WO2015029146A1 - Réservoir de gaz pour véhicule aérospatial, et véhicule aérospatial - Google Patents

Réservoir de gaz pour véhicule aérospatial, et véhicule aérospatial Download PDF

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Publication number
WO2015029146A1
WO2015029146A1 PCT/JP2013/072921 JP2013072921W WO2015029146A1 WO 2015029146 A1 WO2015029146 A1 WO 2015029146A1 JP 2013072921 W JP2013072921 W JP 2013072921W WO 2015029146 A1 WO2015029146 A1 WO 2015029146A1
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WO
WIPO (PCT)
Prior art keywords
strength member
air
working gas
spacecraft
strength
Prior art date
Application number
PCT/JP2013/072921
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English (en)
Japanese (ja)
Inventor
尚喜 草場
晃浩 佐藤
Original Assignee
三菱重工業株式会社
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 三菱重工業株式会社 filed Critical 三菱重工業株式会社
Priority to PCT/JP2013/072921 priority Critical patent/WO2015029146A1/fr
Priority to JP2015533832A priority patent/JP6121541B2/ja
Publication of WO2015029146A1 publication Critical patent/WO2015029146A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B64G1/402—Propellant tanks; Feeding propellants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2205/00—Vessel construction, in particular mounting arrangements, attachments or identifications means
    • F17C2205/01—Mounting arrangements
    • F17C2205/0153—Details of mounting arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2221/00—Handled fluid, in particular type of fluid
    • F17C2221/01—Pure fluids
    • F17C2221/011—Oxygen
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2221/00—Handled fluid, in particular type of fluid
    • F17C2221/01—Pure fluids
    • F17C2221/012—Hydrogen
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2221/00—Handled fluid, in particular type of fluid
    • F17C2221/01—Pure fluids
    • F17C2221/014—Nitrogen
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2221/00—Handled fluid, in particular type of fluid
    • F17C2221/01—Pure fluids
    • F17C2221/016—Noble gases (Ar, Kr, Xe)
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2221/00—Handled fluid, in particular type of fluid
    • F17C2221/01—Pure fluids
    • F17C2221/016—Noble gases (Ar, Kr, Xe)
    • F17C2221/017—Helium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2223/00—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel
    • F17C2223/01—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel characterised by the phase
    • F17C2223/0146—Two-phase
    • F17C2223/0153—Liquefied gas, e.g. LPG, GPL
    • F17C2223/0161—Liquefied gas, e.g. LPG, GPL cryogenic, e.g. LNG, GNL, PLNG
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2223/00—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel
    • F17C2223/03—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel characterised by the pressure level
    • F17C2223/033—Small pressure, e.g. for liquefied gas
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2270/00—Applications
    • F17C2270/01—Applications for fluid transport or storage
    • F17C2270/0186—Applications for fluid transport or storage in the air or in space
    • F17C2270/0194—Applications for fluid transport or storage in the air or in space for use under microgravity conditions, e.g. space
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2270/00—Applications
    • F17C2270/01—Applications for fluid transport or storage
    • F17C2270/0186—Applications for fluid transport or storage in the air or in space
    • F17C2270/0197—Rockets
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02E60/30—Hydrogen technology
    • Y02E60/32—Hydrogen storage

