KR20160073476A - Injector for the protection of the catalyst of the monopropellant thrusters and the monopropellant thrusters - Google Patents

Injector for the protection of the catalyst of the monopropellant thrusters and the monopropellant thrusters Download PDF

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Publication number
KR20160073476A
KR20160073476A KR1020140181569A KR20140181569A KR20160073476A KR 20160073476 A KR20160073476 A KR 20160073476A KR 1020140181569 A KR1020140181569 A KR 1020140181569A KR 20140181569 A KR20140181569 A KR 20140181569A KR 20160073476 A KR20160073476 A KR 20160073476A
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KR
South Korea
Prior art keywords
fuel
catalyst
fuel supply
casing
supply pipe
Prior art date
Application number
KR1020140181569A
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Korean (ko)
Inventor
원수희
김수겸
전형열
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한국항공우주연구원
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Priority to KR1020140181569A priority Critical patent/KR20160073476A/en
Publication of KR20160073476A publication Critical patent/KR20160073476A/en

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
    • F02M63/00—Other fuel-injection apparatus having pertinent characteristics not provided for in groups F02M39/00 - F02M57/00 or F02M67/00; Details, component parts, or accessories of fuel-injection apparatus, not provided for in, or of interest apart from, the apparatus of groups F02M39/00 - F02M61/00 or F02M67/00; Combination of fuel pump with other devices, e.g. lubricating oil pump
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S60/00—Power plants
    • Y10S60/915—Collection of goddard patents

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Catalysts (AREA)

Abstract

The present invention relates to an injector for protecting a catalyst of a monopropellant thruster and a monopropellant thruster and, more specifically, relates to an injector for protecting a catalyst of a monopropellant thruster and a monopropellant thruster, which can extend a life of a catalyst by reducing a mechanical shock applied to the catalyst when injecting fuel and improve stability of catalyst reaction, by installing a screen in a fuel injection nozzle to be overlapped, installing a partition wall wherein an internal hole is provided, or installing a dispersion body to reduce injection pressure and increase an injection area.

Description

Technical Field The present invention relates to an injector and a single propellant thruster for protecting the catalyst of a single propellant thruster,

The present invention relates to an injector and a single propellant thruster for protecting the catalyst of a single propellant thruster, and more particularly, to a propellant thruster for a single propellant thruster, in which a screen is installed in a fuel injection nozzle in an overlapping manner, a partition wall provided with an internal hole, A propellant and a single propellant thruster for protecting the catalyst of a single propellant thruster which can improve the stability of the catalytic reaction and extend the life of the catalyst by reducing the mechanical impact applied to the catalyst during the fuel injection by lowering the injection pressure and increasing the injection area .

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.

9 is a view showing a structure of a conventional hydrazine single propellant thruster.

Referring to FIG. 9, 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 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.

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 fuel injection nozzle, And to provide a single propellant thruster for protecting the catalyst of a single propellant thruster capable of reducing the mechanical impact applied to the catalyst during fuel injection so as to prolong the life of the catalyst and improve the stability of the catalytic reaction .

In order to achieve the above object, the injector for protecting the catalyst of the single propellant thruster according to the present invention comprises a fuel supply pipe and a fuel injection nozzle installed at one end of the fuel supply pipe, and the fuel injection nozzle is provided at a first end A cylindrical casing for receiving the fuel through the fuel supply port and injecting the fuel through the second end; And a screen configured to partition the interior of the casing and allow fuel to pass therethrough, wherein the fuel injected through the fuel supply pipe is injected with the injection pressure reduced by the screen.

Further, the screen of the injector for protecting the catalyst of the single propellant thruster according to the present invention is characterized by having a structure in which a plurality of net members are overlapped.

Further, the casing of the injector for protecting the catalyst of the single propellant thruster according to the present invention is configured to have a larger diameter than the diameter of the fuel supply pipe.

