KR20100110941A - Hydrogen-oxygen bipropellant rocket engine and propulsion method thereof - Google Patents

Abstract

PURPOSE: A hydrogen-oxygen bipropellant rocket engine and an propelling method thereof are provided to eliminate the need for an insulating device for storing hydrogen or oxygen at an extremely low temperature and a tank with a thick wall since the hydrogen and the oxygen are generated through a peroxide decomposition reaction. CONSTITUTION: A hydrogen-oxygen bipropellant rocket engine comprises a peroxide tank(110), a reactor(120), an electrolysis unit(130), a hydrogen-oxygen separating unit(140), a hydrogen tank(150), an oxygen tank(160) and a rocket engine(170). The peroxide decomposition reaction occurs in the reactor. The electrolysis decomposition unit decomposes the water, which is generated by the decomposition in the reactor, into the hydrogen and the oxygen. The hydrogen-oxygen separating unit separates and collects the hydrogen and oxygen, which are decomposed by the electrolysis unit. The hydrogen tank stores the separated hydrogen. The oxygen tank is connected to at least one of the reactor and the hydrogen-oxygen separating unit and stores the generated oxygen. The rocket engine is connected to the hydrogen tank and the oxygen tank. Using the oxygen as an oxidizer, the rocket engine burns the hydrogen and obtains the propulsion.

Description

Hydrogen-Oxygen bipropellant rocket engine and propulsion method

The present invention injects high concentration hydrogen peroxide, an eco-friendly propellant, into the reactor to decompose it into steam and oxygen through reaction with a catalyst, and condenses it back into water to electrolyze and produce hydrogen and oxygen to use oxygen as the oxidant. And a hydrogen-oxygen binary propellant rocket engine which obtains propulsion by burning hydrogen.

The rocket engine is a device that generates thrust and is designed to include a thruster. The rocket engine is a device that allows the rocket engine to fly along a flight trajectory that is attached to a rocket projectile or satellite. Rocket engines can be divided into single-propellant rocket engines driven by a single propellant and binary-propellant rocket engines that burn fuel using oxidants.

In the case of a conventional hydrogen-oxygen binary rocket engine,

First, in order to use hydrogen and oxygen as a propellant of a rocket engine, liquid hydrogen and liquid oxygen must be stored in cryogenic conditions, and thus heat insulation is required.

Second, since two large storage tanks must be operated to store liquid hydrogen and liquid oxygen, they are also disadvantageous in that they are costly due to their weight and volume.

Third, since hydrogen and oxygen are not storage propellants, they should be stored in liquid form in cryogenic conditions. Even though adiabatic treatments are carried out, propellants are continuously vaporized, making them difficult to store for a long time. There is a problem that can only be used in this rocket engine.

Therefore, it is necessary to develop an economical hydrogen-oxygen binary rocket engine that utilizes hydrogen and oxygen as a binary propellant but does not require insulation and can be stored in a small and light tank, reducing the volume and weight of the entire system and storing it for a long time at room temperature. do.

The present invention is to provide a two-propellant rocket engine that can use hydrogen and oxygen as a binary propellant, but do not need a heat insulation device and do not need to have a thick tank wall to contribute to the weight reduction of the entire system.

The present invention is to provide a binary propulsion rocket engine and a propulsion method using hydrogen peroxide decomposition reaction and water electrolysis reaction.

The present invention does not need to provide a separate igniter for ignition of the rocket engine to contribute to the weight reduction of the system and to provide a two-propellant rocket engine with high ignition reliability.

The present invention is a hydrogen peroxide storage tank (110); A reactor 120 connected to the hydrogen peroxide storage tank 110 and generating a hydrogen peroxide decomposition reaction; An electrolysis device (130) connected to the reactor (120) for decomposing water generated by the decomposition reaction in the reactor (120) into hydrogen and oxygen; A hydrogen-oxygen separator (140) connected to the electrolysis device (130) to separate and collect hydrogen and oxygen decomposed in the electrolysis device (130); A hydrogen storage tank 150 connected to the hydrogen-oxygen separator 140 to store separated hydrogen; An oxygen storage tank 160 connected to at least one of the reactor 120 or the hydrogen-oxygen separator 140 to store generated oxygen; And a rocket engine 170 connected to the hydrogen storage tank 150 and the oxygen storage tank 160 to obtain propulsion by burning hydrogen using oxygen as an oxidant. Characterized in that it comprises a.

