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WO2019138788A1 - Structure déployable et son procédé de déploiement - Google Patents

Structure déployable et son procédé de déploiement Download PDF

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Publication number
WO2019138788A1
WO2019138788A1 PCT/JP2018/046315 JP2018046315W WO2019138788A1 WO 2019138788 A1 WO2019138788 A1 WO 2019138788A1 JP 2018046315 W JP2018046315 W JP 2018046315W WO 2019138788 A1 WO2019138788 A1 WO 2019138788A1
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WO
WIPO (PCT)
Prior art keywords
nozzle
distorted
deployment
alloy
shape
Prior art date
Application number
PCT/JP2018/046315
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English (en)
Japanese (ja)
Inventor
伸介 竹内
佐藤　英一
裕史 戸部
Original Assignee
国立研究開発法人宇宙航空研究開発機構
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 国立研究開発法人宇宙航空研究開発機構 filed Critical 国立研究開発法人宇宙航空研究開発機構
Priority to JP2019564357A priority Critical patent/JP7132634B2/ja
Publication of WO2019138788A1 publication Critical patent/WO2019138788A1/fr

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • 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

Definitions

  • the present invention relates to an unfolding structure and an unfolding method thereof.
  • the deployment structure is generally configured to expand the deployment portion. However, when the deployment portion expands, the area and volume after deployment expand more than before deployment, and the accommodation after deployment decreases.
  • a rocket nozzle having a larger aperture ratio at the nozzle end is preferable.
  • Patent Document 1 discloses a nozzle adopting a configuration in which the nozzle is geometrically complicated and folded to fold the entire nozzle. As a result, the aperture ratio is large, and a compact nozzle shape can be realized at the time of accommodation.
  • crease marks remain in the rocket nozzle, the fire from the rocket engine during launch or navigation may cause melting due to local heating. In addition, crease marks cause a decrease in buckling strength.
  • An object of the present invention is to provide an unfolded structure which can be made into a compact shape before being deployed or after being unfolded and which has no crease marks. Also provided is a method of housing and deploying the deployment structure.
  • the present invention has the following configurations (1) to (7).
  • a developed structure that includes a superelastic alloy and is capable of containing a developed portion within the elastic deformation range of the superelastic alloy.
  • the unfolding structure according to (1) wherein the unfolding structure is a rocket nozzle.
  • the rocket nozzle includes a first portion on the front end side and a second portion on the rear end side, the first portion is made of a fiber reinforced composite material or a heat-resistant alloy, and is the expansion portion
  • the expanded structure according to (2), wherein the second portion is made of the superelastic alloy.
  • the diameter of the virtual circle circumscribing the rear end after distortion is stored so as to be smaller than the diameter of the circumscribed circle on the front end side before distortion, and the distortion state is corrected by the distortion fixing member
  • the expansion method according to (6), wherein the expanded structure in the distorted state is expanded to an original shape by removing the distorted shape fixing member.
  • ADVANTAGE OF THE INVENTION According to this invention, it can be made into a compact shape at the time of accommodation after expansion
  • FIG. 5 is a diagram showing changes in atomic position in superelasticity and shape memory. It is a figure which shows the stress-strain curve at the time of 10.8ks annealing and water cooling of Ti-4.5Al-3V-2Fe-2Mo alloy at 1073K.
  • FIG. 6 shows the shape and dimensions of a 1 ⁇ 4 model of a rocket nozzle.
  • FIG. 1 is a schematic cross-sectional view showing a rocket motor 1 equipped with a nozzle according to the present embodiment.
  • the nozzle 10 of the rocket motor 1 according to the present embodiment includes a portion of the fixed nozzle 11 and a portion of the distortable nozzle 12, and the distortable nozzle 12 is a portion on the rear end side of the fixed nozzle 11 (a lower portion of FIG. Is attached and fixed.
  • the distortable nozzle 12 has a frusto-conical shape, and the inner diameter of the rear end portion of the fixed nozzle 11 and the tip end portion (upper part in FIG. 1) of the distortable nozzle 12 is the same.
  • the fixed nozzle 11 is made of, for example, a fiber-reinforced composite material or a heat-resistant alloy as in a normal nozzle.
  • the distortable nozzle 12 is made of a superelastic alloy.
  • the superelastic alloy which comprises the distortable nozzle 12 (deployment part) is demonstrated.
  • the nozzle which can be made into a normal metal and which can be distorted, it is possible to make it distorted like the after-mentioned by making the thickness thin enough.
