JP2018030556A - Spacecraft body structure and spacecraft body - Google Patents

Spacecraft body structure and spacecraft body Download PDF

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JP2018030556A
JP2018030556A JP2016166274A JP2016166274A JP2018030556A JP 2018030556 A JP2018030556 A JP 2018030556A JP 2016166274 A JP2016166274 A JP 2016166274A JP 2016166274 A JP2016166274 A JP 2016166274A JP 2018030556 A JP2018030556 A JP 2018030556A
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spacecraft
rib
rib structure
plate
structure according
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積利 佐藤
Tsumutoshi Sato
積利 佐藤
智博 戸丸
Tomohiro Tomaru
智博 戸丸
祐介 赤池
Yusuke Akaike
祐介 赤池
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Canon Electronics Inc
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Canon Electronics Inc
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Priority to JP2016166274A priority Critical patent/JP2018030556A/en
Priority to PCT/JP2017/024865 priority patent/WO2018008730A1/en
Priority to EP17824333.3A priority patent/EP3483461B1/en
Publication of JP2018030556A publication Critical patent/JP2018030556A/en
Priority to US16/233,639 priority patent/US11518550B2/en
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Abstract

PROBLEM TO BE SOLVED: To provide a spacecraft body structure which is relatively simply structured but yet secures a desired rigidity for the fuselage of the spacecraft while realizing lighter weight.SOLUTION: The present invention relates to a spacecraft body structure to be transported into aerospace, comprising: a pair of cylindrical barrels 201 coupled such that their internal spaces are communicated with each other in one direction; and reinforcement members 101 jointed to interior walls of respective barrels constituting the pair of cylindrical barrels and reinforcing the barrels. The reinforcement member includes: through holes 102 which penetrate, in a thickness direction, a plate-like member constituting the reinforcement member; and rib structure parts formed in a part of the plate-like member so as to respectively surround openings of the through holes at opening peripheral edge parts of the through holes.SELECTED DRAWING: Figure 1

Description

本発明は、宇宙空間へ輸送される宇宙機体構造物であって、互いの内部空間が一方向に連通するように連結される宇宙機体構造物及び宇宙機体に関するものである。   The present invention relates to a spacecraft structure transported to outer space, and to a spacecraft structure and a spacecraft that are connected so that their internal spaces communicate in one direction.

従来、航空機などの飛翔体では、機体の軽量化を図りつつ所望の強度が要求されており、飛翔体の胴体構造については、例えば、胴体プレートに対して複数の補強材や他の部材を組み合わせて接合することで補強した構造が提案されている（特許文献１参照）。   Conventionally, a flying object such as an aircraft has been required to have a desired strength while reducing the weight of the aircraft. For the fuselage structure of a flying object, for example, a plurality of reinforcing materials and other members are combined with the fuselage plate. A structure reinforced by joining them is proposed (see Patent Document 1).

特表２０１１−５００４１５号公報Special table 2011-500415 gazette

しかしながら、特許文献１の構成では、胴体プレートに対して複数の部材を組み合わせて補強しているため、構造が複雑化するだけでなく、質量の増加及び結合の負荷が発生して好ましくない。特に、宇宙機器の筐体構造に適用するためには、更なる軽量化と構造の簡略化が必要となる。   However, in the configuration of Patent Document 1, since a plurality of members are combined and reinforced with respect to the body plate, not only the structure becomes complicated, but also an increase in mass and a load of coupling occur, which is not preferable. In particular, in order to apply to the casing structure of space equipment, further weight reduction and simplification of the structure are required.

本発明は、比較的簡単な構造で、宇宙機体の胴体について所望の剛性を確保しつつ軽量化を併せて実現した宇宙機体構造物を提供するものである。   The present invention provides a spacecraft structure that has a relatively simple structure and achieves a reduction in weight while ensuring a desired rigidity of the fuselage of the spacecraft.

