Preparation method and device of hydrogen absorption and desorption composite material for hydrogen energy aircraft

Abstract

The application provides a preparation method and device of a hydrogen absorption and desorption composite material for a hydrogen energy aircraft, and belongs to the technical field of hydrogen absorption and desorption of an aircraft. The specific preparation method comprises the following steps: Zr 45 V 21 Fe5Ti 29 alloy ingot is prepared; the alloy ingot is crushed and screened to obtain alloy particles; the alloy particles are ultrasonically cleaned; the cleaned alloy particles are fluorinated to form a rough outer surface; the fluorinated alloy particles are sensitized and activated to form platinum particles attached to the surface of the alloy particles; and the activated alloy particles are plated with metal platinum nanoparticles on the surface by a chemical reduction method. The treatment scheme can effectively improve the hydrogen leakage post-treatment capacity of the hydrogen energy aircraft.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of hydrogen absorption and elimination for aircraft, in particular to a preparation method and device of a hydrogen absorption and elimination composite material for hydrogen energy aircraft. BACKGROUND

[0002] In recent years, the continuous progress of science and technology has enabled some small hydrogen energy aircraft to successfully complete test flights, demonstrating the feasibility and great potential of hydrogen energy aircraft. However, the special physical and chemical properties of hydrogen have brought severe challenges to the operation of hydrogen energy aircraft. Therefore, hydrogen adsorption and elimination in the limited space of an aircraft has become a problem to be solved.

[0003] Currently, in terms of hydrogen adsorption materials, whether they are physical adsorption materials or chemical adsorption materials, their adsorption capacity is limited. When facing a larger scale of hydrogen leakage, it is difficult for the adsorbent to reduce the hydrogen concentration in the surrounding environment to within a safe range. Moreover, once the adsorbent is saturated with hydrogen, it needs to be replaced in time, and the maintenance and replacement costs are extremely high. In terms of catalytic hydrogen elimination, Pt-based catalysts usually use porous alumina as a carrier and can safely and efficiently eliminate hydrogen in a confined space at normal temperature and pressure, but the hydrogen elimination performance of such catalysts is sensitive to reaction conditions, and factors such as temperature and humidity can affect the rate and efficiency of the catalytic reaction. For example, in a low-temperature and high-humidity environment, the response speed of catalytic hydrogen elimination will be significantly slower, and the reaction rate will be significantly reduced.

[0004] Moreover, the existing catalytic hydrogen elimination device has problems such as large volume and poor vibration resistance, making it difficult to be applied in the interior of an aircraft with complex internal structure and narrow space. SUMMARY

[0005] Therefore, the present application provides a preparation method and device of a hydrogen absorption and elimination composite material for hydrogen energy aircraft, which solves the problems in the prior art and effectively improves the hydrogen leakage treatment capacity of hydrogen energy aircraft.

[0006] In one aspect, the preparation method of a hydrogen absorption and elimination composite material for hydrogen energy aircraft provided by the present application adopts the following technical scheme:

[0007] A preparation method of a hydrogen absorption and elimination composite material for hydrogen energy aircraft, comprising the following steps:

[0008] A ZrVFe5Ti alloy ingot is prepared by using pure zirconium, vanadium, iron and titanium metals with a purity of ≥99.9% as raw materials, wherein the ZrVFe5Ti alloy ingot contains Zr 45 V 21 Fe5Ti 29 alloy ingot, wherein the Zr 45 V 21 Fe5Ti 29The alloy ingot has the atomic percentage of each metal element as Zr:V:Fe:Ti=45:21:5:29;

[0009] The alloy ingot is crushed and sieved to obtain Zr 45 V 21 Fe5Ti 29 alloy particles;

[0010] The Zr 45 V 21 Fe5Ti 29 alloy particles are ultrasonically cleaned;

[0011] The cleaned Zr 45 V 21 Fe5Ti 29 alloy particles are fluorinated to make Zr 45 V 21 Fe5Ti 29 alloy particles form a rough outer surface;

[0012] The fluorinated Zr 45 V 21 Fe5Ti 29 alloy particles are sensitized and activated to make Zr 45 V 21 Fe5Ti 29 alloy particles form a rough outer surface;

[0013] The activated Zr 45 V 21 Fe5Ti 29 alloy particles are plated with metal platinum nanoparticles on the surface by a chemical reduction method.

