Composite material electric heating anti-icing assembly and manufacturing method thereof

Abstract

The invention discloses a composite material electric heating anti-icing assembly and a manufacturing method thereof. The composite material electric heating anti-icing assembly comprises an electronic temperature control device, a first composite material structure layer, an electric heating sheet layer and a second composite material structure layer. The electric heating sheet layer is positioned between the first composite material structure layer and the second composite material structure layer; and the electronic temperature control equipment is electrically connected with the electric heating sheet layer. According to the aircraft anti-icing structure, the structural design that the first composite material structural layer and the second composite material structural layer clamp and place the electric heating sheet layer is adopted, the weight of the aircraft anti-icing structure can be effectively reduced, manufacturing of a light anti-icing assembly can be achieved through the means of composite material design, material selection and the like, and the application requirement for aircraft light weight is met.

Description

Technical Field

[0001] The present application relates to a composite material electric heating anti-icing component and a manufacturing method thereof, belonging to the technical field of aerospace equipment. Background Art

[0002] When an aircraft is flying at high altitude, ice is easy to form on the leading edge of the air inlet. If the ice is sucked into the air inlet, it will cause engine failure, and in serious cases, it will cause the aircraft to crash.

[0003] At present, most of the anti-icing components of aircraft are made of metal, and the engine heat flow is used to heat and prevent ice. Not only is the structure complex, but the weight of the mechanism is large and the processing cost is high. Therefore, a manufacturing method of a composite material electric heating anti-icing component can effectively reduce the weight of the aircraft anti-icing structure, and through the design and material selection of composite materials, the lightweight anti-icing component can be manufactured to meet the application requirements of lightweight aircraft. Summary of the invention

[0004] In view of the shortcomings of the prior art, on the one hand, the present application provides a composite electric heating anti-icing component, including an electronic temperature control device, a first composite material structure layer, an electric heating sheet layer and a second composite material structure layer; the electric heating sheet layer is located between the first composite material structure layer and the second composite material structure layer; the electronic temperature control device is electrically connected to the electric heating sheet layer.

[0005] In the above technical scheme, further, the first composite material structural layer and the second composite material structural layer are both made of a matrix material and a reinforcement material; the matrix material is a combination of one or more of a thermosetting resin, a thermoplastic resin, a ceramic matrix, and a metal matrix; the reinforcement material is a combination of one or more of glass fiber, carbon fiber, basalt fiber, and aramid fiber, and the fiber form is a combination of one or more of chopped fiber, continuous fiber, and fiber fabric.

[0006] In the above technical solution, further, it also includes an assembly mechanism for fixed connection of the aircraft structure.

[0007] In the above technical solution, further, the electric heating sheet layer is a resistive heating sheet, a graphite heating sheet, or a combination of the two.

[0008] On the other hand, the present application also provides a method for manufacturing a composite material electric heating anti-icing component, comprising:

[0009] Step 1, manufacturing a first composite material structure layer and a second composite material structure layer;

[0010] Step 2: adopt variable thickness ply design according to the load conditions of the anti-icing component, and accurately lay the variable thickness ply using laser projection equipment;

[0011] Step three, disposing an electric heating sheet layer composed of a heating sheet between the first composite material structure layer and the second composite material structure layer;

[0012] Step 4: Install the composite material electric heating anti-icing assembly consisting of the first composite material structure layer, the electric heating sheet layer and the second composite material structure layer on the aircraft through an assembly mechanism.

[0013] In the above technical solution, further, the first composite material structure layer and the second composite material structure layer are both manufactured from a matrix material and a reinforcement material by using a prepreg placement process.

[0014] In the above technical scheme, further, it includes: prepreg cutting and prepreg laying, curing and assembling after the skin is laid, laying the prepreg in the area requiring anti-icing heating after assembly, laying the heating plate and the platinum resistor in this area, and finally laying the inner skin, after laying, the product is encapsulated with a vacuum bag, after the product is encapsulated, the mold is placed in an autoclave for heating and curing, after curing, the mold is taken out of the autoclave, the vacuum bag is removed, and the auxiliary materials on the surface are cleaned.

