A sandwich-type multi-channel reaction system and its application

Abstract

This invention discloses a sandwich-type multi-channel reaction system and its application, comprising a plate-type tank, a multi-channel reforming reactor, a locking solenoid valve, a heat-to-work conversion tank, a safety valve, a power solenoid valve, and a power thruster; an air jacket is provided between the multi-channel reforming reactor and the plate-type tank; the multi-channel reforming reactor contains a catalyst, and the plate-type tank contains a liquid cooling medium; the plate-type tank, the multi-channel reforming reactor, and the heat-to-work conversion tank are connected sequentially, the first outlet of the heat-to-work conversion tank is connected to the power thruster through the power solenoid valve, and the second outlet is connected to the outside through the safety valve; both the plate-type tank and the multi-channel reforming reactor are flat plate structures; the multi-channel reforming reactor has multiple thin-walled pressure-bearing channels inside, and the plate-type tank has reinforcing ribs. This system can be used in high-speed aircraft, effectively improving the system's aerodynamic and thermal management capabilities, while utilizing "harmful" aerodynamic heat to generate high-temperature, high-pressure small-molecule gas to perform work, achieving heat-to-work conversion.

Description

Technical Field

[0001] This invention relates to the field of high-speed aircraft technology, and more specifically, to a sandwich-type multi-channel reaction system and its application. Background Technology

[0002] Thermal protection technologies can be mainly divided into passive and active thermal protection technologies. Passive thermal protection, which utilizes thermal protection materials for insulation or ablation of materials to absorb heat through phase change, is the most widely used aerodynamic heat treatment measure and is applied in many high-speed aircraft. This type of thermal protection technology has a relatively simple structure, but its manufacturing process is complex and costly. In ablation thermal protection systems, the material is gradually ablated as the temperature rises during high-speed flight, easily altering the overall aerodynamic shape and leading to accidents. Furthermore, because passive thermal protection systems have weak heat absorption capacity, the required material thickness and weight are large for long-endurance applications, severely compressing the aircraft's payload. Active thermal protection technologies are mainly divided into two categories: sweating cooling and convection cooling. Sweating cooling commonly uses water as the cooling medium, mimicking the heat dissipation process of organisms through sweating. It utilizes the latent heat of vaporization of water to absorb heat and form a thermal barrier, but the system reliability is relatively poor. Convection cooling is commonly used in aerospace vehicles or aircraft, typically employing circulating liquid hydrocarbon fuel as the coolant. It utilizes the physical heat capacity of the fuel to remove heat from the structural surface. However, due to fuel coking limitations, this heat absorption method is only suitable for supersonic flight at speeds below Mach 5. In recent years, with the further improvement of aircraft performance, especially the development of long-endurance global strike strategic aircraft, their aerodynamic and thermal environments have become more complex and severe. Furthermore, due to the rapid upgrades and iterations of electronic components within aircraft payloads in recent years, operating power and the heat generated have increased rapidly. Therefore, achieving efficient heat dissipation of internal payloads has become one of the key issues for the stable operation of aircraft. Thus, developing an efficient and reliable method for absorbing aerodynamic heat from high-speed aircraft is of great significance.

[0003] Given the above challenges, based on experimental and theoretical research, it has been found that when an alcohol-water mixture is used as the cooling medium in an active thermal protection system, it can absorb a large amount of aerodynamic heat through physical vaporization. In particular, when the system contains a suitable catalyst, it can catalyze a strongly endothermic reforming reaction in alcohol and water. Taking ethanol-water solutions as an example, their vaporization and reforming reaction can produce hydrogen and carbon monoxide (Equation 1), increasing the gas volume threefold, with each mole of fluid absorbing 256.8 kJ of heat. When the aerodynamic temperature reaches 600℃, the heat absorption of pure water is only 3.6 MJ / Kg, while under the same conditions, the total physical and chemical heat absorption of the ethanol-water mixture can reach over 6.2 MJ / Kg. Furthermore, the generated small molecule gases (such as hydrogen and carbon monoxide) can be used to perform external work. Therefore, based on this active thermal protection technology, not only can the system's heat absorption capacity be improved, but aerodynamic heat can also be converted into chemical energy, achieving heat-work conversion, thereby reducing the thickness of the aircraft's thermal insulation layer, increasing the system's effective payload, and improving the aircraft's maneuverability.