[0014] Optionally, the alloy ingot is crushed and sieved to obtain Zr 45 V 21 Fe5Ti 29 alloy particles with a particle size of 250-425 μm.

[0015] Optionally, the cleaned Zr 45 V 21 Fe5Ti 29 alloy particles are fluorinated, and the specific steps include:

[0016] A fluorination solution is prepared, and 0.1 g of KF and 0.1 ml of HF solution with a mass fraction of 40-45% are contained in 100 ml of the fluorination solution;

[0017] The cleaned Zr 45 V 21 Fe5Ti 29The alloy particles are put into the fluorination solution, and the fluorination solution is ensured to submerge the Zr 45 V 21 Fe5Ti 29 The alloy particles are subjected to ultrasonic cleaning for 10-15 min.

[0018] Optionally, the Zr 45 V 21 Fe5Ti 29 The specific steps of the sensitization and activation treatment of the alloy particles include:

[0019] The sensitization solution is configured, and 0.5 g of SnCl2:2H2O and 2 ml of a hydrochloric acid solution with a mass fraction of 36-38% are contained in 100 ml of the sensitization solution;

[0020] The activation solution is configured, and 0.1 g of H2PtCl6·6H2O is contained in 100 ml of the activation solution;

[0021] The sensitization treatment: the Zr 45 V 21 Fe5Ti 29 The alloy particles are immersed in the sensitization solution for 3-5 min under stirring, and after being washed with deionized water for 1 min, SnCl2 on the surface of the alloy is hydrolyzed into a colloid and adheres to the surface of the alloy;

[0022] The activation treatment: the alloy particles subjected to the sensitization are put into the activation solution for 3-5 min under stirring, and then are washed with deionized water again;

[0023] The sensitization treatment and the activation treatment are alternately completed for 3-5 times.

[0024] Optionally, the Zr 45 V 21 Fe5Ti 29 The final platinum loading on the surface of the alloy particles is 1-3 wt%.

[0025] In another aspect, the application provides a hydrogen absorption and consumption device for a hydrogen energy aircraft, which adopts the following technical scheme:

[0026] A device for hydrogen absorption and consumption of a hydrogen energy aircraft, comprising:

[0027] A base for fixing the device in the aircraft;

[0028] A box body fixedly installed on the base, a side wall of the box body is hollow, and a plurality of catalytic elements are arranged in the box body, each of the catalytic elements comprises a plurality of stacked sheet-shaped nickel foams, and a plurality of Zr 45 V21 Fe5Ti 29 alloy particles.

[0029] Optionally, the base is a magnet, used to adsorb and fix the device in the aircraft.

[0030] Optionally, the box is a cuboid or a cube, the box comprises a solid stainless steel bottom plate, four side wall frames and a top wall frame, the solid stainless steel bottom plate and the base are fixedly connected by magnetic attraction, the four side wall frames and the solid stainless steel bottom plate are welded, one side of the top wall frame and any side wall frame are hinged, and the side of the top wall frame opposite to the hinge shaft and the side wall frame are connected by buckles.

[0031] The side wall frames and the top wall frame are arranged in a rectangular frame, and a plurality of intersecting connecting rods are arranged in the rectangular frame to form the side wall or the top wall of the box.

[0032] Optionally, a plurality of clamping structures are arranged in the box, each clamping structure comprises two grid plates arranged at intervals, the grid plates are perpendicular to the solid stainless steel bottom plate, and a space for placing the catalytic element is formed between the two grid plates.

[0033] In summary, the present application has the following beneficial technical effects:

[0034] In the hydrogen absorption and hydrogen elimination composite material of the present application, the zirconium-vanadium-iron-titanium alloy has good hydrogen absorption performance and can absorb hydrogen gas in a low-temperature and low-pressure environment. The noble metal platinum has high catalytic activity, and its principle of catalyzing the reaction of hydrogen gas and oxygen gas is based on its special electronic structure, which can reduce the activation energy of the reaction, so that hydrogen gas and oxygen gas can rapidly react to generate water at a lower temperature and pressure. The catalyst material of the zirconium-vanadium-iron-titanium alloy coated with the noble metal platinum has the characteristics of fast response speed and high hydrogen elimination efficiency in a low-temperature and low-pressure environment.

