CN113978046A - Thermal protection structure and preparation method thereof - Google Patents
Thermal protection structure and preparation method thereof Download PDFInfo
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- CN113978046A CN113978046A CN202111320126.3A CN202111320126A CN113978046A CN 113978046 A CN113978046 A CN 113978046A CN 202111320126 A CN202111320126 A CN 202111320126A CN 113978046 A CN113978046 A CN 113978046A
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Abstract
The invention provides a thermal protection structure and a preparation method thereof, wherein the thermal protection structure comprises a thermal insulation layer, a cavity layer and a skin which are sequentially arranged, wherein the thermal insulation layer is arranged on the outer surface of an inner cabin of an aircraft; the heat insulation layer comprises a porous heat insulation structure, temperature-sensitive hydrogel arranged in the porous heat insulation structure and a cooling working medium adsorbed in the temperature-sensitive hydrogel; when the thermal protection structure is not subjected to thermal protection, the temperature-sensitive hydrogel is in a swelling state and is used for adsorbing a cooling working medium in the temperature-sensitive hydrogel in a solid-phase form; when the thermal protection structure is used for thermal protection, the temperature-sensitive hydrogel absorbs heat radiated inwards by the skin and the cavity layer, so that the thermal protection structure is in a deswelling state, the existence form of the cooling working medium is sequentially changed from a solid phase to a liquid phase and a gas phase, and the gas phase cooling working medium is discharged after being released to the cavity layer. The thermal protection structure provided by the invention has excellent thermal protection performance.
Description
Technical Field
The invention relates to the technical field of thermal protection, in particular to a thermal protection structure and a preparation method thereof.
Background
Nowadays, the high-speed flight technology of the aircraft greatly improves the capability of human beings for exploring space, entering space, controlling space and utilizing space, and has special military strategic significance and important scientific value. However, no matter the hypersonic aircraft in the near space or the spacecraft which enters or returns through interplanetary detection, when the hypersonic aircraft enters or flies in the atmosphere at a hypersonic speed (> mach 5), the aircraft or the spacecraft can face the key technical problem of 'new thermal barrier' due to the severe pneumatic heating environment, and the development of a thermal protection mechanism guides the design and preparation of a thermal protection system of the aircraft, so that the design and preparation method is an effective way for solving the problem.
Thermal protection mechanisms are special mechanisms specifically used for thermal protection of aircraft, and are a class of mechanisms that include thermal protection mechanisms (e.g., based on material properties, physicochemical effects, or structural principles, etc.) and system structural configurations and their operating principles. Currently, the thermal protection mechanisms employed by hypersonic aircraft in service or after test flight (e.g., X-15, X-37B, Apollo re-entry pods, X-43A, and SHEFEX II) are classified into passive (e.g., heat sinks, insulation structures), semi-passive (e.g., ablation, heat pipes), and active (e.g., working fluid, cooling fluid) according to the thermal protection mechanism. These conventional thermal protection mechanisms have common characteristics, and all rely on the consumption, dispersion, resistance and resistance of materials or structures to realize the thermal protection function.
However, the near space hypersonic aircraft develops towards a high-speed domain, a wide airspace, a long endurance and a repeatable direction in the future, and meanwhile, with the development of a plurality of key deep space exploration tasks such as moon, mars, sun and the like in the future, a pneumatic heating environment becomes more severe, the thermal barrier problem of the aircraft is more prominent, and the requirement of the hypersonic aircraft on thermal protection in the future is difficult to meet only by means of a traditional thermal protection mechanism.
Disclosure of Invention
The embodiment of the invention provides a thermal protection structure and a preparation method thereof, which can provide the thermal protection structure and meet the requirement of future hypersonic aircrafts on thermal protection.
In a first aspect, the invention provides a thermal protection structure, which comprises a thermal insulation layer, a cavity layer and a skin, which are arranged in sequence, wherein the thermal insulation layer is arranged on the outer surface of an inner cabin of an aircraft;
the heat insulation layer comprises a porous heat insulation structure, temperature-sensitive hydrogel arranged in the porous heat insulation structure and a cooling working medium adsorbed in the temperature-sensitive hydrogel;
when the thermal protection structure is not subjected to thermal protection, the temperature-sensitive hydrogel is in a swelling state and is used for adsorbing the cooling working medium in the temperature-sensitive hydrogel in a solid-phase existing manner;
when the thermal protection structure is subjected to thermal protection, the temperature-sensitive hydrogel absorbs heat radiated inwards by the skin and the cavity layer, so that the temperature-sensitive hydrogel is in a deswelling state, is used for sequentially converting the existence form of the cooling working medium from a solid phase into a liquid phase and a gas phase, and discharges the gas phase of the cooling working medium after the cooling working medium is released to the cavity layer.