The present invention is characterized in that the reactor 120 is filled with a catalyst 121 coated with an active material 121b reacting with hydrogen peroxide.

In addition, the catalyst 121 is characterized in that the active material 121b is applied to the support 121a, which is a pellet or grain-shaped microbeads.

The present invention is characterized in that the support 121a of the catalyst 121 is a microbead in a porous pellet form.

The present invention is characterized in that the diameter of the support (121a) of the catalyst 121 is 300 ~ 5000 micrometers.

In addition, the present invention is characterized in that the active material 121b of the catalyst 121 is any one selected from noble metal series or transition metal oxide or a combination thereof.

The support 121a of the catalyst 121 is characterized in that the inorganic oxide.

On the other hand, the present invention is a pressurized gas storage tank 210 for pressurizing hydrogen peroxide; And a pressure regulator formed in a path in which the pressurized gas moves from the pressurized gas storage tank 210 to the hydrogen peroxide storage tank 110 to control the pressurized gas supplied from the pressurized gas storage tank 210 to a set pressure. 215; Characterized in that it comprises a.

The present invention is the first valve 221 is formed in the path to move the hydrogen peroxide from the hydrogen peroxide storage tank 110 to the reactor 120 in order to control the amount of hydrogen peroxide supplied to the reactor 120; A second valve 222 formed in a path in which the water moves from the reactor 120 to the electrolysis device 130 to adjust the amount of water supplied to the electrolysis device 130; In order to control the amount of oxygen supplied to the oxygen storage tank 160, the oxygen is formed in the path to move from the reactor 120 and the hydrogen-oxygen separator 140 to the oxygen storage tank 160 Three valve 223; A fourth valve 224 is formed in the path of the hydrogen from the hydrogen-oxygen separator 140 to the hydrogen storage tank 150 to control the amount of hydrogen supplied to the hydrogen storage tank 150. ; A fifth valve 225 formed in a path through which the hydrogen moves from the hydrogen storage tank 150 to the rocket engine 170 to adjust the amount of hydrogen supplied to the rocket engine 170; A sixth valve 226 formed in a path in which the oxygen moves from the oxygen storage tank 160 to the rocket engine 170 to adjust the amount of oxygen supplied to the rocket engine 170; It characterized in that it comprises at least one valve 220 selected from among the valve driving device 230 for controlling the opening and closing of the valve 220.

In addition, the present invention is a condenser for converting the water in the gaseous state generated during the hydrogen peroxide decomposition reaction in the reactor 120 in the path of the water generated in the reactor 120 to the electrolysis device 130 ( 240) is included.

The present invention includes the steps of: (a) pressurizing the hydrogen peroxide in the hydrogen peroxide storage tank 110 at a pressure set using the pressure regulator 215 into the reactor 120; (b) hydrogen peroxide decomposition step of decomposing hydrogen peroxide into hydrogen and oxygen using a catalyst 121 in the reactor 120; (c) transferring the oxygen decomposed in step (b) to the oxygen storage tank 160 for storage and converting the gaseous water into liquid water in the condenser 240; (d) electrolyzing the water converted in step (c) into hydrogen and oxygen; (e) separating and collecting hydrogen and oxygen decomposed in the step (d) and storing the collected hydrogen by moving to the hydrogen storage tank 150 and storing the oxygen by moving to the oxygen storage tank 160; And (f) generating propulsion by burning hydrogen stored in the hydrogen storage tank 150 as fuel using oxygen stored in the oxygen storage tank 160 as an oxidant. Characterized in that consists of.

In addition, the present invention is characterized in that to generate a propulsion force by igniting the rocket engine by injecting hydrogen to high temperature oxygen during the step (f).