[0035] The plurality of clamping structures are arranged at intervals in the present application, which helps the hydrogen-air mixed gas to be in more sufficient contact with the catalytic element, improves the efficiency of the hydrogen elimination reaction, and at the same time, the reasonable space layout also provides a good heat dissipation channel for the catalytic reaction process, effectively avoids the influence of heat accumulation on the catalytic performance, and ensures that the reaction can be continuously, efficiently and stably carried out. Moreover, the compact and flexible structure design takes into account the functionality and spatial adaptability, solving the problem of large volume and difficult installation and fixation of traditional hydrogen elimination devices. BRIEF DESCRIPTION OF DRAWINGS

[0036] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor.

[0037] Figure 1 Structure diagram of the device for hydrogen absorption and hydrogen elimination of hydrogen energy aircraft.

[0038] Explanation of reference numerals: 1, base; 2, box body; 21, stainless steel bottom plate; 22, side wall frame; 23, top wall frame; 24, buckle; 25, cross-shaped structure; 26, X-shaped structure; 3, catalytic element; 31, grid plate. DETAILED DESCRIPTION

[0039] The embodiments of the present application will be described in detail below with reference to the drawings.

[0040] The above embodiments are only some of the embodiments of the present application, but not all the embodiments of the present application. The present application can also be implemented or applied by other different specific embodiments, and each detail in the specification can be modified or changed based on different views and applications without departing from the spirit of the present application. It should be noted that the following embodiments and features in the embodiments can be combined with each other without conflict. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor are within the scope of protection of the present application.

[0041] It should be noted that the various aspects of the embodiments described below are within the scope of the appended claims. It should be apparent that the aspects described herein can be embodied in a wide variety of forms and that any specific structure and / or function described herein is merely illustrative. Based on the teachings herein one skilled in the art should appreciate that an aspect described herein can be implemented independently of any other aspects and that an aspect described herein can be implemented both as any number of software and / or hardware structures and as any number of processes and / or operations. For example, an aspect can be implemented as a software program running on hardware that can process information such as, for example, information stored in a computer-readable storage medium. As another example, an aspect can be implemented as a software program running on hardware that can process information such as, for example, information stored in a computer-readable storage medium.

[0042] It should also be noted that the drawings included in the present disclosure are included to illustrate potentially complex structures associated with the application. However, the drawings are included to illustrate a specific structural aspect of the application and therefore are not included to define or describe features that are not necessary to the spirit and scope of the present application. Further, since numerous modifications and changes can be made to the application without departing from the spirit and scope of the application, it is intended that all such modifications and changes be included within this application and protected by the subsequent claims. It should be noted that the following embodiments and features in the embodiments can be combined with each other without conflict.

[0043] Also in the following description, specific details are given to provide thorough understanding of examples. One skilled in the relevant art will understand, however, that the aspects can be practiced without

[0044] The embodiment of the present application provides a preparation method of hydrogen absorption and desorption composite material for hydrogen energy aircraft.

[0045] A preparation method of hydrogen absorption and desorption composite material for hydrogen energy aircraft, comprising the following steps:

[0046] Zr 45 V 21 Fe5Ti 29 alloy ingot, wherein the atomic percentage of each metal element of the Zr 45 V 21 Fe5Ti 29 alloy ingot is Zr:V:Fe:Ti=45:21:5:29.

[0047] The alloy ingot is crushed and sieved to obtain Zr 45 V 21 Fe5Ti 29 alloy particles; the particle size of the alloy particles is 250-425 μm.

[0048] The Zr 45 V 21 Fe5Ti 29 alloy particles are ultrasonically cleaned using anhydrous ethanol and a sodium hydroxide solution.

[0049] The cleaned Zr 45 V 21 Fe5Ti 29 alloy particles are fluorinated to make the Zr 45 V 21 Fe5Ti 29 alloy particles form a rough outer surface.

[0050] The fluorinated Zr 45 V 21 Fe5Ti 29 alloy particles are sensitized and activated to form platinum particles on the surface of the Zr 45 V 21 Fe5Ti 29 alloy particles.