The invention aims to provide a heat protection mechanism with active and passive synergistic action aiming at the requirements of long-time and repeatable heat protection structures required by next generation hypersonic aircrafts, and particularly realizes heat protection by adding the heat protection mechanism with synergistic action of inward radiation heat dissipation (passive) and solid-phase water phase change heat dissipation (active).
And (3) passive: the traditional thermal protection structure mainly realizes heat dissipation through outward radiation of an outer skin (outer side), the inner side of the skin can also radiate heat inwards by adding a cavity layer between the skin and a heat insulation material on the basis of the outward radiation, the radiation coefficient of the inner side of the skin can be greatly improved to 0.9 at most through modification of the surface layer of the inner side of the skin, so that the purpose of increasing the heat-proof efficiency of the thermal protection structure by adding one item of inward radiation on the basis of the traditional thermal protection is realized;
initiatively, water becomes the best cooling working medium for phase change cooling because of the highest latent heat of phase change, but the flowability and the storage performance of water need to be provided with a series of complex auxiliary structures such as sealing, storage and corrosion prevention in a thermal protection structure, so that the water cannot be applied to an actual engineering thermal protection structure. In order to solve the problem, the invention adopts solid phase water to replace the traditional liquid phase water, changes the liquid phase water into solid phase water small particles through temperature sensitive hydrogel and inorganic-organic assembly technology, and fills the solid phase water small particles into the lower layer inorganic heat insulation material, and selects the alumina porous heat insulation material by comparison. The solid-phase water particles are fixed in the micro-pores of the porous medium through chemical branches. The solid-phase hydrogel can be tightly connected with the porous heat-insulating material after being filled. When the temperature in the cavity is raised due to radiation, the solid phase water can form liquid phase water through slow release, the liquid phase water is immediately evaporated into water vapor after being heated, and then the heat is taken away through the liquid-gas phase change.
The heat protection capability of the heat protection structure can be greatly improved through the mutual synergistic effect of internal radiation heat dissipation (passive) and solid-phase water phase change heat dissipation (active). The thickness of the cavity between the skin and the porous medium, the distribution and the pore size of micropores in the porous medium and the content of solid-phase water can be designed and adjusted according to the requirement of thermal protection.
The heat protection mechanism is an active-passive cooperative heat protection mechanism, and not only is an internal radiation heat dissipation phase increased, but also more importantly, phase change heat dissipation of solid phase water is increased on the basis of fully exerting external surface radiation heat dissipation, the heat dissipation amount is 30-50 times of that of radiation heat dissipation, and the heat protection effect of the heat protection mechanism is superior to that of other single active or passive heat protection machines and structures such as ceramic-based heat insulation type heat prevention, sweating cooling, film cooling and the like.
Based on the inventionThe heat protection structure of the active/passive cooperative heat protection mechanism can be suitable for heat protection structures such as the leading edge and the nose cone of a hypersonic aircraft wing, can also be suitable for a large-area of the windward side and can bear the heat load of 100-10 MW/m2And not less than 30 minutes;
according to different heat load conditions, the thickness of the heat protection structure provided by the invention is 10-100 mm; the back wall temperature of the thermal protection structure provided by the invention is lower than 100 ℃; the heat protection structure provided by the invention has the characteristics of heat prevention, heat insulation and bearing integration.
Preferably, the thermal protection structure further comprises a screw and a nut, and the thermal insulation layer and the skin are fixed on the outer surface of the inner cabin of the aircraft through the matching of the screw and the nut.
Preferably, the screw and the nut are both made of alumina ceramics.
Preferably, the porous heat insulation structure is made of alumina ceramics.
Preferably, in the thermal protection structure according to any one of the first to fourth aspects, the cooling medium includes water.
