CN111038019B - Composite material, aircraft component and anti-icing and deicing method - Google Patents

Composite material, aircraft component and anti-icing and deicing method Download PDF

Info

Publication number
CN111038019B
CN111038019B CN201911093862.2A CN201911093862A CN111038019B CN 111038019 B CN111038019 B CN 111038019B CN 201911093862 A CN201911093862 A CN 201911093862A CN 111038019 B CN111038019 B CN 111038019B
Authority
CN
China
Prior art keywords
composite material
insulating layer
layer
icing
main structure
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN201911093862.2A
Other languages
Chinese (zh)
Other versions
CN111038019A (en
Inventor
白斌
李志茂
曾飞雄
孔子成
任哲钒
钱梦霜
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Commercial Aircraft Corp of China Ltd
Original Assignee
Commercial Aircraft Corp of China Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Commercial Aircraft Corp of China Ltd filed Critical Commercial Aircraft Corp of China Ltd
Priority to CN201911093862.2A priority Critical patent/CN111038019B/en
Publication of CN111038019A publication Critical patent/CN111038019A/en
Application granted granted Critical
Publication of CN111038019B publication Critical patent/CN111038019B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B33/00—Layered products characterised by particular properties or particular surface features, e.g. particular surface coatings; Layered products designed for particular purposes not covered by another single class
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
    • B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
    • B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
    • B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B3/00—Ohmic-resistance heating
    • H05B3/02—Details
    • H05B3/06—Heater elements structurally combined with coupling elements or holders
    • H05B3/08—Heater elements structurally combined with coupling elements or holders having electric connections specially adapted for high temperatures
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/101—Glass fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/106—Carbon fibres, e.g. graphite fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/20—Properties of the layers or laminate having particular electrical or magnetic properties, e.g. piezoelectric
    • B32B2307/206—Insulating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/30—Properties of the layers or laminate having particular thermal properties
    • B32B2307/302—Conductive
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2605/00—Vehicles
    • B32B2605/18—Aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials

Abstract

The invention relates to a composite material, an aircraft component and an anti-icing and de-icing method. The composite material consists of a main structure layer, an upper insulating layer and a lower insulating layer. The main structure layer is made of carbon fiber composite materials and is constructed to be conductive and generate heat in a conductive state; the upper insulating layer is arranged on the upper side of the main structure layer, the lower insulating layer is arranged on the lower side of the main structure layer, and the upper insulating layer and the lower insulating layer are both made of composite materials compatible with carbon fibers. According to the invention, the main structure layer can play a structural bearing role and can be electrified to generate heat, compared with the traditional composite material, the step of processing the electric heating film is omitted, the production process is simplified, and the problems of layering, air bubbles, peeling and the like in repeated use are avoided. And the structure bearing part and the heating part are integrated into a whole, so that the composite material is lighter.