[0051] The activated Zr 45 V 21 Fe5Ti 29The alloy particles are coated with platinum nanoparticles on their surface using a chemical reduction method. In one embodiment, Zr 45 V 21 Fe5Ti 29 The final platinum loading on the surface of the alloy particles is 1-3 wt%.

[0052] In the hydrogen absorption and removal composite material of this application, zirconium-vanadium-iron-titanium alloy has excellent hydrogen absorption performance and can adsorb hydrogen gas under low temperature and low pressure environments. The noble metal platinum has high catalytic activity; its catalytic reaction of hydrogen and oxygen is based on its special electronic structure, which can lower the activation energy of the reaction, allowing hydrogen and oxygen to react rapidly to form water at lower temperatures and pressures. The catalyst material of zirconium-vanadium-iron-titanium alloy coated with noble metal platinum has the characteristics of fast response speed and high hydrogen removal efficiency under low temperature and low pressure environments.

[0053] After cleaning Zr 45 V 21 Fe5Ti 29 The specific steps for fluorination treatment of alloy particles include:

[0054] To prepare a fluorination solution, each 100 ml of the fluorination solution contains 0.1 g of KF and 0.1 ml of HF solution with a mass fraction of 40-50%. For example, to prepare a 1 liter fluorination solution, weigh 1 g of KF into a beaker, add 900 ml of deionized water to dissolve it, then add 1 ml of HF solution with a mass fraction of 40%, and finally add deionized water to make up to 1 liter.

[0055] After cleaning Zr 45 V 21 Fe5Ti 29 The alloy particles are placed in the fluorination solution, ensuring that the fluorination solution submerges Zr. 45 V 21 Fe5Ti 29 The alloy particles are subjected to ultrasonic cleaning for 10-15 minutes.

[0056] Fluorinated Zr 45 V 21 Fe5Ti 29 The specific steps for sensitizing and activating alloy particles include:

[0057] Prepare a sensitization solution containing 0.5 g of SnCl2:2H2O and 2 ml of 36-38% hydrochloric acid solution per 100 ml. For example, to prepare a 1 liter sensitization solution, weigh 5 g of SnCl2:2H2O into a beaker, add 20 ml of 37% hydrochloric acid solution to dissolve the SnCl2:2H2O, and finally add deionized water to make up to 1 liter.

[0058] Prepare an activation solution containing 0.1 g of H2PtCl6·6H2O per 100 mL of the activation solution; for example, to prepare a 1 L activation solution, take 1 g of H2PtCl6·6H2O and put it into a beaker, then add deionized water to 1 L.

[0059] Sensitization treatment: Fluorinated Zr... 45 V 21 Fe5Ti 29 The alloy particles are immersed in the sensitization solution and stirred continuously for 3-5 minutes. After being washed with deionized water for 1 minute, SnCl2 on the alloy surface is hydrolyzed into a colloid and adheres to the alloy surface.

[0060] Activation treatment: The allergenized alloy particles are placed in the activation solution and stirred continuously for 3-5 minutes, followed by rinsing with deionized water for 1 minute; Pt on the alloy surface 2+ Sn 2+ The particles are reduced to Pt and adhere to the alloy surface, thus completing the first sensitization-activation step.

[0061] The sensitization and activation processes are then alternately repeated 3-5 times. In this embodiment, the sensitization-activation steps are repeated 4 times.

[0062] Activated Zr 45 V 21 Fe5Ti 29 The specific steps for coating platinum nanoparticles onto the surface of alloy particles using a chemical reduction method include:

[0063] A platinum precursor solution prepared by chloroplatinic acid hexahydrate (H₂PtCl₆·6H₂O) and a hydrazine hydrate reducing agent solution were simultaneously added dropwise to a beaker containing zirconium-vanadium-iron-titanium alloy particles and deionized water. During the dropwise addition, mechanical stirring was continuously carried out, and water bath heating was used to control the reduction temperature at 50-80℃. After rinsing with anhydrous ethanol, the mixture was transferred to a vacuum drying oven and vacuum dried at 110-130℃ for 6 hours to obtain the Pt / ZrVFeTi hydrogen adsorption elimination catalyst material.

[0064] In the embodiments of this application, the step of depositing platinum nanoparticles is as follows:

[0065] Preparation of precursor solution: Weigh H2PtCl6·6H2O, add deionized water, and prepare a 2-5 g / L Pt precursor solution. Stir until completely dissolved and set aside.