Further, the injector for protecting the catalyst of the single propellant thruster according to the present invention includes a fuel supply pipe and a fuel injection nozzle provided at one end of the fuel supply pipe, and the fuel injection nozzle has a fuel supply port provided at the first end A cylindrical casing that receives fuel through the first end and injects fuel through the second end; A partition wall partitioning the inside of the casing and having a plurality of internal holes; Wherein the fuel injected through the fuel supply pipe is injected in a state in which the injection pressure is reduced while the fuel passes sequentially through the inner hole and the injection hole, .

In addition, a plurality of partitions of the injector for protecting the catalyst of the single propellant thruster according to the present invention are installed apart from each other.

The plurality of internal holes may be formed at a central portion of the partition wall of the injector for protecting the catalyst of the single propellant thruster according to the present invention, and the injection holes may be formed to have a larger area than the internal holes.

Further, the injector for protecting the catalyst of the single propellant thruster according to the present invention includes a fuel supply pipe and a fuel injection nozzle provided at one end of the fuel supply pipe, and the fuel injection nozzle has a fuel supply port provided at the first end A cylindrical casing that receives fuel through the first end and injects fuel through the second end; And a dispersion member installed in the casing and disposed at a position corresponding to the fuel supply port so that the fuel injected through the fuel supply port collides with and disperses.

In addition, the dispersing body of the injector for protecting the catalyst of the single propellant thruster according to the present invention is characterized in that the front end portion thereof is formed in a streamlined shape and is fixed to the casing by a support.

The single propellant thruster according to the present invention further comprises a tube provided with a fuel injection nozzle for supplying fuel, a catalyst bed for catalytically reacting the fuel supplied from the fuel injection nozzle, The fuel injection nozzle includes a fuel injection nozzle for injecting fuel through a fuel supply port provided at a first end of the fuel injection nozzle and a fuel injection nozzle for injecting fuel through a second end of the fuel injection nozzle, A casing; A fuel supply port provided at the first end; And a screen having a structure in which an interior of the casing is partitioned and a plurality of mesh members are stacked, the catalyst unit comprising: a first catalyst unit disposed in front of the catalyst unit; And a second catalyst part disposed behind the first catalyst part, wherein the first catalyst part comprises a first support made of a foamed metal of a steric network structure and a first catalyst attached to the first support, Wherein the second catalyst portion comprises a plurality of second support bodies in the form of beads and a second catalyst attached to the second support body, wherein the fuel injected through the fuel supply pipe And is injected into the first catalytic portion.

According to the injector and the single propellant thruster for protecting the catalyst of the single propellant thruster according to the present invention having the above-described structure, it is possible to provide the fuel injection nozzle with a screen in a superimposed manner, a partition wall provided with an internal hole, By lowering the injection pressure and increasing the injection area, it is possible to reduce the mechanical impact applied to the catalyst during fuel injection, thereby prolonging the life of the catalyst and improving the stability of the catalytic reaction.

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 perspective view showing a first embodiment of the injector for protecting the catalyst of the single propellant thruster according to the present invention.
3 is a sectional view showing a first embodiment of the injector for protecting the catalyst of the single propellant thruster according to the present invention.
4 is a perspective view showing a second embodiment of the injector for protecting the catalyst of the single propellant thruster according to the present invention.
5 is a cross-sectional view showing a second embodiment of the injector for protecting the catalyst of the single propellant thruster according to the present invention.
6 is a perspective view showing a dispersion according to the present invention.
7 is a perspective view showing a third embodiment of the injector for protecting the catalyst of the single propellant thruster according to the present invention.
8 is a sectional view showing a single propellant thruster according to the present invention.
9 is a view showing a 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.

2 is a perspective view showing a first embodiment of the injector for protecting the catalyst of the single propellant thruster according to the present invention; and FIG. 2 is a perspective view showing the first embodiment of the injector for protecting the catalyst of the single propellant thruster according to the present invention. And FIG. 3 is a cross-sectional view showing a first embodiment of the injector for protecting the catalyst of the single propellant thruster according to the present invention.

Referring to FIGS. 1 to 3, the injector 130 for protecting the catalyst of the single propellant thruster according to the present invention induces the spatial dispersion of the fuel to widen the contact area between the raw material and the catalyst, And a fuel injection nozzle 131 for injecting fuel into the catalyst 111 installed at one end of the fuel supply pipe 131 and charged in the catalyst bed 110 (133).

