KR20090073642A - Novel propulsion system combined with bipropellant rocket using hydrogen peroxide gas generator and operating method of the same - Google Patents

Abstract

A propulsion system combined with a bipropellant rocket using hydrogen peroxide gas generator and an operating method of the same are provided to progress as a ramjet gradually by initially forming combustion chamber environment in the ram combustion for thrust generation. A propulsion system combined with a bipropellant rocket using hydrogen peroxide gas generator comprises: a diffuser(160); a fuel injection nozzle(150); a combustion chamber; a control door(400) being equipped at the inlet of the diffuser and controlling air volume; a hydrogen peroxide gas generator(300) equipped at the front end of the combustion chamber; and a controller controlling the control door, a gas generator and a fuel injection nozzle. When the controller controls the control door and the hydrogen peroxide gas generator, inhaled air volume is gradually increased and the power of the hydrogen peroxide gas generator is gradually decreased.

Description

NOVEL PROPULSION SYSTEM COMBINED WITH BIPROPELLANT ROCKET USING HYDROGEN PEROXIDE GAS GENERATOR AND OPERATING METHOD OF THE SAME}

The present invention relates to a ramjet hybrid cycle propulsion system, and more specifically, by applying a binary propulsion rocket using a hydrogen peroxide gas generator to provide an initial thrust, a smooth propulsion transition is possible without an additional booster, and an environmentally friendly ramjet hybrid cycle propulsion system is provided. It is about.

Currently, developed countries in the aerospace industry, including the United States and Japan, are conducting national projects on new concept propulsion systems that can be used as propulsion engines for supersonic and hypersonic stratospheric aircraft. First, the background of this situation is the development of a supersonic transport vehicle to meet the rapidly increasing demand for air traffic in the world and the demand for development of a high-speed propulsion engine. In 2006, the United States and Japan announced plans to develop the next generation of supersonic airliners. The airliner will be able to travel from Tokyo to Los Angeles in half the current five hours. Japan's Aerospace Research and Development Agency (JAXA), Ishikawajima-Harima Heavy Industries and Kawasaki Heavy Industries will participate, and NASA and Boeing will participate in the United States. In addition to large passenger planes, the company is reviewing 8-12-seater supersonic business jets and small supersonic passenger jets targeting specific wealthy and business customers around the world. In Europe, development plans for subsequent models with better performance than Concord are being specified. In recent years, the development of next-generation high-speed aircraft for passenger transportation is becoming a reality.

Development background of new concept propulsion system Secondly, there is a need for a method to drastically improve the current satellite launching method. There are about 500 satellites currently flying over the Korean peninsula, of which about 400 satellites can be photographed or monitored. As the demand for military, meteorological and civilian satellites will increase rapidly, there is a growing demand for new, reusable propulsion engines with high stability and reliability at low cost and capable of transporting satellites to low-altitude orbits.

Third, the background of the development of a new concept propulsion system is because the need for a supersonic propulsion engine has recently emerged for military purposes. Countries, including the United States, are now planning "semi-orbital combat" as a preliminary phase of space warfare. The quasi-orbit is about 100 kilometers above the ground, just below the satellite's orbit. Although the airspace of a country is divided from the surface to the atmosphere, international customs do not include more than 80 to 100 kilometers above the ground. In fact, quasi-orbit is space that anyone can use like the universe. In other words, if you develop a vehicle that enters a quasi-orbit from its own airspace, flies into the airspace of an enemy at supersonic speeds, and reenters just above the enemy, it is possible to attack the enemy with the shortest route completely out of the controversy of invasion of other countries. In contrast to the attack satellites, in 2004, the Virgin Spacecraft One, a British space traveler, Spaceship One, succeeded in flying 111 km above the ground, quasi-orbital aircraft have already reached the stabilization and validation stage. Do it. Representative plans for the development of military quasi-orbital aircraft in this regard include the US Navy Space Command's Sustain Project and the US Air Force's Aurora Project. Sustain is a type of spacecraft that transports naval special forces through suborbits. It is designed as a combination of a 13 crew landing aircraft, the 'Hot Eagle' and a mother ship that will carry it out of the atmosphere, aiming for a prototype flight in 2025. . The Hot Eagles will be equipped with a scramjet engine capable of speeds up to Mach 10. Southeast Asia can be deployed in just a few minutes and arrive in less than two hours, even in the farthest countries.