[0066] Preparation of reducing agent solution: Measure an appropriate amount of hydrazine hydrate with a mass fraction of 80%, dilute it with deionized water to make a hydrazine hydrate solution of 10-20 g / L, stir well, and set aside.

[0067] Reduction reaction: take a clean beaker, add alloy particles after 5 times of sensitization-activation to deionized water, start mechanical stirring, stirring rate 150-200 r / min, at the same time, heat the water bath heating device to 50-80 DEG C.

[0068] Dropwise addition reaction: at the same time, dropwise add Pt precursor solution and hydrazine hydrate solution, dropwise addition rate is 1-2 mL / min, control the ratio through concentration and dropwise addition amount, n (N2H4.H2O): n (H2PtCl6.6H2O) = 5-10:1, continue stirring during dropwise addition, keep the water bath temperature stable at the set value, reaction 30-60 min, in the later stage of reaction, no obvious yellow color can be observed in the solution, and the metal luster of alloy surface is enhanced.

[0069] Post-treatment: after the reaction is completed, stop heating and stirring, rinse the alloy particles with anhydrous ethanol for 3 times, each time with an amount of 1-2 times of the volume of the alloy, remove the surface residual reducing agent, unreacted precursor and the like. Then, transfer the particles to a vacuum drying oven, set the temperature to 110-130 DEG C, vacuum dry for 6 h, obtain Pt / ZrVFeTi hydrogen absorption and elimination catalyst material, detect Pt loading amount, control the Pt loading amount in 1-3 wt% by adjusting the precursor concentration and dropwise addition amount.

[0070] The application further discloses a hydrogen absorption and elimination device for a hydrogen energy airplane.

[0071] As shown in Figure 1 A hydrogen absorption and elimination device for a hydrogen energy airplane, which comprises a base 1 for fixing the device in an airplane, a box body 2 fixedly installed on the base 1, a side wall of the box body 2 being hollow, and a plurality of catalytic elements 3 arranged in the box body 2, each of the catalytic elements 3 comprising a plurality of layers of stacked sheet-shaped nickel foam, and a plurality of ZrVFe5Ti alloy particles plated with platinum nanoparticles on surfaces of the ZrVFe5Ti alloy particles being arranged between adjacent two layers of the sheet-shaped nickel foam and prepared by using the preparation method for the hydrogen absorption and elimination composite material for a hydrogen energy airplane. 45 V 21 Fe5Ti 29 alloy particles. In the embodiment, one catalytic element 3 comprises two layers of stacked sheet-shaped nickel foam.

[0072] The three-dimensional reticular porous structure of the nickel foam is favorable for catalyst dispersion and gas flow, greatly increases the contact interface between the catalyst and hydrogen-air mixed gas, and the good electrical conductivity of the nickel foam is favorable for electron transmission in the catalytic reaction process, further promotes the chemical reaction, and significantly enhances the catalytic reaction effect.

[0073] The preparation process of the catalytic element 3 is as follows: a piece of foamed nickel is laid on the central position of the lower pressing plate, the catalyst particles are uniformly sprinkled on the foamed nickel in multiple small amounts to avoid particle agglomeration. Then, another piece of foamed nickel of the same size is accurately positioned to cover, and the edge positioning tool is used to ensure that the two pieces of foamed nickel are completely aligned to form a sandwich structure. A numerical control tablet press is used to perform the compaction process under a constant pressure of 5 MPa for 30 s. This operation ensures that the catalyst particles are uniformly distributed in the foamed nickel and form a close combination with the foamed nickel framework, fully exerting the catalytic performance of the catalytic element 3.

[0074] The base 1 is a neodymium iron boron magnet, which is used to adsorb and fix the device in the aircraft. The base 1 of the magnet facilitates the fixation of the device at different positions of the aircraft.

