KR101763491B1

KR101763491B1 - Injector for the extention of the catalyst life of the monopropellant thrusters and the monopropellant thrusters

Info

Publication number: KR101763491B1
Application number: KR1020150180280A
Authority: KR
Inventors: 원수희; 김수겸; 전형열
Original assignee: 한국항공우주연구원
Priority date: 2015-12-16
Filing date: 2015-12-16
Publication date: 2017-08-01
Also published as: KR20170071987A

Abstract

[0001] The present invention relates to an injector and a single propellant thruster for prolonging the catalyst life of a single propellant thruster, and more particularly, to a fuel injector and a single propellant thruster which are provided with a sub- To an injector and a single propellant thruster for extending the service life of a single propellant thruster capable of minimizing the load or mechanical impact of the catalyst by enlarging the contact area.

Description

Technical Field [0001] The present invention relates to an injector and a single propellant thruster for extending the catalyst life of a single propellant thruster,

A rocket engine used to launch projectile from ground to high or space requires very strong thrust.

A typical rocket engine consists of a combustion chamber that burns a chemical propellant and a nozzle that accelerates the gas produced in the combustion chamber to provide directionality. When the mass of the propellant is accelerated from the nozzle for a unit of time, The principle of flying will be used. In other words, the gas produced by burning the propellant in the combustion chamber is directed to the nozzle, and the thrust is generated in the opposite direction, so that the air can fly in the space without the atmosphere.

Rocket powered aircraft can be broadly divided into military aircraft, such as ballistic missiles, and space flight aircraft, which are used to launch satellites. The production and operation of such a rocket-powered aircraft is considerably expensive, and thus various propellants and thrusters have been continuously studied to reduce the energy loss in the rocket engine and obtain a stronger thrust.

It is a single propellant or binary propellant rocket engine that generates a large amount of energy in a short time and a large thrust can be obtained by chemical reaction using a liquid propellant. Among them, the single propellant thruster uses one kind of propellant, and the high temperature high pressure product generated through the catalytic reaction is injected to the outside through the nozzle, and the driving force is obtained in the opposite direction of the nozzle injection by the action / reaction principle. Such an engine is an essential element in space development, and it is almost impossible to transfer technology from technologically advanced countries because it is deeply related to defense such as satellite or launch vehicle attitude control and missile. Currently, many studies are under way to secure such rocket technology in many countries, and it is essential to develop original technology through independent development.

11 is a diagram showing the structure of a conventional hydrazine single propellant thruster.

Referring to FIG. 11, in the conventional hydrazine single propellant thruster, the catalyst bed is filled with an alumina-based iridium catalyst, and hydrazine, which is a fuel, is injected into the catalyst bed and the high temperature / high pressure gas is injected into the nozzle by the catalytic / In this case, the high injection pressure of the hydrazine injected by the catalyst and the long-term use cause the charged catalyst to be consumed, thereby generating a void space in the front region of the catalyst. As a result, There is a problem that the life of the thruster is rapidly reduced.

Further, in the case of the conventional showerhead injector, since the contact surface is flat, the load placed on the catalyst disposed on the rear surface of the catalyst is further increased, and the catalyst life is shortened due to mechanical impact.

Korean Patent No. 10-1183453 (September 18, 2012)

SUMMARY OF THE INVENTION Accordingly, the present invention has been made keeping in mind the above problems occurring in the prior art, and it is an object of the present invention to provide a sub-nozzle body inserted into a catalyst bed, Type impeller for prolonging the catalyst life of a single propellant thruster capable of minimizing the load or mechanical impact of the catalyst.

In order to achieve the above object, the present invention relates to an insertion type injector for extending the service life of a single propellant thruster according to the present invention, the insertion type injector having a rear end connected to a fuel supply pipe and a front end inserted into a catalyst bed filled with a plurality of catalysts A main nozzle body having a plurality of distribution passages through which fuel flows, the passive holes being formed at a front end of the distribution passages; And a sub nozzle body which has a rear end coupled to each of the distribution channels of the main nozzle body and a front end inserted into the catalyst base to supply fuel supplied from the distribution channel into the catalyst bed, Wherein the sub-nozzle body is provided at a front end thereof to inject fuel, and a spraying portion which is disposed at a downstream end of the sub-nozzle body so as to be detachably attached to the coupling hole portion, A first sub-nozzle body having a fastening protrusion, And a second sub nozzle body having an extension part between the jet part and the fastening protrusion part, the first sub nozzle body and the second sub nozzle body having different lengths and being detachably coupled to the main nozzle body, The plurality of injection portions can be inserted into the catalyst bed through the nozzle body differently from each other.