[0015] In the above technical solution, further, the prepreg is cut according to the cross-sectional size of each layer, and the prepreg is laid on the surface of the core mold in the order of 0° / ±45° with the length direction as the 0° direction, and the layer positioning is performed by laser projection during the laying process.

[0016] In the above technical solution, further, the matrix material is a combination of one or more of thermosetting resin, thermoplastic resin, ceramic matrix, and metal matrix; the reinforcement material is a combination of one or more of glass fiber, carbon fiber, basalt fiber, and aramid fiber, and the fiber form is a combination of one or more of chopped fiber, continuous fiber, and fiber fabric.

[0017] In the above technical solution, further, the electric heating sheet layer is a resistive heating sheet, a graphite heating sheet, or a combination of the two.

[0018] The present application provides a composite material electric heating anti-icing component and a manufacturing method thereof, and the beneficial effects are as follows:

[0019] A composite material electric heating anti-icing component provided in the present application adopts a structural design in which a first composite material structure layer and a second composite material structure layer sandwich an electric heating sheet layer, which can effectively reduce the weight of the aircraft's anti-icing structure, and through the design and selection of composite materials, it can realize the manufacture of lightweight anti-icing components to meet the application requirements of lightweight aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0021] Figure 1 A front view of a composite material electric heating anti-icing assembly provided in an embodiment of the present application;

[0022] Figure 2 A cross-sectional view of a composite electric heating anti-icing assembly provided in an embodiment of the present application in a first direction;

[0023] Figure 3 A cross-sectional view of a composite electric heating anti-icing assembly provided in an embodiment of the present application in a second direction;

[0024] Figure 4 A process flow chart of a method for manufacturing a composite material electric heating anti-icing component provided in an embodiment of the present application;

[0025] Figure 5 A partial schematic diagram of a composite material electric heating anti-icing assembly in a thickened area provided in an embodiment of the present application. Description of the drawings:

[0027] 1- aircraft leading edge structure; 2- first composite material structure layer; 3- electric heating plate layer; 4- second composite material structure layer; 5- reinforcement rib installation area; 6- skin area; 7- thickening area. DETAILED DESCRIPTION

[0028] In order to make the technical means, creative features, objectives and effects achieved by the present invention easy to understand, the present invention is further explained below in conjunction with specific implementation methods.

[0029] The embodiments based on the concepts of the present disclosure may be subjected to various changes and may have various forms, so specific embodiments will be exemplified in the drawings and described in detail in this specification or application. However, this is not to limit the embodiments based on the concepts of the present disclosure to specific disclosed forms, and should be understood to include all changes, equivalents and substitutes included in the ideas and technical scope of the present disclosure.

[0030] The terms "first" and "second" can be used to describe a variety of components, but the components are not limited by the terms. The terms are only used to distinguish one component from other components. For example, within the scope of the rights based on the concept of the present disclosure, the first component can be named as the second component, and similarly, the second component can also be named as the first component.

[0031] When a certain constituent element is said to be "connected" or "connected to" another constituent element, it should be understood that it can be directly connected to or connected to the other constituent element, or other constituent elements may be present in between. On the contrary, when a certain constituent element is said to be "directly connected to" or "directly connected to" another constituent element, it should be understood that no other constituent elements are present in between. Other expressions used to describe the relationship between constituent elements, that is, "between" or "directly between" or "adjacent to" or "directly adjacent to" etc., should also be interpreted in the same way.

[0032] The terms used in this specification are only used to illustrate specific embodiments and are not intended to limit the meaning of the present disclosure. Unless the contrary meaning is clearly stated in the context, the singular expression includes the plural expression. In this specification, the terms "including" or "having" are intended to specify the existence of a preset feature, number, step, action, constituent element, component or combination thereof, and should be understood as not excluding in advance the existence or additional possibility of one or more other features or numbers, steps, actions, constituent elements, components or combinations thereof.

[0033] Unless otherwise defined, all terms used herein, including technical or scientific terms, have the same meaning as those generally understood by a person of ordinary skill in the art to which the present disclosure belongs. Terms that are the same as those defined in a commonly used dictionary should be interpreted in a manner consistent with the meanings in the context of the relevant art, and should not be interpreted ideally or excessively as formal meanings unless explicitly defined in this specification.