On the other hand, the propulsion engine for a sonic or ultrasonic vehicle can be classified into an air intake type and a rocket and a combined cycle propulsion engine in the form of a mixture thereof, depending on the oxidant supply method. In terms of reusability, future propulsion engines are expected to be mainstream with air suction and combined cycles. Among them, ramjet engine is a representative air suction propulsion engine, which does not require oxidizing agent. It has been intensively researched in developed countries for its merits.

Ramjet propulsion engine adopts air suction method through ram compression effect and is a kind of air suction propulsion engine that does not need a separate compression device.

Figure 1 briefly shows a conventional ramjet propulsion engine. Turbojets use power from turbines to compress air into compressors, while ramjets compress air to air pressure (ram pressure) due to high speed flight. Therefore, the compressor and the turbine are unnecessary, and the structure is very simple. When a vehicle equipped with a ramjet propulsion engine flies at supersonic speed (M> 1), air enters the supersonic state at the ramjet inlet, and passes through a diffuser and drops to subsonic speed (M <1). At this time, the air pressure rises rapidly to obtain the same effect as the compressor of the turbojet. Fuel is injected into the high pressure air from the fuel injector, combustion occurs in the fuel chamber, and the high temperature and high pressure combustion gas is discharged at a supersonic speed through the nozzle. The driving force is generated by the reaction of the discharge gas.

However, the ramjet propulsion engine is not easy to be used despite various advantages. The main reason is that the ramjet engine operates at supersonic speed, which does not work at standstill and is less efficient at low speeds, and requires additional propulsion to provide initial thrust to reach the operating speed.

FIG. 2 illustrates an integrated rocket ramjet (IRR) as a representative embodiment among those implemented to provide initial thrust. IRR is divided into liquid-fueled IRR (LiRR) and solid-fueled IRR (SIRR), which are used for liquid fuel control. Figure 2 is a type of SIRR coupled to the rocket booster using a solid fuel in the combustion chamber 10. In the initial thrust providing step as shown in Figure 2 (a) by burning the fuel of the booster grain 20 in a state in which the inlet door 70 is closed to increase the speed by only the rocket booster. When the speed enters the supersonic speed and changes to an environment in which the ramjet can operate, the booster nozzle 30 is removed and the inlet port cover 40 is ruptured as shown in FIG. 2 (b), and then the inlet door 70 is opened. Proceed with the transition stage to receive air. When the ramjet fuel 60 is supplied as shown in FIG. 2 (c) and the combustion proceeds normally by mixing with the compressed air by the ram pressure, the ramjet propulsion step is completed.

The SIRR's combined cycle propulsion engine has the advantage that the rocket booster is coupled to the combustion chamber of the ramjet and has a simple structure and a higher non-thrust than the rocket. However, since the booster fuel and the liquid ramjet fuel are different from each other, there are differences in combustion characteristics. Due to mechanical difficulties such as removing the booster nozzle at the stage, there is a problem that it is difficult to smoothly transition the driving force.

In addition, the recent trend of space development and aircraft development can be defined as low cost / eco-friendly, which is due to the strengthened environmental standards, the use of propellants which are excellent in performance but toxic or harmful to the environment is gradually being restricted. As the cost of meeting existing environmental requirements is very high with the use of existing propellants, the development of propellants that have minimal impact on the surrounding environment is being actively developed. This eco-friendly propellant is called "green propellant". In addition, academic conferences are being actively held. Hydrazine is widely used as a single propulsion agent for thrusters for satellite or projectile attitude control. However, hydrazine has a high non-thrust, but hydrazine and exhaust gases are carcinogenic and toxic and thus difficult to handle, and thus have a high cost of handling and processing.

