CN113306697A - Novel hypersonic aircraft wing - Google Patents
Novel hypersonic aircraft wing Download PDFInfo
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- CN113306697A CN113306697A CN202110771582.3A CN202110771582A CN113306697A CN 113306697 A CN113306697 A CN 113306697A CN 202110771582 A CN202110771582 A CN 202110771582A CN 113306697 A CN113306697 A CN 113306697A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/36—Structures adapted to reduce effects of aerodynamic or other external heating
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Abstract
The invention provides a novel hypersonic aircraft wing, and relates to the field of wing structures of aircrafts. This novel hypersonic aircraft wing, including wing body and heat pipe, the heat pipe is used for the heat dissipation of wing body, the heat pipe sets up inside one side of wing body, the heat pipe includes imbibition core and shell, the outside fixed connection of imbibition core is in the inboard of shell, the inboard of imbibition core is provided with the evaporation chamber, the inside of imbibition core is provided with liquid working medium. The heat generated by the front edge of the wing is absorbed by the working medium at the evaporation section, the contact temperature of the upper surface of the wing and the outside atmosphere is lower, the heat is absorbed by the liquid absorption core attached to the inside of the heat pipe after the working medium releases the heat and is liquefied, and then the liquefied working medium flows back to the evaporation section, so that the cooling effect is remarkably improved.
Description
Technical Field
The invention relates to the field of wing structures of aircrafts, in particular to a novel hypersonic aircraft wing.
Background
The wing is an important component of an aircraft, mainly used for generating lift force and generally composed of a wing beam, a longitudinal wall, a stringer, a wing rib and a skin, and the interior of the wing is generally an overhead structure and is generally filled with an oil tank and circuits of some control systems. The wing of current supersonic aircraft is thinner, and the wing leading edge can encounter serious aerodynamic heating at high-speed flight in-process, and when high-speed air current and aircraft contacted, the air received the compression on aircraft surface, and gas can stagnate, forms the shock wave at the aircraft front end, and the kinetic energy of air current just can be converted into internal energy for the rapid rising of air current temperature, in addition, because gaseous stickness dissipation effect, can produce the friction with the aircraft surface, and this also can make the conversion temperature of gas energy rise. Therefore, how to effectively reduce the temperature difference between the wing and the background environment becomes one of the key technologies for enhancing the infrared stealth capability of the airplane. The heat pipe is a heat transfer element invented by George Grover (George Grover) of national laboratory of Los Alamos (Los Alamos) in 1963, fully utilizes the heat conduction principle and the rapid heat transfer property of a phase change medium, quickly transfers the heat of a heating object to the outside of a heat source through the heat pipe, and the heat conduction capability of the heat pipe exceeds the heat conduction capability of any known metal.
In the prior art, thermal protection methods for aircraft systems are mainly divided into three categories, passive methods, semi-passive methods and active methods. The passive method is characterized in that the characteristics of heat resistance, heat insulation and heat conduction materials are utilized to prevent heat from entering the interior of the aircraft, including heat insulation, radiation heat dissipation and the like, the selection of materials is required during design, the materials are generally difficult to change after the aircraft is manufactured, and the passive method is mature in the current research, but the efficiency is low; the semi-passive method generally adds some devices or substances on the aircraft structure, typically represents a thermal control protective coating, and the thermal protection method has been greatly researched at present, is used in various high-speed aircrafts in the current aerospace field, is suitable for the situation of local heat density concentration, but maintains high lift-drag ratio in order to keep hypersonic aerodynamic shape, and the thermal protection technology of ablation is greatly limited; however, active cooling can be generally divided into convection cooling, film cooling and transpiration cooling, additional auxiliary structures are required to be added, certain working media are added, the appearance of the aircraft can be changed, and for example, a plurality of small holes are required to be arranged on the head of the aircraft in single-hole jet cooling. The active cooling method has the best heat-proof effect and good research prospect, but has a complex structure and higher cost.
Disclosure of Invention
Technical problem to be solved
Aiming at the defects of the prior art, the invention provides a novel hypersonic aircraft wing, which solves the problem that the temperature of the front edge of the hypersonic aircraft wing is overhigh.
