CN116812153A - Skin cooling system and aircraft - Google Patents
Skin cooling system and aircraft Download PDFInfo
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- CN116812153A CN116812153A CN202310879504.4A CN202310879504A CN116812153A CN 116812153 A CN116812153 A CN 116812153A CN 202310879504 A CN202310879504 A CN 202310879504A CN 116812153 A CN116812153 A CN 116812153A
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- protrusion
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- annular cooler
- heat source
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
- B64D13/08—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
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- Aviation & Aerospace Engineering (AREA)
Abstract
The invention relates to the technical field of cooling equipment, and provides a skin cooling system and an aircraft. The skin cooling system comprises an annular cooler, wherein the annular cooler is sleeved outside the aircraft body, the annular cooler and the heat source form a circulation loop, and the annular cooler is used for cooling a medium in the heat source; the outer surface of the annular cooler is provided with a plurality of protrusions, and the height of each protrusion can be adjusted to adjust the cooling capacity of the annular cooler. Foretell skin cooling system, through the surface design arch at annular cooler, and bellied height can be adjusted, the protruding characteristic that plays the vortex effect to coming flow of usable, through adjusting bellied height, and then adjust annular cooler's cooling capacity, need not set up variable frequency speed regulation equipment or temperature regulation equipment can make annular cooler's cooling capacity carry out adaptive adjustment according to the specific operating mode of aircraft, simplified cooling system's structure, reduced cooling system's cost.
Description
Technical Field
The invention relates to the technical field of cooling equipment, in particular to a skin cooling system and an aircraft.
Background
The cooling system is an important function guarantee system for radiating heat of a moving platform such as an aircraft or an aircraft into the environment, the traditional cooling system introduces external cooling working medium into the cooling system through a pipeline, and then the cooling system cools a heat source through a cooler, so that the cooling system occupies a large amount of effective space in the aircraft, and the pipeline is complex.
To solve the above problems, the relevant scholars propose an external cooling technology to release the internal space, realize heat exchange by means of external water flow flushing, without equipment driving, and have higher reliability, but the external cooling technology has other problems, such as: in order to meet the cooling load regulation requirement under variable working conditions, the working medium flow of the middle loop is required to be changed by setting variable frequency speed regulation equipment, so that the cooling system is complex in composition; on the other hand, in order to meet the requirement of part of sensitive heat sources on the inlet temperature of the cooling water of the intermediate loop, a temperature regulating device needs to be arranged in a cooling system, so that the operation parameter regulating process is complex. Based on the above, it is an urgent need to provide an external cooling system having a simple structure and easy control of the operation process.
Disclosure of Invention
The invention provides a skin cooling system and an aircraft, which are used for solving the defects that an external cooling system in the prior art is complex in structure and complex in operation process regulation and control.
The invention provides a skin cooling system, which comprises an annular cooler, wherein the annular cooler is used for being sleeved outside an aircraft body, the annular cooler is used for forming a circulation loop with a heat source of the aircraft body, and the annular cooler is used for cooling a medium in the heat source; the outer surface of the annular cooler is provided with a plurality of bulges, and the height of each bulge can be adjusted so as to adjust the cooling capacity of the annular cooler.
According to the skin cooling system provided by the invention, the outer surface of the annular cooler has thermal conductivity, and the bulge has elasticity; wherein the height of the protrusion increases in the case where the protrusion is at an increased temperature, and the height of the protrusion decreases in the case where the protrusion is at a decreased temperature.
According to the skin cooling system provided by the invention, the bulge is provided with the cavity, the cavity is internally provided with the first phase-change working medium, and the first phase-change working medium is in an expansion state and a contraction state; the height of the protrusion increases when the first phase change working medium is in the expanded state, and the height of the protrusion decreases when the first phase change working medium is in the contracted state.
According to the skin cooling system provided by the invention, under the condition that the first phase-change working medium is in an endothermic state, the first phase-change working medium expands, and under the condition that the first phase-change working medium is in an exothermic state, the first phase-change working medium contracts.