In addition, the ejecting portion is composed of a cylindrical first screen having front and rear ends opened, and a hemispherical second screen disposed at the front end of the first screen, wherein the first and second screens are configured to have a mesh structure .

In addition, the first and second screens are characterized by a plurality of overlapping structures.

In addition, the central portion of the second screen is provided with a blocking portion so that fuel injected from the distribution passage can not be transmitted.

Further, the second screen may have a denser or denser structure than the first screen so that the fuel permeability is lower than that of the first screen.

In addition, the injection unit has a sub-flow path communicating with the distribution flow path and a plurality of fine holes branched from the sub flow path.

In addition, the jetting portion may have a cylindrical shape, and the fine holes may be formed through the side surface of the sub-nozzle body.

Further, the fine holes are characterized by a forward tilted structure.

Further, the jetting portion is characterized by an empty sphere or an oval inside.

The injection part is characterized by being made of a porous material.

In addition, the jetting section is characterized by comprising a carrier of a net structure and a porous material contained in the carrier.

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Meanwhile, the single propellant thruster according to the present invention comprises: a casing having an inner hollow cylindrical shape; A catalyst bed disposed in the casing and filled with a plurality of catalysts to catalyze the supplied fuel; A nozzle disposed at a front end of the catalyst bed and injecting a product obtained by catalytic reaction in the catalyst bed to the outside; A main nozzle body disposed at a rear end of the catalyst bed and provided with a plurality of distribution channels through which fuel flows; And a sub nozzle body which is connected to each of the distribution channels of the main nozzle body and whose front end is inserted into the catalyst base and supplies the fuel supplied from the distribution channel into the catalyst bed, The catalyst is supplied to the catalyst in a state in which the contact area between the fuel and the catalyst is increased and the injection pressure is reduced.

In the injector-type injector and the single propellant thruster for extending the catalyst life of the single-propellant thruster according to the present invention having the above-described structure, the sub-nozzle body inserted into the catalyst bed is provided so that fuel is not directly injected into only one side of the catalyst bed, The contact area can be enlarged to minimize the load or mechanical impact of the catalyst.

1 is a schematic view showing a state in which a sprayer for protecting a catalyst is installed in a single propellant thruster according to the present invention.
2 is a schematic diagram showing a single propellant thruster of a structure different from that of FIG.
3 is a perspective view showing a configuration of the insertion type injector of the present invention.
Fig. 4 is a front view showing the configuration of the insertion type injector having a structure different from that of Fig. 3
Fig. 5 is a cross-sectional view showing a double-screened screen in Fig. 4
FIG. 6 is a perspective view showing a state in which a sub-nozzle body having fine holes is fastened to a main nozzle body, corresponding to FIG. 3. FIG.
7 is a cross-sectional view showing the sub-nozzle body of Fig.
8 is a sectional view showing a sub nozzle body of the present invention in a spherical shape.
9 is a cross-sectional view showing a sub-nozzle body of the present invention as a porous material.
10 is a photograph of the porous material of the present invention.
11 is a view showing the structure of a conventional hydrazine single propellant thruster.

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

In the description of the present invention, the same or similar elements are denoted by the same or similar reference numerals, and a detailed description thereof will be omitted.

FIG. 1 is a schematic view showing a state in which a sprayer for protecting a catalyst is installed in a single propellant thruster according to the present invention, and FIG. 2 is a schematic view showing a single propellant thruster having a structure different from that of FIG. And Fig. 3 is a perspective view showing a configuration of the insertion type injector of the present invention.

1 to 3, a single propellant thruster 100 according to the present invention mainly includes a casing 101, a catalyst bed 105, a nozzle 103, and an injector 109. The injector 109 includes a main nozzle body 110 and a sub nozzle body 130. The injector 109 has a contact area between the fuel injected through the sub nozzle body 130 and the catalyst 106, And is supplied as a catalyst in a state where the pressure is reduced, thereby prolonging the service life of the catalyst.

The casing 101 may have a hollow cylindrical shape. The connection body 107 connected to the fuel supply pipe 108 is inserted into the rear end of the casing 101, and the nozzle 103 is disposed at the front end thereof.

The catalyst bed 105 can catalyze the supplied fuel, wherein the fuel can be hydrazine (N ₂ H ₂ ), and the catalyst 106 can be an alumina support-based iridium catalyst .

