Distributed fan-shaped reaction system as well as use method and application thereof

Abstract

The invention discloses a distributed fan-shaped reaction system as well as a use method and application thereof. The system comprises a cooling medium storage tank, a fan-shaped reactor, an electric control valve, a gas storage tank, a discharge valve, an electromagnetic valve and a thruster, the cooling medium storage tank is filled with a high-density liquid cooling working medium; the fan-shaped reactor is filled with a catalyst; the cooling medium storage tank, the fan-shaped reactor, the electric control valve and the gas storage tank are sequentially connected, the gas storage tank is provided with a first valve port and a second valve port, the first valve port is connected with the thruster through the electromagnetic valve, and the second valve port is communicated with the outside through the release valve. The distributed fan-shaped reaction system can be used for an active thermal protection system of a high-speed aircraft, the reactor can effectively absorb aerodynamic heat, the effective heat sink of a high-density liquid cooling working medium reaches 6.0 MJ / kg or above, the aerodynamic heat management capacity of the system is effectively improved, meanwhile, harmful aerodynamic heat is utilized to generate high-temperature and high-pressure small molecule gas to do work, the specific impulse reaches 150 s, and the service life of the system is prolonged. And heat-work conversion is realized.

Description

Technical Field

[0001] The present invention relates to the technical field of high-speed aircraft, and more specifically, to a distributed fan-shaped reaction system and a use method and application thereof. Background Art

[0002] High-speed aircraft, with its advantages of rapid response, rapid strike, and easy penetration, have become an important tool for changing the future war form and combat mode, and are the key to international strategic games. When an aircraft flies at high speed, due to shock wave compression, viscous friction, etc., the temperature of its outer wall and nearby areas rises rapidly. In order to ensure that the internal components work normally within the allowable temperature range and maintain their aerodynamic shape, effective structural thermal protection design must be carried out.

[0003] Thermal protection technology can be mainly divided into passive and active thermal protection technology. Passive thermal protection that uses thermal protection materials for insulation or ablative materials for phase change to absorb heat is the most widely used aerodynamic heat treatment measure and is used in many high-speed aircraft (such as the US X-30 and X-47). This type of thermal protection technology has a relatively simple structure, but the preparation process is complex and the cost is high. When the ablative thermal protection system is flying at high speed, the material will gradually be ablated as the temperature rises, which can easily change the overall aerodynamic shape and cause accidents. At the same time, due to the weak heat absorption capacity of the passive thermal protection system, the thickness and weight of the materials required in long-flight applications are large, which seriously compresses the payload of the aircraft. Active thermal protection technology is mainly divided into two categories, namely sweat cooling and convection cooling. The commonly used cooling medium for sweat cooling is water. It draws on the way organisms sweat to dissipate heat, using the latent heat of vaporization of water to absorb heat and form a thermal insulation barrier, but the system reliability is poor. Convection cooling is often used in aerospace vehicles or aviation vehicles. Generally, circulating liquid hydrocarbon fuel is used as a coolant, and the heat of the structure surface is taken away by the physical heat capacity of the fuel. Due to the limitation of fuel coking, this heat absorption mode is only applicable to supersonic flight at speeds below Mach 5. In recent years, with the further improvement of the performance of high-speed aircraft, especially the development of high-speed aircraft, its aerodynamic thermal environment has become more complex and harsh. In addition, due to the rapid upgrading and iteration of electronic components in the internal load of aircraft in recent years, the operating power and the heat generated by it have increased rapidly. Therefore, achieving efficient heat dissipation of internal loads has become one of the key issues for the stable operation of aircraft. It can be seen that it is of great significance to develop an efficient and reliable method to absorb the aerodynamic heat of high-speed aircraft.