[0004]

[0005] However, it was discovered that in the microgravity environment at high altitudes, the various components of the cooling working fluid exhibit non-azeotropic properties, leading to differences in gas and liquid compositions. Simultaneously, the inventors conducted in-depth research on the heat-to-work conversion system and found that, due to space and payload limitations of high-speed aircraft, the aforementioned heat-to-work conversion system must simultaneously possess the following characteristics: 1) Lightweight and thin-walled heat-to-work conversion system; 2) High degree of integration, facilitating in-situ replacement of passive insulation panels; 3) Storage temperature of the alcohol-water working fluid not exceeding 120°C, resulting in lower vapor pressure, thereby reducing tank wall thickness and system weight; 4) Catalyst and reactor temperatures not lower than 300°C, ensuring rapid and efficient reforming reactions. Therefore, developing suitable reaction and storage containers is crucial for the efficient operation of this heat-to-work conversion system. Summary of the Invention

[0006] The purpose of this invention is to overcome the aforementioned deficiencies in the prior art and provide a sandwich-type multi-channel reaction system and its application. This system includes a multi-channel reforming reactor and a plate-type storage tank, thus combining the functions of working fluid storage and reforming reaction. An air gap exists between the multi-channel reforming reactor and the plate-type storage tank, which can effectively prevent aerodynamic heat from being rapidly conducted from the reforming reactor to the storage tank through the metal wall. In addition, this sandwich-type heat-work conversion plate can be integrally molded and replace the heat insulation material of high-speed aircraft in situ. It not only has strong heat absorption capacity, but can also generate high-temperature and high-pressure gas to do work, realizing heat-work conversion, thereby reducing the aircraft's heat insulation layer and increasing the system's effective payload.

[0007] To achieve the above objectives, the technical solution of the present invention is as follows:

[0008] A sandwich-type multi-channel reaction system includes: a plate tank 1, a multi-channel reforming reactor 2, a locking solenoid valve 3, a heat-to-work conversion tank 4, a safety valve 5, a power solenoid valve 6, and a power thruster 7; an air jacket 8 is provided between the multi-channel reforming reactor 2 and the plate tank 1; the multi-channel reforming reactor 2 is filled with a catalyst 9, and the plate tank 1 is filled with a high-density liquid cooling medium 10; the outlet of the plate tank 1 is connected to the inlet of the multi-channel reforming reactor 2, and the multi-channel reforming... The outlet of reactor 2 is connected to the inlet of the heat-to-work conversion tank 4 via the locking solenoid valve 3; the heat-to-work conversion tank 4 is also provided with a first outlet 41 and a second outlet 42, the first outlet 41 is connected to the power thruster 7 via the power solenoid valve 6, and the second outlet 42 is connected to the outside via the safety valve 5; both the plate tank 1 and the multi-channel reforming reactor 2 are plate-type structures; the multi-channel reforming reactor 2 has multiple thin-walled pressure-bearing channels inside, and the plate tank 1 is provided with reinforcing ribs.

[0009] Optionally, the cross-section of the thin-walled pressure-bearing channel is circular or rounded rectangle.

[0010] Optionally, the plate-type storage tank 1 is provided with hydrophilic material or gravity balls, which can ensure that the high-density liquid cooling medium 10 can directly enter the multi-channel reforming reactor 2 under the action of vapor pressure in a high-altitude microgravity environment, thereby solving the problem of different gas-liquid components caused by the non-azeotropic nature of the multiple components of the high-density liquid cooling medium 10.

[0011] Optionally, the hydrophilic material includes high-temperature resistant fibers or absorbent cloth containing silicon and aluminum, which can be fully wetted by the high-density liquid cooling medium 10.