According to the skin cooling system provided by the invention, the bulge is provided with the cavity, the cavity is internally provided with the telescopic column, one end of the telescopic column is connected with the outer surface of the annular cooler, and the other end of the telescopic column is connected with the bulge; the telescoping post has an extended state in which the height of the protrusion increases and a shortened state in which the height of the protrusion decreases.
According to the skin cooling system provided by the invention, the telescopic column is a thermosensitive telescopic column, the telescopic column stretches under the condition that the temperature of the telescopic column is increased, and the telescopic column shortens under the condition that the temperature of the telescopic column is reduced.
According to the skin cooling system provided by the invention, the bulge is of a hemispherical structure, and the hemispherical structure is internally provided with the first phase change working medium.
According to the skin cooling system provided by the invention, the bulge is of a wedge-shaped structure, the telescopic column is arranged in the wedge-shaped structure, and one end of the telescopic column is connected with the tip end of the wedge-shaped structure.
According to the present invention there is provided a skin cooling system, the annular cooler comprising: the annular pipeline comprises an inner wall and an outer wall, the inner wall is used for being sleeved with the aircraft, the outer wall is provided with a plurality of protrusions, an annular flow passage is formed between the inner wall and the outer wall, and a second phase change working medium is filled in the annular flow passage; a first conduit having a first end for communication with the heat source and a second end in communication with the annular flow passage; a second conduit having a first end in communication with the annular flow passage and a second end in communication with the heat source; wherein the second phase change material is capable of absorbing heat from a medium within the heat source to condense the medium from a gaseous state to a liquid state.
The invention also provides an aircraft, which comprises an aircraft body and the skin cooling system, wherein the skin cooling system is sleeved outside the aircraft body.
According to the skin cooling system provided by the invention, the bulges are designed on the outer surface of the annular cooler, the heights of the bulges can be adjusted, the characteristics of the bulges playing a role in turbulent flow can be utilized, the cooling capacity of the annular cooler is adjusted by adjusting the heights of the bulges, and the cooling capacity of the annular cooler can be adaptively adjusted according to the specific working condition of an aircraft without setting variable-frequency speed regulating equipment or temperature regulating equipment, so that the structure of the cooling system is simplified, and the cost of the cooling system is reduced.
Drawings
In order to more clearly illustrate the invention or the technical solutions of the prior art, the following description will briefly explain the drawings used in the embodiments or the description of the prior art, and it is obvious that the drawings in the following description are some embodiments of the invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a skin cooling system provided by the present invention;
FIG. 2 is one of the schematic structural views of the ring cooler shown in FIG. 1;
FIG. 3 is a schematic view of the configuration of the protrusion shown in FIG. 2;
FIG. 4 is a state change schematic of the protrusion shown in FIG. 2;
FIG. 5 is a second schematic view of the ring cooler shown in FIG. 1;
FIG. 6 is a schematic view of the configuration of the protrusion shown in FIG. 5;
FIG. 7 is a state change schematic of the protrusion shown in FIG. 5;
FIG. 8 is one of the operational flow diagrams of the skin cooling system provided by the present invention;
FIG. 9 is a second flowchart of the skin cooling system provided by the present invention;
reference numerals:
10: an annular cooler; 11: an annular pipe; 12: a hemispherical structure; 13: a first phase change working medium; 14: wedge-shaped structures; 15: a telescopic column; 20: a first pipeline; 30: a second pipeline; 100: an aircraft body; 101: a heat source; 111: an inner wall; 112: an outer wall; 121: a cavity.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings, and it is apparent that the described embodiments are some embodiments of the present invention, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The features of the invention "first", "second" and the like in the description and in the claims may be used for the explicit or implicit inclusion of one or more such features. In the description of the present invention, unless otherwise indicated, the meaning of "a plurality" is two or more.
The skin cooling system and aircraft of the present invention are described below in connection with fig. 1-9.
As shown in fig. 1, in an embodiment of the present invention, the skin cooling system includes an annular cooler 10. The annular cooler 10 is used for being sleeved outside the aircraft body 100, the annular cooler 10 and the heat source 101 form a circulation loop, the annular cooler 10 is used for cooling media in the heat source 101, the outer surface of the annular cooler 10 is provided with a plurality of protrusions, and the height of each protrusion can be adjusted so as to adjust the cooling capacity of the annular cooler 10.