[0004] In view of the above difficulties, based on experimental and theoretical research, it is found that when a mixed solution of alcohol and water is used as the cooling medium of the active thermal protection system, it can absorb a large amount of aerodynamic heat through physical vaporization reaction. In particular, when the system contains a suitable catalyst, it can catalyze the strong endothermic reforming reaction of alcohol and water. Taking ethanol and water solution as an example, the reforming reaction after vaporization can generate hydrogen and carbon monoxide (Equation 1), the gas volume increases three times, and the heat absorbed per mole of fluid reaches 256.8kJ. When the aerodynamic heat temperature reaches 600℃, the heat absorption of pure water is only 3.6MJ / Kg, while the total amount of physical and chemical heat absorption of the mixed solution of ethanol and water under the same conditions can reach more than 6.2MJ / Kg. In addition, the small molecular gases (such as hydrogen and carbon monoxide) produced can be used to do work externally. Therefore, based on this active thermal protection technology, not only can the heat absorption capacity of the system be improved, but also aerodynamic heat can be converted into chemical energy to achieve heat-to-work conversion, thereby reducing the thickness of the aircraft insulation layer, increasing the system payload, and improving the maneuverability of the aircraft.

[0005]

[0006] Due to the space and load limitations of high-speed aircraft, the above heat-to-work conversion system must have the following characteristics at the same time: 1) The heat-to-work conversion system is light and thin; 2) It has a high degree of integration, which is convenient for in-situ replacement of passive insulation panels; 3) The storage temperature of the alcohol-water working fluid is not higher than 120°C, so that its vapor pressure is low, thereby reducing the thickness of the storage tank wall and reducing the weight of the system; 4) The temperature of the catalyst and reactor is not lower than 300°C to ensure that the reforming reaction is fast and efficient.

[0007] However, the current heat-to-work conversion system cannot meet the above requirements at the same time. Therefore, the development of suitable reaction and storage containers is the key to the efficient operation of the heat-to-work conversion system. Summary of the invention

[0008] The purpose of the present invention is to overcome the above-mentioned defects of the prior art and to provide a distributed fan-shaped reaction system and its use method and application. The system not only has a strong heat absorption capacity, but also can generate high-temperature and high-pressure gas to do work, realize waste heat utilization, and thus reduce the aircraft insulation layer and increase the system payload.

[0009] To achieve the above object, the technical solution of the present invention is as follows:

[0010] A distributed sector reaction system, the system comprising: a cooling medium storage tank 1, a sector reactor 2, an electric control valve 3, a gas storage tank 4, a discharge valve 5, an electromagnetic valve 6, and a thruster 7; the cooling medium storage tank 1 is filled with a high-density liquid cooling medium 8; the sector reactor 2 is filled with a catalyst 9; the cooling medium storage tank 1, the sector reactor 2, the electric control valve 3 and the gas storage tank 4 are connected in sequence, the gas storage tank 4 is provided with a first valve port 41 and a second valve port 42, the first valve port 41 is connected to the thruster 7 through the electromagnetic valve 6, and the second valve port 42 is connected to the outside through the discharge valve 5.

[0011] Optionally, the catalyst 9 includes a modified Al2O3 carrier and active components and additives supported on the modified Al2O3 carrier.

[0012] Optionally, the active component includes one or more of Cu, Ni, Fe, Ru, and Pt.

[0013] Optionally, the mass of the active component accounts for 5% to 30% of the total mass of the catalyst.

[0014] Optionally, the auxiliary agent includes Zn and / or Ce.

[0015] Optionally, the mass of the auxiliary agent accounts for 1% to 10% of the total mass of the catalyst.

[0016] Optionally, the high-density liquid cooling medium 10 is an alcohol-water mixed solution.

[0017] Optionally, the alcohol component in the alcohol-water mixed solution includes one or more of methanol, ethanol, ethylene glycol, propanol and isopropanol.

[0018] Optionally, the mass concentration of the alcohol component in the alcohol-water mixed solution is 1% to 100%.

[0019] Preferably, the alcohol components in the alcohol-water mixed solution include methanol and ethanol; the mass concentration of methanol in the alcohol-water mixed solution is 10% to 90%, and the mass concentration of ethanol is 30% to 80%.