[0012] Optionally, the gravity ball is made of porous metal and is connected to the outlet of the plate-type storage tank 1 through a hose. Under the action of microgravity, it can move with the high-density liquid cooling medium 10 and be immersed below the liquid surface of the high-density liquid cooling medium 10.

[0013] Optionally, the thickness of the air interlayer 8 is 0.8mm to 5mm.

[0014] Optionally, the wall thickness of the multi-channel reforming reactor 2 is 0.4 mm to 1 mm, preferably 0.4 mm to 0.6 mm.

[0015] Optionally, the wall thickness of the plate-type storage tank 1 is 0.4mm to 1mm, preferably 0.4mm to 0.6mm.

[0016] Optionally, the catalyst 9 includes a modified alumina support and an active component and additives supported on the modified alumina support.

[0017] Optionally, the active component includes at least one of Cu, Ni, Fe, Ru and Pt metals, and the mass of the active component accounts for 5% to 30% of the total mass of the catalyst.

[0018] Optionally, the additives include Zn and / or Ce, and the mass of the additives accounts for 1% to 10% of the total mass of the catalyst.

[0019] Optionally, the high-density liquid cooling medium 10 is an alcohol-water mixture solution.

[0020] Optionally, the alcohol component in the alcohol-water mixture includes at least one of methanol, ethanol, ethylene glycol, propanol, and isopropanol.

[0021] Optionally, the alcohol component in the alcohol-water mixed solution has a mass concentration of 1% to 100%.

[0022] Optionally, the alcohol component in the alcohol-water mixture is methanol and ethanol, wherein the mass content of methanol in the alcohol-water mixture is 10% to 90%, and the mass content of ethanol in the alcohol-water mixture is 10% to 50%.

[0023] This invention also discloses the application of the sandwich-type multi-channel reaction system described above in a high-speed aircraft. The application includes the following steps: the high-density liquid cooling medium 10 in the plate tank 1 is vaporized by aerodynamic heating, and under pressure, it enters the multi-channel reforming reactor 2 through the outlet of the plate tank 1 via a pipeline. It absorbs aerodynamic heat through physical phase change latent heat and sensible heat, and then undergoes a chemical endothermic reaction under the action of catalyst 9 to produce high-pressure gas small molecules. The high-pressure gas small molecules enter the heat-work conversion tank 4 for storage through the locking solenoid valve 3.

[0024] When the high-speed aircraft needs to adjust its attitude, the safety valve 5 is closed, the power solenoid valve 6 is opened to introduce the high-pressure gas molecules into the power thruster 7, and the gas molecules are discharged through the power thruster 7, thereby generating thrust.

[0025] When the high-speed aircraft does not require additional power and the pressure of the heat-to-power conversion tank 4 is >2MPa, the power solenoid valve 6 is closed and the safety valve 5 is opened. The high-pressure gas molecules are discharged through the safety valve 5 until the pressure of the heat-to-power conversion tank 4 is 0.5MPa~1MPa, at which point the safety valve 5 is closed.

[0026] Specifically, after being heated by pneumatic heating, the high-density liquid cooling medium 10 in the plate storage tank 1 vaporizes, increasing the pressure in the plate storage tank 1. This pressure then compresses the high-density liquid cooling medium 10, causing it to enter the multi-channel reforming reactor 2 through pipelines. The vaporized high-density liquid cooling medium 10 absorbs part of the pneumatic heat in the multi-channel reforming reactor 2 through the latent heat and sensible heat of physical phase change. Then, under the action of catalyst 9, it undergoes a strongly endothermic reforming reaction. The resulting high-pressure gas molecules are discharged into and stored in the heat-work conversion storage tank 4. When external work is required, the work solenoid valve 6 is opened, and the high-pressure gas in the heat-work conversion storage tank 4 is discharged through the work thruster 7, generating thrust. When the pressure in the heat-work conversion storage tank 4 exceeds the rated working pressure, the safety valve 5 opens to exhaust gas, ensuring system safety.