(II) technical scheme
In order to achieve the purpose, the invention is realized by the following technical scheme: a novel hypersonic aircraft wing comprising:
the wing body is a hypersonic aircraft wing;
the heat pipe is used for radiating heat of the wing body and is arranged inside one side of the wing body;
the wing body comprises a skin and a supporting framework, the supporting framework is fixedly connected inside the skin, and a wing leading edge is arranged on one side of the skin;
the heat pipe comprises a liquid absorbing core and a shell, the outer side of the liquid absorbing core is fixedly connected to the inner side of the shell, an evaporation cavity is formed in the inner side of the liquid absorbing core, a liquid working medium is arranged inside the liquid absorbing core, and the outer side of the shell is fixedly connected to the inner side of a covering.
Preferably, the shape of the shell is a flat plate, a flat fixing section is arranged at the top end of the shell, an arc fixing section is arranged at the bottom end of the shell, the upper surface of the flat fixing section is fixed on the inner wall of the top of the skin, and the outer side of the arc fixing section is fixed on the inner side of the front edge of the wing.
Preferably, the top side of the shell is fixedly connected with a heat conduction material, and the top of the heat conduction material is fixedly connected with the inner wall of the top side of the skin.
Preferably, the shape of the outer shell is an elliptical arc, one end of the outer shell is fixed on the inner side of the leading edge of the wing, and the top side of the outer shell is fixed on the inner wall of the top of the skin.
Preferably, the shape of the shell is tubular, a pipe clamp is arranged on the outer side of the shell, one end of the pipe clamp is fixedly connected to one side of the skin, the front edge of the wing is fixed in the middle of the shell, and two ends of the shell are fixed to the inner wall of one side of the skin.
Preferably, one end of the outer shell is divided into an evaporation section, a heat insulation section and a condensation section from one end to the other end in sequence, and the evaporation section is connected to the inner side of the front edge of the wing.
Preferably, the inner side of the wick is provided with a heat insulating material.
The working principle is as follows: when the airplane flies at a high speed, aerodynamic heat is generated at the front edge of the wing, so that the liquid working medium stored at the front edge in the heat pipe absorbs heat and evaporates, the vaporized liquid working medium flows through the heat insulation section, the vapor in the condensation section releases heat and liquefies due to the low temperature of the external environment, and then flows back to the front edge of the wing for the next circulation under the action of capillary force and gravity in the capillary core of the liquid absorption core.
(III) advantageous effects
The invention provides a novel hypersonic aircraft wing. The method has the following beneficial effects:
1. the heat generated by the front edge of the wing is absorbed by the working medium of the evaporation section, is transmitted to the lower end of the upper surface of the skin through the steam cavity coated with the heat insulating material outside after being vaporized, the contact temperature of the upper surface of the wing and the outside atmosphere is lower, and the heat is absorbed by the liquid absorption core attached to the inside of the heat pipe after the heat is released and liquefied by the working medium and then flows back to the evaporation section, so that the cooling effect is obviously improved, and the heat pipe device has all the advantages of high heat transfer efficiency, reversibility in the heat flow direction, good isothermal property and the like.
2. The outer side of the liquid absorbing core is fixedly connected to the inner side of the shell, the inner side of the liquid absorbing core is provided with the evaporation cavity, the liquid working medium is arranged inside the liquid absorbing core, the working medium can be recycled, and the working medium consumption is low.
3. According to the invention, the heat pipe is arranged in one side of the wing body, so that the appearance of the airplane is not changed, and the aerodynamic layout of the airplane is not influenced.
4. By arranging the shell into a flat plate shape, an elliptical arc shape or a tubular shape, the shape of the heat pipe can be changed according to the distribution of other elements in the airplane, and the internal space of the airplane is saved.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view of a heat pipe structure according to the present invention;
FIG. 3 is a schematic structural diagram of an embodiment of the present invention;
FIG. 4 is a schematic structural diagram of a second embodiment of the present invention;
FIG. 5 is a schematic diagram of a third structure according to an embodiment of the present invention.
Wherein, 1, the wing body; 2. a support framework; 3. covering a skin; 4. a leading edge of the airfoil; 5. a thermally conductive material; 6. an arc-shaped fixing section; 7. a wick; 8. a housing; 9. a flat fixed section; 10. a condensing section; 11. a thermally insulating section; 12. an evaporation section; 13. a heat pipe; 14. a pipe clamp.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. 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 invention.