  • it is difficult to maintain the properties such as strength and heat resistance required for a rocket nozzle, for example, by using only a thin metal.
  • it must be thick enough to give the nozzle the necessary strength for ordinary metals, but it is difficult to distort with such thick metals, and plastic deformation occurs even if it can be distorted. , It is difficult to restore the original state by its own elastic force.
  • the superelastic alloy can be restored to its original state by its own elastic force by being deformed within the elastic deformation range.
  • the term "superelasticity” refers to a phenomenon in which deformation caused by applying stress to an alloy exhibiting thermoelastic martensitic transformation undergoes shape recovery without heating after unloading.
  • FIG. 4 the change in atomic position in the slip deformation is shown at the top as a reference, and the change in atomic position in superelasticity is shown in the middle, and the change in atom position in the shape memory effect is shown at the bottom.
  • Superelasticity changes to a shape memory effect when the temperature goes below the transformation temperature.
  • the superelastic alloy placed just above the transformation temperature is in the matrix state under no stress.
  • stress-induced martensitic transformation occurs, martensite variants in the direction of stress relaxation are preferentially generated and grown, and the shape of the entire material changes.
  • unloading if the parent phase is originally at a stable temperature, reverse transformation proceeds only by unloading and the shape is recovered. Thus, the property of superelasticity is expressed.
  • the superelastic alloy can be used without particular limitation, but for example, a Ni-Ti alloy, a Cu-Zn alloy, a Ni-Al alloy, etc. can be used.
  • the Ni-Ti-based alloy include Ni-Ti-based alloys of 49 to 52 atomic percent Ni.
  • a Cu—Zn-based alloy for example, a Cu—Zn alloy of 38.5 to 41.5 wt% Zn is exemplified.
  • As the Ni-Al based alloy for example, a Ni-Al alloy of 36 to 38 atomic% Al is exemplified.
  • these materials need to be thin sheet materials.
  • the superelastic alloy in addition to the Ni-Ti alloy, Cu-Zn alloy, Ni-Al alloy, etc. described above, heating to a near ⁇ -Ti alloy for about 1 to 3 hours at about 600 to 1000 ° C. Then, it may be immersed in water and subjected to heat treatment such as rapid cooling to normal temperature to use a thin plate material having developed a superelastic property. More preferably, an alloy obtained by annealing / water cooling a Ti-4.5Al-3V-2Fe-2Mo alloy (SP-700 manufactured by JFE Steel) can be used as the superelastic alloy.
  • SP-700 manufactured by JFE Steel can be used as the superelastic alloy.
  • FIG. 5 is a diagram showing a stress-strain curve when Ti-4.5Al-3V-2Fe-2Mo alloy is subjected to 10.8 ks annealing / water cooling at 1073K.
  • the stress-strain curve of FIG. 5 after applying a strain of 3% at room temperature, the residual strain remains at about 1%, indicating a superelasticity having an elastic recovery strain of about 2%.
  • Such superelastic superelastic alloys can be used to construct the deployed structures of the present invention.
  • the developed structure of the present invention can also use a superelastic alloy with better characteristics.
  • the annealing temperature is preferably 1063 K or more.
  • the annealing temperature is preferably 1083 K or less. From these, the preferable range of the annealing temperature was 1063 K to 1083 K.
  • FIG. 2 is a view showing the shape of a rocket nozzle according to an embodiment of the present invention.
  • the mesh is arranged on the surface of the nozzle so that the state of deformation can be expressed.
  • FIG. 2A is a view showing the rocket nozzle before elastic deformation.
  • FIGS. 2B to 2E show the rocket nozzle 12 and show the process of distortion.
  • FIG. 2B shows that a part (left end area and right end area) is deformed inward by applying a force from the outside to part of the outer surface of the rocket nozzle 12 (left end area and right end area).
  • the opposite side (back side) of the paper also has to be deformed by applying a force from the outside to a part of the outer surface of the rocket nozzle 12.
  • FIG. 2C in addition to the external force of the outer surface of the rocket nozzle 12 (left end region and right end region) being applied from the outside, force is also applied to the central region between the left end region and the right end region, It shows a state in which the amount of deformation is larger than that in FIG. 2B.
  • the reverse side (back side) of the paper also has to be deformed by applying a force from the outside to a part of the outer surface of the rocket nozzle 12.
  • the deformation amount is larger than that in FIG. 2C, and the deformation ratio is large in the left end region, the center region, and the right end region.