The present invention is to solve the above problems, it is possible to provide the initial thrust without difficulty, it is possible to provide a smooth propulsion transition without the need for an additional booster, to provide an environment-friendly ramjet composite cycle propulsion system.

In order to achieve the above object, the present invention provides a ramjet propulsion system including a diffuser 160, a fuel injector 150 and a combustion chamber 130, the ramjet propulsion system is provided at the inlet of the diffuser 160, suction Control door 400 for adjusting the amount of air that is; A hydrogen peroxide gas generator 300 provided at the front end of the combustion chamber 130; And a control unit (not shown) for controlling the control door 400, the gas generator 300, and the fuel injector 150. The ramjet propulsion system in which the binary propulsion rocket is coupled is provided.

The control unit (not shown) is characterized in that to control the control door 400 and the hydrogen peroxide gas generator 300, the power of the hydrogen peroxide gas generator 300 is gradually reduced as the amount of intake air is gradually increased. .

The control door 400 includes a plurality of blades 410, the blade 410 is rotatable by the rotation module 430 connected to the hinge shaft 420.

In addition, the hydrogen peroxide gas generator 300 includes a storage tank 310 for storing hydrogen peroxide; A spray nozzle 320 to droplet hydrogen peroxide supplied from the storage tank 310; Low temperature primary catalyst bed 330; High temperature secondary catalyst bed 340; And a reduction nozzle 350 in sequence.

Further, it is preferable that the first catalyst bed includes a platinum catalyst, and the second catalyst bed includes an LSC catalyst.

On the other hand, a portion of the outer portion of the diffuser 160 is formed by the primary rocket 200 including the cone portion 210, the rear end of the primary rocket 200 includes a recess 220, Hydrogen peroxide gas generator 300 is advantageously mounted to the recess 220.

In another aspect of the present invention, the present invention is a method for operating a ramjet propulsion system coupled to the binary propulsion rocket, the method after closing the control door 400, the hydrogen peroxide gas generator 300 An initial thrust providing step of preheating starting and driving the fuel in the rocket form by injecting fuel from the fuel injector 150; If it is confirmed that the ramjet operation is possible, gradually opening the control door 400, the transition step of gradually reducing the power of the hydrogen peroxide gas generator 300; Ramjet propulsion step to completely open the control door 400, the hydrogen peroxide gas generator 300; provides a method of operating a ramjet propulsion system comprising a.

With the development of a ramjet combined cycle propulsion system using a dual-propellant rocket including a hydrogen peroxide gas generator provided by the present invention, a smooth transition from an initial thrust providing step to a ramjet operation step is possible, an environmentally friendly flight is possible, and a relatively simple method. As a result, various transportation demands can be satisfied.

Specific embodiments of the present invention will be described in detail with reference to the accompanying drawings. Figure 3 is a perspective view of a combined cycle propulsion system applying the binary propulsion rocket of the present invention, Figure 4 is a schematic side cross-sectional view showing the operation of the combined cycle propulsion system of the present invention, Figure 5 is a schematic side cross-sectional view of the hydrogen peroxide gas generator of the present invention Indicates. On the other hand, Figure 6 shows a propulsion control flowchart of the combined cycle propulsion system of the present invention. Matters that are not required as a part that is not different from the prior art are excluded from the description, but the technical spirit and protection scope of the present invention are not limited thereto.

First, the dual cycle propulsion rocket-coupled combined cycle propulsion system using the hydrogen peroxide gas generator of the present invention will be described in detail with reference to FIGS. 3 and 4.

The combined cycle propulsion engine of the present invention is coupled to the primary rocket (200, primary rocket) in front of the body 100 to form a diffuser 160 through which air can pass between the body 100, the primary The rear end of the rocket 200 includes a hydrogen peroxide gas generator 300, and after the stop of the body 100 is configured by having a fuel injector 150. The nozzle 140 is coupled to the rear end of the body 100, maximizing the driving force by the combustion gas.