Specifically, the annular cooler 10 is configured to be sleeved on the outside of the aircraft body 100, the inner wall of the annular cooler 10 is attached to the outer surface of the aircraft body 100, and the outer wall of the annular cooler 10 is in contact with the incoming flow. The medium with higher temperature in the heat source 101 enters the annular cooler 10 to transfer heat to the annular cooler 10, the incoming flow flushes the annular cooler 10 to cool the annular cooler 10, so that the temperature of the medium is reduced, the cooled medium flows back into the heat source 101 to cool the heat source 101, and the medium which is heated again enters the annular cooler 10 again, so that the medium in the heat source 101 is continuously cooled.
Further, the outer wall of the annular cooler 10 is provided with a plurality of protrusions, the protrusions can play a role in turbulence of incoming flow, in this embodiment, the heights of the protrusions can be adjusted, when the heights of the protrusions are increased, the turbulence of the incoming flow by the protrusions is enhanced, the contact area between the incoming flow and the protrusions is increased, and the cooling capacity of the annular cooler 10 is improved, so that the temperature of a medium is further reduced; and when the height of the protrusions is reduced, the turbulence effect of the protrusions on the incoming flow is reduced, the contact area of the incoming flow with the protrusions is reduced, and the cooling capacity of the annular cooler 10 is reduced.
Specifically, when the heat load in the heat source 101 increases, or the temperature of the medium flowing back into the heat source 101 increases, the medium is higher after entering the annular cooler 10, the outer surface of the annular cooler 10 does not release heat as much as the heat conducted to the protrusions increases, the heated height of the protrusions increases, the turbulence effect on the incoming flow increases, the cooling capacity of the annular cooler 10 increases, and the temperature of the medium flowing back into the heat source 101 further decreases; when the heat load in the heat source 101 is reduced, or the temperature of the medium flowing back into the heat source 101 is reduced, after the medium enters the annular cooler 10, the annular cooler 10 radiates heat quickly under the scouring of the incoming flow, the temperature of the outer surface of the annular cooler 10 is reduced, the temperature of the protrusions is also reduced, so that the heights of the protrusions are reduced, the turbulence effect of the protrusions is reduced, the cooling capacity of the annular cooler 10 is reduced, and the temperature of the medium flowing back into the heat source 101 is increased.
Optionally, in an embodiment of the present invention, the protrusion has elasticity, a phase change working medium is disposed in the protrusion, and when the heat absorption volume of the phase change working medium in the protrusion expands, the protrusion is driven to become larger, and the height is increased; when the heat release volume of the phase change working medium in the bulge is reduced, the volume of the bulge is driven to be reduced, and the height is reduced.
Optionally, in another embodiment of the present invention, the protrusion has elasticity, and a heat sensitive material is disposed in the protrusion, and when the temperature of the heat sensitive material increases, the heat sensitive material stretches to drive the height of the protrusion to increase; when the temperature of the thermosensitive material is reduced, the thermosensitive material is shortened, and the height of the driving protrusion is reduced.
According to the skin cooling system provided by the embodiment of the invention, the bulge is designed on the outer surface of the annular cooler, the height of the bulge can be adjusted, the characteristic that the bulge plays a role in turbulence on incoming flow can be utilized, the cooling capacity of the annular cooler is adjusted by adjusting the height of the bulge, and the cooling capacity of the annular cooler can be adaptively adjusted according to the specific working condition of an aircraft without setting variable-frequency speed regulating equipment or temperature regulating equipment, so that the structure of the cooling system is simplified, and the cost of the cooling system is reduced.
As shown in fig. 2, in an embodiment of the present invention, the annular cooler 10 includes an annular pipe 11, a first pipe 20, and a second pipe 30. The annular pipeline 11 comprises an inner wall 111 and an outer wall 112, the inner wall 111 is used for being sleeved with the aircraft body 100, the outer wall 112 is provided with a plurality of protrusions, an annular flow channel is formed between the inner wall 111 and the outer wall 112, and a second phase change working medium is filled in the annular flow channel, wherein the second phase change working medium can absorb heat of a medium in the heat source 101 so as to condense the medium from a gas state to a liquid state. The first end of the first conduit 20 is adapted to communicate with the heat source 101 and the second end of the first conduit 20 is in communication with the annular flow passage. The first end of the second conduit 30 communicates with the annular flow passage and the second end of the second conduit 30 communicates with the heat source 101.