  • FIG. 2F shows a state in which distortion is completed because the deformation amount is larger than in FIGS. 2D and 2E, and the dent ratio in the left end region, the center region, and the right end region is increased.
  • the diameter of an imaginary circle circumscribing the plurality of apexes on the upper side (the rear end side of the nozzle) in FIG. 2F is smaller than the diameter of the circle on the lower side (the tip side of the nozzle) in FIG.
  • the nozzle 12 of FIG. 2F can expand
  • the expansion method for storing or expanding the expansion structure of the present embodiment is (A) distorting the unfolded structure within an elastic deformation range; (B) fixing the unfolded structure in a distorted state by a distorted state fixing member; Is a deployment method comprising
  • the unfolded structure in the distorted state can be developed into the original shape.
  • FIG. 3 As shown in FIG. 3, only the tip of the truncated cone shaped nozzle 12 (deployed portion) is fixed to the substrate, and the nozzle 12 is distorted using a jig 20.
  • the nozzle 12 is fixed such that its front end side is fixed to the substrate with its front end side down, and its rear end side is on top.
  • the shape of the jig 20 body may be a cylindrical shape whose diameter is larger than the rear end of the nozzle 12.
  • each pillar has two holes for inserting the rod-like members 21 from the outside. ing.
  • the nozzle 12 can be most easily folded by providing a hole in each of the six columnar parts, the number of places where the holes are provided is not limited thereto.
  • the rod-like member 21 is inserted into the hole of each columnar portion from the outside. Then, each end of the rod-like member 21 at each portion is brought into contact with the vicinity of the rear end of the nozzle 12, and each portion of the nozzle 12 in contact with the tip of the rod-like member 21 is distorted uniformly. Push the bar-like member of the inside slightly little by little.
  • the outer surface of the nozzle 12 can be uniformly pushed inward and distorted from directions at equal intervals in the circumferential direction perpendicular to the axis of the nozzle.
  • the nozzle has a star-like shape which is pressed from six directions.
  • FIG. 6 is a diagram showing the shape and dimensions of a rocket nozzle model.
  • the rocket nozzle model is assumed to be applied to a real machine, and its 1 ⁇ 4 scale has a truncated cone shape with a lower ⁇ (small diameter) of 120 mm, an upper ⁇ (large diameter) of 168 mm, and a height of 66.5 mm.
  • the rolling direction is indicated by an RD (rolling direction)
  • the rolling perpendicular direction is indicated by an arrow of a TD (transverse direction).
  • plate thickness while it is necessary to have a thickness that withstands circumferential stress and axial buckling due to the internal pressure of the nozzle, strain during storage increases in proportion to the plate thickness, so it is necessary to make it as thin as possible .
  • the elastic recovery strain is large, the strain at the time of storage can be increased.
  • the above-mentioned Ti-4.5Al-3V-2Fe-2Mo alloy which has been subjected to 10.8ks annealing and water cooling at 1073 K, has an elastic recovery strain of about 2%, assuming that it is used, the above-mentioned folded shape
  • the plate thickness was calculated in consideration of the distortion at the time of storage and the nozzle internal pressure, the required minimum safety factor was secured, and it was 60 ⁇ m. This corresponds to 0.25 mm in a real machine.
  • the knotting cord is wound around the rear end of the nozzle 12 from the gap of the columnar part of the jig 20 one round or several rounds if necessary to connect the both ends.
  • This knotted cord is an example of the distorted shape fixing member of the present invention. Thereby, the distorted state of the nozzle 12 is fixed.
  • a knotted string a plastic tie wrap, a metal wire, etc. can be used as a knotted string.
  • the elastic force of the nozzle 12 itself immediately deploys to the original perfect truncated cone shape, for example, by removing the distorted shape fixing member (in the case of a knotted string, simply cutting). be able to.
  • the time required for the above-described rocket nozzle scale model deployment was less than one second. From this, it is understood that even a rocket nozzle of actual dimensions deploys within 1 second. This is a sufficiently fast time to deploy and eject the nozzle in space.
  • the deployable structure of the present invention is not limited to the rocket nozzle.
  • the present invention can be applied to a deployment structure such as an antenna for space deployment, which is devised to be distorted, housed small on the ground, transported to space, and deployed there based on its own elasticity.
  • the expansion method of the present invention is not limited to the method of storing using the jig 20 as described above, and for example, the expanded structure may be distorted using a mold.

