WO2015029146A1 - Gas reservoir for aerospace vehicle, and aerospace vehicle - Google Patents

Gas reservoir for aerospace vehicle, and aerospace vehicle 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
Other languages
French (fr)
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/en
Priority to JP2015533832A priority patent/JP6121541B2/en
Publication of WO2015029146A1 publication Critical patent/WO2015029146A1/en

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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

A gas reservoir (10) for a rocket is provided to a rocket provided with a frame configured using a hollow cylindrical strength member. The gas reservoir (10) is provided with a gas-reservoir structure (20) which is capable of accumulating a working gas inside the strength member (13). The gas-reservoir structure (20) is provided with: a pair of tube plates (21, 22) which are provided inside the strength member (13), and which face each other; and a filling fitting (23) and a discharge fitting (23) which are provided to one of the tube plates (21), and which have, connected thereto, piping for causing the working gas to circulate in and out of the strength member (13) partitioned by the pair of tube plates (21, 22).

Description

宇宙航行体用の気蓄器及び宇宙航行体Air accumulator and spacecraft for spacecraft
　本発明は、作動ガスを蓄圧する宇宙航行体用の気蓄器及び宇宙航行体に関するものである。 The present invention relates to an air accumulator for a spacecraft that accumulates working gas and a spacecraft.
　従来、ロケット上段に設けられ、燃料を貯蔵するタンクが知られている（例えば、特許文献１参照）。このタンクには、ガス供給及び取り出し装置が設けられており、タンク内にガスを供給することで、タンク内の燃料を取り出している。 Conventionally, 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.
特開２００８－１８９３０４号公報JP 2008-189304 A
　ここで、タンクの内部に供給されるガスは、ロケットに設けられる気蓄器に蓄圧されている。ところで、ロケットまたは人工衛星等の宇宙航行体は、その重量が出来るだけ軽いことが望ましい。一方で、ガスが充填される気蓄器は、その重量が、例えば１個当たり２５ｋｇ前後と重いことから、ロケットの軽量化を図る上で妨げとなっている。特に、宇宙航行体の宇宙空間内の航行期間が長くなる場合には、気蓄器を多く搭載する必要があることから、ロケットの軽量化を図ることが困難となる。 Here, the gas supplied to the inside of the tank is accumulated in an air accumulator provided in the rocket. By the way, it is desirable that a spacecraft such as a rocket or an artificial satellite is as light as possible. On the other hand, since 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. In particular, when 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.
　そこで、本発明は、作動ガスを蓄圧すると共に、重量を軽減することができる宇宙航行体用の気蓄器及び宇宙航行体を提供することを課題とする。 Therefore, 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.
　本発明の宇宙航行体用の気蓄器は、中空円筒状の強度部材を用いて構成されるフレームを備える宇宙航行体に設けられる宇宙航行体用の気蓄器であって、前記強度部材の内部に、作動ガスを蓄圧可能な気蓄構造を有することを特徴とする。 An air accumulator for a spacecraft according to the present invention 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.
　また、本発明の宇宙航行体は、中空円筒状の強度部材を用いて構成されるフレームと、前記強度部材の内部に、作動ガスを蓄圧可能な気蓄構造を有する気蓄器と、を備えることを特徴とする。 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.
　この構成によれば、強度部材に気蓄構造を設けることで、強度部材を気蓄器の容器の一部として利用することができる。このため、強度部材を気蓄器として機能させることができることから、専用の気蓄器を設ける必要がなく、宇宙航行体の重量を軽減することができる。また、強度部材の剛性は、専用の気蓄器に比して高くなっている。このとき、専用の気蓄器は、重量を軽減するために、肉厚を薄くしつつ内部のガス圧を高圧にすることから、専用の気蓄器への作動ガスの充填作業は、作業員を退避させ、安全性の高い作業環境で行う必要がある。一方で、本発明では、剛性の高い強度部材を気蓄器の容器の一部として利用することができるため、作業員を退避させることなく、充填作業を行うことができ、専用の気蓄器に比して作動ガスの充填作業を安全に行うことができる。 According to this configuration, 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.