In a second aspect, the present invention provides a method for preparing a thermal protection structure, comprising:
placing the temperature-sensitive hydrogel and the porous heat insulation structure in a container containing a cooling working medium so that the temperature-sensitive hydrogel enters the porous heat insulation structure; the temperature of the cooling working medium is a first preset temperature, and the temperature-sensitive hydrogel is in a deswelling state at the first preset temperature;
reducing the temperature of the cooling working medium to a second preset temperature so that the cooling working medium is adsorbed in the temperature-sensitive hydrogel in a solid-phase form to obtain a heat insulation layer; wherein, at the second preset temperature, the temperature-sensitive hydrogel is in a swelling state;
fixing the heat insulation layer and the skin, and arranging a cavity layer between the heat insulation layer and the skin to form a thermal protection structure; wherein the insulation layer is arranged on the outer surface of the inner cabin of the aircraft.
The invention aims to provide a heat protection mechanism with active and passive synergistic action aiming at the requirements of long-time and repeatable heat protection structures required by next generation hypersonic aircrafts, and particularly realizes heat protection by adding the heat protection mechanism with synergistic action of inward radiation heat dissipation (passive) and solid-phase water phase change heat dissipation (active).
And (3) passive: the traditional thermal protection structure mainly realizes heat dissipation through outward radiation of an outer skin (outer side), the inner side of the skin can also radiate heat inwards by adding a cavity layer between the skin and a heat insulation material on the basis of the outward radiation, the radiation coefficient of the inner side of the skin can be greatly improved to 0.9 at most through modification of the surface layer of the inner side of the skin, so that the purpose of increasing the heat-proof efficiency of the thermal protection structure by adding one item of inward radiation on the basis of the traditional thermal protection is realized;
initiatively, water becomes the best cooling working medium for phase change cooling because of the highest latent heat of phase change, but the flowability and the storage performance of water need to be provided with a series of complex auxiliary structures such as sealing, storage and corrosion prevention in a thermal protection structure, so that the water cannot be applied to an actual engineering thermal protection structure. In order to solve the problem, the invention adopts solid phase water to replace the traditional liquid phase water, changes the liquid phase water into solid phase water small particles through temperature sensitive hydrogel and inorganic-organic assembly technology, and fills the solid phase water small particles into the lower layer inorganic heat insulation material, and selects the alumina porous heat insulation material by comparison. The solid-phase water particles are fixed in the micro-pores of the porous medium through chemical branches. The solid-phase hydrogel can be tightly connected with the porous heat-insulating material after being filled. When the temperature in the cavity is raised due to radiation, the solid phase water can form liquid phase water through slow release, the liquid phase water is immediately evaporated into water vapor after being heated, and then the heat is taken away through the liquid-gas phase change.
The heat protection capability of the heat protection structure can be greatly improved through the mutual synergistic effect of internal radiation heat dissipation (passive) and solid-phase water phase change heat dissipation (active). The thickness of the cavity between the skin and the porous medium, the distribution and the pore size of micropores in the porous medium and the content of solid-phase water can be designed and adjusted according to the requirement of thermal protection.
The heat protection mechanism is an active-passive cooperative heat protection mechanism, and not only is an internal radiation heat dissipation phase increased, but also more importantly, phase change heat dissipation of solid phase water is increased on the basis of fully exerting external surface radiation heat dissipation, the heat dissipation amount is 30-50 times of that of radiation heat dissipation, and the heat protection effect of the heat protection mechanism is superior to that of other single active or passive heat protection machines and structures such as ceramic-based heat insulation type heat prevention, sweating cooling, film cooling and the like.
The heat protection structure based on the active/passive cooperative heat protection mechanism can be suitable for heat protection structures such as the leading edge and the nose cone of a hypersonic aircraft wing, can also be suitable for a large-area of a windward side and can bear the heat load of 100-10 MW/m2And not less than 30 minutes;
according to different heat load conditions, the thickness of the heat protection structure provided by the invention is 10-100 mm; the back wall temperature of the thermal protection structure provided by the invention is lower than 100 ℃; the heat protection structure provided by the invention has the characteristics of heat prevention, heat insulation and bearing integration.
Preferably, the fixing the thermal insulation layer and the skin includes:
and fixing the thermal insulation layer and the skin by utilizing the matching of a screw and a nut.