Specifically, the medium in the gaseous state in the heat source 101 enters the annular pipeline 11 through the first pipeline 20, the second phase-change working medium absorbs heat of the medium, the medium is condensed into the liquid state from the gaseous state, the second phase-change working medium conducts the heat to the outer wall 112 of the annular pipeline 11, and the heat is scoured and absorbed by the incoming flow. The liquid medium flows back into the heat source 101 through the second pipeline 30, and the heat source 101 is continuously cooled.
Further, in the embodiment of the present invention, the outer surface of the ring cooler 10 has thermal conductivity, and the protrusions have elasticity. Wherein the height of the protrusions increases in case the protrusions are at an elevated temperature and decreases in case the protrusions are at a reduced temperature.
Specifically, in the present embodiment, the outer wall 112 of the annular duct 11 has thermal conductivity, when the heat load in the heat source 101 increases or the temperature of the medium flowing back into the heat source 101 increases, the outer wall of the annular duct 11 does not dissipate heat as soon as the medium enters the annular duct 11, the heat conducted to the protrusions increases, the height of the protrusions increases after being heated, the turbulence effect of the protrusions on the incoming flow is improved, and thus the cooling capacity of the annular cooler 10 is improved, and the temperature of the medium flowing back into the heat source 101 is reduced.
When the heat load in the heat source 101 is reduced or the temperature of the medium flowing back into the heat source 101 is reduced, after the medium enters the annular pipeline 11, the heat dissipation of the outer wall 112 of the annular pipeline 11 is faster, the temperature of the outer wall 112 of the annular pipeline 11 is reduced, the temperature of the protrusions is also reduced, so that the heights of the protrusions are reduced, the contact area between the protrusions and the incoming flow is reduced, the cooling capacity of the annular cooler 10 is reduced, and the temperature of the medium flowing back into the heat source 101 is increased.
In one embodiment of the invention, as shown in fig. 3, the protrusion has a cavity 121, and the cavity 121 is filled with a first phase change working medium 13, and the first phase change working medium 13 has thermal conductivity. The first phase change working medium 13 has an expanded state and a contracted state, and the height of the protrusion increases in the case where the first phase change working medium 13 is in the expanded state and decreases in the case where the first phase change working medium 13 is in the contracted state.
Specifically, as shown in fig. 4, wherein (b) is a schematic diagram when the protrusion and the first phase change working medium 13 are in the reference state; (a) Is a schematic diagram of the bulge and the first phase change working medium 13 in an expansion state; (c) Is a schematic illustration of the protrusion and the first phase change working medium 13 in a contracted state.
As shown in fig. 8, when the heat load in the heat source 101 increases or the temperature of the medium flowing back into the heat source 101 increases, the outer wall 112 of the annular pipe 11 does not release the heat in the annular pipe 11 until the temperature of the outer wall 112 of the annular pipe 11 increases, so that the heat conducted into the protrusion through the outer wall 112 of the annular pipe 11 increases, as shown in fig. 4 (a), the heated volume of the first phase change working medium 13 is continuously expanded, the volume of the protrusion is also expanded, the height of the protrusion is increased, the disturbance effect on the incoming flow is enhanced, the cooling capacity of the annular cooler 10 is increased, the temperature of the outer wall 112 of the annular pipe 11 and the temperature of the second phase change working medium are reduced, and finally, the balance state is reached, so that the cooling capacity of the annular cooler 10 satisfies the heat load guiding capacity of the heat source 101.