　また、前記気蓄構造を有する前記強度部材は、内部洗浄後に前記作動ガスが蓄圧されることが好ましい。 Moreover, it is preferable that the working gas is accumulated in the strength member having the air storage structure after internal cleaning.
　この構成によれば、強度部材の内部洗浄後に、作動ガスを強度部材内に充填することができるため、強度部材内へのダストの混入を抑制することができる。このため、ダストによる詰まり、またはダストによる機器の作動不良等の発生を抑制することができる。 According to this configuration, 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 | occurrence | production of the clogging by dust or the malfunctioning of the apparatus by dust, etc. can be suppressed.
　また、前記気蓄構造は、前記強度部材の内部に設けられる対向する一対の管板と、前記一方の管板に設けられ、前記一対の管板により区画された前記強度部材の内外において、前記作動ガスを流通させるための配管が接続される継手と、を有することが好ましい。 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.
　この構成によれば、気蓄構造を、一対の管板と継手とにより簡易な構成にすることができる。また、一対の管板により区画された強度部材の内部に、継手を介して作動ガスを充填したり、強度部材の内部に蓄圧された作動ガスを、継手を介して排出したりすることができる。 According to this configuration, 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. .
　また、前記強度部材は、全周に亘って複数設けられ、一方の前記強度部材の内部と、他方の前記強度部材の内部とを連通する連通管を、さらに備えることが好ましい。 Further, it is preferable that 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.
　この構成によれば、気蓄構造を有する強度部材を複数設ける場合、連通管により複数の強度部材の内部を接続することができる。このため、気蓄構造を有する複数の強度部材を、単一の気蓄器として使用することができる。 According to this configuration, when a plurality of strength members having an air storage structure are provided, the insides of the plurality of strength members can be connected by the communication pipe. For this reason, the several intensity | strength member which has an air storage structure can be used as a single air accumulator.
　また、前記強度部材は、全周に亘って複数設けられ、前記作動ガスが使用される設備を、さらに備え、前記設備に最も近い前記強度部材に、前記気蓄構造を設けると共に、前記強度部材と前記設備とを配管により接続することが好ましい。 In addition, 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.
　この構成によれば、設備に最も近い強度部材に気蓄構造を設けることができるため、強度部材と設備とを接続する配管の長さを短くすることができる。このため、配管の長さを短くすることができる分、配管の重量を軽減することができ、これにより、宇宙航行体の重量の軽減を図ることができる。 According to this configuration, since 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.
図１は、本実施例に係る宇宙航行体としてのロケットを模式的に表した概略構成図である。FIG. 1 is a schematic configuration diagram schematically showing a rocket as a spacecraft according to the present embodiment. 図２は、気蓄器を模式的に表した概略構成図である。FIG. 2 is a schematic configuration diagram schematically illustrating the air accumulator.
　以下に、本発明に係る実施例を図面に基づいて詳細に説明する。なお、この実施例によりこの発明が限定されるものではない。また、下記実施例における構成要素には、当業者が置換可能かつ容易なもの、あるいは実質的に同一のものが含まれる。 Embodiments according to the present invention will be described below in detail with reference to the drawings. Note that the present invention is not limited to the embodiments. In addition, constituent elements in the following embodiments include those that can be easily replaced by those skilled in the art or those that are substantially the same.
　図１は、本実施例に係る宇宙航行体としてのロケットの一部を模式的に表した概略構成図であり、図２は、気蓄器を模式的に表した概略構成図である。図１及び図２に示すように、本実施例の気蓄器１０は、宇宙航行体に設けられ、宇宙航行体で使用される作動ガスを蓄圧するものである。ここで、宇宙航行体としては、ロケット等の飛翔体、人工衛星または宇宙基地等があり、本実施例の気蓄器１０は、ロケットに適用されている。なお、本実施例では、気蓄器１０を多段式ロケットの２段目のロケットに適用して説明するが、気蓄器１０は、ロケットのいずれの段数であっても適用が可能であり、また、人工衛星または宇宙基地等の宇宙航行体に適用してもよく、特に限定されない。先ず、図１を参照して、気蓄器１０が設けられる２段目のロケット１（以下、単にロケットという）について説明する。
FIG. 1 is a schematic configuration diagram schematically showing a part of a rocket as a spacecraft according to the present embodiment, and FIG. 2 is a schematic configuration diagram schematically showing an air reservoir. As shown in FIG.1 and FIG.2, the air accumulator 10 of a present Example is provided in a spacecraft, and accumulates the working gas used with a spacecraft. Here, 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. In this embodiment, 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. First, with reference to FIG. 1, the 2nd stage rocket 1 (henceforth only a rocket) provided with the air accumulator 10 is demonstrated.