Preferably, the screw and the nut are both made of alumina ceramics.
Preferably, the porous heat insulation structure is made of alumina ceramics.
Preferably, in the method for manufacturing a thermal protection structure according to any one of the above second aspects, the cooling medium includes water.
Compared with the prior art, the invention at least has the following beneficial effects:
the thermal protection structure comprising the thermal insulation layer, the cavity layer and the skin is arranged on the outer surface of the inner cabin of the aircraft, so that the thermal protection structure has excellent thermal protection performance.
The skin and the cavity in the thermal protection structure have a passive thermal protection function, and the passive thermal protection mechanism is used for partially releasing absorbed heat in a thermal radiation mode after the skin absorbs external heat and is heated. The skin has two ways of thermal radiation, namely the skin releases external radiation to the external environment and releases internal radiation to the cavity. According to the invention, the cavity layer is arranged, so that the skin can radiate heat to the cavity layer while radiating heat to the outside, and an inward radiation path is added on the basis of the traditional thermal protection, thereby improving the thermal protection efficiency of passive thermal protection.
The heat insulation layer in the thermal protection structure comprises a porous heat insulation structure, temperature-sensitive hydrogel arranged in the porous heat insulation structure and a cooling working medium adsorbed in the temperature-sensitive hydrogel. The pores in the porous heat insulation structure can accommodate temperature-sensitive hydrogel, and the temperature-sensitive hydrogel can absorb a liquid-phase cooling working medium and convert the liquid-phase cooling working medium into a solid phase.
The heat insulation layer and the cavity in the heat protection structure have an active heat protection function. When the thermal protection structure is used for thermal protection, the temperature-sensitive hydrogel absorbs heat radiated inwards by the skin and the cavity layer, so that the thermal protection structure is in a deswelling state, the existence form of the cooling working medium is sequentially changed from a solid phase to a liquid phase and a gas phase, and the gas phase of the cooling working medium is released to the cavity layer and then discharged. The thermal insulation layer contains temperature-sensitive hydrogel, and when the temperature of the thermal insulation layer is lower than the Lower Critical Solution Temperature (LCST) of the temperature-sensitive hydrogel, the temperature-sensitive hydrogel is in a swelling state, absorbs the cooling working medium and converts the cooling working medium into a solid phase to obtain the thermal insulation layer; when the thermal protection structure is used, the temperature of the use environment is higher than the Lower Critical Solution Temperature (LCST) of the temperature-sensitive hydrogel, the temperature-sensitive hydrogel absorbs heat to be in a deswelling state, the cooling working medium is converted from a solid phase to a liquid phase and is released, then the liquid phase cooling working medium continuously absorbs heat and is further converted into a gas phase to be released to the cavity to be discharged, and therefore the excellent thermal protection function is achieved.
In addition, the heat protection structure provided by the invention can be repeatedly used. The thermal protection structure can be repeatedly used by the characteristic that temperature-sensitive hydrogel in the thermal insulation layer generates reversible swelling-deswelling along with the change of environmental temperature. The used thermal protection structure can swell the temperature-sensitive hydrogel in the thermal protection structure in a cooling and cooling working medium supplementing mode to absorb the cooling working medium, so that the excellent thermal protection performance is recovered.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic diagram of a thermal protection structure provided by an embodiment of the present invention;
FIG. 2 is a flow chart of a method for fabricating a thermal protect structure according to an embodiment of the present invention;
FIG. 3(a) is a perspective view of a thermal protection structure provided by an embodiment of the present invention;
FIG. 3(b) is a partial cross-sectional view of a thermal shield structure provided by an embodiment of the present invention;
fig. 4 is a graph comparing the heat shielding effect of the heat shielding structure provided in example 1 of the present invention with that of the heat shielding structure provided in comparative example 1.
In the figure:
1. covering a skin; 2. a cavity layer; 3. a thermal insulation layer; 4. a base plate; 5. a screw; 6. and a nut.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer and more complete, the technical solutions in the embodiments of the present invention will be described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention, and based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative efforts belong to the scope of the present invention.