Hydrogen-oxygen binary propellant rocket engine according to the present invention,

First, since hydrogen and oxygen are generated through the decomposition of hydrogen peroxide, it is not necessary to insulate the hydrogen and oxygen in cryogenic conditions or to have a tank with a thick wall. .

Second, in terms of the tank weight of the whole system, it is advantageous in terms of weight and cost of the entire system because only one propellant tank and a small tank for temporarily storing fuel and oxidant may be provided instead of a large and thick fuel tank and an oxidant tank.

Third, since only hydrogen peroxide, which is a storage propellant, is stored, there is almost no loss of propellant due to vaporization and it can be stored for a long time.

In addition, in the present invention, since the oxygen produced during the hydrogen peroxide decomposition reaction is a high temperature state, it is possible to ignite the rocket engine by directly injecting hydrogen to high temperature oxygen, so that it is not necessary to provide a separate ignition device, which contributes to the weight reduction of the system and reliability of ignition. There is an advantage that can be increased.

In general, a rocket is a device that obtains propulsion by exhaling high-pressure gas produced by burning fuel, and such an engine is called a rocket engine. Rocket engines are the most powerful engines of their size, producing more than 3,000 times the power of car engines of the same size. The rocket burns fast because of its high power, consuming a lot of fuel in a short time and generating high temperatures. Therefore, rocket engines need to be very complex and difficult because they have to withstand high temperatures, high pressures, and strong forces.

The working principle of a rocket is the law of action-reaction, which allows a powerful rocket to move forward by using reactions of the same magnitude but opposite direction when a force is applied to an object. The propellant burns in the rocket's combustion chamber, creating a gas that expands very rapidly, and the pressure of the expanding gas acts uniformly in all directions within the rocket, and the pressure exerted in one direction is equal to the pressure applied in the opposite direction. Balance However, the gas flowing behind the rocket is blown out through the nozzle and out of balance with the pressure in front of the rocket, causing the rocket to move forward. The gas exhaled through the nozzle corresponds to Newton's law of motion, and the propulsion to push the rocket toward the opposite direction of the exhaled gas corresponds to the reaction.

There are two main types of rockets, liquid fuel and solid fuel. The propulsion method using liquid fuel is a high velocity jet of gas generated at the rear of the gas while the gas generated by the combustion of the fuel and the oxidant filled in the gas is advanced at the reaction force, and the propulsion method using the solid fuel is a gas. Combustion of the solid fuel contained in the chamber allows the engine to move forward using its propulsion force. Of the two propulsion methods, the non-thrust defining the thrust that can be produced by the unit mass propellant is larger than the solid fuel rocket, and the liquid fuel rocket is larger than the solid fuel rocket.

In addition, there is a single propellant method of obtaining a thrust using only one propellant, and a two-propellant method of burning a fuel using an oxidant to obtain a thrust. The single-propellant method is superior in terms of system simplification and light weight, but the non-thrust generated per unit mass of the propellant is relatively small, while the dual-propellant method can complicate the system, but the non-thrust is twice as efficient as the single-propellant method. to be.

Hereinafter, an embodiment of the present invention will be described in detail with reference to the accompanying drawings.

1 is a system structural diagram of a hydrogen-oxygen binary propellant rocket engine according to the present invention, FIG. 2 is a sectional view of a reactor according to the present invention, and FIG. 3 is an enlarged sectional view of a pellet catalyst according to the present invention. 4 is an enlarged cross-sectional view of a porous pellet-type catalyst according to the present invention, Figure 5 is a block diagram showing the propulsion method of the hydrogen-oxygen binary propellant rocket engine according to the present invention.

Referring to FIG. 1, a hydrogen-oxygen binary propellant rocket engine 170 includes a hydrogen peroxide storage tank 110, a reactor 120, an electrolysis device 130, a hydrogen-oxygen separator 140, and a hydrogen storage tank 150. It may include an oxygen storage tank 160, a rocket engine 170. In addition, the pressurized gas storage tank 210, the pressure regulator 215, the valve 220, the valve driving device 230, it may optionally include a condenser 240. It looks at in detail below.