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)

Abstract

La présente invention concerne une structure déployable qui peut présenter une forme compacte tout en étant stockée avant ou après un déploiement et qui ne garde pas de lignes de pliage. La buse (10) d'un moteur-fusée (1) est constituée d'une buse fixe (11) et d'une buse déformable (12) et la buse déformable (12) est attachée et fixée à l'extrémité arrière (côté inférieur sur la Fig. 1) de la buse fixe (11). La buse déformable (12) présente une forme de cône tronqué et l'extrémité arrière de la buse fixe (11) et l'extrémité avant (côté supérieur sur la Fig. 1) de la buse déformable (12) présentent sensiblement le même diamètre. La buse fixe (11) est composée d'un matériau similaire à celui utilisé dans des buses régulières, telles qu'un matériau composite renforcé par des fibres. La buse déformable (12) est composée d'un alliage superélastique.
PCT/JP2018/046315 2018-01-11 2018-12-17 Structure déployable et son procédé de déploiement WO2019138788A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP2019564357A JP7132634B2 (ja) 2018-01-11 2018-12-17 展開構造体及びその展開方法

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2018-002848 2018-01-11
JP2018002848 2018-01-11

Publications (1)

Publication Number Publication Date
WO2019138788A1 true WO2019138788A1 (fr) 2019-07-18

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PCT/JP2018/046315 WO2019138788A1 (fr) 2018-01-11 2018-12-17 Structure déployable et son procédé de déploiement

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Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6277135A (ja) * 1985-08-21 1987-04-09 サイオコール　コーポレイション ロケツトエンジン用ノズル出口構造体およびその製造方法
JPH08509899A (ja) * 1994-04-01 1996-10-22 プログラフト メディカル，インコーポレイテッド 自己拡張可能なステントおよびステント−グラフトならびにそれらの使用方法
JP2003531673A (ja) * 2000-05-03 2003-10-28 アドバンスド、カーディオバスキュラー、システムズ、インコーポレーテッド 脈管内ステント
JP2006521865A (ja) * 2003-04-02 2006-09-28 ボストン サイエンティフィック リミテッド 塞栓摘出術用器具

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6505795B1 (en) 2000-09-05 2003-01-14 Hughes Electronics Corporation Application of carbon fiber mesh for space and airborne platform applications
WO2013113913A1 (fr) 2012-02-03 2013-08-08 Ion Beam Applications S.A. Structure magnétique pour un cyclotron compact isochrone supraconducteur

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6277135A (ja) * 1985-08-21 1987-04-09 サイオコール　コーポレイション ロケツトエンジン用ノズル出口構造体およびその製造方法
JPH08509899A (ja) * 1994-04-01 1996-10-22 プログラフト メディカル，インコーポレイテッド 自己拡張可能なステントおよびステント−グラフトならびにそれらの使用方法
JP2003531673A (ja) * 2000-05-03 2003-10-28 アドバンスド、カーディオバスキュラー、システムズ、インコーポレーテッド 脈管内ステント
JP2006521865A (ja) * 2003-04-02 2006-09-28 ボストン サイエンティフィック リミテッド 塞栓摘出術用器具

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JPWO2019138788A1 (ja) 2020-12-24
JP7132634B2 (ja) 2022-09-07

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