　図１に示すように、ロケット１は、フレーム５と、フレーム５の一方側に支持される燃料タンク６と、フレーム５の他方側に支持される酸化剤タンク７と、燃料を燃焼させて推進力を発生させるロケットエンジン８と、気蓄器１０とを備えている。 As shown in FIG. 1, 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.
　フレーム５は、トラス構造となっており、燃料タンク６側（一方側：図示上側）に設けられる第１支持部材１１と、酸化剤タンク７側（他方側：図示下側）に設けられる第２支持部材１２と、第１支持部材１１と第２支持部材１２との間に設けられる複数の強度部材１３とを有している。 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.
　第１支持部材１１は、燃料タンク６の外側の全周に亘って環状に設けられている。この第１支持部材１１には、強度部材１３の一端が接続される。第２支持部材１２は、酸化剤タンク７の外側の全周に亘って環状に設けられている。この第２支持部材１２には、強度部材１３の他端が接続される。複数の強度部材１３は、第１支持部材１１と第２支持部材１２との間に設けられている。そして、複数の強度部材１３は、複数の強度部材１３、第１支持部材１１及び第２支持部材１２で三角形状を形成するように、全周に亘って配置されている。各強度部材１３は、内部が中空となる円筒形状に形成されている。なお、詳細は後述するが、この強度部材１３の内部には、作動ガスを蓄圧可能な気蓄構造２０が設けられている。 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. Although details will be described later, an air storage structure 20 capable of accumulating working gas is provided inside the strength member 13.
　燃料タンク６は、例えば、燃料として液体水素を溜める液体水素タンクとなっており、円筒形状に形成されている。燃料タンク６は、気蓄器１０から作動ガスが供給されることで、ロケットエンジン８へ向けて液体水素を供給可能となっている。酸化剤タンク７は、例えば、酸化剤として液体酸素を溜める液体酸素タンクとなっており、円筒形状に形成されている。酸化剤タンク７は、気蓄器１０から作動ガスが供給されることで、ロケットエンジン８へ向けて液体酸素を供給可能となっている。そして、燃料タンク６及び酸化剤タンク７は、フレーム５を挟んで対向して配置されている。 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.
　ロケットエンジン８は、酸化剤タンク７の他方側（図示下側）、つまり、酸化剤タンク７を挟んで、燃料タンク６の反対側に設けられている。ロケットエンジン８は、燃料タンク６から供給された液体水素及び酸化剤タンク７から供給された液体酸素を混合して燃焼させることで、推進力を発生させる。 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.
　次に、図２を参照して、気蓄器１０について説明する。図２に示すように、気蓄器１０は、中空円筒状の強度部材１３の内部に、気蓄構造２０を設けることで、作動ガスを蓄圧可能となっている。気蓄器１０は、蓄圧した作動ガスを、燃料タンク６及び酸化剤タンク７へ向けて供給可能となっている。また、気蓄器１０は、燃料タンク６及び酸化剤タンク７の他、ロケットエンジン８、ロケット１に設けられる機体システムを制御するための各種バルブ、姿勢制御及び軌道を修正するスラスタ等へ向けて、蓄圧した作動ガスを供給可能となっている。つまり、燃料タンク６、酸化剤タンク７及びスラスタ等は、作動ガスが使用される設備となっている。 Next, the air accumulator 10 will be described with reference to FIG. As shown in FIG. 2, 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. In addition to 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.