Referring to FIG. 1, the hydrogen peroxide storage tank 110 is a storage tank for storing hydrogen peroxide, and since FIG. 1 is a structural diagram, the shape of the storage tank may be formed in various shapes such as a cylinder as well as a sphere. . In the case of a conventional propellant storage tank, a thick tank wall must be constructed to withstand high pressure, but the hydrogen peroxide storage tank 110 is composed of a metal material and an outer surface of the tank wall. It is also possible. The metal materials that make up the inner wall of the tank may vary within the range of metal materials that are compatible with hydrogen peroxide, the propellant, and the composite materials that make up the outer surface of the tank wall may be glass fiber, carbon fiber, kevlar, or the like. It can be a variety of materials within the range of materials that can withstand high pressures while contributing to light weight.

Referring to FIG. 1, the pressurized gas storage tank 210 may be selectively connected to the hydrogen peroxide storage tank 110. The pressurized gas storage tank 210 is filled with a high pressure inert gas for pressurizing hydrogen peroxide, which is a propellant, and nitrogen or helium gas may be used as the inert gas. The gas charged at high pressure in the pressurized gas storage tank 210 pressurizes hydrogen peroxide in the hydrogen peroxide storage tank 110 and supplies it to the reactor 120. 1 is a structural diagram, the shape of the pressurized gas storage tank 210 is illustrated as an example, but is not limited thereto, and may be formed in various shapes such as a cylinder and a sphere. The material of the pressurized gas storage tank 210 is the same as that described in the hydrogen peroxide storage tank 110 and will be omitted.

Referring to FIG. 1, the pressure regulator 215 may be selectively formed between the pressurized gas storage tank 210 and the hydrogen peroxide storage tank 110. When nitrogen or helium gas charged to the pressurized gas storage tank 210 at high pressure pressurizes hydrogen peroxide in the hydrogen peroxide storage tank 110, pressure reduction is required at a set pressure. Decompression may be performed at the pressure regulator 215. Although not shown in the drawings, a fine adjustment valve (not shown) may be formed between the pressure regulator 215 and the hydrogen peroxide storage tank 110, and in this case, the pressure gas may be finely adjusted with the pressure regulator 215. The pressure may be adjusted in a valve (not shown), and the pressure controller 215 may first reduce the pressure to a design pressure, and then fine pressure adjustment and correction may be performed in a fine adjustment valve (not shown). Using a blow-down system with fluctuating pressurization pressure, the pressurization pressure is varied according to the amount of hydrogen peroxide used as the propellant and the flow rate of the propellant is variable accordingly, so that hydrogen and oxygen required in the design conditions are constant. There is a problem that is difficult to occur. Therefore, the pressure regulator 215 can supply a certain amount of hydrogen peroxide to the reactor 120 regardless of the amount of residual propellant, thereby generating the required hydrogen and oxygen flow rates. Since the specific configuration of the pressure regulator 215 is the same as the pressure regulator commonly used, a detailed description thereof will be omitted.

Referring to FIG. 2, the reactor 120 is filled with a catalyst 121 so that hydrogen peroxide decomposition reaction occurs, and the catalyst 121 may be formed of a support 121a and an active material 121b. have. The decomposition reaction of hydrogen peroxide is similar to the combustion reaction in that it generates gas at high temperature and high pressure. The method of using a catalyst in the hydrogen peroxide decomposition reaction is a liquid-liquid type, which is a method in which a liquid hydrogen peroxide and a liquid catalyst are sprayed and reacted at the same time, but the efficiency is reduced by moisture, and two supply pipes are installed. There are disadvantages, such as not concise. Therefore, many catalysts in the form of pellets or grains in the solid state or in the form of screens are used. In the case of an electron pellet or grain type catalyst, hydrogen peroxide is sprayed onto the agglomerated solid catalyst to react. This method has an advantage that the contact area between hydrogen peroxide and the catalyst is large and the mass transfer is easy, so that an excellent effect can be expected in the decomposition reaction of hydrogen peroxide. The latter type of screen (catalyst) catalyst has a merit of using a pack compressed with high pressure by stacking wire woven screens, which is not pulverized like a pellet catalyst in a decomposition reaction, and thus has excellent durability. Therefore, the catalyst may be selected according to the operating conditions of the system, but in order to obtain high thrust in the hydrogen-oxygen binary propellant rocket engine 170, it is preferable to use a catalyst in the form of pellets or grains.