本発明は、宇宙空間へ輸送される宇宙機体構造物であって、互いの内部空間が一方向に連通するように連結される一対の円筒状胴体と、前記一対の円筒状胴体を構成する各胴体の内周面にそれぞれ接合されて前記胴体を補強する補強部材とを備え、前記補強部材は、前記補強部材を構成する板状部材を厚さ方向に貫通する貫通孔と、前記貫通孔の開口周縁部において前記貫通孔の開口を取り囲むように前記板状部材の一部で形成されたリブ構造部とを有することを特徴とする。   The present invention is a spacecraft structure transported to outer space, each of which constitutes a pair of cylindrical fuselages connected so that their internal spaces communicate in one direction, and the pair of cylindrical fuselage A reinforcing member that is joined to the inner peripheral surface of the body and reinforces the body, and the reinforcing member includes a through-hole that penetrates the plate-like member that constitutes the reinforcing member in the thickness direction, and the through-hole And a rib structure part formed by a part of the plate-like member so as to surround the opening of the through-hole in the opening peripheral part.

本発明によれば、比較的簡単な構造で、宇宙機体の胴体について所望の剛性を確保しつつ軽量化を併せて実現した宇宙機体構造物を提供できる。   According to the present invention, it is possible to provide a spacecraft structure that has a relatively simple structure and achieves a reduction in weight while ensuring a desired rigidity of the fuselage of the spacecraft.

本発明の一実施形態における宇宙機体構造物の分解斜視図。The disassembled perspective view of the spacecraft structure in one Embodiment of this invention. 本発明の一実施形態における宇宙機体構造物の結合図。The joint figure of the spacecraft structure in one embodiment of the present invention. 本発明の一実施形態における宇宙機体構造物の結合解除図。The joint release figure of the spacecraft structure in one Embodiment of this invention. 本発明の一実施形態における宇宙機体構造物の断面図。Sectional drawing of the spacecraft structure in one Embodiment of this invention. 本発明の一実施形態における宇宙機体構造物の断面図。Sectional drawing of the spacecraft structure in one Embodiment of this invention. 本発明の一実施形態における宇宙機体構造物の要部拡大図。The principal part enlarged view of the spacecraft structure in one Embodiment of this invention. 本発明の一実施形態における宇宙機体構造物の要部拡大図。The principal part enlarged view of the spacecraft structure in one Embodiment of this invention. 本発明の他の実施形態における宇宙機体構造物の分解斜視図。The disassembled perspective view of the spacecraft structure in other embodiment of this invention. 本発明の他の実施形態における宇宙機体構造物の要部拡大図。The principal part enlarged view of the spacecraft structure in other embodiment of this invention. 本発明の他の実施形態における宇宙機体構造物の要部拡大図。The principal part enlarged view of the spacecraft structure in other embodiment of this invention. 本発明の他の実施形態における宇宙機体構造物の斜視図。The perspective view of the spacecraft structure in other embodiment of this invention. 本発明の他の実施形態における宇宙機体構造物の斜視図。The perspective view of the spacecraft structure in other embodiment of this invention. 本発明の他の実施形態における宇宙機体構造物の斜視図。The perspective view of the spacecraft structure in other embodiment of this invention. 本発明の他の実施形態における宇宙機体構造物の例の斜視図。The perspective view of the example of the spacecraft structure in other embodiment of this invention. 本発明の他の実施形態における宇宙機体構造物の例の斜視図。The perspective view of the example of the spacecraft structure in other embodiment of this invention.

（第一実施形態）
本発明の第一実施形態に係る宇宙機体構造物について、図１から図１４を用いて説明する。
図１に示すように、本実施形態の宇宙機体構造物は、互いの内部空間が一方向に連通するように連結される一対の円筒状胴体２０１（以下、各胴体ともいう）の内周面２０１ａに対し、詳細は後述するが、補強部材としてリブ構造部材１０１がそれぞれ接合される。 (First embodiment)
The spacecraft structure according to the first embodiment of the present invention will be described with reference to FIGS.
As shown in FIG. 1, the spacecraft structure of the present embodiment has an inner peripheral surface of a pair of cylindrical bodies 201 (hereinafter also referred to as each body) connected so that their internal spaces communicate with each other in one direction. Although details will be described later on 201a, rib structural members 101 are joined as reinforcing members.