The body 100 is made of a substantially cylindrical rigid body, but need not be limited thereto, and may be optimized according to the shape of a main vehicle attached to a missile or a vehicle. A nose 110 is included at the front end of the body 100. The nose 110 forms an outer duct of the diffuser 160 and is optimized to minimize resistance due to aerodynamic force when the aircraft flies at supersonic speed. The nose 110 also serves as a support for the control door 400 to be described later. As described above, the front end of the fuselage 100 includes a primary rocket 200.

The primary rocket 200 is provided to have a cone portion 210 and a recess 220 having a pointed tip. The primary rocket 200 constitutes an air passage inlet of the diffuser 160 between the nose and the nose 110, and serves as a support of the control door 400. The recess 220 is equipped with a hydrogen peroxide gas generator 300, and is provided in an open form so that a discomposed jet 360 formed in the gas generator 300 may be discharged.

The fuel injector 150 is included in the rear of the air flow of the primary rocket 200. The fuel injector 150 is connected to the fuel tank 3 to inject fuel in the form of a spray. Fuel is kerosine and kerosene uses Jet A-1 aviation but is not limited to this. In FIG. 3, the fuel injector 150 may be provided to the upper and lower portions of the combustion chamber 130, but may be provided in three or more circumferences of the body 100. Naturally, the fuel injector 150 and the fuel tank 3 should include an apparatus (not shown) for adjusting fuel pressure which is well known in the art.

Meanwhile, as shown in FIG. 4, a mixing chamber 120 is included between the hydrogen peroxide gas generator 300 and the fuel injector 150. The mixing chamber 120 is an area in which the high-temperature, high-pressure air and the dissociation jet 360 of hydrogen peroxide introduced through the diffuser 160 in the ramjet operation step are smoothly mixed. When fuel is injected from the fuel injector 150 into the high-temperature, high-pressure air in which oxygen is concentrated and mixed, stable and normal combustion occurs in the combustion chamber 130, and combustion gas by combustion is discharged to the nozzle 140 to generate propulsion force. Let's do it.

The combined cycle propulsion system of the present invention is to adjust the amount of air sucked in accordance with the operating step. As shown in FIG. 3, a control door 400 is provided between the primary rocket 200 and the nose 110 of the fuselage 100 to adjust the amount of air introduced therein. The control door 400 is disposed at the inlet side of the diffuser 160 to enter the diffuser 160 to adjust the amount of air compressed by the ram pressure. For this purpose, the control door 400 includes a plurality of blades 410. The blade 410 may be adjusted from 0 degrees to 90 degrees by a rotating module (not shown) including a driving actuator (not shown) starting from a hinge axis (not shown). The rotary module (not shown) is suitably controlled by the entire control unit (not shown) of the propulsion system. When the angle of the blade 410 is 0 degrees, the amount of air sucked is maximized, and when the angle of the blade 410 is 90 degrees, the air is completely enclosed and the intake of air is minimized. In the present invention, although the shutter-type embodiment using the blade 410 is shown, the same object can be achieved by mobilizing various techniques known in the art. In Figure 4 it is shown to simplify the aerodynamic height instead of the blade 410 to help understand the technical configuration of the invention. FIG. 4 (a) illustrates the case where the control door 400 is completely closed, FIG. 4 (b) illustrates the case where the control door 400 is fully opened, and FIG.

Next, the hydrogen peroxide gas generator 300 of the present invention will be described in detail with reference to FIGS. 4 and 5.