[0020] Optionally, the sector-shaped reactor 2 includes an arc-shaped wall 21, a straight wall 22, and an outlet 23 fixedly connected end to end in sequence, and the outlet 23 is connected to the outside; the arc-shaped wall 21 is provided with an inlet 211, and the feed port of the inlet 211 is connected to the cooling medium storage tank 1 through a cooling medium pipeline; a sector-shaped catalyst bed 24 is provided in the space enclosed by the arc-shaped wall 21, the straight wall 22, and the outlet 23, and the sector-shaped catalyst bed 24 is filled with a catalyst 9.

[0021] Optionally, the system includes at least two sector-shaped reactors 2 arranged in adjacent circles, and the outlet 23 of each sector-shaped reactor 2 is connected through a pipeline to form a flow channel for the reaction gas.

[0022] Optionally, the inlet 211 is located outside the arc-shaped long side of the sector-shaped reactor 2 and is uniformly distributed small holes, which can make the gas and liquid evenly distributed and thus fully contact with the catalyst 9 in the sector-shaped catalyst bed 24.

[0023] Optionally, the cross-sectional area of ​​the feed port of the inlet 211 is 10 cm 2 ~100cm 2 The cross-sectional area of ​​the outlet 23 is 0.2 cm 2 ~10cm 2 .

[0024] Specifically, the arc-shaped long side of the sector-shaped reactor 2 of the present invention is the inlet of the cooling medium, which can use aerodynamic heat to quickly heat the low-temperature, low-flow rate working fluid, and then decompose the working fluid through the action of the catalyst. The narrow side of the sector-shaped reactor 2 is the reactor outlet, which is connected to the gas storage tank 4 and the thruster 7, and uses the gas generated by the decomposition of the endothermic working fluid to do work.

[0025] The present invention also discloses a method for using the distributed sector reaction system as described above, comprising the following steps:

[0026] The high-density liquid cooling medium 8 in the cooling medium storage tank 1 is heated and vaporized by aerodynamic heat, and then enters the fan-shaped reactor 2 through a pipeline under pressure to absorb aerodynamic heat by physical phase change latent heat and sensible heat, and then undergoes a chemical endothermic reaction under the action of the catalyst 9 to produce high-pressure gas small molecules, and the high-pressure gas small molecules enter the gas storage tank 4 through the electric control valve 3 for storage;

[0027] When the high-speed aircraft needs to adjust its attitude, the discharge valve 5 is closed, and the electromagnetic valve 6 is opened to introduce the high-pressure fuel gas small molecules into the thruster 7, and the small molecules are discharged through the thruster 7, thereby generating thrust by performing work;

[0028] When the high-speed aircraft does not need additional power and the pressure of the gas tank 4 is greater than 2MPa, the solenoid valve 6 is closed and the discharge valve 5 is opened. The small molecules of the high-pressure fuel gas are discharged through the discharge valve 5 until the pressure of the gas tank 4 is 0.5-1MPa, and then the discharge valve 5 is closed.

[0029] The invention also discloses a high-speed aircraft, comprising the above-mentioned distributed fan-shaped reaction system.

[0030] Specifically, the specific application process is: under the action of aerodynamic heat of high-speed aircraft, it can quickly evaporate and absorb heat, so that the temperature of the cooling medium storage tank 1 is maintained below 120°C, ensuring the normal operation of the internal load of the high-speed aircraft; the fan-shaped reactor 2 can use high-temperature aerodynamic heat (300°C~800°C) to catalytically decompose the high-density liquid cooling medium 8 to produce high-pressure combustion gas small molecules, which are used to do work to generate thrust, with a specific impulse of 150s, realizing heat-to-work conversion.

[0031] Implementing the embodiments of the present invention will have the following beneficial effects:

[0032] (1) Compared with the traditional passive insulation method, the distributed fan-shaped reaction system of the present invention belongs to the active thermal protection technology, which has the advantages of strong cooling capacity, ability to withstand long-term heating of high-density heat flow, realization of closed-loop temperature control, etc., and has a high degree of integration.

[0033] (2) Compared with the active heat insulation method of water sweating, the distributed fan-shaped reaction system of the present invention can not only take advantage of the physical heat absorption of the liquid heat absorbing medium, but also enhance the heat absorption through chemical reactions. The theoretical maximum heat absorption capacity of the system is more than doubled (>6MJ / kg) compared with the heat absorption of water sweating (~3MJ / kg). When further coupled with ammonia decomposition, alcohol decomposition or alcohol-water reforming reactions, the heat absorption performance of the system can be further enhanced, and thrust can be generated to do work.