Referring to FIG. 3, the active material 121b used in the catalyst 121 is a precious metal-based metal such as platinum, silver, palladium, or manganese oxide, which reacts with hydrogen peroxide. It is preferably any one selected from oxides of transition metals such as manganese oxide, oxidized iron, or the like, or a combination thereof. The active material 121b reacts with a high concentration of hydrogen peroxide, a propellant, to generate gaseous water vapor and oxygen.

Referring to FIG. 4, the catalyst 121 in a pellet form may be porous. Pellets or grains of the microbeads constituting the support 121a are formed by coating a plurality of holes and coating the active material 121b thereon. Therefore, the voids are maximized, and the contact area between the particles of hydrogen peroxide and grains of the active material 121b is also maximized, thereby increasing the reaction speed. As a result, the decomposition rate of hydrogen peroxide (hydrogen peroxide) is increased to obtain a high specific force as the propellant flow rate is increased.

Referring to FIG. 3, the support 121a may be a microbead of pellets or grains. The diameter of the support 121a greatly affects the decomposition efficiency of the propellant and is preferably 300 to 5000 micrometers. It is possible to reduce the production cost of pellets by making the diameters of the plurality of pellets substantially the same. On the other hand, by using two kinds of pellets having different diameters and the same number, excellent results can be obtained in terms of collection rate of particulate matter. The support 121a should be excellent in physicochemical properties, and should not react with hydrogen peroxide. Therefore, the support 121a is preferably an inorganic oxide such as alumina, silica, and titania.

Referring to FIG. 1, the electrolysis device 130 receives water generated by a hydrogen peroxide decomposition reaction in the reactor 120 to fill water in an electrolytic cell having a plurality of electrodes disposed therein, and both ends of the electrodes. The positive (+) and negative (-) terminals of the battery are connected to decompose water into hydrogen and oxygen. The decomposition scheme is as follows.

The whole scheme is

2H ₂ O-> 2H ₂ + O ₂

Lt;

-Pole (reduced) 4H ₂ O + 4e--> 2H ₂ (gas) + 4OH-

+ Pole (oxidation) 2H ₂ 0-> O ₂ (gas) + 4H + + 4e-

Same as

Detailed description of the method of electrolyzing water is the same as in the conventional case, and a detailed description thereof will be omitted. Hydrogen and oxygen decomposed in the electrolysis device 130 are moved to the hydrogen-oxygen separator 140 which will be described later.

Referring to FIG. 1, the condenser 240 may be selectively formed in a path through which water generated in the reactor 120 moves to the electrolysis device 130. Hydrogen peroxide decomposition equation is as follows and it is exothermic.

2H ₂ O _2- > 2H ₂ O + O ₂

Water and oxygen generated during the decomposition reaction are hot and water may be gaseous steam. Therefore, in order to electrolyze water, a process of condensing water in a gaseous state into a liquid state is required in the previous step, and the condenser 240 is a device that condenses water into water through heat exchange with steam.

Referring to FIG. 1, the hydrogen-oxygen separator 140 is connected to the electrolysis device 130. The hydrogen-oxygen separator 140 is a device for capturing hydrogen in a gaseous state except for OH- at a reduction reaction and collecting oxygen in a gaseous state except H + at a + pole where an oxidation reaction occurs. The collected hydrogen and oxygen are moved to the hydrogen storage tank 150 and oxygen storage tank 160, respectively.