[0034] At present, most of the anti-icing components of aircraft are made of metal, and the engine heat flow is used to heat and prevent ice. Not only is the structure complex, but the weight of the mechanism is large and the processing cost is high. In this regard, the present application provides a composite material electric heating anti-icing component and a manufacturing method thereof, which can effectively reduce the weight of the aircraft anti-icing structure, and through the design and material selection of composite materials, the lightweight anti-icing component can be manufactured to meet the application requirements of lightweight aircraft.

[0035] The technical solution of the present application is further described below in conjunction with the accompanying drawings of the specification.

[0036] See also Figure 1-Figure 3 The present application provides a composite material electric heating anti-icing component, an electronic temperature control device, a first composite material structure layer 2, an electric heating sheet layer 3 and a second composite material structure layer 4; the electric heating sheet layer 3 is located between the first composite material structure layer 2 and the second composite material structure layer 4; the electronic temperature control device is electrically connected to the electric heating sheet layer 3.

[0037] The structural design in which the electric heating plate layer 3 is sandwiched between the first composite material structure layer 2 and the second composite material structure layer 4 can effectively reduce the weight of the aircraft's anti-icing structure, and through the design and selection of composite materials, the manufacture of lightweight anti-icing components can be achieved to meet the application requirements of lightweight aircraft.

[0038] In some embodiments, the first composite material structural layer 2 and the second composite material structural layer 4 are both made of a matrix material and a reinforcement material; the matrix material is a combination of one or more of a thermosetting resin, a thermoplastic resin, a ceramic matrix, and a metal matrix; the reinforcement material is a combination of one or more of glass fiber, carbon fiber, basalt fiber, and aramid fiber, and the fiber form is a combination of one or more of chopped fiber, continuous fiber, and fiber fabric.

[0039] In some embodiments, an assembly mechanism for fixed connection to an aircraft structure is also included, and the anti-icing assembly is fixed to the aircraft leading edge structure 1 using the assembly mechanism.

[0040] In some embodiments, the electric heating plate layer 3 is a resistive heating plate, a graphite heating plate, or a combination of the two.

[0041] See also Figure 4 The present application also provides a method for manufacturing a composite material electric heating anti-icing component, comprising:

[0042] Step 1, manufacturing a first composite material structure layer 2 and a second composite material structure layer 4;

[0043] The first composite material structure layer 2 and the second composite material structure layer 4 are both manufactured from a matrix material and a reinforcement material by using a prepreg placement process.

[0044] Specifically, it includes: prepreg cutting and prepreg laying, curing and assembly after the skin is laid, laying of prepreg in the area requiring anti-icing heating after assembly, laying of heating plates and platinum resistors in this area, and finally laying of the inner skin. After laying, the product is sealed with a vacuum bag. After the product is sealed, the mold is placed in an autoclave for heating and curing. After curing, the mold is taken out of the autoclave, the vacuum bag is removed, and the auxiliary materials on the surface are cleaned.

[0045] Furthermore, the method is characterized in that the prepreg is cut according to the cross-sectional dimensions of each ply, and is laid on the surface of the core mold in the order of 0° / ±45° with the length direction being the 0° direction, and laser projection is used for ply positioning during the laying process.

[0046] The matrix material is a combination of one or more of thermosetting resin, thermoplastic resin, ceramic matrix, and metal matrix; the reinforcement material is a combination of one or more of glass fiber, carbon fiber, basalt fiber, and aramid fiber, and the fiber form is a combination of one or more of chopped fiber, continuous fiber, and fiber fabric.

[0047] Step 2: Use variable thickness ply design according to the load conditions at the location of the anti-icing component, and accurately lay the variable thickness ply using laser projection equipment.

[0048] See also Figure 5 The anti-icing assembly is provided with a reinforcement rib installation area 5, a skin area 6 and a thickened area 7. The thickened area 7 plays the following role: at a location with a greater load, the strength is improved by increasing the thickness.