また、各胴体２０１の両端部には、リング形状の固定部材３０１がそれぞれ接合され、各胴体２０１にリブ構造部材１０１及び固定部材３０１を接合した第一構造物１、第二構造物２は、例えば、分離可能なバンド構造を有する結合部材３により相互連結されている（図２参照）。   In addition, ring-shaped fixing members 301 are joined to both ends of each body 201, and the first structure 1 and the second structure 2 in which the rib structure member 101 and the fixing member 301 are joined to each body 201, For example, they are interconnected by a connecting member 3 having a separable band structure (see FIG. 2).

そして、本実施形態では、図３に示すように、結合部材３の連結状態を解除することにより、第一構造物１、第二構造物２の完全分離が可能となる。   In the present embodiment, as shown in FIG. 3, the first structure 1 and the second structure 2 can be completely separated by releasing the connection state of the coupling member 3.

ここで、各胴体２０１は、例えば、本実施形態では、アルミ等の金属板により形成され、それぞれ同一の外形で設けられている。これら各胴体２０１は、例えば、一枚のアルミ板の両端を相互に連結することで作製できるが、他にも削り出し等により一体物として作製してもよい。なお、各胴体２０１を形成する材料は、上述した金属材料に限らず、炭素繊維等の他の材料でもよいし、異なる複数の材料を組み合わせた複合体で構成してもよい。   Here, for example, in the present embodiment, each body 201 is formed of a metal plate such as aluminum and is provided with the same outer shape. Each of the body 201 can be manufactured by, for example, connecting both ends of a single aluminum plate to each other, but may be manufactured as a single body by cutting or the like. The material forming each body 201 is not limited to the above-described metal material, but may be other materials such as carbon fiber, or may be composed of a composite of a plurality of different materials.

また、このような各胴体２０１の内周面２０１ａには、それぞれリブ構造部材１０１が接合される。これら各リブ構造部材１０１は、例えば、本実施形態では、２分割された一対の板状部材で構成される（図１参照）。これにより、各胴体２０１に対して各リブ構造部材１０１が接合し易くなる。   Further, the rib structure member 101 is joined to the inner peripheral surface 201a of each body 201 as described above. For example, in the present embodiment, each of the rib structural members 101 is composed of a pair of plate-like members divided into two (see FIG. 1). Thereby, each rib structure member 101 becomes easy to join to each body 201.

さらに、１つのリブ構造部材１０１には、図５，図６，図７に示すように、略矩形の貫通孔１０２が複数個設けられ、更にこの貫通孔１０２の開口周縁部には、リブ構造部１０３が一体的に設けられている。また、本実施形態では、各リブ構造部材１０１に設ける貫通孔１０２の形状を同一形状としているが、別の形状を組み合わせてもよい。   Furthermore, as shown in FIGS. 5, 6, and 7, one rib structure member 101 is provided with a plurality of substantially rectangular through holes 102, and a rib structure is provided at the opening peripheral edge of the through hole 102. The part 103 is provided integrally. Moreover, in this embodiment, although the shape of the through-hole 102 provided in each rib structure member 101 is made into the same shape, you may combine another shape.