[0034] (3) The fan-shaped reforming reactor in the distributed fan-shaped reaction system of the present invention has the advantages of large inlet volume and small outlet volume, which can realize rapid heating of alcohol-water working fluid; when the catalyst dosage is the same, compared with the traditional plate-type structure reactor, the alcohol-water working fluid conversion rate is increased by about 20%, and the aerodynamic heat absorption capacity is increased by about 15%, thereby having better aerodynamic heat management and work performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 This is a schematic diagram of a distributed sector reaction system according to Example 1 of the present invention.

[0036] Figure 2 This is a schematic diagram of a distributed sector reaction system according to Example 2 of the present invention.

[0037] Figure 3 This is a graph showing the change in gas composition at the reactor outlet as a function of temperature in Example 3 of the present invention.

[0038] Figure 4 This is a graph showing the total heat sink test results of the alcohol-water working fluid of Example 4 of the present invention.

[0039] Figure 5 This is a schematic diagram of a common multi-channel plate reactor of Comparative Example 1 of the present invention.

[0040] Among them, 1. cooling medium storage tank; 2. sector-shaped reactor, 21, arc-shaped wall, 211, inlet, 22, straight wall, 23, outlet, 24, sector-shaped catalyst bed; 3. electric control valve; 4. gas storage tank, 41, first valve port, 42, second valve port; 5. discharge valve; 6. solenoid valve; 7. thruster; 8. high-density liquid cooling medium; 9. catalyst. DETAILED DESCRIPTION

[0041] The present invention is further described below in conjunction with specific embodiments, but the present invention is not limited in any way.

[0042] The present invention discloses a distributed sector reaction system, which comprises: a cooling medium storage tank 1, a sector reactor 2, an electric control valve 3, a gas storage tank 4, a discharge valve 5, an electromagnetic valve 6, and a thruster 7; the cooling medium storage tank 1 is filled with a high-density liquid cooling medium 8; the sector reactor 2 is filled with a catalyst 9; the cooling medium storage tank 1, the sector reactor 2, the electric control valve 3 and the gas storage tank 4 are connected in sequence, and the gas storage tank 4 is provided with a first valve port 41 and a second valve port 42, the first valve port 41 is connected to the thruster 7 through the electromagnetic valve 6, and the second valve port 42 is connected to the outside through the discharge valve 5.

[0043] In a specific embodiment, the catalyst 9 includes a modified Al2O3 carrier and active components and additives supported on the modified Al2O3 carrier.

[0044] In a specific embodiment, the active component includes one or more of Cu, Ni, Fe, Ru, and Pt.

[0045] In a specific embodiment, the mass of the active component accounts for 5% to 30% of the total mass of the catalyst.

[0046] In a specific embodiment, the additive includes Zn and / or Ce.

[0047] In a specific embodiment, the mass of the auxiliary agent accounts for 1% to 10% of the total mass of the catalyst.

[0048] In a specific embodiment, the high-density liquid cooling medium 10 is an alcohol-water mixed solution.

[0049] In a specific embodiment, the alcohol component in the alcohol-water mixed solution includes one or more of methanol, ethanol, ethylene glycol, propanol and isopropanol.

[0050] In a specific embodiment, the mass concentration of the alcohol component in the alcohol-water mixed solution is 1% to 100%.

[0051] Preferably, the alcohol components in the alcohol-water mixed solution include methanol and ethanol; the mass concentration of methanol in the alcohol-water mixed solution is 10% to 90%, and the mass concentration of ethanol is 30% to 80%.

[0052] In a specific embodiment, the sector-shaped reactor 2 includes an arc-shaped wall 21, a straight wall 22, and an outlet 23 which are fixedly connected end to end in sequence, and the outlet 23 is connected to the outside; the arc-shaped wall 21 is provided with an inlet 211, and the feed port of the inlet 211 is connected to the cooling medium storage tank 1 through a cooling medium pipeline; a sector-shaped catalyst bed 24 is provided in the space enclosed by the arc-shaped wall 21, the straight wall 22, and the outlet 23, and the sector-shaped catalyst bed 24 is filled with a catalyst 9.