As shown in fig. 9, when the heat load of the heat source is reduced or the temperature of the medium flowing back into the heat source 101 is reduced, the heat released through the outer wall 112 of the annular pipe 11 is higher than the design heat load of the heat source 101, which results in the temperature of the second phase-change working medium in the annular pipe 11 being reduced, and further causes the temperature of the outer wall 112 of the annular pipe 11 to be reduced, so that the heat conducted into the protrusion through the outer wall 112 of the annular pipe 11 is reduced, as shown in fig. 4 (c), the volume of the first phase-change working medium 13 in the protrusion is changed from the reference state to the contracted state, the volume of the first phase-change working medium 13 dispersed in the protrusion cavity 121 is contracted, the wall surface of the protrusion is contracted, the height of the protrusion is continuously reduced, the disturbance effect of the protrusion on the incoming flow is weakened, the cooling capacity of the annular cooler 10 is reduced, and thus the temperatures of the second phase-change working medium in the annular pipe 11 and the outer wall 112 of the annular pipe 11 are backwashed, and finally the equilibrium state is reached, and the cooling capacity of the annular cooler 10 is realized to meet the heat load derivation capacity of the heat source 101.
Further, in the embodiment of the present invention, the first phase-change working substance is expanded in the case where the first phase-change working substance 13 is in the endothermic state, and contracted in the case where the first phase-change working substance 13 is in the exothermic state.
Specifically, the first phase-change working medium 13 may be a solid-gas phase-change material or a liquid-gas phase-change material. When the temperature of the outer wall 112 of the annular pipeline 11 is increased, the first phase change working medium 13 absorbs heat, and is converted from solid state or liquid state into gas state and expands in volume; when the temperature of the outer wall 112 of the annular pipeline 11 is reduced, the first phase change working medium 13 releases heat, and is converted from a gaseous state into a liquid state or a solid state, and the volume is contracted.
Optionally, in an embodiment of the present invention, the first phase-change working medium 13 and the second phase-change working medium may be normal-temperature phase-change materials such as high-thermal-conductivity phase-change silicone grease, polyethylene glycol or polyoxymethylene.
Further, in the above embodiment, the protrusion is a hemispherical structure 12, and the hemispherical structure 12 is provided with the first phase change working medium. Specifically, the cavity 121 in the protrusion is also hemispherical, and the first phase change working substance 13 fills the hemispherical cavity. Compared with other shapes of bulges, the hemispherical bulges have larger surface area, and when the hemispherical bulges expand or contract, the contact area between the hemispherical bulges and incoming flow changes greatly, so that the cooling capacity of the annular cooler 10 is greatly influenced, and the cooling capacity of the annular cooler 10 and the working condition of the aircraft can be adaptively adjusted.
In another embodiment of the present invention, as shown in fig. 5, the protrusion is provided with a cavity 121, a telescopic column 15 is provided in the cavity 121, one end of the telescopic column 15 is connected with the outer surface of the ring cooler 10, and the other end of the telescopic column 15 is connected with the protrusion. The telescopic column 15 has an extended state and a shortened state, and in the case where the telescopic column 15 is in the extended state, the height of the protrusion increases, and in the case where the telescopic column 15 is in the shortened state, the height of the protrusion decreases.
Specifically, as shown in fig. 7, wherein (b) is a schematic view of the projection and the telescopic column 15 in the reference state; (a) Is a schematic diagram of the bulge and the telescopic column in an extension state; (c) Is a schematic illustration of the projection and telescoping column 15 in a shortened condition.
As shown in fig. 8, when the heat load in the heat source 101 increases or the temperature of the medium flowing back into the heat source 101 increases, after the medium enters the annular pipe 11, the outer wall 112 of the annular pipe 11 does not release the heat in the annular pipe 11, and the temperature of the outer wall 112 of the annular pipe 11 is further increased, so that the heat conducted into the protrusion through the outer wall 112 of the annular pipe 11 increases, as shown in fig. 7 (a), the heated length of the telescopic column 15 is continuously increased, the height of the protrusion is driven to increase, the disturbance effect on the incoming flow is enhanced, the cooling capacity of the annular cooler 10 is increased, the temperature of the outer wall 112 of the annular pipe 11 and the temperature of the second phase change working medium are reduced, and finally, the equilibrium state is reached, so that the cooling capacity of the annular cooler 10 satisfies the heat load leading-out capacity of the heat source 101.