　ここで、気蓄器１０に蓄圧される作動ガスとしては、例えば、ヘリウムガスが用いられる。なお、作動ガスは、ヘリウムガスに限定されず、不活性ガスであればいずれであってもよく、例えば、窒素ガスまたはアルゴンガス等を用いてもよい。 Here, for example, helium gas is used as the working gas accumulated in the air accumulator 10. Note that the working gas is not limited to helium gas, and any working gas may be used. For example, nitrogen gas or argon gas may be used.
　気蓄器１０は、強度部材１３を容器の一部として利用している。このとき、強度部材１３の肉厚は、例えば、１０ｍｍ～２０ｍｍとなっている。これに対し、ロケット１に搭載される専用の気蓄器の肉厚は、例えば、約３ｍｍとなっている。このため、強度部材１３の肉厚は、専用の気蓄器の肉厚に比して厚くなっていることから、本実施例の気蓄器１０の剛性は、専用の気蓄器の剛性に比して高くなっている。また、強度部材１３は、その外径が、約１００ｍｍ前後となっており、その長手方向（軸方向）における長さが、約１０００ｍｍ～２０００ｍｍとなっている。 The air reservoir 10 uses the strength member 13 as a part of the container. At this time, the thickness of the strength member 13 is, for example, 10 mm to 20 mm. On the other hand, the thickness of the dedicated air reservoir mounted on the rocket 1 is, for example, about 3 mm. For this reason, since the thickness of the strength member 13 is larger than the thickness of the dedicated air reservoir, 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.
　所定の強度部材１３の内部に設けられる気蓄構造２０は、一対の管板２１，２２と、充填用継手２３と、排出用継手２４と、を有している。一対の管板２１，２２のうち、一方の管板２１は、強度部材１３の軸方向の一方側（図示上側）に設けられ、他方の管板２２は、強度部材１３の軸方向の他方側（図示下側）に設けられている。このため、強度部材１３の内部は、一対の管板２１，２２により区画される。また、一対の管板２１，２２は、溶接等により強度部材１３の内部へ接合されていることから、強度部材１３と管板２１，２２との間は、気密に封止された構造となっている。このため、強度部材１３の内部から、作動ガスが漏出することを抑制することができる。 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. Of the pair of tube plates 21, 22, 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). For this reason, the inside of the strength member 13 is partitioned by the pair of tube plates 21 and 22. Further, since 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.
　充填用継手２３は、一方の管板２１に設けられ、作動ガスの充填時に使用される。充填用継手２３は、強度部材１３の内部に作動ガスを充填する場合に、ガス充填管が接続される。作動ガスは、充填用継手２３を介して、強度部材１３の内部に供給される。なお、ガス充填管は、作動ガスの充填が終了すると取り外される。 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.
　排出用継手２４は、一方の管板２１に設けられ、作動ガスの排出時に使用される。排出用継手２４は、燃料タンク６、酸化剤タンク７及びスラスタ等の設備に、排出配管２５を介して接続されている。強度部材１３の内部に充填された作動ガスは、排出用継手２４及び排出配管２５を介して、燃料タンク６、酸化剤タンク７及びスラスタ等の設備へ向けて供給される。 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.
　上記のように構成された気蓄器１０は、作動ガスの充填前に、内部洗浄が行われることで、一対の管板２１，２２により区画された強度部材１３の内部に付着するダストを排出する。 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.
　以上のように、本実施例の構成によれば、強度部材１３の内部に気蓄構造２０を設けることで、強度部材１３を気蓄器１０の容器の一部として利用することができる。このため、強度部材１３を気蓄器１０として機能させることができることから、専用の気蓄器を設ける必要がなく、ロケット１の重量を軽減することができる。また、強度部材１３の剛性は、専用の気蓄器に比して高くなっている。このとき、専用の気蓄器は、重量を軽減するために、肉厚を薄くしつつ内部のガス圧を高圧にすることから、専用の気蓄器への作動ガスの充填作業は、作業員を退避させ、安全性の高い作業環境で行う必要がある。一方で、本実施例の気蓄器１０では、剛性の高い強度部材１３を気蓄器１０の容器の一部として利用することができるため、作業員を退避させることなく、充填作業を行うことができ、専用の気蓄器に比して作動ガスの充填作業を安全に行うことができる。 As described above, according to the configuration of this embodiment, 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. On the other hand, in the air reservoir 10 of the present embodiment, since 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.