Description

Composite material, aircraft component and anti-icing and deicing method
Technical Field
The invention relates to the field of aircraft maintenance and manufacturing, in particular to a composite material for preventing and removing ice, an aircraft part and an anti-icing and deicing method.
Background
With the increasing adoption of composite materials in modern civil aircraft structures and the application of the multi-electrical technology of the aircraft and the development of the electrical anti-icing technology, the electrical anti-icing and deicing of the aircraft become the development trend in the future anti-icing field. The key part of the electric anti-icing and deicing system of the airplane is an electric heating functional unit which is a structural functional part and has four basic elements of structural bearing, electrification heating, internal insulation, lightning protection, rainwater erosion and the like.
The composite material electric anti-icing functional unit is a structural functional member formed by introducing a metal heating element into a composite material, and the basic structural form from outside to inside is 'protective layer 4-insulating layer 2-electric heating film 3-insulating layer 2-composite material layer 1-insulating layer 2', and is specifically shown in figure 1. Wherein the composite material layer plays a role in structural bearing and shaping; the electric heating film layer can generate heat after being electrified; the insulating layer is used for insulating the heating layer from other structural layers; the protective layer is used for preventing lightning, rain erosion and the like.
The design and processing process flow of the multilayer structure of the electric deicing function unit of the composite material are relatively complex, and due to the material property difference of the electric heating film metal material and other composite material layers, such as the difference of adhesion, thermal expansion coefficient and the like, the phenomena of delamination, bubbling, peeling and the like are easy to occur in the repeated heating cycle use process.
It is therefore desirable to provide a composite material, aircraft component and method of ice protection and removal that at least partially addresses the above problems.
Disclosure of Invention
The invention aims to provide a composite material for an aircraft, an aircraft component and a method for using the composite material. Compared with the traditional composite material, the main structure layer of the composite material can play a role in structural bearing and can be electrified to generate heat, the step of processing an electric heating film is omitted, the production process is simplified, and the problems of layering, air bubbles, peeling and the like in repeated use are avoided.
According to one aspect of the present invention, there is provided a composite material for an aircraft, the composite material consisting of:
a main structural layer made of a carbon fiber composite material and configured to be electrically conductive and to generate heat in an electrically conductive state;
the upper insulation layer is arranged on the upper side of the main structure layer, the lower insulation layer is arranged on the lower side of the main structure layer, and the upper insulation layer and the lower insulation layer are made of composite materials compatible with carbon fibers.
In one embodiment, the primary structural layer is a unitary homogeneous structure and the primary structural layer serves as a structural load carrying unit for the composite material.
In one embodiment, the material of the upper insulating layer is different from the material of the lower insulating layer.
In one embodiment, the lower insulating layer has a thermal conductivity lower than that of the upper insulating layer, and the lower insulating layer has a thickness greater than that of the upper insulating layer.
In one embodiment, the thickness of the primary structural layer is 1/5 the same as the thickness of the composite material.
According to another aspect of the invention, there is provided an aircraft component made from the composite material of any one of the preceding aspects, further comprising an electrical connection component embedded at one end within the primary structural layer of the composite material and at the other end for connection to a power source.
In one embodiment, the power connection part is formed in a T-shaped structure including an output part having a strip structure and embedded inside the main structure layer, opposite ends of the output part are electrically connected to the positive and negative electrodes of the power supply, respectively, and a pin part extending outward perpendicular to the output part.
In one embodiment, the aircraft component further comprises a protective layer disposed on an upper side of the upper insulating layer of the composite material.
According to a further aspect of the present invention there is provided a method of anti-icing and de-icing an aircraft component provided with a composite material according to any one of the preceding aspects, the method comprising the steps of: and electrifying the main structure layer of the composite material to generate heat, thereby realizing the anti-icing and deicing.
According to the invention, the main structure layer of the composite material can play a structural bearing role and can be electrified to generate heat, compared with the traditional composite material, the step of processing the electric heating film is omitted, the production process is simplified, and the problems of layering, air bubbles, peeling and the like in repeated use are avoided. And the structure bearing part and the heating part are integrated into a whole, so that the whole thickness can be reduced, and the composite material is lighter.
Drawings
For a better understanding of the above and other objects, features, advantages and functions of the present invention, reference should be made to the preferred embodiments illustrated in the accompanying drawings. Like reference numerals in the drawings refer to like parts. It will be appreciated by persons skilled in the art that the drawings are intended to illustrate preferred embodiments of the invention without any limiting effect on the scope of the invention, and that the various components in the drawings are not drawn to scale.
FIG. 1 is a prior art composite structure;
FIG. 2 is a schematic structural view of a composite material according to a preferred embodiment of the present invention;
fig. 3 is a schematic view of the installation of the power receiving member in the preferred embodiment.