As shown in fig. 9, when the heat load of the heat source is reduced or the temperature of the medium flowing back into the heat source 101 is reduced, the heat released through the outer wall 112 of the annular pipe 11 is higher than the design heat load of the heat source 101, which results in the temperature of the second phase-change working medium in the annular pipe 11 being reduced, and further causes the temperature of the outer wall 112 of the annular pipe 11 to be reduced, so that the heat conducted into the protrusion through the outer wall 112 of the annular pipe 11 is reduced, and as shown in fig. 7 (c), the length of the telescopic column 15 in the protrusion is changed from the reference state to the shortened state, the height of the protrusion is driven to be continuously reduced, the disturbance effect of the protrusion on the incoming flow is reduced, the cooling capacity of the annular cooler 10 is reduced, so that the temperatures of the second phase-change working medium in the annular pipe 11 and the outer wall 112 of the annular pipe 11 are raised, and finally the equilibrium state is reached, and the cooling capacity of the annular cooler 10 is realized to meet the heat load guiding capacity of the heat source 101.
Further, in the above-described embodiment, the telescopic column 15 is a thermosensitive telescopic column, and when the telescopic column 15 is at an elevated temperature, the telescopic column 15 is elongated, and when the telescopic column 15 is at a reduced temperature, the telescopic column 15 is shortened.
As shown in fig. 6, in the embodiment of the present invention, the protrusion is a wedge-shaped structure 14, and a telescopic column 15 is disposed in the wedge-shaped structure 14, and one end of the telescopic column 15 is connected to the tip of the wedge-shaped structure 14.
Specifically, in the present embodiment, when the temperature of the outer wall 112 of the annular pipe 11 increases, the temperature of the telescopic column 15 increases, the length thereof is continuously elongated, the height of the protrusion is driven to increase, and since the protrusion is of the wedge-shaped structure 14, the surface area of the protrusion gradually increases in the process of increasing the height of the protrusion, the contact area between the protrusion and the incoming flow increases, and the cooling capacity of the annular cooler 10 is further improved; when the temperature of the outer wall 112 of the annular pipeline 11 is reduced, the temperature of the telescopic column 15 is reduced, the length of the telescopic column is continuously shortened, the height of the protrusion is driven to be reduced, the surface area of the protrusion is gradually reduced in the process of reducing the height of the protrusion, the contact area between the protrusion and the incoming flow is reduced, and the cooling capacity of the annular cooler 10 is further reduced.
The embodiment of the invention also provides an aircraft, which comprises an aircraft body 100 and a skin cooling system, wherein the skin cooling system is sleeved outside the aircraft body 100.
Specifically, the annular cooler 10 is configured to be sleeved on the outside of the aircraft body 100, the inner wall of the annular cooler 10 is attached to the outer surface of the aircraft body 100, and the outer wall of the annular cooler 10 is in contact with the incoming flow. The medium with higher temperature in the heat source 101 enters the annular cooler 10 to transfer heat to the annular cooler 10, and the incoming flow flushes the annular cooler 10 to cool the annular cooler 10, so that the temperature of the medium is reduced, the cooled medium flows back into the heat source 101, and the medium heated again continuously enters the annular cooler 10, so that the medium in the heat source 101 is continuously cooled.
Further, the outer wall of the annular cooler 10 is provided with a plurality of protrusions, the protrusions can play a role in turbulence of incoming flow, in this embodiment, the heights of the protrusions can be adjusted, when the heights of the protrusions are increased, the turbulence of the incoming flow by the protrusions is enhanced, the contact area between the incoming flow and the protrusions is increased, and the cooling capacity of the annular cooler 10 is improved, so that the temperature of a medium is further reduced; and when the height of the protrusions is reduced, the turbulence effect of the protrusions on the incoming flow is reduced, the contact area of the incoming flow with the protrusions is reduced, and the cooling capacity of the annular cooler 10 is reduced.
Specifically, when the heat load in the heat source 101 increases, or the temperature of the medium flowing back into the heat source 101 increases, the medium temperature is higher after entering the annular cooler 10, the outer surface of the annular cooler 10 does not release heat as much as the heat conducted to the protrusions increases, the height of the protrusions increases, the turbulence effect on the incoming flow increases, the cooling capacity of the annular cooler 10 increases, and the temperature of the medium flowing back into the heat source 101 further decreases; when the heat load in the heat source 101 is reduced, or the temperature of the medium flowing back into the heat source 101 is reduced, after the medium enters the annular cooler 10, the annular cooler 10 radiates heat quickly under the scouring of the incoming flow, the temperature of the outer surface of the annular cooler 10 is reduced, the temperature of the protrusions is also reduced, so that the heights of the protrusions are reduced, the turbulence effect of the protrusions is reduced, the cooling capacity of the annular cooler 10 is reduced, and the temperature of the medium flowing back into the heat source 101 is increased.
