utility model. 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.

An integrated icing detector with a novel structural form consists of a vibrator component, a base, a bracket, a circuit board, a sealing strip, a sealing ring, a sealing gasket, a socket and a rear cover.

The vibrator component is installed on an installation column reserved on the base through a pressing plate and fastened by using screws.

The base is directly installed on the aircraft skin through the holes on the flange surface, and the appearance of the base is designed along with the aircraft skin.

Two concave grooves are arranged at the root of the flange surface of the base and are used for installing a sealing ring and a sealing strip to ensure the integral electromagnetic sealing and waterproof sealing of the detector.

The support is installed on four screw holes that the base reserved through four screw columns in the bottom, and the screw thread size selects M5 to guarantee the structural strength of detector.

The support adopts a truss structure form, and the shock resistance of the detector is improved through a structure form of interconnecting multiple cross beams.

Screw holes are arranged on the side face of the support beam, so that a circuit board can be conveniently installed on the side face by screws, and the shape of the circuit board is square and basically consistent with the area of the side face of the support.

Four threaded holes are arranged on the bracket cross beam, so that the socket can be conveniently installed for signal transmission.

The sealing gasket is tightly pressed by the screw mounting screw on the upper bracket of the sealing gasket and tightly attached to the mounting surface of the socket by the rear cover, so that electromagnetic leakage is prevented.

The rear cover is fastened on the bracket by adopting a screw, and the whole bracket and the circuit board are covered to form an internal sealing environment.

It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this utility model belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein. While the foregoing is directed to embodiments of the present utility model, other and further details of the utility model may be had by the present utility model, it should be understood that the foregoing description is merely illustrative of the present utility model and that no limitations are intended to the scope of the utility model, except insofar as modifications, equivalents, improvements or modifications are within the spirit and principles of the utility model.

Claims

1. An aircraft deicing and deicing integrated icing detector is characterized by comprising a vibrator assembly (1), a base (2), a bracket (3), a circuit board (4), a socket (8) and a rear cover (9); the vibrator assembly (1) is mounted on a mounting column reserved on the base (2) through a pressing plate and fastened by using screws, the base (2) is directly mounted on an aircraft skin through holes in a flange surface, the appearance of the base (2) is designed along with the aircraft skin, and the clamping end of the bracket (3) is embedded into a groove on the base (2) to realize fastening; the circular ring end of the bracket (3) is tightly attached to the socket (8), the socket (8) is fixed on the rear cover (9) by adopting a screw, the circuit board (4) is fixed on the bracket (3) by adopting a screw, and the rear cover (9) is fastened with the base (2) by adopting a screw; the socket also comprises a sealing gasket (7), wherein the sealing gasket (7) covers a threaded mounting screw on the bracket (3), and the sealing gasket (7) is tightly pressed by a rear cover (9) to be tightly attached to the mounting surface of the socket (8); the rear cover (9) is fastened on the bracket (3) by adopting a screw, and the whole bracket (3) and the circuit board cover to form an internal sealing environment.

2. An aircraft ice protection and control integrated icing detector according to claim 1, further comprising a sealing strip (5), wherein the sealing strip (5) is arranged in a first concave groove arranged at the root of the flange surface of the base (2).

3. An aircraft ice protection and control integrated ice detector according to claim 1, further comprising a sealing ring (6), wherein the sealing ring (6) is arranged in a second concave groove arranged at the root of the flange surface of the base (2).

4. An aircraft ice protection and control integrated ice detector according to claim 1, characterised in that the support (3) is of truss construction.

5. An aircraft ice protection and control integrated ice detector according to claim 1, characterised in that the circuit board (4) is arranged vertically and the circuit board is rectangular in shape.