ここで、本実施形態の各リブ構造部材１０１は、例えば、折り曲げ等の加工が可能な程度の厚みを有する板状部材に対し、その一部を打ち抜く又は成形して複数の貫通孔１０２を形成しつつ且つその貫通孔１０２の開口周縁部を一体的に絞り加工するなどして凸状に曲げ加工を施すことで、貫通孔１０２の開口周縁に沿って連続した環状のリブ構造部１０３をそれぞれ形成している。また、本実施形態のリブ構造部１０３は、リブ構造部材１０１の厚さ方向、すなわち、貫通孔１０２の貫通方向に平行な方向に凸状に立設されている。なお、このような各リブ構造部材１０１を構成する板状部材の厚みは、例えば、リブ構造部１０３の厚みよりも薄く形成してもよいが、同等の厚みで形成してもよい。   Here, each rib structure member 101 of the present embodiment forms, for example, a plurality of through holes 102 by punching or molding a part of a plate-like member having a thickness that can be processed such as bending. In addition, the annular rib structures 103 that are continuous along the opening periphery of the through hole 102 are formed by bending the opening periphery of the through hole 102 integrally, for example, by drawing it into a convex shape. Forming. Further, the rib structure portion 103 of the present embodiment is erected in a convex shape in the thickness direction of the rib structure member 101, that is, in a direction parallel to the through direction of the through hole 102. In addition, although the thickness of the plate-shaped member which comprises each such rib structure member 101 may be formed thinner than the thickness of the rib structure part 103, for example, you may form with equivalent thickness.

そして、本実施形態のリブ構造部材１０１は、全体として薄板状でありながら複数のリブ構造部１０３が均等に且つ等間隔で設けられることで、強度のばらつきがなく均等に剛性が高められ、更に貫通孔１０２を複数個設けているので、軽量化にも寄与する。すなわち、本実施形態では、貫通孔１０２の大きさにより重量を調整でき、リブ構造部１０３の高さや厚さ等によって強度を調整できる。   The rib structure member 101 of the present embodiment is a thin plate as a whole, and a plurality of rib structure portions 103 are provided equally and at equal intervals, so that the rigidity is evenly increased without variation in strength, and further, Since a plurality of through holes 102 are provided, it contributes to weight reduction. That is, in the present embodiment, the weight can be adjusted by the size of the through hole 102, and the strength can be adjusted by the height, thickness, etc. of the rib structure portion 103.

また、各リブ構造部１０３は、板状部材の短手方向に延びる略長方形の貫通孔１０２を取り囲むようにそれぞれ設けられているので、長辺のリブ構造部１０３ａと短辺のリブ構造部１０３ｂとを四隅のリブ構造部１０３ｃで連結することで一体的に構成される。   In addition, since each rib structure portion 103 is provided so as to surround the substantially rectangular through hole 102 extending in the short direction of the plate-like member, the long-side rib structure portion 103a and the short-side rib structure portion 103b are provided. Are connected integrally by the rib structure portions 103c at the four corners.

これにより、各リブ構造部材１０１を各胴体２０１に接合して一体化した状態では、長辺のリブ構造部１０３ａが各胴体２０１の連通方向における梁構造となる一方、短辺のリブ構造部１０３ａの両端が長辺のリブ構造１０３ａに連結されて各胴体２０１の周方向における梁構造となり、このようなリブ構造部１０３が各胴体２０１の周方向に複数併設され、更に長辺のリブ構造部１０３ａと短辺のリブ構造部１０３ｂとを四隅のリブ構造部１０３ｃで連結しているので、各構造物１，２の剛性を格段に向上することができる。   Thus, in a state where each rib structure member 101 is joined and integrated with each body 201, the long-side rib structure portion 103a becomes a beam structure in the communication direction of each body 201, while the short-side rib structure portion 103a. Both ends are connected to a rib structure 103a having a long side to form a beam structure in the circumferential direction of each body 201, and a plurality of such rib structures 103 are provided side by side in the circumferential direction of each body 201. 103a and the short-side rib structure portion 103b are connected by the rib structure portions 103c at the four corners, so that the rigidity of the structures 1 and 2 can be significantly improved.

また、本実施形態の各リブ構造部１０３は、四隅の形状がＲ形状、すなわち、弧形状の隅部で構成されるリブ構造部１０３ｃによって長辺のリブ構造部１０３ａと短辺のリブ構造部１０３ｂとを相互に連結した構造としている。これにより、外部応力が加わったときに各リブ構造部１０３の四隅において応力が集中するのを防ぐ、すなわち、応力分散が可能となる。なお、本発明は勿論これに限定されず、各リブ構造部１０３の四隅を直角に連結してもよいし、不連続となるように分断してもよい。   In addition, each rib structure portion 103 of the present embodiment has a rib structure portion 103a having a long side and a rib structure portion having a short side by a rib structure portion 103c having four corners having an R shape, that is, an arc-shaped corner portion. 103b is connected to each other. This prevents stress from concentrating at the four corners of each rib structure portion 103 when external stress is applied, that is, enables stress distribution. Of course, the present invention is not limited to this, and the four corners of each rib structure portion 103 may be connected at right angles or may be divided so as to be discontinuous.