The first embodiment is as follows:
as shown in fig. 1 to 3, an embodiment of the present invention provides a novel hypersonic aircraft wing, including:
the wing body 1 is a hypersonic aircraft wing;
the heat pipe 13 is used for radiating heat of the wing body 1, and the heat pipe 13 is arranged inside one side of the wing body 1;
the wing body 1 comprises a skin 3 and a supporting framework 2, the supporting framework 2 is fixedly connected inside the skin 3, and a wing leading edge 4 is arranged on one side of the skin 3;
the heat pipe 13 comprises a liquid absorbing core 7 and a shell 8, the outer side of the liquid absorbing core 7 is fixedly connected to the inner side of the shell 8, an evaporation cavity is formed in the inner side of the liquid absorbing core 7, liquid working media are arranged inside the liquid absorbing core 7, and the outer side of the shell 8 is fixedly connected to the inner side of the skin 3.
When the airplane flies at a high speed, aerodynamic heat is generated at the wing leading edge 4, so that the liquid working medium stored at the leading edge in the heat pipe 13 absorbs heat and evaporates, the vaporized liquid flows through the heat insulation section 11, the vapor in the condensation section 10 releases heat and liquefies due to the low temperature of the external environment, and then flows back to the wing leading edge 4 for next circulation under the action of capillary force and gravity in the capillary core of the liquid absorption core 7.
The shape of the shell 8 is manufactured into a flat plate shape, the top end of the shell 8 is provided with a flat fixing section 9, the bottom end of the shell 8 is provided with an arc fixing section 6, the upper surface of the flat fixing section 9 is fixed on the inner wall of the top of the skin 3, the outer side of the arc fixing section 6 is fixed on the inner side of the wing front edge 4, and the flat fixing section 9 and the arc fixing section 6 are fully attached to the shape of the wing, so that heat dissipation and cooling are facilitated.
The top side fixedly connected with heat conduction material 5 of shell 8, the top fixed connection of heat conduction material 5 is at the top one side inner wall of covering 3, and heat conduction material 5 is convenient for heat conduction heat dissipation.
One end of the shell 8 is divided into an evaporation section 12, a heat insulation section 11 and a condensation section 10 from the other end in sequence, the evaporation section 12 is connected to the inner side of the wing leading edge 4, the evaporation section 12 is attached to the inside of the wing leading edge 4, and heat generated by the wing leading edge 4 can be absorbed by working media of the evaporation section 12.
The heat insulating material is arranged on the inner side of the liquid absorption core 7, so that the steam cavity can be wrapped by the heat insulating material, and the steam-liquid conversion of the working medium is facilitated.
The wing leading edge 4 is used as an evaporation section 12, the heat pipe 13 is made into a closed flat plate structure, the shape and the area of the flat plate structure can be changed according to the shape of the wing and the amount of the internal space of the wing, the flat plate heat pipe 13 is arranged below the wing skin 3 in a welding mode, the internal surface of the upper surface of the wing is flush with the outside of a condensation section 10 of the heat pipe 13, the heat conduction material 5 is filled between the heat pipe 13 and the skin 3, the heat generated by the wing leading edge 4 is absorbed by a working medium of the evaporation section 12, the heat is transmitted to the lower end of the upper surface of the skin 3 through a steam cavity coated with a heat insulation material outside after being vaporized, the contact temperature of the upper surface of the wing and the outside atmosphere is lower, the heat is absorbed by a liquid absorption core 7 attached to the inside of the heat pipe 13 after the heat is released and liquefied by the working medium, and then flows back to the evaporation section 12, and the cooling effect is remarkably improved.
Example two
As shown in fig. 1 to 4, an embodiment of the present invention provides a novel hypersonic aircraft wing, including:
the wing body 1 is a hypersonic aircraft wing;
the heat pipe 13 is used for radiating heat of the wing body 1, and the heat pipe 13 is arranged inside one side of the wing body 1;
the wing body 1 comprises a skin 3 and a supporting framework 2, the supporting framework 2 is fixedly connected inside the skin 3, and a wing leading edge 4 is arranged on one side of the skin 3;
the heat pipe 13 comprises a liquid absorbing core 7 and a shell 8, the outer side of the liquid absorbing core 7 is fixedly connected to the inner side of the shell 8, an evaporation cavity is formed in the inner side of the liquid absorbing core 7, liquid working media are arranged inside the liquid absorbing core 7, and the outer side of the shell 8 is fixedly connected to the inner side of the skin 3.