Definitions

  • the present invention relates to an air accumulator for a spacecraft that accumulates working gas and a spacecraft.
  • a tank that is provided in the upper stage of a rocket and stores fuel is known (for example, see Patent Document 1).
  • the tank is provided with a gas supply and extraction device, and the fuel in the tank is extracted by supplying gas into the tank.
  • the gas supplied to the inside of the tank is accumulated in an air accumulator provided in the rocket.
  • a spacecraft such as a rocket or an artificial satellite is as light as possible.
  • the weight of the gas accumulator filled with gas is as heavy as, for example, about 25 kg per piece, it is an obstacle to reducing the weight of the rocket.
  • the navigation period of the spacecraft is long, it is difficult to reduce the weight of the rocket because it is necessary to mount a large number of air reservoirs.
  • an object of the present invention is to provide an air accumulator for a spacecraft and a spacecraft capable of accumulating working gas and reducing the weight.
  • An air accumulator for a spacecraft is an air accumulator for a spacecraft provided in a spacecraft including a frame configured using a hollow cylindrical strength member, It has an air storage structure capable of accumulating working gas inside.
  • the spacecraft of the present invention includes a frame configured using a hollow cylindrical strength member, and an air accumulator having an air storage structure capable of accumulating working gas inside the strength member. It is characterized by that.
  • the strength member can be used as part of the container of the air accumulator by providing the strength member with the air storage structure. For this reason, since the strength member can function as an air reservoir, it is not necessary to provide a dedicated air reservoir, and the weight of the spacecraft can be reduced. Moreover, the rigidity of the strength member is higher than that of a dedicated air reservoir. At this time, in order to reduce the weight, the dedicated air reservoir reduces the wall thickness while increasing the internal gas pressure. Must be carried out in a highly safe working environment. On the other hand, in the present invention, since a highly rigid strength member can be used as a part of the container of the air accumulator, the filling operation can be performed without evacuating the worker. Compared to this, the working gas can be filled safely.
  • the working gas is accumulated in the strength member having the air storage structure after internal cleaning.
  • the working gas can be filled into the strength member after the strength member is cleaned, so that dust can be prevented from being mixed into the strength member. For this reason, generation
  • the air storage structure includes a pair of opposing tube plates provided inside the strength member, and the inside and outside of the strength member provided on the one tube plate and partitioned by the pair of tube plates. It is preferable to have a joint to which a pipe for circulating the working gas is connected.
  • the air storage structure can be simplified by a pair of tube sheets and joints. Moreover, the working gas filled in the strength member partitioned by the pair of tube plates can be filled through the joint, or the working gas accumulated in the strength member can be discharged through the joint. .
  • a plurality of the strength members are provided over the entire circumference, and further provided with a communication pipe that communicates the inside of one of the strength members and the inside of the other strength member.
  • the insides of the plurality of strength members can be connected by the communication pipe.
  • strength member which has an air storage structure can be used as a single air accumulator.
  • the strength member is provided in a plurality over the entire circumference, and further includes equipment for using the working gas, and the strength member closest to the equipment is provided with the air storage structure, and the strength member And the equipment are preferably connected by piping.
  • the air storage structure can be provided in the strength member closest to the facility, the length of the pipe connecting the strength member and the facility can be shortened. For this reason, since the length of the piping can be shortened, the weight of the piping can be reduced, and thereby the weight of the spacecraft can be reduced.
  • FIG. 1 is a schematic configuration diagram schematically showing a rocket as a spacecraft according to the present embodiment.
  • FIG. 2 is a schematic configuration diagram schematically illustrating the air accumulator.
  • FIG. 1 is a schematic configuration diagram schematically showing a part of a rocket as a spacecraft according to the present embodiment
  • FIG. 2 is a schematic configuration diagram schematically showing an air reservoir.
  • the air accumulator 10 of a present Example is provided in a spacecraft, and accumulates the working gas used with a spacecraft.
  • the spacecraft includes a flying object such as a rocket, an artificial satellite or a space base, and the air reservoir 10 of this embodiment is applied to a rocket.
  • the air accumulator 10 is described as applied to the second stage rocket of the multistage rocket, but the air accumulator 10 can be applied to any number of stages of the rocket, Further, the present invention may be applied to a space navigation body such as an artificial satellite or a space base, and is not particularly limited.
  • a space navigation body such as an artificial satellite or a space base, and is not particularly limited.
  • the rocket 1 is propelled by burning a fuel with a frame 5, a fuel tank 6 supported on one side of the frame 5, an oxidant tank 7 supported on the other side of the frame 5.
  • a rocket engine 8 that generates force and an air reservoir 10 are provided.
  • the frame 5 has a truss structure, and a first support member 11 provided on the fuel tank 6 side (one side: upper side in the figure) and a second support member provided on the oxidant tank 7 side (the other side: the lower side in the figure). It has a support member 12 and a plurality of strength members 13 provided between the first support member 11 and the second support member 12.
  • the first support member 11 is provided in an annular shape over the entire outer periphery of the fuel tank 6.
  • One end of a strength member 13 is connected to the first support member 11.
  • the second support member 12 is provided in an annular shape over the entire outer periphery of the oxidant tank 7.
  • the other end of the strength member 13 is connected to the second support member 12.
  • the plurality of strength members 13 are provided between the first support member 11 and the second support member 12.
  • the plurality of strength members 13 are arranged over the entire circumference so that the plurality of strength members 13, the first support member 11, and the second support member 12 form a triangular shape.
