CN209938966U

CN209938966U - Anti-icing electric heating unit

Info

Publication number: CN209938966U
Application number: CN201920086784.2U
Authority: CN
Inventors: 白斌; 任哲钒; 李志茂; 霍西恒; 曾飞雄; 李革萍
Original assignee: Commercial Aircraft Corp of China Ltd
Current assignee: Commercial Aircraft Corp of China Ltd; Shanghai Aircraft Design and Research Institute Commercial Aircraft Corporation of China Ltd
Priority date: 2019-01-18
Filing date: 2019-01-18
Publication date: 2020-01-14
Anticipated expiration: 2029-01-18

Abstract

The utility model discloses an anti-icing electrical heating unit. The utility model discloses an anti-icing electrical heating unit, including the primary structure layer, the primary structure layer has the combined material layer of symmetry, and primary structure layer and second insulation structure layer have been laid respectively to the upper and lower surface of primary structure layer, and the metal inoxidizing coating has been laid respectively to the outside of insulation structure layer, and insulation structure layer and metal inoxidizing coating have arranged the electrical heating membrane for the primary structure layer symmetry separately in the primary structure layer. The utility model discloses an anti-icing electrical heating unit can reduce structural deformation and structural stress strain that functional unit leads to in the course of being heated in machine-shaping process and work, avoids the warp of relevant structure, and the quick-witted installation of being convenient for, and the pneumatic appearance that helps improving the product life of electric anti-icing system, the aircraft position that guarantee anti-icing electrical heating unit corresponds is not destroyed.

Description

Anti-icing electric heating unit

Technical Field

The utility model relates to an anti-icing unit design of aircraft especially relates to an anti-icing electrical heating unit that is used for positions such as aircraft wing leading edge, engine lip of aircraft.

Background

With the development of multi-electric aircraft and the application of composite materials to aircraft, aircraft anti-icing systems have been developed from traditional hot gas anti-icing to electric anti-icing. The advantages of the electric anti-icing system include that the energy consumption is only half of that of the traditional hot gas anti-icing system, and the electric anti-icing heating temperature is matched with the temperature endured by the composite material. As a key component of the electric anti-icing system, the anti-icing electric heating functional unit converts electric energy into heat energy to carry out anti-icing, anti-icing and anti-icing heating. The anti-icing electric heating function unit is a structure function piece, an electric heating film is embedded in a multi-layer composite material structure, and the anti-icing electric heating function unit has a structure bearing function and an electric heating anti-icing/deicing function and also needs to have the protection capability on environments such as thunder and lightning which are possibly suffered after the anti-icing electric heating function unit is installed.

However, the conventional anti-icing electric heating unit introduces an electric heating film inside the structure, which causes asymmetry of the structure, and the anti-icing electric heating unit needs to be cured and molded many times during the processing, which easily causes warpage and deformation of the unit structure. Heating of the cell during operation also tends to cause structural deformation of the stress strain within the asymmetric structure after installation.

In summary, there is a need for a new anti-icing electric heating unit to reduce the structural deformation and the structural stress strain of the functional unit during the forming process and the thermal process.

SUMMERY OF THE UTILITY MODEL

The to-be-solved technical problem of the utility model is to provide an anti-icing electric heating unit in order to overcome current aircraft anti-icing electric heating unit and to lead to the defect that structural deformation and structural stress meet an emergency easily at the machine-shaping process with the work in-process of being heated.

The utility model discloses a solve above-mentioned technical problem through following technical scheme:

the utility model provides an anti-icing electrical heating unit, its characteristics lie in, it includes the major structure layer, the major structure layer has the combined material layer of symmetry, first insulation structure layer and second insulation structure layer have been laid respectively to the upper and lower surface of major structure layer, the metal inoxidizing coating has been laid respectively to the outside of insulation structure layer, insulation structure layer with the metal inoxidizing coating respectively for major structure layer symmetry has arranged the electrical heating membrane in the first insulation structure layer.

Preferably, the first insulating structure layer has two sub-insulating layers, and the electric heating film is attached to the inner side surface of one of the sub-insulating layers.

Preferably, the electric heating film is sprayed on the inner side surface of the sub-insulating layer.

Preferably, the second insulating structure layer has two or three sub-insulating layers.

Preferably, the sub-insulating layers are glass fiber layers stacked on each other.

Preferably, the shape of the primary structural layer is configured as a whole or part of a leading edge of a wing of an aircraft.

Preferably, the shape of the primary structural layer is configured as a whole or part of an engine lip of an aircraft.

On the basis of the common knowledge in the field, the above preferred conditions can be combined at will to obtain the preferred embodiments of the present invention.

The utility model discloses an actively advance the effect and lie in:

the utility model discloses an anti-icing electrical heating unit can reduce structural deformation and structural stress strain that functional unit leads to in the course of being heated in machine-shaping process and work, avoids the warp of relevant structure, and the quick-witted installation of being convenient for, and the pneumatic appearance that helps improving the product life of electric anti-icing system, the aircraft position that guarantee anti-icing electrical heating unit corresponds is not destroyed.

Drawings

Fig. 1 is a schematic view of a layered structure of an anti-icing electric heating unit according to a preferred embodiment of the present invention.

Fig. 2 is a schematic view of an anti-icing electric heating unit according to a preferred embodiment of the present invention.

Detailed Description

The following detailed description of the preferred embodiments of the present invention is provided in conjunction with the accompanying drawings, and the following description is exemplary and not intended to limit the present invention, and any other similar situations may fall within the scope of the present invention.