Referring to FIG. 1, the hydrogen storage tank 150 and the oxygen storage tank 160 store hydrogen and oxygen in a gas state as tanks for storing hydrogen and oxygen, respectively. In the case of the hydrogen storage tank 150, only hydrogen generated in the hydrogen-oxygen separator 140 is stored, but in the case of the oxygen storage tank 160, the oxygen and the oxygen separated and collected in the hydrogen-oxygen separator 140 In the reactor 120, all the oxygen generated by the hydrogen peroxide decomposition reaction is stored. As described above, since the hydrogen peroxide decomposition reaction is an exothermic reaction, oxygen generated in the reactor 120 may be very high temperature.

Referring to FIG. 1, the rocket engine 170 generates propulsion by burning oxygen using oxygen supplied from the oxygen storage tank 160 as an oxidant and hydrogen supplied from the hydrogen storage tank 150 as a fuel. to be. When decomposing hydrogen peroxide (hydrogen peroxide) and converting it into a binary propellant of hydrogen and oxygen through electrolysis as in the present invention, hydrogen peroxide (hydrogen peroxide) as a single propellant can obtain more than twice the non-thrust There is an advantage. In addition, as described above, since the oxygen generated in the reactor 120 is very high temperature, hydrogen is injected from the hydrogen storage tank 150 after injecting high temperature oxygen through the oxygen storage tank 160 to the rocket engine 170. Can be fired immediately. Therefore, the ignition device for ignition of the rocket engine 170 is not required separately, which contributes to the weight reduction of the system and has the advantage of ensuring the reliability of the ignition device.

Referring to FIG. 1, the valve 220 may be selectively formed among the first valve 221 to the sixth valve 226. Specifically, the first valve 221 is a hydrogen peroxide (hydrogen peroxide) from the hydrogen peroxide storage tank 110 to adjust the amount of hydrogen peroxide (hydrogen peroxide) supplied to the reactor 120 from the reactor 120 It may optionally be formed on the path to move to. The second valve 222 may be selectively formed in a path through which the water moves from the reactor 120 to the electrolysis device 130 to adjust the amount of water supplied to the electrolysis device 130. have. The third valve 223 is the oxygen storage tank 160 to the oxygen from the reactor 120 and the hydrogen-oxygen separator 140 to adjust the amount of oxygen supplied to the oxygen storage tank 160 It may optionally be formed on the path to move to. The fourth valve 224 is a path in which the hydrogen moves from the hydrogen-oxygen separator 140 to the hydrogen storage tank 150 to control the amount of hydrogen supplied to the hydrogen storage tank 150. May be optionally formed. The fifth valve 225 may be selectively formed in a path through which the hydrogen moves from the hydrogen storage tank 150 to the rocket engine 170 to adjust the amount of hydrogen supplied to the rocket engine 170. Can be. The sixth valve 226 may be selectively formed in a path through which the oxygen moves from the oxygen storage tank 160 to the rocket engine 170 to adjust the amount of oxygen supplied to the rocket engine 170. Can be. As described above, the valves 220 do not need to be provided at all, and only some of them may be selectively configured according to the design of the system. A valve driving device 230 may be formed as a control device for controlling the opening and closing of the valve 220. The valve driving device 230 may be configured to supply and shut off hydrogen peroxide, water, oxygen, and hydrogen by controlling the opening and closing of the valve 220. It can be adjusted and flow rate can be adjusted at the time of supply. The valve 220 may be in various forms such as a stop valve, a parallel slide valve, a wedge valve, a check valve, a pressure reducing valve, an escape valve, a safety valve, a throttle valve, such as a globe valve or an angle valve, and the material may include hydrogen peroxide, water, It may vary within the range of metal materials that do not react with oxygen, hydrogen. In addition, the valve 220 may be a solenoid valve that uses a attraction force generated when a current flows through the solenoid to form a magnetic field, whereby the valve driving device 230 may be an electrical signal. Opening and closing of the valve 220 may be adjusted.

Referring to FIG. 5, the propulsion method of the hydrogen-oxygen binary propellant rocket engine is as follows.

step (a)

After setting the pressurized gas pressure using the pressure regulator 215, the hydrogen peroxide in the hydrogen peroxide storage tank 110 is pressurized using the pressurized gas stored in the pressurized gas storage tank 210 and injected into the reactor 120.