  • Each strength member 13 is formed in a cylindrical shape whose inside is hollow.
  • the fuel tank 6 is, for example, a liquid hydrogen tank that stores liquid hydrogen as a fuel, and is formed in a cylindrical shape.
  • the fuel tank 6 can supply liquid hydrogen to the rocket engine 8 by supplying the working gas from the gas accumulator 10.
  • the oxidant tank 7 is, for example, a liquid oxygen tank that stores liquid oxygen as an oxidant, and is formed in a cylindrical shape.
  • the oxidant tank 7 can supply liquid oxygen toward the rocket engine 8 by supplying the working gas from the gas accumulator 10.
  • the fuel tank 6 and the oxidant tank 7 are disposed to face each other with the frame 5 interposed therebetween.
  • the rocket engine 8 is provided on the other side (the lower side in the drawing) of the oxidant tank 7, that is, on the opposite side of the fuel tank 6 with the oxidant tank 7 interposed therebetween.
  • the rocket engine 8 mixes the liquid hydrogen supplied from the fuel tank 6 and the liquid oxygen supplied from the oxidant tank 7 and burns them to generate a propulsive force.
  • the air accumulator 10 is capable of accumulating working gas by providing an air accumulating structure 20 inside a hollow cylindrical strength member 13.
  • the gas accumulator 10 can supply the accumulated working gas toward the fuel tank 6 and the oxidant tank 7.
  • the air accumulator 10 is directed to various valves for controlling the airframe system provided in the rocket engine 8 and the rocket 1, attitude control, and a thruster for correcting the trajectory.
  • the accumulated working gas can be supplied. That is, the fuel tank 6, the oxidant tank 7, the thruster, and the like are facilities that use working gas.
  • helium gas is used as the working gas accumulated in the air accumulator 10.
  • the working gas is not limited to helium gas, and any working gas may be used.
  • nitrogen gas or argon gas may be used.
  • the air reservoir 10 uses the strength member 13 as a part of the container.
  • the thickness of the strength member 13 is, for example, 10 mm to 20 mm.
  • the thickness of the dedicated air reservoir mounted on the rocket 1 is, for example, about 3 mm.
  • the rigidity of the air reservoir 10 of the present embodiment is equal to the rigidity of the dedicated air reservoir. It is higher than that.
  • the strength member 13 has an outer diameter of about 100 mm and a length in the longitudinal direction (axial direction) of about 1000 mm to 2000 mm.
  • the air storage structure 20 provided inside the predetermined strength member 13 has a pair of tube sheets 21, 22, a filling joint 23, and a discharge joint 24.
  • one tube plate 21 is provided on one side (the upper side in the drawing) of the strength member 13, and the other tube plate 22 is the other side of the strength member 13 in the axial direction. (Lower side in the figure).
  • the inside of the strength member 13 is partitioned by the pair of tube plates 21 and 22.
  • the pair of tube plates 21 and 22 are joined to the inside of the strength member 13 by welding or the like, the structure between the strength member 13 and the tube plates 21 and 22 is hermetically sealed. ing. For this reason, it is possible to suppress leakage of the working gas from the inside of the strength member 13.
  • the filling joint 23 is provided on one tube plate 21 and is used when filling the working gas.
  • the filling joint 23 is connected to a gas filling pipe when the working gas is filled in the strength member 13.
  • the working gas is supplied into the strength member 13 through the filling joint 23.
  • the gas filling tube is removed when the working gas filling is completed.
  • the discharge joint 24 is provided on one tube plate 21 and is used when the working gas is discharged.
  • the discharge joint 24 is connected to facilities such as the fuel tank 6, the oxidant tank 7, and the thruster via a discharge pipe 25.
  • the working gas filled in the strength member 13 is supplied to facilities such as the fuel tank 6, the oxidant tank 7, and the thruster via the discharge joint 24 and the discharge pipe 25.
  • the air reservoir 10 configured as described above discharges dust adhering to the inside of the strength member 13 partitioned by the pair of tube plates 21 and 22 by performing internal cleaning before filling with the working gas. To do.
  • the strength member 13 can be used as a part of the container of the air reservoir 10 by providing the air storage structure 20 inside the strength member 13. For this reason, since the strength member 13 can function as the air accumulator 10, there is no need to provide a dedicated air accumulator, and the weight of the rocket 1 can be reduced. Moreover, the rigidity of the strength member 13 is higher than that of a dedicated air reservoir. At this time, in order to reduce the weight, the dedicated air reservoir reduces the wall thickness while increasing the internal gas pressure. Must be carried out in a highly safe working environment.
  • the highly rigid strength member 13 can be used as a part of the container of the air accumulator 10, the filling operation is performed without retracting the worker. Therefore, the working gas can be filled more safely than a dedicated air accumulator.
  • the working gas can be filled into the strength member 13 after the strength member 13 is internally cleaned, so that dust can be prevented from being mixed into the strength member 13. For this reason, generation
  • the air storage structure 20 can be simplified by the pair of tube sheets 21 and 22 and the various joints 23 and 24. Further, the inside of the strength member 13 partitioned by the pair of tube plates 21 and 22 is filled with the working gas via the filling joint 23, or the working gas accumulated in the strength member 13 is discharged into the joint for discharging. 24 can be discharged.
  • the air accumulator 10 may be configured by a single strength member 13 having the air storage structure 20 or may be configured by providing a plurality of strength members 13 having the air storage structure 20.
  • the air accumulator 10 may be configured by a single strength member 13 having the air storage structure 20 or may be configured by providing a plurality of strength members 13 having the air storage structure 20.
  • the inside of the plurality of strength members 13 may be connected using a communication pipe.
  • a plurality of strength members 13 having the air storage structure 20 can be used as a single air storage device 10.
  • the air storage structure 10 when configured by providing the air storage structures 20 on the plurality of strength members 13, the air storage structure 20 May be provided.
  • the discharge pipe 25 connecting the discharge joint 24 of the strength member 13 and each facility can be shortened.
  • the weight of the discharge pipe 25 can be reduced, and thus the weight of the rocket 1 can be reduced.
  • the insides of the plurality of strength members 13 may be connected using communication pipes, or may not be connected.