As shown in fig. 1, 3(a) and 3(b), the present invention provides a thermal protection structure, which includes a thermal insulation layer 3, a cavity layer 2 and a skin 1, which are sequentially disposed, wherein the thermal insulation layer 3 is disposed on a bottom plate 4;
the heat insulation layer 3 comprises a porous heat insulation structure, temperature-sensitive hydrogel arranged in the porous heat insulation structure and a cooling working medium adsorbed in the temperature-sensitive hydrogel;
when the thermal protection structure is not subjected to thermal protection, the temperature-sensitive hydrogel is in a swelling state and is used for adsorbing a cooling working medium in the temperature-sensitive hydrogel in a solid-phase form;
when the thermal protection structure is used for thermal protection, the temperature-sensitive hydrogel absorbs heat radiated inwards by the skin 1 and the cavity layer 2, so that the thermal protection structure is in a deswelling state, the existence form of the cooling working medium is sequentially changed from a solid phase to a liquid phase and a gas phase, and the gas phase cooling working medium is discharged after being released to the cavity layer 2.
It should be noted that the floor 4 is a part of the outer surface of the interior cabin of the aircraft, and the commonly used material is an aluminum alloy.
According to the invention, the heat protection structure comprising the heat insulation layer 3, the cavity layer 2 and the skin 1 is arranged on the bottom plate 4, so that the heat protection structure has excellent heat protection performance.
The skin 1 and the cavity in the thermal protection structure have a passive thermal protection function, and the passive thermal protection mechanism is used for partially releasing absorbed heat in a thermal radiation mode after the skin 1 absorbs external heat and is heated. The skin 1 has two ways of heat radiation, namely the skin 1 releases external radiation to the external environment and releases internal radiation to the cavity. According to the invention, the cavity layer 2 is arranged, so that the skin 1 can radiate heat to the cavity layer 2 while radiating heat to the outside, and an inward radiation path is added on the basis of the traditional thermal protection, thereby improving the thermal protection efficiency of passive thermal protection.
The heat insulation layer 3 in the thermal protection structure comprises a porous heat insulation structure, temperature-sensitive hydrogel arranged in the porous heat insulation structure and a cooling working medium adsorbed in the temperature-sensitive hydrogel. The pores in the porous heat insulation structure can accommodate temperature-sensitive hydrogel, and the temperature-sensitive hydrogel can absorb a liquid-phase cooling working medium and convert the liquid-phase cooling working medium into a solid phase.
The heat insulation layer 3 and the cavity in the heat protection structure have an active heat protection function. When the thermal protection structure is used for thermal protection, the temperature-sensitive hydrogel absorbs heat radiated inwards by the skin 1 and the cavity layer 2, so that the temperature-sensitive hydrogel is in a deswelling state, is used for sequentially converting the existence form of the cooling working medium from a solid phase into a liquid phase and a gas phase, and discharges the gas phase of the cooling working medium after the cooling working medium is released to the cavity layer 2. The thermal insulation layer 3 contains temperature-sensitive hydrogel, and when the temperature of the thermal insulation layer 3 is lower than the Lower Critical Solution Temperature (LCST) of the temperature-sensitive hydrogel, the temperature-sensitive hydrogel is in a swelling state, absorbs the cooling working medium and converts the cooling working medium into a solid phase to obtain the thermal insulation layer 3; when the thermal protection structure is used, the temperature of the use environment is higher than the Lower Critical Solution Temperature (LCST) of the temperature-sensitive hydrogel, the temperature-sensitive hydrogel absorbs heat to be in a deswelling state, the cooling working medium is converted from a solid phase to a liquid phase and is released, then the liquid phase cooling working medium continuously absorbs heat and is further converted into a gas phase to be released to the cavity to be discharged, and therefore the excellent thermal protection function is achieved.
In addition, the heat protection structure provided by the invention can be repeatedly used. The thermal protection structure can be reused by the characteristic that temperature-sensitive hydrogel in the thermal insulation layer 3 can generate reversible swelling-deswelling along with the change of environmental temperature. The used thermal protection structure can swell the temperature-sensitive hydrogel in the thermal protection structure in a cooling and cooling working medium supplementing mode to absorb the cooling working medium, so that the excellent thermal protection performance is recovered. In the invention, the heat protection structure realizes excellent heat protection performance through an active-passive cooperative heat protection mechanism. On the basis of fully exerting the radiation heat dissipation of the outer surface, the internal radiation heat dissipation (passive heat protection) is increased; in addition, phase change heat dissipation (active heat protection) of solid phase water is increased, and the heat dissipation capacity is 30-50 times of that of radiation heat dissipation of the outer surface. The thermal protection structure provided by the invention can ensure that the temperature of the outer surface of the inner cabin of the hypersonic aerocraft is less than 100 ℃ in a pneumatic heating environment, and the thermal protection effect is obviously superior to other single active or passive thermal protection mechanisms such as ceramic-based heat insulation type heat prevention, sweating cooling, film cooling and the like.