The fuel supply pipe 131 serves to supply the raw material to the fuel injection nozzle 133 and is installed in the tube 101.

The fuel injection nozzle 133 includes a cylindrical casing 135 that receives fuel through the first end and injects fuel through the second end and a fuel supply port 139 provided at the first end 138 And a screen 143 configured to partition the interior of the casing 135 and to allow fuel to pass therethrough.

The casing 135 is formed in a cylindrical shape to be installed in the catalyst bed 110. A fuel supply port 139 for inserting the fuel supply pipe 131 is provided at a first end of the casing 135, It can be made of an open structure.

The casing 135 may have a structure in which the separated upper casing 135a and the lower casing 135b are fixed and at least one coupling groove 136 to which the screen 143 can be coupled is formed on the inner circumferential surface .

The screen 143 serves to lower the injection pressure of the fuel supplied through the fuel supply pipe 131 and is made of a material capable of partitioning the interior of the casing 135 and allowing fuel to pass therethrough.

Specifically, the screen may include a coupling ring 145 formed in a ring shape and fitted in the coupling groove 136, and a mesh member 148 fixed in the coupling ring 145.

The mesh member 148 may be formed by processing fibers, metals, ceramics, plastics or the like into a net shape.

A plurality of the screens 143 may be installed in a superimposed manner, and the number of the screens 143 may be appropriately adjusted in consideration of the injection pressure of fuel and the like.

Meanwhile, the upper casing 135 and the lower casing 135 may be joined by welding or the like, but they may be configured to be coupled to each other by a flange structure so as to be detachable.

Since the plurality of screens 143 provided in the casing 135 are provided in this way, the fuel injected through the fuel supply pipe 131 is supplied to the catalyst in a state in which the injection pressure is reduced. Therefore, The mechanical impact can be reduced and the damage can be prevented. Also, since at least the second end portion 141 of the casing 135 is configured to be larger than the diameter of the fuel supply port 139, there is an advantage that the contact area with respect to the catalyst can be widened and the catalyst activation efficiency can be improved.

Hereinafter, other embodiments of the injector for protecting the catalyst of the single propellant thruster according to the present invention will be described in detail with reference to the accompanying drawings. However, the same or similar reference numerals are given to the same or similar components as in the above-described embodiment, and a detailed description thereof will be omitted.

FIG. 4 is a perspective view showing a second embodiment of the injector for protecting the catalyst of the single propellant thruster according to the present invention, and FIG. 5 is a view showing a second embodiment of the injector for protecting the catalyst of the single propellant thruster according to the present invention Fig.

4 and 5, the sprayer 130 according to the present invention differs from the first embodiment in that a partition wall 150 is provided instead of the screen 143.

Specifically, the fuel injection nozzle 133 includes a cylindrical casing 135 that receives fuel through a fuel supply port 139 provided at the first end portion 138 and injects fuel through the second end portion 141 A partition 150 having a plurality of internal holes 151 is formed in the interior of the casing 135 and a plurality of injection holes 142 are formed in the second end 141 .

The number of the barrier ribs 150 may be one or plural, and each barrier rib may be formed of metal, plastic, ceramic, or the like.

When the plurality of barrier ribs 150 are provided, the barrier ribs 150 may be spaced apart from each other by a predetermined distance, and the barrier ribs are engaged with the coupling grooves 136 formed in the casing 135.

As shown in the figure, when two barrier ribs 150 are formed, a plurality of inner holes 151 are formed at the central portion of the left barrier rib 150, and a barrier rib 150 And an injection hole 142 is formed on the entire surface of the second end 141 of the casing 135. The injection hole 142 is formed on the entire surface of the casing 135,

As the inner hole 151 and the injection hole 142 are disposed closer to the catalyst bed 101, the distribution area and the number of the inner holes 151 and the number of the injection holes 142 are increased so that the injection pressure of the fuel becomes smaller toward the catalyst bed 101 Since the increased injection area is wider, the physical impact on the catalyst packed in the catalyst bed can be reduced.