　また、本実施例の構成によれば、強度部材１３の内部洗浄後に、作動ガスを強度部材１３内に充填することができるため、強度部材１３内へのダストの混入を抑制することができる。このため、ダストによる詰まり、またはダストによる機器の作動不良等の発生を抑制することができる。 Further, according to the configuration of the present embodiment, 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 | occurrence | production of the clogging by dust or the malfunctioning of the apparatus by dust, etc. can be suppressed.
　また、本実施例の構成によれば、気蓄構造２０を、一対の管板２１，２２と各種継手２３，２４とにより簡易な構成にすることができる。また、一対の管板２１，２２により区画された強度部材１３の内部に、充填用継手２３を介して作動ガスを充填したり、強度部材１３の内部に蓄圧された作動ガスを、排出用継手２４を介して排出したりすることができる。 Further, according to the configuration of the present embodiment, 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.
　なお、本実施例において、気蓄器１０は、気蓄構造２０を有する強度部材１３を単体により構成してもよいし、気蓄構造２０を有する強度部材１３を複数設けて構成してもよい。ここで、複数の強度部材１３に気蓄構造２０をそれぞれ設けて気蓄器１０を構成する場合、複数の強度部材１３の内部を、連通管を用いて接続してもよい。この構成によれば、気蓄構造２０を有する複数の強度部材１３を、単一の気蓄器１０として使用することができる。 In the present embodiment, 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. . Here, when each of the strength members 13 is provided with the air storage structure 20 to constitute the air reservoir 10, the inside of the plurality of strength members 13 may be connected using a communication pipe. According to this configuration, a plurality of strength members 13 having the air storage structure 20 can be used as a single air storage device 10.
　また、複数の強度部材１３に気蓄構造２０をそれぞれ設けて気蓄器１０を構成する場合、燃料タンク６、酸化剤タンク７及びスラスタ等の設備に最も近い強度部材１３に、気蓄構造２０を設けてもよい。この構成によれば、強度部材１３の排出用継手２４と各設備とを接続する排出配管２５を短くすることができる。このため、排出配管２５の長さを短くすることができる分、排出配管２５の重量を軽減することができ、これにより、ロケット１の重量の軽減を図ることができる。この場合、複数の強度部材１３の内部を、連通管を用いて接続してもよいし、接続しなくてもよい。 Further, when the air storage structure 10 is configured by providing the air storage structures 20 on the plurality of strength members 13, the air storage structure 20 May be provided. According to this configuration, the discharge pipe 25 connecting the discharge joint 24 of the strength member 13 and each facility can be shortened. For this reason, since the length of the discharge pipe 25 can be shortened, the weight of the discharge pipe 25 can be reduced, and thus the weight of the rocket 1 can be reduced. In this case, the insides of the plurality of strength members 13 may be connected using communication pipes, or may not be connected.
１　ロケット
５　フレーム
６　燃料タンク
７　酸化剤タンク
８　ロケットエンジン
１０　気蓄器
１１　第１支持部材
１２　第２支持部材
１３　強度部材
２０　気蓄構造
２１，２２　管板
２３　充填用継手
２４　排出用継手
２５　排出配管 DESCRIPTION OF SYMBOLS 1 Rocket 5 Frame 6 Fuel tank 7 Oxidant tank 8 Rocket engine 10 Air reservoir 11 First support member 12 Second support member 13 Strength member 20 Air storage structures 21 and 22 Tube plate 23 Filling joint 24 Discharge joint 25 Discharge Piping

Claims (6)

  1. 　中空円筒状の強度部材を用いて構成されるフレームを備える宇宙航行体に設けられる宇宙航行体用の気蓄器であって、
    　前記強度部材の内部に、作動ガスを蓄圧可能な気蓄構造を有することを特徴とする宇宙航行体用の気蓄器。     An air reservoir for a spacecraft provided in a spacecraft including a frame configured using a hollow cylindrical strength member,
    An air accumulator for a spacecraft having an air accumulating structure capable of accumulating working gas inside the strength member.