The main nozzle body 110 is disposed at a rear end of the catalyst bed 105, and has a plurality of distribution channels 111 through which fuel flows.

The rear end of the sub nozzle body 130 is coupled to each of the distribution channels 111 of the main nozzle body 110. The front end of the sub nozzle body 130 is inserted into the catalyst support 105, Into the catalyst bed (105).

In the present invention, the sub-nozzle body 130 is inserted into the catalyst bed 105 as a main technical feature.

In the case of the conventional showerhead injector, since high-pressure fuel is continuously injected as the catalyst, the catalyst directly contacting the injected fuel has a problem that the catalyst life is shortened due to mechanical impact or the like. Further, while the contact surface of the injected fuel is a planar contact type localized at the rear end of the catalyst bed, in the present invention, since the sub nozzle body is inserted into the catalyst bed and the fuel is injected into more catalysts in a three-dimensional contact manner, Thereby improving the catalytic reaction and reducing the injection pressure, thereby prolonging the catalyst life.

The sub nozzle body 130 may be in contact with the main nozzle body 110 through welding as shown in FIG.

As shown in FIGS. 2 and 3, the sub-nozzle bodies 130 and 130 'may be coupled to each other through a screw connection. For this purpose, a fastening hole 113 is formed at the front end of the distribution passage 111 And a fastening protrusion 139 for screwing into the fastening hole portion 113 is formed at a rear end of the sub-nozzle body 130, 130 '.
2, the sub-nozzle body 130, 130 'includes a jet portion 130a for injecting fuel, a first sub-nozzle body 130 composed of the fastening protrusion 139, And a second sub nozzle body 130 'in which an extension part 130b is formed between the jet part 130a and the fastening protrusion 139. [

3, the spray portion 130a of the sub nozzle body 130 may be a screen having a net structure. Specifically, the spray portion 130a may include a cylindrical first screen 131 having front and rear open ends, And a second hemispherical screen 133 disposed at the front end of the first screen 131.

3 is a front view showing the structure of the injector of FIG. 3. Referring to FIG. 4, a central region of the second screen 133 of the sub-nozzle body 130 is provided with a fuel injected from the distribution passage 111 The blocking portion 135 may be formed to have a closed structure. By forming the blocking portion 135, the fuel injected from the distribution passage 111 can directly reach the blocking portion 135 without contacting the catalyst, and the fuel injection pressure can be lowered.

FIG. 5 is a cross-sectional view showing a screen of a double net structure in FIG. 4. Referring to FIG. 5, the jetting unit 130a includes a plurality of first screens 131 and a plurality of first screens 131, Two screens 133 may be stacked so as to overlap with each other, or may have a structure in which only one screen is stacked.

FIG. 6 is a perspective view showing a state in which a sub-nozzle body formed with fine holes is fastened to the main nozzle body, corresponding to FIG. 3, and FIG. 7 is a sectional view showing the sub-nozzle body of FIG. FIG. 9 is a cross-sectional view showing the sub-nozzle body of the present invention as a porous material, FIG. 10 is a cross-sectional view illustrating the sub- It's a picture.

6 and 7, the jetting part 130a of the present invention has a cylindrical shape and includes a sub-channel 136 communicating with the distribution channel 111, A plurality of fine holes 137 may be formed.

In addition, the fine holes 137 may be formed through the side surface and the front surface of the sub nozzle body 130, and the fine holes 137 may be inclined forward.

Referring to FIG. 8, the jetting part 130a of the present invention may have a structure in which the interior of the jetting part 130a has an empty sphere and a plurality of fine holes 137 are formed.

9 and 10, the jetting part 130a of the present invention may include a carrier 138 having a net structure and a porous material 138a accommodated in the carrier 138.

The carrier 138 may be made of a synthetic resin net, or may be made of a wire mesh or the like.

As shown in FIG. 10, the porous material 138a may be a foamed metal having a three-dimensional network structure. The porous metal is a porous metal material having a cubic network structure and a remarkably large porosity. The porous metal material may be copper, aluminum, stainless steel , Nickel, titanium, or alloys thereof may be added to the molten metal.

While the present invention has been particularly shown and described with reference to exemplary embodiments thereof, it is to be understood that the invention is not limited to the disclosed embodiments, but, on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the invention. Therefore, it is to be understood that the present invention is not limited to the above-described embodiments. Accordingly, the true scope of the present invention should be determined by the technical idea of the appended claims. It is also to be understood that the invention includes all modifications, equivalents, and alternatives falling within the spirit and scope of the invention as defined by the appended claims.