[0027] Specifically, under the aerodynamic heat of the high-speed aircraft, it can rapidly evaporate and absorb heat, keeping the temperature of the plate tank 1 below 120°C, ensuring the normal operation of the internal load of the high-speed aircraft; the multi-channel reforming reactor 2 can use high-temperature aerodynamic heat (300°C~800°C) to catalytically decompose the high-density liquid cooling medium 10, generating high-pressure gas molecules to do work and generate thrust; the air jacket 8 can effectively prevent aerodynamic heat from being rapidly conducted from the multi-channel reforming reactor 2 to the plate tank 1 through the metal wall; the jacketed multi-channel reaction system of the present invention can effectively absorb aerodynamic heat, and the effective heat sink of the high-density liquid cooling medium 10 reaches more than 6.0 MJ / kg, effectively improving the system's aerodynamic heat management capability, while using "harmful" aerodynamic heat to generate high-temperature and high-pressure small molecule gas to do work, with a specific impulse of 150s, realizing heat-work conversion.

[0028] Implementing the embodiments of the present invention will have the following beneficial effects:

[0029] (1) Compared with traditional passive heat insulation methods, the sandwich-type multi-channel reaction system of the present invention belongs to active thermal protection technology and can be used in the active thermal protection system of high-speed aircraft. It has the advantages of strong cooling capacity, long-term heating with high-density heat flow, and closed-loop temperature control.

[0030] (2) Compared with the active heat insulation method of water sweating, the sandwich multi-channel reaction system of the present invention can not only utilize the physical heat absorption of the liquid heat-absorbing working fluid, but also enhance the heat absorption through chemical reaction. The theoretical maximum heat absorption capacity of the system is more than twice that of water sweating heat absorption (~3 MJ / kg) (>6 MJ / kg). When further coupled with ammonia decomposition, alcohol decomposition or alcohol-water reforming reaction, the heat absorption performance of the system can be further enhanced, and thrust can be generated to do work.

[0031] (3) In the sandwich-type multi-channel reaction system of the present invention, the sandwich-type heat-power conversion plate can be integrated into the equipment, and has the functions of working fluid storage and reforming reaction. There is an air gap between the reactor and the storage tank, which can effectively prevent aerodynamic heat from being quickly conducted from the reforming reactor to the storage tank through the metal wall. It can save space and can also be used as a cooling device, while absorbing aerodynamic heat and heat dissipation caused by the operation of the load (electronic components inside the aircraft). Attached Figure Description

[0032] Figure 1 This is a schematic diagram of the sandwich-type multichannel reaction system of Embodiment 1 of the present invention.

[0033] Figure 2 This is a side view of the 3D model of the multi-channel reforming reactor of Embodiment 1 of the present invention.

[0034] Figure 3 This is a cross-sectional view of the 3D model of the multi-channel reforming reactor in Embodiment 1 of the present invention.

[0035] Figure 4 This is a schematic diagram of a plate-type storage tank with a gravity ball according to Embodiment 1 of the present invention.

[0036] Figure 5 This is a graph showing the change in gas composition at the outlet of the heat-work conversion plate in Example 2 of this embodiment as a function of temperature.

[0037] Figure 6 The graph shows the total heat sink test results of the alcohol-water working fluid in Example 4 of the present invention.

[0038] Among them, 1. Plate tank; 2. Multi-channel reforming reactor; 3. Locking solenoid valve; 4. Heat-power conversion tank; 41. First outlet; 42. Second outlet; 5. Safety valve; 6. Power solenoid valve; 7. Power thruster; 8. Air jacket; 9. Catalyst; 10. High-density liquid cooling medium. Detailed Implementation

[0039] The present invention will be further described below with reference to specific embodiments, but this does not limit the present invention in any way.