Hydrogen peroxide can be stored at room temperature, making it easy to handle, non-toxic, decomposed into water and oxygen when in contact with a catalyst, and the simple and eco-friendly thruster for satellite attitude control, RCS (reaction control system), turbo It is widely used in many fields such as a gas generator for driving a pump. However, due to the disadvantage that the non-thrust is slightly lower than the conventional propellant, such as hydrazine, it has not attracted attention for a while, and as the most suitable propellant for the recent space development trend, various advantages have been highlighted and attracted attention again in the space field. In addition, hydrogen peroxide is the most environmentally friendly propellant that meets the 80/20 law (80% performance at 20% cost of existing fuel), which is required by the US Air Force.

Hydrogen peroxide is a chemical formula H ₂ O ₂ with one more oxygen atom than water. It is a colorless and odorless liquid that is extremely soluble in water. When it comes into contact with a catalyst, it causes chemical reactions as below and produces hot gases. Hydrogen peroxide reacts as follows.

2H ₂ O ₂ (l) → 2H ₂ O (g) + O ₂ (g) + Heat

  100% hydrogen peroxide is an exothermic reaction with 2884.47kJ / kg of heat, and below 67%, the generated heat is absorbed by the latent heat of water in which hydrogen peroxide is dissolved, so the temperature does not rise above the boiling point of hydrogen peroxide. Therefore, more than 70% of the concentration is used as a propellant, and more than 85% of hydrogen peroxide is called Rocket grade peroxide. 100% of hydrogen peroxide has a non-thrust of about 163 sec when used as a single propulsion agent and a maximum of 335 sec when using kerosene as fuel. The advantages of hydrogen peroxide as a propellant are:

(1) has a very high density; 100% of hydrogen peroxide has a specific gravity of 1.45, which is about 23% greater than that of liquid oxygen and about 44% greater than 1.01 hydrazine. Therefore, the size and weight of the propellant tank can be reduced, and the 90% hydrogen peroxide system has a density specific impulse of about 6% higher than the hydrazine system under the same conditions. High density non-thrust compensates for the low non-thrust, a disadvantage of hydrogen peroxide. High density ratio thrust can reduce the volume of the projectile / satellite, thereby reducing the weight and aerodynamic drag of the system and consequently mitigating system design constraints.

(2) excellent storage; Hydrogen peroxide maintains its liquid state at room temperature and can be stored for a long time in a suitable container, so there is no need to insulate storage tanks, pipes, etc. like liquid oxygen. It was applied to Syncom II, III of the earth's first geostationary satellite and used for 3 ~ 5 years. It showed 0.4% concentration drop for 17 years under Texas climate condition of USA and little change in 5 ℃ storage.

(3) no toxicity; Unlike most hypotonic propellants, such as those that cause cancer, hydrogen peroxide is naturally broken down and produced in the human respiratory tract. 3% hydrogen peroxide is used as a disinfectant, so it does not harm the human body. Due to the very low vapor pressure, it is difficult to generate steam at room temperature and only needs to be well ventilated. Since the material produced after the catalytic reaction is also non-toxic as water and oxygen, the effect on the surrounding environment is very small. Because of its no toxicity, no special equipment is required for handling and no special equipment is needed to deal with the combustion products.

(4) does not react with the atmosphere; Hydrogen peroxide does not react chemically with any component of the atmosphere, so even if air is introduced into a thruster using hydrogen peroxide, there is no particular problem. Hydrazine, on the other hand, reacts with carbon dioxide to produce compounds, so special care must be taken to prevent air from entering the hydrazine system.

(5) has a high mixing ratio; When hydrogen peroxide is used as an oxidant, it has a relatively high mixing ratio for the same fuel compared to other oxidizing agents (about 8 mixing ratio when 85% concentration is applied to kerosine). And consequently reduces the weight of the storage tank.

(6) low evaporation pressure; Since hydrogen peroxide has a much lower evaporation pressure than liquid oxygen, when applied to a propulsion system with a turbopump, the inlet pressure may be low, thereby reducing the weight of the propellant tank.

(7) has a high specific heat; Hydrogen peroxide has a specific heat (0.6 cal / g ° C at 100% concentration) that is comparable to water, making the system very simple when used for regenerative cooling of liquid rockets.