Detailed Description
Reference will now be made in detail to the embodiments of the present invention, examples of which are illustrated in the accompanying drawings. What has been described herein is merely a preferred embodiment in accordance with the present invention and other ways of practicing the invention will occur to those skilled in the art and are within the scope of the invention.
The invention provides a composite material for an aircraft, an aircraft component with the composite material and an anti-icing and de-icing method. Fig. 2 and 3 show a composite material according to a preferred embodiment of the invention and further material layers arranged on the composite material.
Reference is first made to fig. 2. The composite material mainly plays a role in preventing ice and removing ice and is composed of a main structure layer 5, an upper insulating layer 61 and a lower insulating layer 62.
Wherein, the main structure layer 5 is an integral homogeneous structure made of carbon fiber composite material, the main structure layer 5 is a structure bearing unit made of composite material, and the main structure layer 5 is constructed to be capable of conducting electricity and generating heat, and the generated heat can be led out outwards so as to play a role in preventing and removing ice. That is, in the composite material, the integrated main structural layer 5 serves two functions at the same time: the structure bears the weight of and the effect of generating heat under the electrified condition.
Preferably, the thickness of the main structural layer 5 is 1/5 of the overall thickness of the composite material, and as a component for structural load bearing and heat generation, the thickness value of the main structural layer 5 is small, so that the structure is light, the material is saved, and the production and the manufacture are convenient.
An upper insulation layer 61 of composite material is provided on the top side of the main structural layer 5, a lower insulation layer 62 is provided on the bottom side of the main structural layer 5, and the upper insulation layer 61 and the lower insulation layer 62 are made of composite material compatible with carbon fiber such as glass fiber to serve as insulation on the top side and the bottom side of the main structural layer 5, respectively. Preferably, the upper insulating layer 61 may be made of a material different from that of the lower insulating layer 62.
For example, when the composite material is used, the target device is usually placed above the composite material, so that the lower insulating layer 62 can be set to have a thermal conductivity lower than that of the upper insulating layer 61, and the thickness of the lower insulating layer 62 is greater than that of the upper insulating layer 61, so that heat can be conveniently transmitted upwards as far as possible, and downward heat transmission is avoided.
The aircraft component provided by the embodiment comprises the composite material. In this aircraft component, the upper side of the composite material is provided with a protective layer 7, the protective layer 7 being in particular provided on the top side of the insulating layer located on the top side of the main structural layer 5, and the protective layer 7 being made of a metallic material.
Preferably, the aircraft component of the present embodiment further comprises a power connection component 8, one end of the power connection component 8 being disposed inside the main structural layer 5, the other end being for connection with a power source. More preferably, referring to fig. 3, the power receiving part 8 may include an output part 81 and a pin part 82. The output portion 81 has a plate-like structure or a strip-like structure, and both ends thereof are connected to the positive electrode and the negative electrode of the power supply, respectively. The output portion 81 is embedded inside the main structure layer 5; the pin portion 82 extends outward perpendicularly to the output portion 81, so that the power receiving member 8 is formed in a T-shaped structure. Such setting can promote electrically conductive heating efficiency, makes main structural layer 5 can generate heat fast.
Since the main structure layer 5 is in point contact with the electrode points, a strip-shaped high-level region is present on the main structure layer 5. Preferably, if the voltage application area is wide, the main structure layer 5 will be heated as a whole.
Of course, the power receiving member 8 may not be included in the composite material, and the power receiving member 8 may be used independently of the composite material and merely in cooperation therewith.
The method for preventing and removing ice provided by the embodiment comprises the following steps: electricity is applied to the primary structural layer 5 of the composite material to cause it to generate heat, thereby achieving ice protection and ice removal.
According to the invention, the main structure layer of the composite material can play a structural bearing role and can be electrified to generate heat, so that the arrangement of an additional heating layer is omitted, the consistency of the material properties of the main structure of the functional unit is ensured, and the composite material has better strength and longer service life. This also eliminates the step of processing the electric heating film, simplifies the production process, and avoids the occurrence of problems such as delamination, bubbling, and peeling in repeated use. And the structure bearing part and the heating part are integrated into a whole, so that the whole thickness can be reduced, and the composite material is lighter.
The foregoing description of various embodiments of the invention is provided for the purpose of illustration to one of ordinary skill in the relevant art. It is not intended to be exhaustive or to limit the invention to a single disclosed embodiment. As mentioned above, many alternatives and modifications of the present invention will be apparent to those skilled in the art of the above teachings. Thus, while some alternative embodiments are specifically described, other embodiments will be apparent to, or relatively easily developed by, those of ordinary skill in the art. The present invention is intended to embrace all such alternatives, modifications and variances of the present invention described herein, as well as other embodiments that fall within the spirit and scope of the present invention as described above.
Reference numerals:
main structure layer 5
Upper insulating layer 61
Lower insulating layer 62
Protective layer 7
Connection device 8
Output section 81
And a pin portion 82.