(b) step

In the reactor 120, the active material 121b of the catalyst 121 is reacted with hydrogen peroxide to cause a hydrogen peroxide decomposition reaction. As a result of the hydrogen peroxide decomposition reaction, hot oxygen and gaseous water are generated.

step (c)

The high temperature oxygen decomposed in the step (b) is moved to the oxygen storage tank 160 and stored, and the gaseous water is converted into the liquid water in the condenser 240.

(d) step

In the step (c), the water converted into the liquid state through the condenser 240 is electrolyzed by the electrolysis device 130 into hydrogen and oxygen.

(e) step

In step (d), the hydrogen and oxygen decomposed through the electrolysis device 130 are separated and collected in the hydrogen-oxygen separator 140, and the collected hydrogen is moved to and stored in the hydrogen storage tank 150. Oxygen is stored by moving to the oxygen storage tank (160).

(f) step

By using the oxygen stored in the oxygen storage tank 160 as an oxidant, hydrogen stored in the hydrogen storage tank 150 is combusted by the rocket engine 170 to generate a propulsion force. As described above, the high temperature oxygen generated in the reactor 120 is injected into the rocket engine 170 via the oxygen storage tank 160 and then hydrogen is injected from the hydrogen storage tank 150 to immediately start the rocket engine ( Can light 170).

The technical idea should not be interpreted as being limited to the above-described embodiment of the present invention. Various modifications may be made at the level of those skilled in the art without departing from the spirit of the invention as claimed in the claims. Therefore, such improvements and modifications fall within the protection scope of the present invention, as will be apparent to those skilled in the art.

1 is a system structural diagram of a hydrogen-oxygen binary propellant rocket engine according to the present invention.

2 is a cross-sectional view of a reactor according to the present invention.

3 is an enlarged cross-sectional view of a pellet type catalyst according to the present invention.

4 is an enlarged cross-sectional view of a porous pellet form catalyst according to the present invention.

5 is a block diagram showing a propulsion method of a hydrogen-oxygen binary propellant rocket engine according to the present invention;

<Description of the symbols for the main parts of the drawings>

100 hydrogen-oxygen binary propellant rocket engine

110: hydrogen peroxide storage tank

120 reactor 121 catalyst

121a: support 121b: active substance

130: electrolysis device 140: hydrogen-oxygen separator

150: hydrogen storage tank 160: oxygen storage tank

170: Rocket Engine

210: pressurized gas storage tank 215: pressure regulator

220: valve 221: first valve

222: second valve 223: third valve

224: fourth valve 225: fifth valve

226: sixth valve

230: valve drive device 240: condenser

Claims (12)