[0049] Step three: an electric heating sheet layer 3 composed of heating sheets is arranged between the first composite material structure layer 2 and the second composite material structure layer 4 .

[0050] The electric heating sheet layer 3 is a resistive heating sheet, a graphite heating sheet, or a combination of the two.

[0051] Step 4: Install the composite material electric heating anti-icing assembly consisting of the first composite material structure layer 2, the electric heating sheet layer 3 and the second composite material structure layer 4 on the aircraft through an assembly mechanism.

[0052] In addition, it should be understood that although this specification is described according to implementation methods, not every implementation method contains only one independent technical solution. This narrative method of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole and the technical solutions in each embodiment.

Claims

1. A composite material electric heating anti-icing component, characterized in that: It comprises an electronic temperature control device, a first composite material structure layer, an electric heating sheet layer and a second composite material structure layer; the electric heating sheet layer is located between the first composite material structure layer and the second composite material structure layer; the electronic temperature control device is electrically connected to the electric heating sheet layer.

2. The composite material electric heating anti-icing component according to claim 1, characterized in that: The first composite material structural layer and the second composite material structural layer are both made of a matrix material and a reinforcement material; the matrix material is a combination of one or more of a thermosetting resin, a thermoplastic resin, a ceramic matrix, and a metal matrix; the reinforcement material is a combination of one or more of glass fiber, carbon fiber, basalt fiber, and aramid fiber, and the fiber form is a combination of one or more of chopped fiber, continuous fiber, and fiber fabric.

3. A composite material electric heating anti-icing component according to claim 1 or 2, characterized in that: Also included is an assembly mechanism for fixed connection to an aircraft structure.

4. The composite material electric heating anti-icing component according to claim 1, characterized in that: The electric heating sheet layer is a resistive heating sheet, a graphite heating sheet, or a combination of the two.

5. A method for manufacturing a composite material electric heating anti-icing component, characterized in that: include: Step 1, manufacturing a first composite material structure layer and a second composite material structure layer; Step 2: adopt variable thickness ply design according to the load conditions of the anti-icing component, and accurately lay the variable thickness ply using laser projection equipment; Step three, disposing an electric heating sheet layer composed of a heating sheet between the first composite material structure layer and the second composite material structure layer; Step 4: Install the composite material electric heating anti-icing assembly consisting of the first composite material structure layer, the electric heating sheet layer and the second composite material structure layer on the aircraft through an assembly mechanism.

6. The method for manufacturing a composite material electric heating anti-icing component according to claim 5, characterized in that: The first composite material structure layer and the second composite material structure layer are both manufactured from a matrix material and a reinforcement material by using a prepreg placement process.

7. The method for manufacturing a composite material electric heating anti-icing component according to claim 6, characterized in that: include: Prepreg cutting and prepreg laying, curing and assembly after prepreg laying; After assembly, prepreg is laid in the area that needs anti-icing heating, heating plates and platinum resistors are laid in this area, and finally the inner skin is laid. After laying, the product is encapsulated with a vacuum bag. After the product is encapsulated, the mold is placed in an autoclave for heating and curing. After curing, the mold is taken out of the autoclave, the vacuum bag is removed, and the auxiliary materials on the surface are cleaned.

8. The method for manufacturing a composite material electric heating anti-icing component according to claim 7, characterized in that: The prepreg is cut according to the cross-sectional dimensions of each layer, and laid on the surface of the core mold in the order of 0° / ±45° with the length direction as the 0° direction. Laser projection is used for layer positioning during the laying process.

9. The method for manufacturing a composite material electric heating anti-icing component according to claim 6, characterized in that: The matrix material is a combination of one or more of thermosetting resin, thermoplastic resin, ceramic matrix, and metal matrix; the reinforcement material is a combination of one or more of glass fiber, carbon fiber, basalt fiber, and aramid fiber, and the fiber form is a combination of one or more of chopped fiber, continuous fiber, and fiber fabric.

10. The method for manufacturing a composite material electric heating anti-icing component according to claim 5, characterized in that: The electric heating sheet layer is a resistive heating sheet, a graphite heating sheet, or a combination of the two.

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