Recognizing the eco-friendliness of hydrogen peroxide as described above, the present invention has been devised an invention that constitutes a binary propellant rocket using hydrogen peroxide and combined with a ramjet propulsion system. The hydrogen peroxide gas generator 300 of the present invention is mounted in a recess 220 provided at the rear end of the primary rocket 200 to make the hydrogen peroxide haze jet 360. The gas generator 300 includes a storage tank 310 of hydrogen peroxide.

5 shows a gas generator 300 of the present invention. The high concentration of hydrogen peroxide stored in the storage tank 310 is introduced into the spray nozzle 320 through a known pressure regulator (not shown). The spray nozzle 320 droplets hydrogen peroxide, and when the hydrogen peroxide in the droplet state enters the primary catalyst bed 330 of the gas generator 300, it is decomposed into gaseous oxygen and water while contacting the active material of the catalyst. The heat generated during decomposition decomposes water vapor again and the undecomposed hydrogen peroxide heats up in a gaseous state. The heated gaseous products pass through the secondary catalyst bed 340 to increase the temperature of the catalyst and at the same time the undecomposed hydrogen peroxide gases come into contact with the active material, resulting in vigorous catalytic cracking and some of which are decomposed by heat. . The velocity of the product gas is rapidly increased by the reduction nozzle 350 before being discharged, and eventually, the released hydrogen peroxide is discharged into the mixing chamber 120 of the body 100 in the form of a jet 360.

In the present invention, as the primary catalyst bed 330, a hydrogen peroxide is vaporized using a platinum catalyst having excellent low temperature startability, and an LSC catalyst having excellent stability at high temperature is disposed in the secondary catalyst bed 340 to provide a catalyst at high temperature. And pyrolysis. This enables non-preheating start, stable life and withstands catalytic decomposition temperatures of high concentrations of hydrogen peroxide.

Next, the operation and advantages of the combined cycle propulsion system of the present invention will be described with reference to FIGS. 4 and 6. First, in the initial thrust providing step, the control door 400 of the diffuser 160 is closed (S100). In the closed state, the hydrogen peroxide gas generator 300 is preheated and started, a high concentration dissociation jet 360 is generated, and the fuel kerosene is injected from the fuel injector 150 to be ignited (S100). Oxygen generated by the gas generator 300 may maintain a temperature capable of spontaneous combustion without the need for another ignition device even though passing through the reduction nozzle 350 at a high temperature and high pressure of about 700 degrees. The combustion gas of high temperature and high pressure, which is combusted and discharged through the nozzle 140, provides initial thrust to the body 100. This initial thrust providing step proceeds until the fuselage 100 reaches the supersonic speed (M> 1) is possible ram propulsion (S200).

When the fuselage 100 enters the ramjet operation speed, the transition of thrust proceeds as shown in FIG. 4 (b). While the control door 400 of the diffuser 160 is gradually opened, air is introduced into the diffuser 160 and air compressed by the ram pressure is supplied to the mixing chamber 120 (S300). As the amount of air supplied to the mixing chamber 120 increases, the amount of hydrogen peroxide supplied to the hydrogen peroxide gas generator 300 is gradually reduced to reduce the size of the dissociation jet 360 (S300). Even if the strength of the dissociation jet 360 decreases, since the high temperature and high pressure air is properly supplied from the diffuser 160 by the ram pressure, the combustion phenomenon does not rapidly change or change abnormally. In other words, by forming the combustion chamber environment at the time of ram combustion for the generation of thrust has the advantage that it is possible to proceed gradually to the ramjet without significant change in the existing flow of the ramjet. In addition, as in the conventional SIRR, since the combustion characteristics do not suddenly change greatly from the fuel of the rocket to the fuel of the ramjet, smooth propulsion is possible. In addition, since external force such as removing the nozzle of the rocket booster does not work, a more secure transition is possible.