FIG. 6 is a perspective view showing a dispersion according to the present invention, and FIG. 7 is a perspective view showing a third embodiment of a sprayer for protecting a catalyst of a single propellant thruster according to the present invention.

6 and 7, this embodiment differs from the first embodiment in that a dispersion body 155 is formed instead of the screen 143 of the first embodiment.

The injector 130 for catalyst protection of the single propellant thruster according to the present embodiment is supplied with fuel through the fuel supply port 139 provided at the first end 138 and injects fuel through the second end 141 And is disposed in the casing 135 and is disposed at a position corresponding to the fuel supply port 139. The dispersion of the fuel sprayed through the fuel supply port 139 A body 155 is provided.

The dispersion body 155 is fixed to the casing 135 by a support stand 156.

The support base 156 includes a ring-shaped coupling portion 158 coupled to the coupling groove 136 formed in the casing 135 and a support portion 157 connecting the coupling portion 158 and the dispersion body 155 Lt; / RTI >

Since the front end 155a of the dispersion body 155 is made streamlined, the fuel collides with the dispersion body 155 and disperses while spreading.

8 is a sectional view showing a single propellant thruster according to the present invention.

Referring to FIGS. 1 and 8, a single propellant thruster according to the present invention includes a tube 101 in which a fuel supply pipe is installed to supply fuel, a catalyst bed 110 for catalyzing the supplied fuel, And a nozzle 160 for injecting the catalytically reacted product to the outside of the vessel 110 in sequence.

The catalyst bed 110 includes a first catalytic unit 111 disposed at the front side and a second catalytic unit 115 disposed at a rear side of the first catalytic unit 111.

The first catalyst part 111 includes a first support 113 formed of a foamed metal having a three-dimensional network structure and a first catalyst attached to the first support 113. The second catalyst part 115 Is composed of a plurality of bead-shaped second supports 117 and a second catalyst attached to the second support 117. The fuel injected through the fuel injection nozzles 133 passes through the screen 143 The injected fuel is injected into the first catalyst part 111 in a state where the injection pressure is reduced.

The first catalyst part 111 having a structure that is structurally durable is disposed in front of the catalyst bed 110 and the second catalyst part 115 having excellent reactivity is disposed behind the catalyst bed 110, It is possible to prevent formation of voids and to realize stable catalytic reactivity.

Here, it is exemplified that the first and second catalysts are iridium, the second support is alumina (Al 2 O 3 ), and the fuel is hydrazine (N 2 H 2 ).

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 exemplary 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: Tube
130: Injector 131: Fuel supply pipe
133: injection nozzle 135: casing
136: coupling groove 138: first end
139: fuel supply port 141: second end
142: injection hole 143: screen
145: Coupling ring
148: net member 150: partition wall
151: inner hole 155: dispersing element
155a: front end portion 156:
157: support part 158:
160: Nozzle

Claims (9)