[0040] This invention discloses a sandwich-type multi-channel reaction system, comprising: a plate-type tank 1, a multi-channel reforming reactor 2, a locking solenoid valve 3, a heat-to-work conversion tank 4, a safety valve 5, a power solenoid valve 6, and a power thruster 7; an air jacket 8 is provided between the multi-channel reforming reactor 2 and the plate-type tank 1; the multi-channel reforming reactor 2 is filled with a catalyst 9, and the plate-type tank 1 is filled with a high-density liquid cooling medium 10; the outlet of the plate-type tank 1 is connected to the inlet of the multi-channel reforming reactor 2, and the outlet of the multi-channel reforming reactor 2 is connected to the inlet of the heat-to-work conversion tank 4 through the locking solenoid valve 3; the heat-to-work conversion tank 4 is also provided with a first outlet 41 and a second outlet 42, the first outlet 41 is connected to the power thruster 7 through the power solenoid valve 6, and the second outlet 42 is connected to the outside through the safety valve 5; both the plate-type tank 1 and the multi-channel reforming reactor 2 are plate-type structures; the multi-channel reforming reactor 2 has multiple thin-walled pressure-bearing channels inside, and the plate-type tank 1 is provided with reinforcing ribs.

[0041] In one specific embodiment, the cross-section of the thin-walled pressure-bearing channel is circular or rounded rectangle.

[0042] In one specific embodiment, the plate-type storage tank 1 is provided with hydrophilic material or gravity balls, which can ensure that the high-density liquid cooling medium 10 can directly enter the multi-channel reforming reactor 2 under the action of vapor pressure in a high-altitude microgravity environment, thereby solving the problem of different gas-liquid components caused by the non-azeotropic nature of the multiple components of the high-density liquid cooling medium 10.

[0043] In one specific embodiment, the hydrophilic material includes high-temperature resistant fibers or absorbent cloth containing silicon and aluminum, which can be fully wetted by the high-density liquid cooling medium 10.

[0044] In one specific embodiment, the gravity ball is made of porous metal and is connected to the outlet of the plate-type storage tank 1 through a hose. Under the action of microgravity, it can move with the high-density liquid cooling medium 10 and be immersed below the liquid surface of the high-density liquid cooling medium 10.

[0045] In one specific embodiment, the thickness of the air interlayer 8 is 0.8 mm to 5 mm.

[0046] In one specific embodiment, the wall thickness of the multi-channel reforming reactor 2 is 0.4 mm to 1 mm, preferably 0.4 mm to 0.6 mm.

[0047] In one specific embodiment, the wall thickness of the plate-type storage tank 1 is 0.4mm to 1mm, preferably 0.4mm to 0.6mm.

[0048] In one specific embodiment, catalyst 9 includes a modified alumina support and an active component and additives supported on the modified alumina support.

[0049] In one specific embodiment, the active component includes at least one of Cu, Ni, Fe, Ru and Pt metals, and the mass of the active component accounts for 5% to 30% of the total mass of the catalyst.

[0050] In one specific embodiment, the additives include Zn and / or Ce, and the mass of the additives accounts for 1% to 10% of the total mass of the catalyst.

[0051] In one specific embodiment, the high-density liquid cooling medium 10 is an alcohol-water mixture solution.

[0052] In one specific embodiment, the alcohol component in the alcohol-water mixture includes at least one of methanol, ethanol, ethylene glycol, propanol, and isopropanol.

[0053] In one specific embodiment, the alcohol component in the alcohol-water mixed solution has a mass concentration of 1% to 100%.

[0054] In one specific embodiment, the alcohol component in the alcohol-water mixture is methanol and ethanol, wherein the mass content of methanol in the alcohol-water mixture is 10%~90%, and the mass content of ethanol in the alcohol-water mixture is 10%~50%.

[0055] The present invention also discloses the application of a sandwich-type multi-channel reaction system as described in any embodiment of the present invention in a high-speed aircraft. The application includes the following steps: the high-density liquid cooling working fluid 10 in the plate tank 1 is vaporized by aerodynamic heating, and under pressure, it enters the multi-channel reforming reactor 2 through the outlet of the plate tank 1 via a pipeline. It absorbs aerodynamic heat through physical phase change latent heat and sensible heat, and then undergoes a chemical endothermic reaction under the action of catalyst 9 to produce high-pressure gas small molecules. The high-pressure gas small molecules enter the heat-work conversion tank 4 for storage through the locking solenoid valve 3.