Claims (6)

1. A composite material for an aircraft, characterized in that it consists of the following structure:
a main structural layer made of a carbon fiber composite material and configured to be electrically conductive and to generate heat in an electrically conductive state, the main structural layer being an integral homogeneous structure and serving as a structural load-bearing unit of the composite material;
an upper insulating layer and a lower insulating layer, wherein the upper insulating layer is arranged on the upper side of the main structure layer, the lower insulating layer is arranged on the lower side of the main structure layer, the upper insulating layer and the lower insulating layer are both made of composite materials compatible with carbon fibers,
wherein the thermal conductivity of the lower insulating layer is lower than the thermal conductivity of the upper insulating layer, and the thickness of the lower insulating layer is greater than the thickness of the upper insulating layer.
2. The composite of claim 1, wherein the thickness of the primary structural layer is 1/5 times the thickness of the composite.
3. An aircraft component made of a composite material according to any one of claims 1-2, characterized in that it further comprises an electrical connection means, one end of which is embedded inside the main structural layer of the composite material and the other end is intended to be connected to an electrical power source.
4. An aircraft component according to claim 3, wherein the electrical connection component is formed as a T-shaped structure comprising an output portion having a strip-like structure and embedded inside the main structural layer, opposite ends of the output portion being electrically connected to the positive and negative electrodes of the power supply respectively, and a pin portion extending outwardly perpendicularly to the output portion.
5. An aircraft component according to claim 3, further comprising a protective layer provided on the upper side of the upper insulating layer of the composite material.
6. A method of anti-icing and de-icing an aircraft component provided with a composite material according to any one of claims 1-2, characterized in that the method comprises the steps of: and electrifying the main structure layer of the composite material to generate heat, thereby realizing the anti-icing and deicing.
CN201911093862.2A 2019-11-11 2019-11-11 Composite material, aircraft component and anti-icing and deicing method Active CN111038019B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201911093862.2A CN111038019B (en) 2019-11-11 2019-11-11 Composite material, aircraft component and anti-icing and deicing method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201911093862.2A CN111038019B (en) 2019-11-11 2019-11-11 Composite material, aircraft component and anti-icing and deicing method

Publications (2)

Publication Number Publication Date
CN111038019A CN111038019A (en) 2020-04-21
CN111038019B true CN111038019B (en) 2022-06-14

Family

ID=70232670

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201911093862.2A Active CN111038019B (en) 2019-11-11 2019-11-11 Composite material, aircraft component and anti-icing and deicing method

Country Status (1)

Country Link
CN (1) CN111038019B (en)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2528795A1 (en) * 1982-06-17 1983-12-23 Westland Plc DEFROST DEVICE FOR AIRCRAFT
JP2014187233A (en) * 2013-03-25 2014-10-02 Panasonic Corp Heat radiation sheet and heat radiation structure using the same
US10708979B2 (en) * 2016-10-07 2020-07-07 De-Ice Technologies Heating a bulk medium
CN206602672U (en) * 2017-01-20 2017-10-31 中国商用飞机有限责任公司 Aircraft electricity anti-icing and deicing electric heating device
EP3800048B1 (en) * 2018-04-24 2022-02-23 Qarbon Aerospace (Foundation), LLC Composite aerostructure with integrated heating element
DE102018111703A1 (en) * 2018-05-16 2019-11-21 Airbus Defence and Space GmbH Structural component for an aircraft

Also Published As

Publication number Publication date
CN111038019A (en) 2020-04-21

Similar Documents

Publication Publication Date Title
US7789620B2 (en) Heater assembly for deicing and/or anti-icing a component
US8760838B2 (en) Lightning protection sheet with patterned discriminator
CN103925169A (en) Wind Turbine Rotor Blade De-icing Arrangement
CA2913600C (en) Conductor joint and conductor joint component
US20120019973A1 (en) Method and apparatus for grounding a composite aircraft structure
EP0983437A1 (en) Device and method for heating and deicing wind energy turbine blades
WO2011127997A1 (en) Heating mats arranged in a loop on a blade
EP3530938B1 (en) Ice melting device for blade, blade and wind turbine
WO2007136260A1 (en) Heated aerodynamic profile for composite structures
CN112757717A (en) Directional heat conduction electric heating device and preparation method
CN111038019B (en) Composite material, aircraft component and anti-icing and deicing method
CN110615107A (en) Heatable leading edge device, leading edge heating system and aircraft with same
CN111963393B (en) Blade electric heating device, blade, wind generating set and blade ice melting method
CN111016319B (en) Composite material and method for producing the same
CN216741850U (en) Partitioned composite carbon fiber heating device
CN215370126U (en) Heating device, wind power blade and wing
CN214821500U (en) Directional electric heating heat conduction device
CN110356540A (en) For aircraft can heating floor panel and floor heating system
CN101702332A (en) Ice-coating-proof power conducting wire
CN106803442B (en) Cold-resistant high-strength pulling-resisting cable
CN219421076U (en) Insulating glass ceramic heating sheet
CN114104299B (en) Device and method for preventing and removing ice by compounding superhydrophobic coating plasma and graphene electric heating
CN209625845U (en) Flame retardant type all-insulating tubular bus
CN107435617B (en) Carbon fiber heating chip assembly of wind power generation blade and manufacturing method thereof
CN201522862U (en) Ice-covering-proof power conductor

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant