CN113120213A - Deformable wave-rider high-temperature-resistant flexible skin and design method thereof - Google Patents
Deformable wave-rider high-temperature-resistant flexible skin and design method thereof Download PDFInfo
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- CN113120213A CN113120213A CN202110348456.7A CN202110348456A CN113120213A CN 113120213 A CN113120213 A CN 113120213A CN 202110348456 A CN202110348456 A CN 202110348456A CN 113120213 A CN113120213 A CN 113120213A
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- layer
- flexible skin
- anisotropy
- aerogel
- deformable
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- 238000000034 method Methods 0.000 title claims abstract description 19
- 239000004964 aerogel Substances 0.000 claims abstract description 31
- 239000011159 matrix material Substances 0.000 claims abstract description 26
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 21
- 238000009413 insulation Methods 0.000 claims abstract description 21
- 239000002131 composite material Substances 0.000 claims abstract description 20
- 239000002041 carbon nanotube Substances 0.000 claims abstract description 12
- 229910021393 carbon nanotube Inorganic materials 0.000 claims abstract description 12
- 239000004433 Thermoplastic polyurethane Substances 0.000 claims abstract description 11
- 229920002803 thermoplastic polyurethane Polymers 0.000 claims abstract description 11
- 229910021389 graphene Inorganic materials 0.000 claims abstract description 9
- 238000002474 experimental method Methods 0.000 claims description 9
- 239000000463 material Substances 0.000 claims description 9
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims description 7
- 238000004519 manufacturing process Methods 0.000 claims description 7
- 229910052710 silicon Inorganic materials 0.000 claims description 7
- 239000010703 silicon Substances 0.000 claims description 7
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 4
- 239000004917 carbon fiber Substances 0.000 claims description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 4
- 238000010030 laminating Methods 0.000 claims description 3
- 239000011152 fibreglass Substances 0.000 claims 1
- 238000005452 bending Methods 0.000 abstract description 2
- 239000004965 Silica aerogel Substances 0.000 abstract 1
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 abstract 1
- 239000003365 glass fiber Substances 0.000 description 3
- 230000035939 shock Effects 0.000 description 3
- 238000005457 optimization Methods 0.000 description 2
- 210000001015 abdomen Anatomy 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 239000002071 nanotube Substances 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
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- 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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
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- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The application belongs to the field of aircraft skins, and particularly relates to a deformable waverider high-temperature-resistant flexible skin and a design method thereof. The skin comprises an aerogel heat insulation layer (1), an elastic matrix layer (2) and a high anisotropy supporting layer (3) which are sequentially arranged from the outer side to the inner side, wherein the aerogel heat insulation layer (1) is made of graphene reinforced silica aerogel; the elastic matrix layer (2) is made of a composite material of carbon nanotubes and thermoplastic polyurethane; the high-anisotropy supporting layer (3) is made of a 0 Poisson ratio composite material. The aerogel is used for thermal protection, can resist the high temperature of more than 1300 ℃, and has the mechanical properties of large deformation, high strength, wide temperature range and stability and impact resistance; the elastic matrix of the composite material of the carbon nano tube and the thermoplastic polyurethane also has the capabilities of high temperature resistance, high strength, large deformation and the like; the high anisotropy support may further improve the bending stiffness of the large deformation skin while maintaining the large deformation capability.
Description
Technical Field
The application belongs to the field of aircraft skins, and particularly relates to a deformable waverider high-temperature-resistant flexible skin and a design method thereof.
Background
In the flight process of the waverider hypersonic aircraft, the flight height and the speed change range of the waverider hypersonic aircraft are large, and the conventional hypersonic aircraft structure with a fixed shape is difficult to keep the aerodynamic performance of high lift-drag ratio all the time. To solve this problem, designers have proposed the concept of a deformable waverider aircraft, primarily by varying the shape of the belly-side waverider. However, the waverider hypersonic aircraft needs to meet the requirements of high temperature resistance, high pressure resistance and shock wave impact resistance, the extreme environment makes structural deformation difficult to realize, and particularly, a large-deformation skin structure firstly makes the best impact, and the working environment is the most severe.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The application aims to provide a deformable waverider high-temperature-resistant flexible skin and a design method thereof, so as to solve at least one problem in the prior art.
The technical scheme of the application is as follows:
the first aspect of the application provides a deformable waverider high-temperature-resistant flexible skin, which comprises an aerogel heat insulation layer, an elastic matrix layer and a high-anisotropy supporting layer which are arranged in sequence from the outer side to the inner side, wherein,
the aerogel heat insulation layer is made of graphene reinforced silicon aerogel;
the elastic matrix layer is made of a composite material of carbon nanotubes and thermoplastic polyurethane;
the high-anisotropy supporting layer is made of a 0 Poisson's ratio composite material.
Optionally, the elastic matrix layer and the aerogel thermal insulation layer are bonded by bonding.
Optionally, the elastic matrix layer is integrally formed with the aerogel thermal insulation layer.
Optionally, the highly anisotropic support layer and the elastic base layer are bonded by adhesion.
Optionally, the material of the high-anisotropy support layer is a carbon fiber material with a poisson ratio of 0.
Optionally, the material of the high-anisotropy support layer is a 0 poisson ratio glass fiber material.
A second aspect of the present application provides a method for designing a deformable waverider-derived high-temperature-resistant flexible skin, based on the deformable waverider-derived high-temperature-resistant flexible skin described above, including:
the method comprises the following steps of firstly, obtaining deformation, bearing and high temperature resistance requirements of a flexible skin;
step two, preparing graphene reinforced silicon aerogel to obtain an aerogel heat insulation layer;
step three, preparing a carbon nano tube and thermoplastic polyurethane composite material to obtain an elastic matrix layer;
step four, preparing the composite material with the Poisson ratio of 0 to obtain a high-anisotropy supporting layer;
fifthly, carrying out three-layer laminating process design on the aerogel heat insulation layer, the elastic matrix layer and the high-anisotropy supporting layer to obtain a flexible skin;
and step six, performing a deformation experiment, a bearing experiment and a thermal protection experiment on the flexible skin, and repeating the step two to the step six until the flexible skin meeting the performance requirement is obtained.
The invention has at least the following beneficial technical effects:
the deformable waverider high-temperature-resistant flexible skin is thermally protected by the aerogel, can resist the high temperature of more than 1300 ℃, and has the mechanical properties of large deformation, high strength, stable wide temperature range and impact resistance; the elastic matrix of the composite material of the carbon nano tube and the thermoplastic polyurethane also has the capabilities of high temperature resistance, high strength, large deformation and the like; the high-anisotropy support body can further improve the bending rigidity of the large-deformation skin, and simultaneously keeps the large-deformation capacity; the skin structure with high temperature resistance, high pressure resistance, shock wave impact resistance and large deformation can be realized.
Drawings
FIG. 1 is a schematic view of a deformable waverider high temperature resistant flexible skin according to one embodiment of the present application;
FIG. 2 is a cross-sectional view of a deformable waverider high temperature resistant flexible skin according to one embodiment of the present application;
FIG. 3 is a bottom view of a deformable waverider high temperature resistant flexible skin according to one embodiment of the present application;
FIG. 4 is a flow chart of a method for designing a deformable waverider high temperature resistant flexible skin according to an embodiment of the present application.
Wherein:
1-an aerogel thermal insulation layer; 2-an elastic matrix layer; 3-high anisotropy support layer.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1 to 4.
The first aspect of the application provides a flexible skin that can deform and is resistant to high temperature of wave-rider, as shown in fig. 1 to 3, is a three-layer composite structure, and includes aerogel insulating layer 1, elastic matrix layer 2 and high anisotropy supporting layer 3 that set gradually from outside to inside.
According to the deformable waverider high-temperature-resistant flexible skin, the aerogel heat insulation layer 1 can be graphene reinforced silicon aerogel or other high-temperature-resistant aerogels, and the elastic matrix layer 2 can be an elastic matrix formed by carbon nanotubes and thermoplastic polyurethane composite materials or other similar composite materials; the high-anisotropy supporting layer 3 may be a 0 poisson ratio supporting structure made of similar materials such as a 0 poisson ratio carbon fiber composite material supporting structure or a glass fiber composite material supporting structure shown in fig. 3, the high-anisotropy supporting layer 3 has the characteristic that the difference of mechanical properties of the inner surface and the outer surface in each direction is large, the high-anisotropy supporting layer has the properties of small elastic modulus of the inner surface in each direction and large elastic modulus of the outer surface in each direction, one direction of the inner surface meets the requirement of the 0 poisson ratio, the adopted structural form is a two-dimensional or three-dimensional lattice structure, and the processing is carried out through a material increase manufacturing processing mode. In this embodiment, aerogel insulating layer 1 can be through bonding or integrated into one piece with elasticity base member layer 2, and elasticity base member layer 2 and high anisotropic supporting layer 3 can combine through bonding.
According to the high-temperature-resistant flexible skin of the deformable waverider, firstly, the aerogel thermal insulation layer 1 is a high-supersonic aircraft thermal insulation structure which has both thermal insulation performance and mechanical performance, can resist high temperature of more than 1300 ℃, has stable mechanical performance and large deformation capacity, and can meet the requirement of self-adaptive deformation; secondly, the elastic matrix layer 2 of the carbon nanotube and thermoplastic polyurethane composite material utilizes the high strength of the elastic nanotube and the large deformation capacity of the elastic matrix, has high cutting design, can realize large deformation and high strength at the same time, and has high temperature resistance; finally, the high-anisotropy elastic supporting layer 3 can simultaneously realize large deformation and high bearing capacity through a curved beam structure and a reinforcing structure, has high anisotropy, and can meet the requirements of large deformation and high bearing capacity of the abdomen wave-rider of the wave-rider.
The flexible high-temperature-resistant flexible skin of the deformable wave carrier can meet the functional requirements of high temperature resistance, shock wave impact resistance, high pressure resistance, large deformation and the like simultaneously, so that the function of real-time optimization of the pneumatic appearance of the wave carrier according to different flight environments and states is realized, the requirement of multi-task and large envelope flight is further realized, and the problem of matching of the pneumatic performance of the wave carrier in the wide-airspace and wide-speed-domain range is solved. In conclusion, the combination of the three-layer structure can well solve the technical bottlenecks of high temperature resistance, high bearing capacity, high pressure resistance, large deformation and the like of the deformable waverider, and has a good application prospect.
A second aspect of the present application provides a method for designing a deformable waverider high-temperature-resistant flexible skin, where the flowchart of implementation steps is shown in fig. 4, and the method includes the following steps:
the method comprises the following steps of firstly, obtaining the deformation, bearing and high temperature resistance requirements of a flexible skin according to the overall performance requirements of the aircraft;
step two, designing graphene reinforced silicon aerogel by determining the graphene proportion and a molding process, and manufacturing an aerogel heat insulation layer 1 by using the graphene reinforced silicon aerogel;
thirdly, designing the carbon nano tube and thermoplastic polyurethane composite material through the selection of the elastic matrix, the determination of the proportion of the carbon nano tube and the forming process, and manufacturing the elastic matrix layer 2 by adopting the carbon nano tube and thermoplastic polyurethane composite material;
fourthly, performing topological optimization design on the high-anisotropy elastic support body, and manufacturing a high-anisotropy supporting layer 3 by adopting a high-anisotropy elastic support body structure made of a carbon fiber or glass fiber material with a Poisson ratio of 0;
fifthly, carrying out three-layer laminating process design on the aerogel heat insulation layer 1, the elastic matrix layer 2 and the high-anisotropy supporting layer 3 to obtain a flexible skin;
and step six, performing a deformation experiment, a bearing experiment and a thermal protection experiment on the flexible skin, and repeating the step two to the step six until the flexible skin meeting the performance requirement is obtained.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. A deformable wave rider high-temperature-resistant flexible skin is characterized by comprising an aerogel heat insulation layer (1), an elastic matrix layer (2) and a high-anisotropy supporting layer (3) which are sequentially arranged from the outer side to the inner side,
the aerogel heat insulation layer (1) is made of graphene reinforced silicon aerogel;
the elastic matrix layer (2) is made of a composite material of carbon nanotubes and thermoplastic polyurethane;
the high-anisotropy supporting layer (3) is made of a 0 Poisson ratio composite material.