[0056] When the high-speed aircraft needs to adjust its attitude, the safety valve 5 is closed and the power solenoid valve 6 is opened to introduce high-pressure gas molecules into the power thruster 7, which are then discharged through the power thruster 7, thereby generating thrust.

[0057] When the high-speed aircraft does not require additional power and the pressure of the heat-to-power conversion tank 4 is >2MPa, the power solenoid valve 6 is closed and the safety valve 5 is opened. The high-pressure gas molecules are discharged through the safety valve 5 until the pressure of the heat-to-power conversion tank 4 is 0.5MPa~1MPa, at which point the safety valve 5 is closed.

[0058] The following are specific embodiments.

[0059] Example 1

[0060] The sandwich-type multi-channel reaction system of this embodiment, such as Figure 1-4 As shown, Figure 1 This is a schematic diagram of a sandwich-type multichannel reaction system according to an embodiment of the present invention. Figure 2, Figure 3 The images show a side view and a cross-sectional view of a 3D model of a multi-channel reforming reactor. Figure 4 This is a schematic diagram of a plate-type storage tank with a gravity ball. The system includes: a plate-type storage tank 1, a multi-channel reforming reactor 2, a locking solenoid valve 3, a heat-to-work conversion tank 4, a safety valve 5, a work solenoid valve 6, and a work thruster 7; an air jacket 8 is provided between the multi-channel reforming reactor 2 and the plate-type storage tank 1; the multi-channel reforming reactor 2 is filled with a catalyst 9, and the plate-type storage tank 1 is filled with a high-density liquid cooling medium 10; the outlet of the plate-type storage tank 1 is connected to the inlet of the multi-channel reforming reactor 2. The outlet of the multi-channel reforming reactor 2 is connected to the inlet of the heat-to-work conversion tank 4 via a locking solenoid valve 3. The heat-to-work conversion tank 4 is also provided with a first outlet 41 and a second outlet 42. The first outlet 41 is connected to the work thruster 7 via a work solenoid valve 6, and the second outlet 42 is connected to the outside via a safety valve 5. Both the plate tank 1 and the multi-channel reforming reactor 2 are plate-type structures. The multi-channel reforming reactor 2 has multiple thin-walled pressure-bearing channels inside, and the plate tank 1 is provided with reinforcing ribs.

[0061] The cross-section of the thin-walled pressure channel is circular or rounded rectangle.

[0062] Among them, a gravity ball is provided in the plate-type storage tank 1. The gravity ball is made of porous metal and is connected to the outlet of the plate-type storage tank 1 through a hose. Under the action of microgravity, it can move with the high-density liquid cooling medium (10) and be immersed below the liquid surface of the high-density liquid cooling medium (10).

[0063] The thickness of the air jacket 8 is 2 mm; the wall thickness of the multi-channel reforming reactor is 0.6 mm; and the wall thickness of the plate tank 1 is 0.6 mm.

[0064] Catalyst 9 includes a modified alumina support and an active component Pt and an auxiliary agent Ce supported on the modified alumina support. The mass contents of the active component Pt and the auxiliary agent Ce in catalyst 9 are 20% and 5%, respectively.

[0065] The high-density liquid cooling medium 10 is a mixed solution of ethanol and water, with an ethanol mass concentration of 50%.

[0066] The method of using the sandwich-type multi-channel reaction system in this embodiment includes the following steps: After the high-density liquid cooling working fluid 10 in the plate tank 1 is vaporized by pneumatic heating, it enters the multi-channel reforming reactor 2 through the outlet of the plate tank 1 under pressure. It absorbs pneumatic heat through physical phase change latent heat and sensible heat. Then, under the action of catalyst 9, a chemical endothermic reaction occurs and high-pressure gas small molecules are generated. The high-pressure gas small molecules enter the heat-work conversion tank 4 for storage through the locking solenoid valve 3.

[0067] Furthermore, when the high-speed aircraft needs to adjust its attitude, the safety valve 5 is closed, the power solenoid valve 6 is opened to introduce high-pressure gas molecules into the power thruster 7, and the gas molecules are discharged through the power thruster 7, thereby generating thrust.