It should be noted that, in the process of deswelling the temperature-sensitive hydrogel in the thermal insulation layer 3, the cooling working medium continuously absorbs heat through the phase change process of solid phase, liquid phase and gas phase, and at this time, solid-liquid-gas phase balance exists in the thermal insulation layer 3, so that the temperature of the thermal insulation layer 3 is kept below the boiling point temperature of the cooling working medium until the solid phase cooling working medium is exhausted, and the active thermal protection mechanism fails.
In the invention, the time of the active thermal protection mechanism can be adjusted by the aperture and the pore distribution of the porous heat insulation structure, the water controlled release rate of the temperature-sensitive hydrogel and the quality of the cooling working medium.
It should be noted that the cooling working medium selected by the conventional active thermal protection structure is a liquid phase, and since the liquid phase cooling working medium has fluidity, a series of complex auxiliary structures such as sealing, storage and corrosion prevention need to be configured when the liquid phase cooling working medium is placed in the thermal protection structure, so that the liquid phase cooling working medium is difficult to be applied to the actual thermal protection structure. In order to solve the problem, the temperature-sensitive hydrogel is added into the heat insulation layer 3, and the temperature-sensitive hydrogel can absorb the cooling working medium and convert the cooling working medium into a solid phase, so that an auxiliary structure required for storing the liquid-phase cooling working medium is avoided being arranged in the heat protection structure. In addition, the active thermal protection mechanism in the thermal protection structure is completely automatically triggered by temperature change, thermal protection is realized by phase change heat absorption of the cooling working medium, and no sensor or control device is needed in the whole process.
The thermal protection structure provided by the invention can be suitable for the front edge, the nose cone and other parts of the hypersonic aircraft wing, can also be suitable for a large-area of the windward side and can bear 100kW/m2～10MW/m2The heat load is carried, and the loading time can reach 30min at most. Wherein, the loading time is the effective time of the active thermal protection mechanism.
According to some preferred embodiments, the thermal protection structure further comprises screws 5 and nuts 6, and the insulation package 3 and the skin 1 are fixed to the floor panel 4 by the cooperation of the screws 5 and the nuts 6.
According to some preferred embodiments, both the screw 5 and the nut 6 are made of alumina ceramic.
According to some preferred embodiments, the porous insulating structure is made of alumina ceramic.
As shown in fig. 3(a) and 3(b), the thermal protection structure may sequentially fix the skin 1, the insulation layer 3, and the bottom plate 4 together by means of screws 5 and nuts 6, wherein the nuts 6 are fixed on both sides of the skin 1 to maintain the cavity layer 2 between the insulation layer 3 and the skin 1.
In the invention, the skin 1 is made of high-temperature alloy plate; the porous heat insulation structure and the bolts 5 and the nuts 6 are made of alumina ceramic materials which have excellent heat insulation performance. Compared with other porous heat insulating materials (such as zirconia ceramic materials), the alumina ceramic material has lower unit price and more uniform pore distribution.
According to some preferred embodiments, the thermal protection structure of any one of the first aspect, the cooling medium comprises water.
It should be noted that water is selected as the optimal cooling medium for phase change cooling because the latent heat of phase change of water is the highest.