When the airplane flies at a high speed, aerodynamic heat is generated at the wing leading edge 4, so that the liquid working medium stored at the leading edge in the heat pipe 13 absorbs heat and evaporates, the vaporized liquid flows through the heat insulation section 11, the vapor in the condensation section 10 releases heat and liquefies due to the low temperature of the external environment, and then flows back to the wing leading edge 4 for next circulation under the action of capillary force and gravity in the capillary core of the liquid absorption core 7.
The wing leading edge 4 is used as an evaporation section 12, the heat pipe 13 is made into a closed elliptical structure, the shape and the area of the elliptical structure can be changed according to the shape of the wing and the amount of the internal space of the wing, when an aircraft flies at a high speed, aerodynamic heat is generated at the wing leading edge 4, a liquid working medium stored at the inner leading edge of the heat pipe 13 absorbs heat and evaporates, the liquid working medium flows through the heat insulation section 11 after being vaporized, steam at the condensation section 10 releases heat and is liquefied due to the low temperature of the external environment, and then flows back to the wing leading edge 4 for next circulation under the action of capillary force and gravity in the capillary core of the liquid absorption core 7, and the cooling effect is remarkably improved.
The top side fixedly connected with heat conduction material 5 of shell 8, the top fixed connection of heat conduction material 5 is at the top one side inner wall of covering 3, and heat conduction material 5 is convenient for heat conduction heat dissipation.
One end of the shell 8 is divided into an evaporation section 12, a heat insulation section 11 and a condensation section 10 from the other end in sequence, the evaporation section 12 is connected to the inner side of the wing leading edge 4, the evaporation section 12 is attached to the inside of the wing leading edge 4, and heat generated by the wing leading edge 4 can be absorbed by working media of the evaporation section 12.
The heat insulating material is arranged on the inner side of the liquid absorption core 7, so that the steam cavity can be wrapped by the heat insulating material, and the steam-liquid conversion of the working medium is facilitated.
EXAMPLE III
As shown in fig. 1, 2, 3 and 5, an embodiment of the present invention provides a novel hypersonic aircraft wing, including:
the wing body 1 is a hypersonic aircraft wing;
the heat pipe 13 is used for radiating heat of the wing body 1, and the heat pipe 13 is arranged inside one side of the wing body 1;
the wing body 1 comprises a skin 3 and a supporting framework 2, the supporting framework 2 is fixedly connected inside the skin 3, and a wing leading edge 4 is arranged on one side of the skin 3;
the heat pipe 13 comprises a liquid absorbing core 7 and a shell 8, the outer side of the liquid absorbing core 7 is fixedly connected to the inner side of the shell 8, an evaporation cavity is formed in the inner side of the liquid absorbing core 7, liquid working media are arranged inside the liquid absorbing core 7, and the outer side of the shell 8 is fixedly connected to the inner side of the skin 3.
The top side fixedly connected with heat conduction material 5 of shell 8, the top fixed connection of heat conduction material 5 is at the top one side inner wall of covering 3, and heat conduction material 5 is convenient for heat conduction heat dissipation.
The shell 8 is sequentially divided into an evaporation section 12, a heat insulation section 11 and a condensation section 10 from left to right, the evaporation section 12 is connected to the inner side of the wing leading edge 4, heat generated by the wing leading edge 4 can be absorbed by working media of the evaporation section 12, and the heat insulation section 11 and the condensation section 10 are divided into an upper part and a lower part.
The heat insulating material is arranged on the inner side of the liquid absorption core 7, so that the steam cavity can be wrapped by the heat insulating material, and the steam-liquid conversion of the working medium is facilitated.
The shape of the shell 8 is tubular, the shell 8 is fixed on the inner wall of the skin 3 through the pipe clamp 14, the middle part of the shell 8 is fixed in the wing front edge 4, the two ends of the shell 8 are respectively provided with the heat insulation section 11 and the condensation section 10, the wing front edge 4 is used as the evaporation section 12, when the aircraft flies at high speed, aerodynamic heat is generated at the wing front edge 4, so that a liquid working medium stored at the front edge in the heat pipe 13 absorbs heat and evaporates, the vaporized liquid working medium flows through the heat insulation section 11, the steam at the condensation section 10 is liquefied due to heat release of the low temperature of the external environment, and then flows back to the wing front edge 4 for next circulation under the action of capillary force and gravity of the liquid absorption core 7, and the cooling effect is remarkably improved.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (7)
1. A novel hypersonic aircraft wing is characterized in that: the method comprises the following steps:
the wing body (1) is a hypersonic aircraft wing;
the heat pipe (13), the heat pipe (13) is used for heat dissipation of the wing body (1), and the heat pipe (13) is arranged inside one side of the wing body (1);
the wing body (1) comprises a skin (3) and a supporting framework (2), the supporting framework (2) is fixedly connected inside the skin (3), and a wing leading edge (4) is arranged on one side of the skin (3);
heat pipe (13) are including imbibing core (7) and shell (8), the outside fixed connection of imbibing core (7) is in the inboard of shell (8), the inboard of imbibing core (7) is provided with the evaporation chamber, the inside of imbibing core (7) is provided with liquid working medium, the outside fixed connection of shell (8) is in the inboard of covering (3).