Hydrogen peroxide storage tank 110; A reactor 120 connected to the hydrogen peroxide storage tank 110 and generating a hydrogen peroxide decomposition reaction; An electrolysis device (130) connected to the reactor (120) for decomposing water generated by the decomposition reaction in the reactor (120) into hydrogen and oxygen; A hydrogen-oxygen separator (140) connected to the electrolysis device (130) to separate and collect hydrogen and oxygen decomposed in the electrolysis device (130); A hydrogen storage tank 150 connected to the hydrogen-oxygen separator 140 to store separated hydrogen; An oxygen storage tank 160 connected to at least one of the reactor 120 or the hydrogen-oxygen separator 140 to store generated oxygen; And A rocket engine (170) connected to the hydrogen storage tank (150) and the oxygen storage tank (160) to obtain propulsion by burning hydrogen using oxygen as an oxidant; Hydrogen-oxygen binary propellant rocket engine comprising a. The method of claim 1, The reactor 120 is a hydrogen-oxygen binary propellant rocket engine, characterized in that the catalyst 121 is filled with an active material (121b) is applied to react with hydrogen peroxide. The method of claim 2, The catalyst 121 is a hydrogen-oxygen binary propellant rocket engine, characterized in that the active material (121b) is applied to the support (121a) that is a pellet or grain-shaped microbeads. The method of claim 3, wherein The support (121a) of the catalyst 121 is a hydrogen-oxygen binary propellant rocket engine, characterized in that the porous pellet form microbeads. The method of claim 4, wherein Hydrogen-oxygen binary propellant rocket engine, characterized in that the diameter of the support (121a) of the catalyst 121 is 300 ~ 5000 micrometers. The method of claim 5, The active material (121b) of the catalyst 121 is any one selected from noble metal-based or transition metal oxide or a combination thereof hydrogen-oxygen binary propellant rocket engine. The method of claim 6, Hydrogen-oxygen binary propellant rocket engine, characterized in that the support (121a) of the catalyst 121 is an inorganic oxide. The method of claim 7, wherein A pressurized gas storage tank 210 for pressurizing hydrogen peroxide; And In order to control the pressurized gas supplied from the pressurized gas storage tank 210 to a set pressure, a pressure regulator formed in a path in which the pressurized gas moves from the pressurized gas storage tank 210 to the hydrogen peroxide storage tank 110 ( 215); Hydrogen-oxygen binary propellant rocket engine comprising a. The method of claim 8, A first valve 221 formed in a path through which the hydrogen peroxide moves from the hydrogen peroxide storage tank 110 to the reactor 120 to control the amount of hydrogen peroxide supplied to the reactor 120; A second valve 222 formed in a path in which the water moves from the reactor 120 to the electrolysis device 130 to adjust the amount of water supplied to the electrolysis device 130; In order to control the amount of oxygen supplied to the oxygen storage tank 160, the oxygen is formed in the path to move from the reactor 120 and the hydrogen-oxygen separator 140 to the oxygen storage tank 160 Three valve 223; A fourth valve 224 is formed in the path of the hydrogen from the hydrogen-oxygen separator 140 to the hydrogen storage tank 150 to control the amount of hydrogen supplied to the hydrogen storage tank 150. ; A fifth valve 225 formed in a path through which the hydrogen moves from the hydrogen storage tank 150 to the rocket engine 170 to adjust the amount of hydrogen supplied to the rocket engine 170; A sixth valve 226 formed in a path in which the oxygen moves from the oxygen storage tank 160 to the rocket engine 170 to adjust the amount of oxygen supplied to the rocket engine 170; Hydrogen-oxygen binary propellant rocket engine comprising at least one selected from among the valve 220 and the valve driving device 230 for controlling the opening and closing of the valve 220. The method of claim 9, The path from which the water generated in the reactor 120 moves to the electrolysis device 130 includes a condenser 240 for converting gaseous water generated in the hydrogen peroxide decomposition reaction in the reactor 120 into a liquid state. Hydrogen-oxygen binary propellant rocket engine, characterized in that. (a) pressurizing the hydrogen peroxide in the hydrogen peroxide storage tank 110 at a pressure set using the pressure regulator 215 and injecting the hydrogen peroxide into the reactor 120; (b) hydrogen peroxide decomposition step of decomposing hydrogen peroxide into hydrogen and oxygen using a catalyst 121 in the reactor 120; (c) transferring the oxygen decomposed in step (b) to the oxygen storage tank 160 for storage and converting the gaseous water into liquid water in the condenser 240; (d) electrolyzing the water converted in step (c) into hydrogen and oxygen; (e) separating and collecting hydrogen and oxygen decomposed in the step (d) and storing the collected hydrogen by moving to the hydrogen storage tank 150 and storing the oxygen by moving to the oxygen storage tank 160; And (f) generating propulsion by burning hydrogen stored in the hydrogen storage tank 150 as a fuel using oxygen stored in the oxygen storage tank 160 as an oxidant; Propulsion method of a hydrogen-oxygen binary propellant rocket engine, characterized in that consisting of. The method of claim 11, Propulsion of hydrogen-oxygen binary propellant rocket engine, characterized in that to generate a propulsion force by igniting the rocket engine by injecting hydrogen to high temperature oxygen during the step (f).

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