As shown in fig. 2, the present invention further provides a method for manufacturing a thermal protection structure, comprising:
placing the temperature-sensitive hydrogel and the porous heat insulation structure in a container containing a cooling working medium so that the temperature-sensitive hydrogel enters the porous heat insulation structure; the temperature of the cooling working medium is a first preset temperature, and the temperature-sensitive hydrogel is in a deswelling state at the first preset temperature;
reducing the temperature of the cooling working medium to a second preset temperature so that the cooling working medium is adsorbed in the temperature-sensitive hydrogel in a solid-phase form to obtain a heat insulation layer; wherein, at a second preset temperature, the temperature-sensitive hydrogel is in a swelling state;
fixing the heat insulation layer and the skin, and arranging a cavity layer between the heat insulation layer and the skin to form a heat protection structure; wherein, the insulating layer sets up on the bottom plate. It should be noted that the first preset temperature is slightly higher than the LCST (lower critical solution temperature of the temperature sensitive hydrogel in the thermal insulation layer), and the second preset temperature is lower than the LCST. When the temperature of the temperature-sensitive hydrogel is higher than LCST, the temperature-sensitive hydrogel is in a deswelling state, and the interior of the hydrogel is anhydrous; when the temperature of the temperature-sensitive hydrogel is lower than LCST, the temperature-sensitive hydrogel is in a swelling state, can absorb liquid-phase water and forms solid-phase water in the temperature-sensitive hydrogel.
In the invention, when the cooling working medium is at the first preset temperature, the temperature-sensitive hydrogel in the container is in a liquid phase deswelling state, the temperature-sensitive hydrogel enters the inner pores of the porous heat insulation structure, and macromolecules of the temperature-sensitive hydrogel are combined with the inner walls of the pores of the porous heat insulation structure in a grafting mode.
In the invention, when the temperature of the cooling working medium is reduced to a second preset temperature, the temperature-sensitive hydrogel in the pores of the porous heat-insulating structure is in a swelling state in the temperature reduction process, a large amount of distilled water is absorbed by the high polymer of the hydrophilic group network structure to swell, the swelling speed is increased along with the reduction of the temperature, and when the temperature in the container is reduced to the second preset temperature, the temperature-sensitive hydrogel achieves the swelling balance, so that the heat-insulating layer is obtained. The temperature in the container is reduced, so that the temperature-sensitive hydrogel in the porous heat insulation structure absorbs water to swell, liquid-phase water in the container is converted into solid-phase water, and the solid-phase water exists in the temperature-sensitive hydrogel in the forms of bound water and free water.
The thickness of the thermal protection structure provided by the invention is 10-100 mm (the thickness comprises the bottom plate), and the thermal protection structure has the functions of heat prevention, heat insulation and bearing integration.
The preparation method provided by the invention has the advantages of simple structure, low cost, convenience in installation and strong designability, and can design the thickness of the thermal insulation layer, the path and distribution of the micro-channel and the quality of the cooling working medium according to the flight time and the heat load of the flight corridor so as to meet the requirements of different flight tasks.
According to some preferred embodiments, securing the insulation pack and the skin comprises:
and the thermal insulation layer and the skin are fixed by the cooperation of the screw and the nut.
According to some preferred embodiments, both the screw and the nut are made of alumina ceramic.
According to some preferred embodiments, the porous insulating structure is made of alumina ceramic.
As shown in fig. 3, the thermal protection structure may sequentially fix the skin, the insulation layer, and the bottom plate together by means of a screw and nut combination, wherein the nut is fixed on both sides of the skin to maintain a cavity layer between the insulation layer and the skin.
In the invention, the skin is made of high-temperature alloy plate; the porous heat insulation structure and the screw nut are made of alumina ceramic materials, and the alumina ceramic materials have excellent heat insulation performance. Compared with other porous heat insulating materials (such as zirconia ceramic materials), the alumina ceramic material has lower unit price and more uniform pore distribution.
According to some preferred embodiments, in the method for manufacturing a thermal protection structure of any one of the above embodiments, the cooling medium includes water.
It should be noted that water is selected as the optimal cooling medium for phase change cooling because the latent heat of phase change of water is the highest.
In order to more clearly illustrate the technical solution and advantages of the present invention, a thermal protection structure and a method for manufacturing the same are described in detail by several embodiments.