[0075] The box body 2 is a rectangular or cubic box body, which comprises a solid stainless steel bottom plate 21, four side wall frames 22 and a top wall frame 23. The solid stainless steel bottom plate 21 is fixedly connected to the base 1 by magnetic attraction, the four side wall frames 22 are welded to the solid stainless steel bottom plate 21, and one side of the top wall frame 23 is hingedly connected to any side wall frame 22. The side of the top wall frame 23 opposite to the hinge shaft is connected to the side wall frame 22 by a buckle 24. The side wall frames 22 and the top wall frame 23 are arranged in a rectangular frame, and a plurality of intersecting connecting rods are arranged in the rectangular frame to form a side wall or a top wall. In the embodiment of the application, the plurality of intersecting connecting rods of the side wall of the box body 2 form a rice-shaped structure 25, and the two intersecting connecting rods of the top wall of the box body 2 form an X-shaped structure 26.

[0076] The base 1 is fixed on the aircraft by magnetic attraction, and the box body 2 is fixed on the base 1 by magnetic attraction, so as to ensure that the device is firmly adsorbed on the metal parts inside the aircraft, and the entire device has strong anti-vibration performance, solving the problems of displacement or failure risk of the traditional hydrogen removal device caused by vibration. The catalytic hydrogen removal reaction is an exothermic reaction, even if the heat is transferred to the magnet, the maximum working temperature of the neodymium iron boron magnet of the application can reach 220℃, and the strong magnetism can still be maintained.

[0077] A plurality of clamping structures are arranged in the box body 2, each clamping structure comprises two grid plates 31 arranged at intervals, the grid plates 31 are perpendicular to the solid stainless steel bottom plate 21, and a space for placing the catalytic element 3 is formed between the two grid plates 31. The catalytic element 3 is placed between the two grid plates 31 of a single clamping structure, and the catalytic element 3 can be replaced after the top wall of the box body is opened. In the embodiment of the application, the grid plate 31 is welded to the solid stainless steel bottom plate 21, the grid plate 31 comprises a rectangular outer frame and an X-shaped cross rod, and the end of the X-shaped cross rod is welded to the rectangular outer frame or designed in one piece.

[0078] The plurality of clamping structures in the application are uniformly distributed, and a regular and uniform spacing space is constructed. This design helps the hydrogen-air mixture to be more fully in contact with the catalytic element 3, improving the efficiency of the hydrogen elimination reaction. At the same time, the reasonable space layout also provides a good heat dissipation channel for the catalytic reaction process, effectively avoiding the influence of heat accumulation on the catalytic performance, and ensuring that the reaction can be carried out continuously, efficiently and stably.

[0079] In other embodiments, the base 1 can also be fixed in the aircraft by bolts, and the box 2 can also be fixed on the base 1 by bolts or welding.

[0080] When the aircraft is flying normally, the device is in standby state. Once hydrogen leakage occurs, the hydrogen-air mixture enters the box 2 and fully contacts the catalytic element 3, and the catalytic element 3 quickly starts the hydrogen adsorption elimination reaction to convert hydrogen into water. As the reaction proceeds, the hydrogen concentration gradually decreases until it reaches a safe range. Such a hydrogen adsorption and elimination composite material and device can quickly and effectively capture and eliminate the leaked hydrogen, solve the problems of large volume, difficult installation and fixation, low hydrogen elimination efficiency and difficulty in adapting to the special environment of high altitude in the prior art, and effectively improve the safety and reliability of hydrogen energy aircraft.

[0081] The above is only a specific embodiment of the application, but the protection scope of the application is not limited thereto. Any changes or replacements within the technical scope disclosed in the application can be easily thought of by those skilled in the art, and should be covered within the protection scope of the application. Therefore, the protection scope of the application should be subject to the protection scope of the claims.

Claims

1. A method for preparing a hydrogen absorbing and desorbing composite material for a hydrogen energy aircraft, characterized by, The method comprises the following steps: Zr was prepared using zirconium, vanadium, iron, and titanium metals with a purity ≥ 99.9% as raw materials. 45 V 21 Fe5Ti 29 Alloy ingots, wherein Zr 45 V 21 Fe5Ti 29 The atomic percentages of each metal element in the alloy ingot are Zr:V:Fe:Ti = 45:21:5:29; The alloy ingot is crushed and sieved to obtain Zr 45 V 21 Fe5Ti 29 alloy particles; Zr 45 V 21 Fe5Ti 29 alloy particles are ultrasonically cleaned; The Zr 45 V 21 Fe5Ti 29 alloy particles are fluorinated to make Zr 45 V 21 Fe5Ti 29 alloy particles form a rough outer surface; Zr 45 V 21 Fe5Ti 29 sensitization and activation treatment to the alloy particles to form adherent platinum particles on the surface of the Zr 45 V 21 Fe5Ti 29 sensitization and activation treatment to the alloy particles to form adherent platinum particles on the surface of the Zr Zr after activation is complete 45 V 21 Fe5Ti 29 The alloy particles are coated with metal platinum nanoparticles on the surface by a chemical reduction method.