ここで、図４には、上述したリブ構造部材１０１により各胴体２０１が補強された宇宙機体構造物の断面図を示す。図４に示すように、結合部材３により相互連結された第一構造物１及び第二構造物２（以下、各構造物ともいう）は、各両端部の開口縁部に対して固定部材３０１がそれぞれ挿嵌されている。このため、各固定部材３０１も補強部材としての機能を果たす。   Here, FIG. 4 shows a cross-sectional view of the spacecraft structure in which each fuselage 201 is reinforced by the rib structure member 101 described above. As shown in FIG. 4, the first structure 1 and the second structure 2 (hereinafter also referred to as each structure) interconnected by the coupling member 3 are fixed members 301 with respect to the opening edge portions at both ends. Are inserted. For this reason, each fixing member 301 also functions as a reinforcing member.

また、結合部材３は、第一構造物１及び第二構造物２のうち連結側の端部同士が固定部材３０１で構成され、当接した各固定部材３０１を結合部材３により径方向内側に締め付け、これにより、各構造物１，２を相互に結合している。   Further, the coupling member 3 includes the first structure 1 and the second structure 2, and the coupling-side ends thereof are configured by the fixing members 301. By tightening, the structures 1 and 2 are coupled to each other.

すなわち、結合部材３は、図４に示すように、第一構造物１の固定部材３０１と第二構造物２の固定部材３０１とを突き合わせた状態で、当接した各固定部材３０１を径方向外側から締め付け保持しているので、実質的に隙間のない結合が可能である。   That is, as shown in FIG. 4, the coupling member 3, in the state where the fixing member 301 of the first structure 1 and the fixing member 301 of the second structure 2 are in contact with each other, Since it is clamped and held from the outside, it is possible to bond substantially without gaps.

これにより、各構造物１，２は結合部材３によって強固に実質的に一体化した状態となり、その状態から結合部材３を解除すれば各構造物１，２が相互に分離可能となる。   Thereby, each structure 1 and 2 will be in the state firmly integrated substantially by the coupling member 3, and if the coupling member 3 is cancelled | released from the state, each structure 1 and 2 will become mutually separable.

さらに、各構造物１，２は、それぞれ、上述したリブ構造部材１０１のうちリブ構造部１０３が突出する側とは反対側の面がその内周面２０１ａに接合される。これにより、各構造物１，２においては、径方向内側に向かって各リブ構造部材１０１のリブ構造部１０３が突出する構造になる。   Further, in each of the structures 1 and 2, the surface of the rib structure member 101 that is opposite to the side from which the rib structure portion 103 protrudes is joined to the inner peripheral surface 201a. Thereby, in each structure 1, 2, it becomes a structure where the rib structure part 103 of each rib structure member 101 protrudes toward radial inside.

また、これら各リブ構造部材１０１は、例えば、本実施形態では、各胴体２０１のうち各固定部材３０１が挿嵌された部分以外の各固定部材３０１で挟まれた部分に対し、固定部材３０１とは別別に接合される。これら各固定部材３０１とリブ構造部材１０１とは、お互いに接合しなくてもよいが、例えば、溶接や接着剤等により相互に接合してもよい。   In addition, for example, in the present embodiment, each of the rib structural members 101 has a fixing member 301 and a portion sandwiched between the fixing members 301 other than the portion in which the fixing members 301 are inserted in the body 201. Are joined separately. The fixing members 301 and the rib structure member 101 do not have to be joined to each other, but may be joined to each other by welding or an adhesive, for example.