2. The novel hypersonic aircraft wing of claim 1, wherein: the shape of shell (8) is flat, the top of shell (8) is provided with flat fixed segment (9), the bottom of shell (8) is provided with arc fixed segment (6), the upper surface of flat fixed segment (9) is fixed at the top inner wall of covering (3), the inboard at wing leading edge (4) is fixed in the outside of arc fixed segment (6).
3. The novel hypersonic aircraft wing of claim 1, wherein: the heat conduction material (5) is fixedly connected to the top side of the shell (8), and the top of the heat conduction material (5) is fixedly connected to the inner wall of the top side of the skin (3).
4. The novel hypersonic aircraft wing of claim 1, wherein: the shape of the outer shell (8) is an elliptical arc, one end of the outer shell (8) is fixed on the inner side of the wing leading edge (4), and the top side of the outer shell (8) is fixed on the inner wall of the top of the skin (3).
5. The novel hypersonic aircraft wing of claim 1, wherein: the shape of shell (8) is the tubulose, the outside of shell (8) is provided with pipe clamp (14), the one end fixed connection of pipe clamp (14) is in one side of covering (3), wing leading edge (4) are fixed in the middle part of shell (8), the both ends of shell (8) are all fixed at one side inner wall of covering (3).
6. The novel hypersonic aircraft wing of claim 1, wherein: one end of the shell (8) is sequentially divided into an evaporation section (12), a heat insulation section (11) and a condensation section (10) from one end to the other end, and the evaporation section (12) is connected to the inner side of the wing leading edge (4).
7. The novel hypersonic aircraft wing of claim 1, wherein: and the inner side of the liquid absorbing core (7) is provided with a heat insulating material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110771582.3A CN113306697A (en) | 2021-07-08 | 2021-07-08 | Novel hypersonic aircraft wing |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110771582.3A CN113306697A (en) | 2021-07-08 | 2021-07-08 | Novel hypersonic aircraft wing |
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| CN113306697A true CN113306697A (en) | 2021-08-27 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1994823A (en) * | 2006-12-27 | 2007-07-11 | 中国科学院力学研究所 | Ablation-free self-adaptive heat-resistant and damping system for high supersonic aerocraft |
| CN107914862A (en) * | 2017-11-20 | 2018-04-17 | 北京临近空间飞行器***工程研究所 | A kind of full active cooling hypersonic aircraft |
| CN109823510A (en) * | 2019-03-06 | 2019-05-31 | 中南大学 | Hypersonic aircraft and its thermal protection structure and coolant circulating system |
| CN110641683A (en) * | 2019-11-04 | 2020-01-03 | 中国航空制造技术研究院 | Thermal protection structure and processing method |
| CN110979633A (en) * | 2019-12-13 | 2020-04-10 | 西北工业大学 | Cooling enhancement structure for front edge of hypersonic aircraft |
-
2021
- 2021-07-08 CN CN202110771582.3A patent/CN113306697A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1994823A (en) * | 2006-12-27 | 2007-07-11 | 中国科学院力学研究所 | Ablation-free self-adaptive heat-resistant and damping system for high supersonic aerocraft |
| CN107914862A (en) * | 2017-11-20 | 2018-04-17 | 北京临近空间飞行器***工程研究所 | A kind of full active cooling hypersonic aircraft |
| CN109823510A (en) * | 2019-03-06 | 2019-05-31 | 中南大学 | Hypersonic aircraft and its thermal protection structure and coolant circulating system |
| CN110641683A (en) * | 2019-11-04 | 2020-01-03 | 中国航空制造技术研究院 | Thermal protection structure and processing method |
| CN110979633A (en) * | 2019-12-13 | 2020-04-10 | 西北工业大学 | Cooling enhancement structure for front edge of hypersonic aircraft |
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