According to the aircraft provided by the embodiment of the invention, the skin cooling system is sleeved outside the aircraft body, the skin cooling system can adjust the cooling capacity of the aircraft body, and the cooling capacity can be adaptively adjusted according to the specific working condition of the aircraft without setting variable-frequency speed regulating equipment or a temperature regulating device, so that the structure of the cooling system of the aircraft is simplified, and the cost of the aircraft is reduced.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and are not limiting; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. A skin cooling system, comprising:
the annular cooler is used for being sleeved outside the aircraft body, forming a circulation loop with a heat source of the aircraft body, and cooling a medium in the heat source;
the outer surface of the annular cooler is provided with a plurality of bulges, and the height of each bulge can be adjusted so as to adjust the cooling capacity of the annular cooler.
2. The skin cooling system of claim 1, wherein an outer surface of the annular cooler has thermal conductivity and the protrusions have elasticity;
wherein the height of the protrusion increases in the case where the protrusion is at an increased temperature, and the height of the protrusion decreases in the case where the protrusion is at a decreased temperature.
3. The skin cooling system of claim 1 or 2, wherein the protrusion has a cavity, a first phase change working medium is disposed in the cavity, and the first phase change working medium has an expanded state and a contracted state;
the height of the protrusion increases when the first phase change working medium is in the expanded state, and the height of the protrusion decreases when the first phase change working medium is in the contracted state.
4. The skin cooling system of claim 3, wherein the first phase change working substance expands when the first phase change working substance is in an endothermic state and contracts when the first phase change working substance is in an exothermic state.
5. The skin cooling system of claim 3, wherein the protrusion is provided with a cavity, a telescopic column is arranged in the cavity, one end of the telescopic column is connected with the outer surface of the annular cooler, and the other end of the telescopic column is connected with the protrusion;
the telescoping post has an extended state in which the height of the protrusion increases and a shortened state in which the height of the protrusion decreases.
6. The skin cooling system of claim 5, wherein the telescoping mast is a heat sensitive telescoping mast that stretches when the telescoping mast is at an elevated temperature and shortens when the telescoping mast is at a reduced temperature.
7. The skin cooling system of claim 3, wherein the protrusion is a hemispherical structure having the first phase change working fluid disposed therein.
8. The skin cooling system of claim 5, wherein the protrusion is a wedge-shaped structure, the telescopic column is arranged in the wedge-shaped structure, and one end of the telescopic column is connected with a tip end of the wedge-shaped structure.
9. The skin cooling system of claim 1, wherein the annular cooler comprises:
the annular pipeline comprises an inner wall and an outer wall, the inner wall is used for being sleeved with the aircraft, the outer wall is provided with a plurality of protrusions, an annular flow passage is formed between the inner wall and the outer wall, and a second phase change working medium is filled in the annular flow passage;
a first conduit having a first end for communication with the heat source and a second end in communication with the annular flow passage;
a second conduit having a first end in communication with the annular flow passage and a second end in communication with the heat source;
wherein the second phase change material is capable of absorbing heat from a medium within the heat source to condense the medium from a gaseous state to a liquid state.
10. An aircraft comprising an aircraft body and the skin cooling system of any one of claims 1-9, the skin cooling system being disposed externally of the aircraft body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310879504.4A CN116812153B (en) | 2023-07-17 | Skin cooling system and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310879504.4A CN116812153B (en) | 2023-07-17 | Skin cooling system and aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116812153A true CN116812153A (en) | 2023-09-29 |
| CN116812153B CN116812153B (en) | 2026-02-17 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN119318840A (en) * | 2024-12-17 | 2025-01-17 | 豫西黄河河务局经济发展管理局 | Sediment filtration equipment is used in water conservancy river course treatment |
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