2. The deformable waverider high temperature resistant flexible skin of claim 1, wherein the elastic matrix layer (2) is bonded to the aerogel insulation layer (1) by bonding.
3. The deformable waverider refractory flexible skin of claim 1, wherein the elastomeric matrix layer (2) is integrally formed with the aerogel insulation layer (1).
4. The deformable waverider refractory flexible skin of claim 1, wherein the highly anisotropic support layer (3) is bonded to the elastomeric matrix layer (2) by bonding.
5. The flexible skin of claim 1, wherein the high-anisotropy support layer (3) is made of a 0 Poisson's ratio carbon fiber material.
6. The flexible skin of claim 1, wherein the high-anisotropy support layer (3) is made of 0 Poisson's ratio fiberglass material.
7. A method for designing a deformable waverider high-temperature-resistant flexible skin based on any one of claims 1 to 6, comprising:
the method comprises the following steps of firstly, obtaining deformation, bearing and high temperature resistance requirements of a flexible skin;
step two, manufacturing an aerogel heat insulation layer (1) by adopting the graphene reinforced silicon aerogel;
thirdly, manufacturing an elastic matrix layer (2) by adopting a carbon nano tube and thermoplastic polyurethane composite material;
fourthly, manufacturing a high-anisotropy supporting layer (3) by adopting a composite material with a Poisson ratio of 0;
fifthly, carrying out three-layer laminating process design on the aerogel heat insulation layer (1), the elastic matrix layer (2) and the high-anisotropy supporting layer (3) to obtain a flexible skin;
and step six, performing a deformation experiment, a bearing experiment and a thermal protection experiment on the flexible skin, and repeating the step two to the step six until the flexible skin meeting the performance requirement is obtained.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110348456.7A CN113120213B (en) | 2021-03-31 | 2021-03-31 | Deformable waverider high-temperature-resistant flexible skin and design method thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110348456.7A CN113120213B (en) | 2021-03-31 | 2021-03-31 | Deformable waverider high-temperature-resistant flexible skin and design method thereof |
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| CN113120213B CN113120213B (en) | 2023-11-28 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114056544A (en) * | 2021-12-24 | 2022-02-18 | 中国商用飞机有限责任公司 | Skin structure for a wing, aircraft with a skin structure and method for mounting a skin structure |
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| WO1999038610A1 (en) * | 1998-02-02 | 1999-08-05 | The Regents Of The University Of California | Flexible aerogel composite for mechanical stability and process of fabrication |
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| DE202017105966U1 (en) * | 2017-09-29 | 2017-11-07 | Airbus Operations Gmbh | Carbon airgel composite prepreg |
| GB2559979A (en) * | 2017-02-23 | 2018-08-29 | Graphene Composites Ltd | Graphene/Aerogel composite |
| GB2571292A (en) * | 2018-02-22 | 2019-08-28 | Graphene Composites Ltd | Composite structure and method of manufacture |
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2021
- 2021-03-31 CN CN202110348456.7A patent/CN113120213B/en active Active
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| WO1999038610A1 (en) * | 1998-02-02 | 1999-08-05 | The Regents Of The University Of California | Flexible aerogel composite for mechanical stability and process of fabrication |
| US20100272950A1 (en) * | 2009-04-27 | 2010-10-28 | Tsinghua University | Positive and negative poisson ratio material |
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| CN113120213B (en) | 2023-11-28 |
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