[0053] In a specific embodiment, the system includes at least two sector-shaped reactors 2 arranged in adjacent circles, and the outlet 23 of each sector-shaped reactor 2 is connected through a pipeline to form a flow channel for the reaction gas.

[0054] In a specific embodiment, the inlet 211 is located outside the arc-shaped long side of the sector-shaped reactor 2 and is a uniformly distributed small hole, which can make the gas and liquid evenly distributed and thus fully contact with the catalyst 9 in the sector-shaped catalyst bed 24.

[0055] In one specific embodiment, the cross-sectional area of ​​the feed opening of the inlet 211 is 10 cm 2 ~100cm 2 The cross-sectional area of ​​the outlet 23 is 0.2 cm 2 ~10cm 2 .

[0056] The present invention also discloses a method for using the distributed sector reaction system as described above, comprising the following steps:

[0057] The high-density liquid cooling medium 8 in the cooling medium storage tank 1 is heated and vaporized by aerodynamic heat, and then enters the fan-shaped reactor 2 through the pipeline under pressure to absorb aerodynamic heat by physical phase change latent heat and sensible heat, and then undergoes a chemical endothermic reaction under the action of the catalyst 9 to produce high-pressure gas small molecules, which enter the gas storage tank 4 through the electric control valve 3 for storage;

[0058] When the high-speed aircraft needs to adjust its attitude, the discharge valve 5 is closed, and the solenoid valve 6 is opened to introduce high-pressure fuel gas small molecules into the thruster 7, and the small molecules are discharged through the thruster 7, thereby generating thrust by doing work;

[0059] When the high-speed aircraft does not need additional power and the pressure of the gas tank 4 is greater than 2MPa, the solenoid valve 6 is closed, the relief valve 5 is opened, and the small molecules of high-pressure fuel gas are discharged through the relief valve 5 until the pressure of the gas tank 4 is 0.5-1MPa, and then the relief valve 5 is closed.

[0060] The present invention also discloses a high-speed aircraft, comprising the distributed fan-shaped reaction system of any embodiment of the present invention.

[0061] The following are specific embodiments

[0062] Example 1

[0063] The distributed sector reaction system of this embodiment, such as Figure 1 As shown, Figure 1 This is a schematic diagram of a distributed sector reaction system according to Example 1 of the present invention, comprising: a cooling medium storage tank 1, a sector reactor 2, an electric control valve 3, a gas storage tank 4, a discharge valve 5, a solenoid valve 6, and a thruster 7; the cooling medium storage tank 1 is filled with a high-density liquid cooling medium 8;

[0064] The fan-shaped reactor 2 includes an arc wall 21, a straight wall 22, and a cross-sectional area of ​​0.79 cm 2 The outlet 23 is connected to the outside; the arc wall 21 is provided with a cross-sectional area of ​​7.9cm 2 The inlet 211 is a uniformly distributed small hole, and the feed port of the inlet 211 is connected to the cooling medium storage tank 1 through a cooling medium pipeline; a fan-shaped catalyst bed 24 is provided in the space surrounded by the arc wall 21, the straight wall 22 and the outlet 23, and the fan-shaped catalyst bed 24 is filled with a catalyst 9.

[0065] Among them, the outlet pipeline of the cooling medium storage tank 1 is connected to the inlet 211 of the sector-shaped reactor 2, the outlet 23 of the sector-shaped reactor 2 is connected to the inlet of the electric control valve 3 through a pipeline, the outlet of the electric control valve 3 is connected to the gas storage tank 4, and the gas storage tank 4 is provided with a first valve port 41 and a second valve port 42. The first valve port 41 is connected to the thruster 7 through the solenoid valve 6, and the second valve port 42 is connected to the outside through the discharge valve 5.

[0066] The catalyst 9 includes a modified Al2O3 carrier and active components Cu and an auxiliary agent Zn loaded on the modified Al2O3 carrier.