さらに、各リブ構造部材１０１は、図７に示すように、リブ構造部１０３の貫通孔１０２を除く各胴体２０１との接合面において、例えば、接着剤または溶接等による結合、またはボルト・ナットまたはリベット等による締結により、各胴体２０１と結合される。   Further, as shown in FIG. 7, each rib structure member 101 is connected to each body 201 except for the through hole 102 of the rib structure portion 103 by, for example, bonding by an adhesive or welding, or a bolt / nut or Each body 201 is coupled by fastening with rivets or the like.

このように、本実施形態の宇宙機体構造物は、リブ構造部材１０１及び固定部材３０１により補強された各胴体２０１で各構造物１，２をそれぞれ構成し、各構造物１，２を結合部材３によって分離可能に連結している。   As described above, in the spacecraft structure of the present embodiment, the structures 1 and 2 are configured by the fuselage 201 reinforced by the rib structure member 101 and the fixing member 301, and the structures 1 and 2 are coupled members. 3 are separably connected.

このため、各構造物１，２は、結合状態では相互に補強関係が相乗的に作用して全体としての強度も高められており、その状態から結合部材３により結合が解除されて分離されたとしても、互いにリブ構造部材１０１及び固定部材３０１により個別に補強されているので、分離後も各構造物１，２は十分な剛性をそれぞれ維持できる。   For this reason, the structures 1 and 2 are combined with each other in a coupled state, and the overall strength is enhanced by the synergistic reinforcement relationship. However, since the rib structural member 101 and the fixing member 301 are individually reinforced, the structures 1 and 2 can maintain sufficient rigidity even after separation.

また、本実施形態では、各構造物１，２において２分割されたリブ構造部材１０１を接合するようにしたので、各胴体２０１に対してリブ構造部材１０１を挿入配置して接合し易くなっている。なお、２分割された各リブ構造部材１０１は、各胴体２０１内において、連結しなくてもよいが、剛性を高めるために、それぞれを連結してもよい。なお、本実施形態では、リブ構造部材１０１を２分割したが、３分割以上にしてもよいし、分割しなくてもよい。   Further, in this embodiment, since the rib structural member 101 divided into two in each of the structures 1 and 2 is joined, the rib structural member 101 is easily inserted into the body 201 and joined. Yes. The rib structural members 101 divided into two do not need to be connected in each body 201, but may be connected to increase rigidity. In the present embodiment, the rib structural member 101 is divided into two parts, but it may be divided into three parts or more, or may not be divided.

さらに、本実施形態では、上述したように各胴体２０１を各リブ構造部材１０１により簡単な構成で軽量、且つ効果的に補強できるので、例えば、各胴体２０１の厚みをより薄くしたり、あるいは、リブ構造部材１０１を構成する板状部材の厚みをより薄くしたり、もしくは、貫通孔１０２及びリブ構造部１０３の数や形状、大きさや位置等を適宜変更したりすることで、所望の強度を確保しながら、更なる軽量化を図ることもできる。   Furthermore, in the present embodiment, as described above, each body 201 can be reinforced by each rib structure member 101 with a simple structure, and can be reinforced effectively. For example, the thickness of each body 201 can be made thinner, or By reducing the thickness of the plate-like member constituting the rib structure member 101, or by appropriately changing the number, shape, size, position, etc. of the through holes 102 and the rib structure portion 103, the desired strength can be obtained. While securing, further weight reduction can be achieved.

（他の実施形態）
以上、本発明を第一実施形態に基づいて詳細に説明したが、本発明は上述した第一実施形態に限定されるものではない。
上述した第一実施形態では、リブ構造部１０３を長辺のリブ構造部１０３ａと短辺のリブ構造部１０３ｂとで構成したが、本発明は勿論これに限定されず、例えば、長辺のリブ構造部だけでリブ構造部を構成するようにしてもよいし、短辺のリブ構造部だけでリブ構造部を構成するようにしてもよい。 (Other embodiments)
As mentioned above, although this invention was demonstrated in detail based on 1st embodiment, this invention is not limited to 1st embodiment mentioned above.
In the first embodiment described above, the rib structure portion 103 is composed of the long-side rib structure portion 103a and the short-side rib structure portion 103b. However, the present invention is of course not limited to this. A rib structure part may be comprised only by a structure part, and a rib structure part may be comprised only by the rib structure part of a short side.