A fuel supply pipe, and a fuel injection nozzle provided at one end of the fuel supply pipe,
The fuel injection nozzle
A cylindrical casing that receives fuel through a fuel supply port provided at a first end and injects fuel through a second end;
And a screen configured to partition the interior of the casing and allow fuel to pass therethrough,
Wherein the fuel injected through the fuel supply pipe is injected by the screen with the injection pressure reduced. The method according to claim 1,
Wherein the screen has a structure in which a plurality of net members are overlapped. The method according to claim 1,
Wherein the casing is configured to be larger than the diameter of the fuel supply pipe. A fuel supply pipe, and a fuel injection nozzle provided at one end of the fuel supply pipe,
The fuel injection nozzle
A cylindrical casing that receives fuel through a fuel supply port provided at a first end and injects fuel through a second end;
A partition wall partitioning the inside of the casing and having a plurality of internal holes;
And a plurality of ejection holes provided at the second end,
Wherein the fuel injected through the fuel supply pipe is injected in a state in which the injection pressure is decreased while the injected fuel passes sequentially through the inner hole and the injection hole, and the injection range is widened. 5. The method of claim 4,
Wherein a plurality of the partition walls are spaced apart from each other. 5. The method of claim 4,
Wherein the plurality of inner holes in the partition are formed at a central portion,
Wherein the injection hole is formed in a larger area than the inner hole. A fuel supply pipe, and a fuel injection nozzle provided at one end of the fuel supply pipe,
The fuel injection nozzle
A cylindrical casing that receives fuel through a fuel supply port provided at a first end and injects fuel through a second end;
A dispersion member installed in the casing and disposed at a position corresponding to the fuel supply port to cause the fuel injected through the fuel supply port to hit and disperse;
Wherein the injector is adapted to inject fuel into the combustion chamber of the single propellant thruster. 8. The method of claim 7,
Characterized in that the dispersing body has a front end made streamlined and fixed to the casing by means of a support. A tube provided with a fuel injection nozzle and supplying fuel, a catalyst bed for catalyzing the fuel supplied from the fuel injection nozzle, and a nozzle for spraying the catalyst-reacted product out of the catalyst bed in sequence In a single propellant thruster,
The fuel injection nozzle
A cylindrical casing that receives fuel through a fuel supply port provided at a first end and injects fuel through a second end; A fuel supply port provided at the first end; And a screen having a structure in which the inside of the casing is partitioned and a plurality of network members are overlapped,
Wherein the catalyst bed comprises: a first catalyst unit disposed in front of the catalyst unit; And a second catalyst portion disposed behind the first catalyst portion,
Wherein the first catalytic portion comprises a first support comprising a foamed metal of a steric network structure and a first catalyst attached to the first support, the second catalytic portion comprises a plurality of bead-shaped second supports, 2 < / RTI > support,
Wherein the fuel injected through the fuel supply pipe is injected into the first catalyst portion with the injection pressure reduced by the screen.
KR1020140181569A 2014-12-16 2014-12-16 Injector for the protection of the catalyst of the monopropellant thrusters and the monopropellant thrusters KR20160073476A (en)

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20180058431A (en) * 2016-11-24 2018-06-01 한국항공우주연구원 injector for thruster
CN108332559A (en) * 2018-03-29 2018-07-27 广东盛达穗南环保科技有限公司 Based on spiral tube heat exchange to realize the perlite bloating plant for the function that cools
CN111379646A (en) * 2020-04-14 2020-07-07 西安中科宇航动力技术有限公司 3D prints integral single unit thruster
CN113309634A (en) * 2021-05-17 2021-08-27 北京宇航***工程研究所 Pressurization energy dissipater for propellant storage tank of liquid carrier rocket
CN114455104A (en) * 2022-04-13 2022-05-10 北京凌空天行科技有限责任公司 Liquid aircraft propellant tank energy dissipater and propulsion device

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101183453B1 (en) 2010-06-07 2012-09-18 한국항공우주연구원 Monopropellant Thruster

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101183453B1 (en) 2010-06-07 2012-09-18 한국항공우주연구원 Monopropellant Thruster

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20180058431A (en) * 2016-11-24 2018-06-01 한국항공우주연구원 injector for thruster
CN108332559A (en) * 2018-03-29 2018-07-27 广东盛达穗南环保科技有限公司 Based on spiral tube heat exchange to realize the perlite bloating plant for the function that cools
CN111379646A (en) * 2020-04-14 2020-07-07 西安中科宇航动力技术有限公司 3D prints integral single unit thruster
CN113309634A (en) * 2021-05-17 2021-08-27 北京宇航***工程研究所 Pressurization energy dissipater for propellant storage tank of liquid carrier rocket
CN113309634B (en) * 2021-05-17 2022-03-04 北京宇航***工程研究所 Pressurization energy dissipater for propellant storage tank of liquid carrier rocket
CN114455104A (en) * 2022-04-13 2022-05-10 北京凌空天行科技有限责任公司 Liquid aircraft propellant tank energy dissipater and propulsion device
CN114455104B (en) * 2022-04-13 2022-07-12 北京凌空天行科技有限责任公司 Liquid aircraft propellant tank energy dissipater and propulsion device

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