Abstract

L'invention concerne un réservoir de gaz (10) pour une fusée, qui est fourni à une fusée pourvue d'un cadre configuré à l'aide d'un organe de résistance cylindrique creux. Le réservoir de gaz (10) est pourvu d'une structure de réservoir de gaz (20) qui est capable d'accumuler un gaz de travail à l'intérieur de l'organe de résistance (13). La structure de réservoir de gaz (20) est pourvue : d'une paire de plaques formant tube (21, 22) qui sont ménagées à l'intérieur de l'organe de résistance (13), et qui sont en regard l'une de l'autre ; et d'un accessoire de remplissage (23) et d'un accessoire d'évacuation (23) qui sont fournis à l'une des plaques formant tube (21) et auxquels est raccordée une tuyauterie pour amener le gaz de travail à circuler dans et hors de l'organe de résistance (13) cloisonné par la paire de plaques formant tube (21, 22).
PCT/JP2013/072921 2013-08-27 2013-08-27 Réservoir de gaz pour véhicule aérospatial, et véhicule aérospatial WO2015029146A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PCT/JP2013/072921 WO2015029146A1 (fr) 2013-08-27 2013-08-27 Réservoir de gaz pour véhicule aérospatial, et véhicule aérospatial
JP2015533832A JP6121541B2 (ja) 2013-08-27 2013-08-27 宇宙航行体用の気蓄器及び宇宙航行体

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/JP2013/072921 WO2015029146A1 (fr) 2013-08-27 2013-08-27 Réservoir de gaz pour véhicule aérospatial, et véhicule aérospatial

Publications (1)

Publication Number Publication Date
WO2015029146A1 true WO2015029146A1 (fr) 2015-03-05

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WO (1) WO2015029146A1 (fr)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH02500100A (ja) * 1987-06-24 1990-01-18 エーリコン―コントラベス・アクチェンゲゼルシャフト 膨張可能な折り畳み構造体及び折り畳み構造体を製造するための方法
JPH0381551A (ja) * 1989-08-25 1991-04-05 Nissan Motor Co Ltd ロケット用作動油圧供給源の作動油監視装置
JP2000220795A (ja) * 1999-02-01 2000-08-08 Mitsubishi Heavy Ind Ltd 気蓄器の気体置換装置
JP2008189304A (ja) * 2007-02-03 2008-08-21 Astrium Gmbh 極低温液体および貯蔵可能な燃料を貯蔵するためのタンク
US20100012788A1 (en) * 2005-09-07 2010-01-21 The Boeing Company Exchangeable Propellant Cartridge System

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH02500100A (ja) * 1987-06-24 1990-01-18 エーリコン―コントラベス・アクチェンゲゼルシャフト 膨張可能な折り畳み構造体及び折り畳み構造体を製造するための方法
JPH0381551A (ja) * 1989-08-25 1991-04-05 Nissan Motor Co Ltd ロケット用作動油圧供給源の作動油監視装置
JP2000220795A (ja) * 1999-02-01 2000-08-08 Mitsubishi Heavy Ind Ltd 気蓄器の気体置換装置
US20100012788A1 (en) * 2005-09-07 2010-01-21 The Boeing Company Exchangeable Propellant Cartridge System
JP2008189304A (ja) * 2007-02-03 2008-08-21 Astrium Gmbh 極低温液体および貯蔵可能な燃料を貯蔵するためのタンク

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JP6121541B2 (ja) 2017-04-26

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