  2. 　前記気蓄構造を有する前記強度部材は、内部洗浄後に前記作動ガスが蓄圧されることを特徴とする請求項１に記載の宇宙航行体用の気蓄器。 2. The space accumulator according to claim 1, wherein the strength member having the air accumulating structure accumulates the working gas after internal cleaning. 3.
  3. 　前記気蓄構造は、
    　前記強度部材の内部に設けられる対向する一対の管板と、
    　前記一方の管板に設けられ、前記一対の管板により区画された前記強度部材の内外において、前記作動ガスを流通させるための配管が接続される継手と、を有することを特徴とする請求項１または２に記載の宇宙航行体用の気蓄器。     The air storage structure is
    A pair of opposing tube plates provided inside the strength member;
    And a joint to which a pipe for circulating the working gas is connected inside and outside the strength member provided on the one tube sheet and partitioned by the pair of tube sheets. An air reservoir for a spacecraft according to 1 or 2.
  4. 　前記強度部材は、全周に亘って複数設けられ、
    　一方の前記強度部材の内部と、他方の前記強度部材の内部とを連通する連通管を、さらに備えることを特徴とする請求項１から３のいずれか１項に記載の宇宙航行体用の気蓄器。     A plurality of the strength members are provided over the entire circumference,
    The space navigation vehicle according to any one of claims 1 to 3, further comprising a communication pipe that communicates the inside of the one strength member and the inside of the other strength member. Accumulator.
  5. 　前記強度部材は、全周に亘って複数設けられ、
    　前記作動ガスが使用される設備を、さらに備え、
    　前記設備に最も近い前記強度部材に、前記気蓄構造を設けると共に、前記強度部材と前記設備とを配管により接続することを特徴とする請求項１から４のいずれか１項に記載の宇宙航行体用の気蓄器。     A plurality of the strength members are provided over the entire circumference,
    A facility for using the working gas;
    The space navigation according to any one of claims 1 to 4, wherein the strength member closest to the facility is provided with the air storage structure, and the strength member and the facility are connected by a pipe. Air reservoir for the body.
  6. 　中空円筒状の強度部材を用いて構成されるフレームと、
    　前記強度部材の内部に、作動ガスを蓄圧可能な気蓄構造を有する気蓄器と、を備えることを特徴とする宇宙航行体。     A frame configured using a hollow cylindrical strength member;
    A spacecraft comprising an air reservoir having an air storage structure capable of accumulating working gas inside the strength member.
PCT/JP2013/072921 2013-08-27 2013-08-27 Gas reservoir for aerospace vehicle, and aerospace vehicle WO2015029146A1 (en)

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JP2015533832A JP6121541B2 (en) 2013-08-27 2013-08-27 Air accumulator and spacecraft for spacecraft

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH02500100A (en) * 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 Expandable folding structure and method for manufacturing folding structure
JPH0381551A (en) * 1989-08-25 1991-04-05 Nissan Motor Co Ltd Apparatus for monitoring hydraulic oil of hydraulic oil pressure supply source for rocket
JP2000220795A (en) * 1999-02-01 2000-08-08 Mitsubishi Heavy Ind Ltd Gas replacement device for gas accumulator
JP2008189304A (en) * 2007-02-03 2008-08-21 Astrium Gmbh Cryogenic liquid and tank for storing storable fuel
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 (en) * 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 Expandable folding structure and method for manufacturing folding structure
JPH0381551A (en) * 1989-08-25 1991-04-05 Nissan Motor Co Ltd Apparatus for monitoring hydraulic oil of hydraulic oil pressure supply source for rocket
JP2000220795A (en) * 1999-02-01 2000-08-08 Mitsubishi Heavy Ind Ltd Gas replacement device for gas accumulator
US20100012788A1 (en) * 2005-09-07 2010-01-21 The Boeing Company Exchangeable Propellant Cartridge System
JP2008189304A (en) * 2007-02-03 2008-08-21 Astrium Gmbh Cryogenic liquid and tank for storing storable fuel

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