[0067] The high-density liquid cooling medium 10 is a mixed solution of ethanol and water, and the mass concentration of ethanol is 50%.

[0068] The method for using the distributed sector reaction system of the present embodiment in the active thermal protection system of a high-speed aircraft comprises the following steps: the high-density liquid cooling medium 8 in the cooling medium storage tank 1 is vaporized by aerodynamic heat heating, and then enters the sector reactor 2 through a pipeline under pressure to absorb aerodynamic heat by physical phase change latent heat and sensible heat, and then undergoes a chemical endothermic reaction under the action of a catalyst 9 to produce high-pressure fuel gas small molecules, and the high-pressure fuel gas small molecules enter the gas storage tank 4 through the electric control valve 3 for storage.

[0069] When the high-speed aircraft needs to adjust its attitude, the discharge valve 5 is closed, and the solenoid valve 6 is opened to introduce small molecules of high-pressure combustion gas into the thruster 7, and the small molecules are discharged through the thruster 7, thereby performing work to generate thrust.

[0070] When the high-speed aircraft does not need additional power and the pressure of the gas tank 4 is greater than 2MPa, the solenoid valve 6 is closed, the relief valve 5 is opened, and the small molecules of high-pressure fuel gas are discharged through the relief valve 5 until the pressure of the gas tank 4 is 0.5-1MPa, and then the relief valve 5 is closed.

[0071] Example 2

[0072] The distributed sector reaction system of this embodiment, such as Figure 2 As shown, Figure 2 This is a schematic diagram of a distributed sector-shaped reaction system of Example 2 of the present invention. Compared with Example 1, this embodiment is different only in that the reactor is composed of a plurality of sector-shaped reactors 2 arranged adjacent to each other in a circular pattern, and the outlet 23 of each sector-shaped reactor 2 is connected by a pipeline to form a flow channel for the reaction gas.

[0073] The method of using the distributed sector reaction system of this embodiment in the active thermal protection system of a high-speed aircraft is the same as that of Embodiment 1.

[0074] Example 3

[0075] The only difference between this embodiment and embodiment 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%.

[0076] Example 4

[0077] The only difference between this embodiment and embodiment 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%.

[0078] Comparative Example 1

[0079] The difference between this comparative example and Example 1 is that the reactor of this comparative example is a common plate structure, and the overall thickness and wall thickness of the reactor are the same as those of the sector reactor. Figure 5 As shown, the rest are the same as in Example 1.

[0080] Test Case

[0081] The reactors of Examples 3-4 and Comparative Example 1 were heated by quartz lamps to evaluate the catalytic reaction activity of the catalyst in the catalytic reforming reactor for different alcohol-water components, thereby simulating the aerodynamic thermal scene of a high-speed aircraft. The surface temperature of the reactor was adjusted by controlling the power of the quartz lamp array, and the outlet gas was quantified by gas chromatography.

[0082] Depend on Figure 3It can be seen that in the test temperature range, the methanol conversion rate increases significantly with the increase of temperature, and the conversion rate reaches 100% at 600°C. From the product composition, it can be seen that when the reaction temperature is lower than 550°C, the products are mainly H2 and CO, indicating that the main methanol decomposition reaction occurs (CH3OH→CO+2H2). When the reaction temperature reaches 600°C, CO2 appears in the product, indicating that the water vapor shift reaction occurs (CO+H2O→CO2+H2).

[0083] Depend on Figure 4 It can be seen that the working fluid heat sink corresponding to Example 4 at different temperatures reaches 4.5MJ / kg at 400°C, which is 43% higher than the water working fluid heat sink; at 400°C, the working fluid heat sink reaches 4.5MJ / kg, which is 43% higher than the water working fluid heat sink; at 600°C, the heat sink reaches 5.6MJ / kg, which is 55% higher than the water working fluid heat sink, and the reaction gas phase impulse in the whole temperature range exceeds 150s.