Example 1
Placing the temperature-sensitive hydrogel and a porous alumina ceramic plate with the thickness of 100mm multiplied by 8mm in a container containing distilled water so that the temperature-sensitive hydrogel enters the porous alumina ceramic plate; wherein the temperature of the distilled water is 36 ℃, and the temperature-sensitive hydrogel is in a deswelling state;
reducing the temperature of the distilled water to 25 ℃ so that the distilled water is adsorbed in the temperature-sensitive hydrogel in the form of a solid phase to obtain a heat insulation layer; wherein the temperature-sensitive hydrogel is in a swollen state;
and fixing the heat insulation layer, the skin and the bottom plate in a screw and nut matching mode to obtain the thermal protection structure bottom plate. Wherein, the skin is made of 100mm × 100mm × 5mm high-temperature alloy plate, the bottom plate is made of 100mm × 100mm × 5mm aluminum alloy plate, and the screw nut is made of M4 alumina ceramic screw nut. Wherein, the nut is fixed in covering both sides for reserve 8mm cavity layer between insulating layer and covering.
Placing the prepared thermal protection structure bottom plate on a heat insulation felt, respectively bonding thermocouples on the outer surface of the skin and the outer surface of the heat insulation layer, placing the thermal protection structure bottom plate under a high-power quartz lamp, and adjusting the heat flux density to 0.9MW/m through the high-power quartz lamp2And performing thermal examination test, and measuring that the temperature of the outer surface of the skin is 865 ℃, the temperature of the outer surface of the thermal insulation layer is not more than 100 ℃ and the temperature lasts for 3min (the effective time of an active thermal protection mechanism).
Example 2
Example 2 was prepared essentially identically to example 1, except that:
the heat flow density is 0.1MW/m2The thickness of the porous alumina ceramic plate is 5 mm.
The temperature of the outer surface of the skin is measured to be 420 ℃, and the effective time of the active thermal protection mechanism is 30 min.
Example 3
Example 3 was prepared essentially identically to example 1, except that:
the thermal protection structure is arranged in a high-frequency plasma wind tunnel, and the heat flux density is adjusted to 5MW/m2The thickness of the porous alumina ceramic plate is 15 mm.
The temperature of the outer surface of the skin is measured to be 870 ℃, and the effective time of the active thermal protection mechanism is 15 min.
Example 4
Example 4 was prepared essentially identically to example 1, except that:
the thermal protection structure is arranged in a high-frequency plasma wind tunnel, and the heat flux density is adjusted to 10MW/m2The thickness of the porous alumina ceramic plate is 30 mm.
The temperature of the outer surface of the skin is measured to be 910 ℃, and the effective time of the active thermal protection mechanism is 20 min.
Comparative example 1
Selecting a high-temperature alloy plate with the thickness of 100mm multiplied by 5mm as a skin, bonding a thermocouple on the outer surface of the skin, placing the skin under a high-power quartz lamp, and adjusting the heat flux density to 0.9MW/m through the high-power quartz lamp2And carrying out thermal examination test, and measuring that the temperature of the outer surface of the skin is 1170 ℃.
The thermal assessment test data of examples 1-4 and comparative example 1 are summarized in table 1:
TABLE 1
As can be seen from the embodiments 1 to 4, the thermal protection structure provided by the invention can bear 10W/m of load at most2Heat load, active heat protection machineThe effective time can reach 30 min.
From embodiments 1 to 4, it can be further known that the active thermal protection mechanism in the thermal protection structure has an excellent thermal protection effect, the temperature of the outer surface of the inner cabin of the internal aircraft can be controlled below 100 ℃, and the time of the active thermal protection mechanism can be adjusted through the thickness and the heat flow density of the porous heat insulation structure.
As can be seen from example 1 and comparative example 1 (see FIG. 4), the skin external surface temperature of example 1 is 865 ℃, and the skin external surface temperature of comparative example 1 is 1170 ℃, which proves that the thermal protection structure provided by the invention can improve the thermal protection effect of the material through internal radiation in a passive thermal protection mechanism.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present 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 solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (10)
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| CN115435523A (en) * | 2022-07-20 | 2022-12-06 | 浙江师范大学 | Solid passive evaporative cooling system and method |
| WO2023082528A1 (en) * | 2021-11-09 | 2023-05-19 | 厦门大学 | Thermal protection structure and preparation method therefor |
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| US20240052227A1 (en) * | 2022-08-12 | 2024-02-15 | Raytheon Company | Water-based polymer network for transpirant cooling applications |
| CN119383931B (en) * | 2024-12-27 | 2025-03-25 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A heat pipe heat dissipation system and method based on temperature-sensitive hydrogel |
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