[0068] Furthermore, when the high-speed aircraft does not require additional power and the pressure of the heat-to-power conversion tank 4 is >2MPa, the power solenoid valve 6 is closed and the safety valve 5 is opened. The high-pressure gas molecules are discharged through the safety valve 5 until the pressure of the heat-to-power conversion tank 4 is 0.5~1MPa, at which point the safety valve 5 is closed.

[0069] Example 2

[0070] The only difference between this embodiment and Example 1 is that the cooling medium is a mixed solution of methanol and water, and the mass concentration of methanol in the mixed solution is 60%.

[0071] Example 3

[0072] The only difference between this embodiment and Example 1 is that the cooling medium is a mixed solution of methanol and water, and the mass concentration of methanol in the mixed solution is 80%.

[0073] Test case

[0074] The reactors of Examples 2-3 were heated using quartz lamps to evaluate the catalytic activity of the catalyst in the catalytic reforming reactor for different alcohol-water components, thereby simulating the aerodynamic thermal scenario of a high-speed aircraft. The reactor surface temperature was adjusted by controlling the power of the quartz lamp array, and the outlet gas was quantified by gas chromatography.

[0075] Depend on Figure 5 It is evident that within the tested temperature range, the methanol conversion rate increases significantly with increasing temperature, reaching 100% at 600℃. The product composition indicates that when the reaction temperature is below 550℃, the main products are H2 and CO, suggesting that the primary reaction is methanol decomposition (CH3OH→CO+2H2). When the reaction temperature reaches 600℃, CO2 appears in the products, indicating that a water-vapor shift reaction (CO+H2O→CO2+H2) occurs.

[0076] Depend on Figure 6 As can be seen, the heat sink of the working fluid in Example 3 at different temperatures reaches 4.5 MJ / kg at 400℃, which is 43% higher than that of water. At 600℃, the heat sink reaches 5.6 MJ / kg, which is 55% higher than that of water. The phase impulse of the reaction gas exceeds 150s across the entire temperature range.

[0077] Example 5

[0078] Furthermore, in order to analyze the effect of the air jacket thickness on the heat absorption effect of the system, the wall thickness of the multi-channel reforming reactor in this embodiment is set to 0mm, 1mm, 2mm and 4mm respectively, and the rest is the same as in Example 1. The plate tank 1 and the multi-channel reforming reactor 2 are shown in Table 1.

[0079] Table 1 Surface temperature difference between plate tanks and multi-channel reforming reactors

[0080]

[0081] The experimental results show that when the reforming reactor and the storage tank are in close contact, the surface temperature of the storage tank (362℃) differs from that of the reforming reactor (600℃) by only 238℃. This indicates that aerodynamic heat can be rapidly conducted through the metal outer wall, thereby increasing the temperature of the storage tank. When the thickness of the air jacket increases to 2mm, the surface temperature of the storage tank drops to 115℃. When it is further increased to 4mm, the surface temperature of the storage tank does not decrease significantly, only to 108℃. This shows that the air jacket can effectively reduce and prevent the temperature rise of the storage tank caused by heat conduction, and a thickness of 2mm is more suitable.

[0082] The embodiments described above are merely illustrative of several implementations of the present invention, and while the descriptions are specific and detailed, they should not be construed as limiting the scope of the patent application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these all fall within the scope of protection of the present invention. Therefore, the scope of protection of this patent should be determined by the appended claims.

Claims

1. A sandwich-type multi-channel reaction system, characterized in that, The system includes: a plate tank (1), a multi-channel reforming reactor (2), a locking solenoid valve (3), a heat-power conversion tank (4), a safety valve (5), a power solenoid valve (6), and a power thruster (7); An air jacket (8) is provided between the multi-channel reforming reactor (2) and the plate tank (1); the multi-channel reforming reactor (2) is filled with a catalyst (9), and the plate tank (1) is filled with a high-density liquid cooling medium (10); The outlet of the plate tank (1) is connected to the inlet of the multi-channel reforming reactor (2), and the outlet of the multi-channel reforming reactor (2) is connected to the inlet of the heat-power conversion tank (4) through the locking solenoid valve (3). The heat-to-work conversion tank (4) is also provided with a first outlet (41) and a second outlet (42). The first outlet (41) is connected to the power-generating thruster (7) through the power-generating solenoid valve (6), and the second outlet (42) is connected to the outside through the safety valve (5). Both the plate-type storage tank (1) and the multi-channel reforming reactor (2) are plate-type structures; the multi-channel reforming reactor (2) has multiple thin-walled pressure-bearing channels inside, and the plate-type storage tank (1) is provided with reinforcing ribs.