In the following detailed description, directional terms, such as "left", "right", "upper", "lower", "front", "rear", and the like, are used with reference to the orientation as illustrated in the drawings. The components of embodiments of the present invention can be positioned in a number of different orientations and the directional terminology is used for purposes of illustration and is in no way limiting.

Referring to fig. 1, according to the preferred embodiment of the anti-icing electric heating unit of the present invention, the layered structure of the anti-icing electric heating unit includes 5 structural layer modules, which are sequentially a first metal protective layer a, a first insulating structural layer B, a main structural layer C, a second insulating structural layer D, and a second metal protective layer E from top to bottom.

The main structure layer C is provided with symmetrical composite material layers, a first insulating structure layer B and a second insulating structure layer D are respectively paved on the upper surface and the lower surface of the main structure layer C, a first metal protective layer A and a second metal protective layer E are respectively paved on the outer sides of the insulating structure layers B and D, the first insulating structure layer B and the second insulating structure layer D, the first metal protective layer A and the second metal protective layer E are respectively symmetrical relative to the main structure layer C, and an electric heating film B2 is arranged in the first insulating structure layer B.

In the conventional anti-icing electric heating functional unit, an insulating layer, a metal layer and an electric heating film are usually arranged on one side surface of a main structural layer, so that structural asymmetry is caused, the warping and deformation of a unit structure are easily caused, and the structural deformation of internal stress strain of the asymmetric structure is easily caused by heating of the unit in the working process after installation. In contrast, the heating element for preventing diseases according to the above embodiment of the present invention has a substantially symmetrical layered structure arrangement, so that the problem of structural deformation can be avoided to the maximum extent.

According to some preferred embodiments, the first insulating structure layer B has two sub-insulating layers B1 and B3, and the electric heating film B2 may be attached to an inner side surface of one sub-insulating layer. For example, the electric heating film B2 may be sprayed on the inner side surface of the sub-insulating layer B1 or B3. Alternatively, the electrically heated film B2 may also be a conductive circuit previously processed on the inner side surface of the sub-insulating layer. The second insulating structure layer D may have two or three sub-insulating layers corresponding to the first insulating structure layer B, thereby constituting a substantially symmetrical arrangement with respect to the main structure layer C.

According to some preferred embodiments of the present invention, the sub-insulating layer is a glass fiber layer. The composite material layer is made of a carbon fiber material. The metal protective layer may be made of an aluminum alloy or a titanium alloy.

According to some preferred embodiments of the present invention, as shown with reference to fig. 2, the shape of the primary structural layer is configured as a whole or as part of the leading edge of the wing of the aircraft. Alternatively, the shape of the primary structural layer is configured as an entirety or portion of an engine lip of the aircraft.

According to the utility model discloses an anti-icing electric heating unit of preferred embodiment can adopt the positive membrane shaping mode in the processing of combined material base member, accomplishes following step in proper order and processes:

1) processing a second metal protective layer E according to the structural shape of the relevant airplane part, wherein the material of the second metal protective layer E can be metal such as aluminum alloy, titanium alloy and the like, and arranging the second metal protective layer E on a male die;

2) laying a second insulating structure layer D on the second metal protective layer E, wherein the second insulating structure layer D can be a multilayer structure, such as multiple glass fiber layers or made of other insulating materials;

3) laying a main structural layer C, which can be a multi-layer carbon fiber structure, on the second insulating structural layer;

4) laying a sub-insulating layer B3 of a first insulating structure layer on the main structure layer C, then arranging an electric heating film B2 on the sub-insulating layer B3 in a spraying processing mode, and then arranging a sub-insulating layer B1;

5) the first metal protective layer a is processed and arranged outermost.

In addition, in order to improve the bonding strength between the metal protective layer and the insulating structure layer, a processing mode of adhesive bonding can be selected. The insulating structure layer can be laid layer by layer, and a sandwich structure processed in advance can also be adopted. The metal protective layer can be a metal structure processed in advance, and can also be processed and formed on the basis of the insulating structure layer in a spraying mode.

Although particular embodiments of the present invention have been described above, it will be appreciated by those skilled in the art that these are examples only and that the scope of the present invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and the principles of the present invention, and these changes and modifications are all within the scope of the present invention.

Claims

1. The utility model provides an anti-icing electrical heating unit, its characterized in that, it includes the major structure layer, the major structure layer has the combined material layer of symmetry, first insulating structure layer and second insulating structure layer have been laid respectively to the upper and lower surface of major structure layer, the metal inoxidizing coating has been laid respectively to the outside of first and second insulating structure layer, first and second insulating structure layer with the metal inoxidizing coating respectively for the major structure layer symmetry has arranged the electrical heating membrane in the first insulating structure layer.

2. The anti-icing electric heating unit according to claim 1, wherein the first insulating structure layer has two sub-insulating layers, and the electric heating film is attached to an inner side surface of one of the sub-insulating layers.

3. The anti-icing electric heating unit according to claim 2, wherein said electric heating film is sprayed on an inner side surface of said sub-insulating layer.

4. The anti-icing electric heating unit according to claim 2, wherein the second insulating structure layer has two or three sub-insulating layers.

5. The anti-icing electric heating unit of any one of claims 2 to 4, wherein said sub-insulating layers are glass fiber layers laminated to each other.

6. The anti-icing electric heating unit of claim 1, wherein said primary structural layer is shaped to be configured as a whole or as part of a leading edge of an aircraft wing.

7. The anti-icing electric heating unit of claim 1, wherein said primary structural layer is shaped to be configured as an entirety or a portion of an engine lip of an aircraft.