2. The method for preparing the hydrogen absorption and desorption composite material for hydrogen-powered aircraft according to claim 1, characterized in that, The alloy ingot is crushed and sieved to obtain Zr having a particle size of 250 to 425 μm 45 V 21 Fe5Ti 29 alloy particles.

3. The method for preparing the hydrogen-absorbing and hydrogen-removing composite material for hydrogen-powered aircraft according to claim 1, characterized in that, The Zr 45 V 21 Fe5Ti 29 The specific steps for fluorination of the alloy particles include: A fluorination solution is prepared, containing 0.1 g of KF and 0.1 ml of HF solution with a mass fraction of 40-45% per 100 ml of the fluorination solution; The cleaned Zr 45 V 21 Fe5Ti 29 alloy particles were placed in the fluorination solution and the fluorination solution was made to submerge the Zr 45 V 21 Fe5Ti 29 alloy particles were subjected to ultrasonic cleaning for 10-15 min.

4. The method for preparing the hydrogen absorption and desorption composite material for hydrogen-powered aircraft according to claim 1, characterized in that, Zr 45 V 21 Fe5Ti 29 The specific steps for sensitizing and activating the alloy particles include: A sensitization solution is prepared, containing 0.5 g of SnCl2:2H2O and 2 ml of hydrochloric acid solution with a mass fraction of 36-38% per 100 ml of the sensitization solution; An activation solution is prepared, containing 0.1 g of H2PtCl6·6H2O per 100 ml of the activation solution; Sensitization: The fluorinated Zr 45 V 21 Fe5Ti 29 The alloy particles were immersed in the sensitization solution for 3-5 min with stirring, and then washed with deionized water for 1 min, so that the SnCl2 on the alloy surface was hydrolyzed into colloidal and adhered to the alloy surface; Activation treatment: the sensitized alloy particles are placed in the activation solution for 3-5 min with continuous stirring, and then washed with deionized water; The sensitization treatment and the activation treatment are alternately completed for 3-5 times.

5. The method for preparing the hydrogen absorption and desorption composite material for hydrogen-powered aircraft according to claim 1, characterized in that, Zr 45 V 21 Fe5Ti 29 The final platinum loading on the alloy particle surface was 1-3 wt%.

6. A device for hydrogen uptake and hydrogen removal for a hydrogen-powered aircraft, characterized in that It comprises: a base for fixing the device in an airplane; A box is fixedly installed on the base, a side wall of the box is hollowed out, a plurality of catalytic elements are arranged in the box, each catalytic element comprises a plurality of stacked sheet-shaped nickel foams, and a plurality of Zr 45 V 21 Fe5Ti 29 alloy particles.

7. The hydrogen uptake and abatement device for a hydrogen-powered aircraft of claim 6, wherein, the base is a magnet for adsorbing and fixing the device in the airplane.

8. The hydrogen uptake and abatement device for a hydrogen-powered aircraft of claim 7, wherein, The box body is a cuboid or a square, the box body comprises a solid stainless steel bottom plate, four side wall frames and a top wall frame, the solid stainless steel bottom plate is fixedly connected with the base by magnetic attraction, the four side wall frames are welded with the solid stainless steel bottom plate, one side of the top wall frame is hingedly connected with any side wall frame, and the side of the top wall frame opposite to the hinged shaft is connected with the side wall frame by a buckle. The side wall frame and the top wall frame are arranged in a rectangular frame, a plurality of cross connecting rods are arranged in the rectangular frame to form the side wall or the top wall of the box body.

9. The hydrogen uptake and abatement device for a hydrogen-powered aircraft of claim 8, wherein, A plurality of clamping structures are arranged in the box body, each clamping structure comprises two grid plates arranged at intervals, the grid plates are perpendicular to the solid stainless steel bottom plate, and a space for placing a catalytic element is formed between the two grid plates.

Images