2. The sandwich-type multi-channel reaction system according to claim 1, characterized in that, The cross-section of the thin-walled pressure-bearing channel is circular or rounded rectangle.

3. The sandwich-type multi-channel reaction system according to claim 1, characterized in that, The plate-type storage tank (1) is equipped with hydrophilic materials or gravity balls.

4. The sandwich-type multi-channel reaction system according to claim 3, characterized in that, The hydrophilic material includes high-temperature resistant fibers or absorbent cloth containing silicon and aluminum.

5. The sandwich-type multi-channel reaction system according to claim 3, characterized in that, The gravity ball is made of porous metal and is connected to the outlet of the plate-type storage tank (1) through a hose. Under the action of microgravity, it can move with the high-density liquid cooling medium (10) and be immersed below the liquid surface of the high-density liquid cooling medium (10).

6. The sandwich-type multi-channel reaction system according to claim 1, characterized in that, The wall thickness of the multi-channel reforming reactor (2) is 0.4 mm to 1 mm; The wall thickness of the plate-type storage tank (1) is 0.4 mm to 1 mm; The thickness of the air interlayer (8) is 0.8 mm to 5 mm.

7. The sandwich-type multi-channel reaction system according to claim 1, characterized in that, The catalyst (9) comprises a modified alumina support and an active component and an auxiliary agent supported on the modified alumina support; wherein the active component accounts for 5% to 30% of the total mass of the catalyst, and the auxiliary agent accounts for 1% to 10% of the total mass of the catalyst. The active component includes at least one of the metals Cu, Ni, Fe, Ru, and Pt; The adjuvants include Zn and / or Ce.

8. The sandwich-type multi-channel reaction system according to claim 1, characterized in that, The high-density liquid cooling medium (10) is an alcohol-water mixture solution; The alcohol component in the alcohol-water mixture includes at least one of methanol, ethanol, ethylene glycol, propanol, and isopropanol; The alcohol-water mixture has an alcohol concentration of 1% to 100% by mass.

9. The sandwich-type multi-channel reaction system according to claim 8, characterized in that, The alcohol components in the alcohol-water mixture are methanol and ethanol, wherein the mass content of methanol in the alcohol-water mixture is 10% to 90%, and the mass content of ethanol in the alcohol-water mixture is 10% to 50%.

10. An application of the sandwich-type multi-channel reaction system as described in any one of claims 1-9 in a high-speed aircraft, characterized in that, The application includes the following steps: The high-density liquid cooling medium (10) in the plate tank (1) is vaporized by aerodynamic heating. Under pressure, it enters the multi-channel reforming reactor (2) through the outlet of the plate tank (1) and the aerodynamic heat is absorbed by the latent heat and sensible heat of physical phase change. Then, under the action of the catalyst (9), a chemical endothermic reaction occurs and high-pressure gas molecules are generated. The high-pressure gas molecules enter the heat-work conversion tank (4) for storage through the locking solenoid valve (3). When the high-speed aircraft needs to adjust its attitude, the safety valve (5) is closed, the power solenoid valve (6) is opened, the high-pressure gas molecules are introduced into the power thruster (7), and discharged through the power thruster (7), thereby generating thrust. When the high-speed aircraft does not require additional power and the pressure of the heat-power conversion tank (4) is >2MPa, the power solenoid valve (6) is closed and the safety valve (5) is opened. The high-pressure gas molecules are discharged through the safety valve (5) until the pressure of the heat-power conversion tank (4) is 0.5-1MPa, at which point the safety valve (5) is closed.

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