[0084] Depend on Figure 5 It can be seen that in Comparative Example 1, a common plate-type reforming reactor was made. When the surface temperature was 500°C and 600°C, the corresponding methanol conversion rates were 54% and 81%, respectively, while the corresponding temperature conversion rates of the sector-shaped reactor were 78% and 100%, respectively. It can be seen that the sector-shaped reactor can significantly improve the efficiency of the heat-to-work conversion system by improving the heat and mass transfer efficiency.

[0085] The above-mentioned embodiments only express several implementation methods of the present invention, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the patent application. It should be pointed out that, for a person of ordinary skill in the art, several variations and improvements can be made without departing from the concept of the present invention, and these all belong to the protection scope of the present invention. Therefore, the protection scope of the patent of the present invention shall be subject to the attached claims.

Claims

1. A distributed sector reaction system, characterized in that: The system comprises: a cooling medium storage tank (1), a sector reactor (2), an electric control valve (3), a gas storage tank (4), a discharge valve (5), a solenoid valve (6), and a thruster (7); The cooling medium storage tank (1) is filled with a high-density liquid cooling medium (8); The sector-shaped reactor (2) is filled with a catalyst (9); The cooling medium storage tank (1), the sector reactor (2), the electric control valve (3) and the gas storage tank (4) are connected in sequence. The gas storage tank (4) is provided with a first valve port (41) and a second valve port (42). The first valve port (41) is connected to the thruster (7) through the solenoid valve (6), and the second valve port (42) is connected to the outside through the discharge valve (5).

2. The distributed sector reaction system according to claim 1, characterized in that: The catalyst (9) comprises a modified Al2O3 carrier and an active component and an auxiliary agent supported on the modified Al2O3 carrier; wherein the mass of the active component accounts for 5% to 30% of the total mass of the catalyst, and the mass of the auxiliary agent accounts for 1% to 10% of the total mass of the catalyst; The active components include one or more of Cu, Ni, Fe, Ru and Pt; The auxiliary agent includes Zn and / or Ce.

3. The distributed sector reaction system according to claim 1, characterized in that: The high-density liquid cooling medium (10) is an alcohol-water mixed solution; The alcohol component in the alcohol-water mixed solution includes one or more of methanol, ethanol, ethylene glycol, propanol and isopropanol; The mass concentration of the alcohol component in the alcohol-water mixed solution is 1% to 100%.

4. The distributed sector reaction system according to claim 3, characterized in that: The alcohol components in the alcohol-water mixed solution include methanol and ethanol; The mass concentration of methanol in the alcohol-water mixed solution is 10% to 90%, and the mass concentration of ethanol is 30% to 80%.

5. The distributed sector reaction system according to claim 1, characterized in that: The system comprises at least two sector-shaped reactors (2) arranged in adjacent circumferences, and the outlets (23) of each sector-shaped reactor are connected through a pipeline to form a flow channel for the reaction gas.

6. A method for using the distributed sector reaction system according to any one of claims 1 to 5, characterized in that: The following steps are involved: The high-density liquid cooling medium (8) in the cooling medium storage tank (1) is heated and vaporized by aerodynamic heat, and then enters the fan-shaped reactor (2) through a pipeline under pressure to absorb aerodynamic heat by physical phase change latent heat and sensible heat, and then undergoes a chemical endothermic reaction under the action of a catalyst (9) to generate high-pressure gas small molecules, and the high-pressure gas small molecules enter the gas storage tank (4) through an electric control valve (3) for storage; When the high-speed aircraft needs to adjust its attitude, the discharge valve (5) is closed, and the electromagnetic valve (6) is opened to allow the high-pressure combustion gas small molecules to flow into the thruster (7), and the small molecules are discharged through the thruster (7), thereby performing work to generate thrust; When the high-speed aircraft does not need additional power and the pressure of the gas tank (4) is greater than 2 MPa, the solenoid valve (6) is closed and the discharge valve (5) is opened, and the small molecules of the high-pressure fuel gas are discharged through the discharge valve (5) until the pressure of the gas tank (4) is 0.5-1 MPa, and then the discharge valve (5) is closed.

7. A high-speed aircraft, characterized in that: A distributed sector reaction system comprising any one of claims 1-5.

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