When the control door 400 is completely opened (S400) and the generation of hydrogen peroxide from the hydrogen peroxide gas generator 300 stops completely, the transition step ends and the ramjet propulsion step as shown in FIG. 4 (c) is entered (S500). Ramjet propulsion has higher non-thrust than rockets, low-altitude high-speed flight, and applied to military weapons, showing excellent penetration and survivability.

The combined cycle propulsion system combined with the dual-propellant rocket according to the present invention may be mounted on a commercial airplane to enable efficient high-speed flight, and may be applied to a weapon system or the like, so that industrial application is sufficient.

1 is a side schematic cross-sectional view of a conventional ramjet propulsion engine

Figure 2 is a schematic cross-sectional view of the ramjet propulsion engine of the IRR combined with the rocket booster

3 is a perspective view of a combined cycle propulsion system to which the dual-propellant rocket of the present invention is applied.

4 is a schematic side cross-sectional view showing operation of the combined cycle propulsion system of the present invention.

5 is a schematic side cross-sectional view of a hydrogen peroxide gas generator of the present invention.

6 is a flow chart of the propulsion control of the combined cycle propulsion system of the present invention

** Description of the symbols for the main parts of the drawings **

1: engine

3: fuel tank 100: fuselage

110: nose 130: combustion chamber

140: nozzle 150: fuel injection

200: primary rocket 300: gas generator

330: first catalyst bed 340: second catalyst bed

400: control door 410: blade

Claims (7)

In a ramjet propulsion system comprising a diffuser 160, a fuel injector 150, and a combustion chamber 130, the ramjet propulsion system is A control door 400 provided at an inlet of the diffuser 160 to adjust an amount of air sucked in; A hydrogen peroxide gas generator 300 provided at the front end of the combustion chamber 130; And And a control unit (not shown) for controlling the control door (400), the gas generator (300), and the fuel injector (150). The method of claim 1, The control unit (not shown) is characterized in that in controlling the control door 400 and the hydrogen peroxide gas generator 300, the power of the hydrogen peroxide gas generator 300 is gradually reduced as the amount of intake air is gradually increased. Ramjet propulsion system combined with binary propulsion rocket. The method of claim 1, The control door 400 includes a plurality of blades 410, the blade 410 is a binary propellant rocket, characterized in that rotatable by a rotating module (not shown) connected to a hinge axis (not shown) Combined Ramjet Propulsion System. The method of claim 1, The hydrogen peroxide gas generator 300 includes a storage tank 310 for storing hydrogen peroxide; A spray nozzle 320 to droplet hydrogen peroxide supplied from the storage tank 310; Low temperature primary catalyst bed 330; High temperature secondary catalyst bed 340; And Ramjet propulsion system coupled to the binary propulsion rocket characterized in that it comprises a reduction nozzle 350 in sequence. The method of claim 4, wherein The first catalyst bed includes a platinum catalyst, the second catalyst bed is a ramjet propulsion system combined with a binary propulsion rocket, characterized in that the LSC catalyst. The method according to any one of claims 1 to 5, A portion of the outer portion of the diffuser 160 is formed by the primary rocket 200 including the cone portion 210, the rear end of the primary rocket 200 includes a recess 220, the hydrogen peroxide gas Generator 300 is a ramjet propulsion system coupled to the binary propulsion rocket, characterized in that mounted to the recess (220). A method of driving a ramjet propulsion system incorporating a binary propulsion rocket according to any one of claims 1 to 5, After closing the control door 400, the pre-heating start of the hydrogen peroxide gas generator 300, an initial thrust providing step of injecting fuel from the fuel injector 150 to operate in the form of a rocket; If it is confirmed that the ramjet operation is possible, gradually opening the control door 400, the transition step of gradually reducing the power of the hydrogen peroxide gas generator 300; Ramjet propulsion step of completely opening the control door (400), off the hydrogen peroxide gas generator (300); operating method of a ramjet propulsion system comprising a.

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