100: single propellant thruster 101: casing
103: nozzle 105: catalyst bed
106: catalyst 107: connecting body
108: fuel supply pipe 109: injector
110: Main nozzle body 111: Dispensing channel
113: fastening hole part 130: sub nozzle body
131: first screen 133: second screen
135: breaking portion 136:
137: fine hole 138: carrier
138a: porous material 139: fastening protrusion

Claims

Wherein the rear end is communicated with a fuel supply pipe and the front end is inserted into a catalyst bed filled with a plurality of catalysts,
A main nozzle body having a plurality of distribution passages through which fuel flows, the passive holes being formed at a front end of the distribution passages;
And a sub nozzle body coupled to each of the distribution channels of the main nozzle body and having a front end inserted into the catalyst base and supplying the fuel supplied from the distribution channel into the catalyst base,
Wherein the catalyst is supplied in a state in which the contact area between the fuel injected through the sub nozzle body and the catalyst is increased and the injection pressure is reduced,
A sub nozzle body disposed at a front end of the nozzle body and configured to inject a fuel; and a fastening protrusion disposed at a rear end of the sub nozzle body and detachably coupled to the fastening hole; And a second sub-nozzle body having an extension portion between the jetting portion and the fastening protrusion,
The first sub-nozzle body and the second sub-nozzle body, which are made of different lengths and are detachably coupled to the main nozzle body, are capable of differently inserting a plurality of injecting portions into the catalyst bed in different distances Wherein the single injector thruster has an injector for extending the catalyst life of the single propellant thruster.

The method according to claim 1,
Wherein the injection unit comprises a cylindrical first screen having front and rear ends opened and a hemispherical second screen disposed at a front end of the first screen, wherein the first and second screens are mesh structures Wherein the single injector thruster has an injector for extending the catalyst life of the single propellant thruster.

3. The method of claim 2,
Wherein the first and second screens have a structure in which a plurality of the first and second screens are overlapped.

3. The method of claim 2,
Wherein the central portion of the second screen is provided with a blocking portion to prevent fuel injected from the distribution passage from permeating.

3. The method of claim 2,
Wherein the second screen is denser or denser than the first screen so that fuel permeability of the second screen is lower than that of the first screen.

The method according to claim 1,
Wherein the injector has a sub-passage communicated with the distribution passage and a plurality of fine holes branched from the sub-passage.

The method according to claim 6,
Wherein the injection part is cylindrical and the fine holes are formed to be sideways. The injector for extending the life of a single propellant thruster.

8. The method of claim 7,
Wherein the fine hole is a forwardly inclined structure. &Lt; RTI ID = 0.0 > 20. < / RTI >

The method according to claim 6,
Wherein the injector is hollow spherical or elliptical in shape. The injector for extending the life of a single propellant thruster.

The method according to claim 1,
Wherein the injector is made of a porous material. The injector for extending the life of a single propellant thruster.

The method according to claim 1,
Wherein the injector is made of a carrier having a net structure and a porous material contained in the carrier, wherein the injector is for extending the catalyst life of the single propellant thruster.

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A casing having an inner hollow cylindrical shape;
A catalyst bed disposed in the casing and filled with a plurality of catalysts to catalyze the supplied fuel;
A nozzle disposed at a front end of the catalyst bed and injecting a product obtained by catalytic reaction in the catalyst bed to the outside;
A main nozzle body disposed at a rear end of the catalyst bed and provided with a plurality of distribution channels for moving fuel therein, and a coupling hole formed at a front end of the distribution channel;
And a sub nozzle body which has a rear end coupled to each of the distribution channels of the main nozzle body and a front end inserted into the catalyst base to supply fuel supplied from the distribution channel into the catalyst base,
Wherein the catalyst is supplied in a state in which the contact area between the fuel injected through the sub nozzle body and the catalyst is increased and the injection pressure is reduced,
A sub nozzle body disposed at a front end of the nozzle body and configured to inject a fuel; and a fastening protrusion disposed at a rear end of the sub nozzle body and detachably coupled to the fastening hole; And a second sub-nozzle body having an extension portion between the jetting portion and the fastening protrusion,
The first sub-nozzle body and the second sub-nozzle body, which are made of different lengths and are detachably coupled to the main nozzle body, are capable of differently inserting a plurality of injecting portions into the catalyst bed in different distances Wherein the thruster is a single propellant.