また、上述した第一実施形態では、１枚の板状部材に複数個のリブ構造部１０３を設けた構造を例示して説明したが、図８に示すように、リブ構造部１０３を持つ複数個のリブ構造部材１０１を各胴体２０１に接合するようにしてもよい。この場合、リブ構造部１０３を有する複数のリブ構造部材１０１は、図９に示すように、各々が胴体２０１と結合されるが隣接するリブ構造部材１０１同士は接着剤または溶接等による結合またはボルト・ナット、またはリベット等による締結をしなくとも成形が可能である。   In the first embodiment described above, a structure in which a plurality of rib structures 103 are provided on one plate-like member has been described as an example. However, as shown in FIG. A single rib structure member 101 may be joined to each body 201. In this case, as shown in FIG. 9, each of the plurality of rib structure members 101 having the rib structure portion 103 is coupled to the body 201, but the adjacent rib structure members 101 are coupled or bolted by an adhesive or welding. -Molding is possible without fastening with nuts or rivets.

また、上述した第一実施形態では、各構造物１，２をそれぞれ同一の構成として説明したが、本発明は勿論これに限定されず、それぞれ別々の構成としてもよく、この場合には、少なくとも一方の構造物について本発明の構成を適用すればよい。すなわち、本発明は、互いに分離可能に接合される構造物１，２を有する宇宙機体構造物に限定されず、例えば、分離不可能な胴体の補強構造に適用してもよい。   In the first embodiment described above, the structures 1 and 2 have been described as having the same configuration. However, the present invention is of course not limited thereto, and may be configured separately. In this case, at least What is necessary is just to apply the structure of this invention about one structure. That is, the present invention is not limited to the spacecraft structure having the structures 1 and 2 that are joined to each other so as to be separable from each other, and may be applied to, for example, a body reinforcing structure that cannot be separated.

さらに、上述した第一実施形態では、リブ構造部材１０１の厚さ方向に平行な方向（直角）に凸状のリブ構造部１０３を設けた構造について説明したが、本発明は勿論これに限定されず、例えば、図１０（ａ）及び図１０（ｂ）に示すようにリブ構造部１０３をリブ構造部材１０１の厚さ方向（貫通孔１０２の貫通方向）に対して交差する方向に折れ曲がった構造としてもよいが、図１０（ａ）に示すようにリブ構造部材１０１のリブ構造部１０３が凸となる側の一方面とリブ構造部１０３とで成す角が鋭角、すなわち、リブ構造部１３５がリブ構造部材１０１の一方面側に傾いた構造とすることで、リブ構造部材１０１の強度を高めることができる。   Furthermore, in the first embodiment described above, the structure in which the convex rib structure portion 103 is provided in a direction (right angle) parallel to the thickness direction of the rib structure member 101 has been described, but the present invention is of course limited to this. For example, as shown in FIGS. 10A and 10B, the rib structure 103 is bent in a direction intersecting with the thickness direction of the rib structure member 101 (through direction of the through hole 102). However, as shown in FIG. 10 (a), the angle formed between the rib structure portion 103 of the rib structure member 101 and the rib structure portion 103 on one side where the rib structure portion 103 is convex is acute, that is, the rib structure portion 135 is By setting it as the structure inclined to the one surface side of the rib structure member 101, the intensity | strength of the rib structure member 101 can be raised.

ここで、上述した第一実施形態の宇宙機体構造物は、図１１に示すように各構造物１，２を結合部材３によって連結した状態から、図１２に示す結合部材３が有する結合ピン５を火薬やモータ、手動等によって連結解除し、図１３に示すように各構造物１，２の切り離しが可能となる。このような連結・分離の機構は、図１４及び図１５に示すような２つの人工衛星７，８を連結した宇宙機体における継手構造の分離装置の構造に適用できる他、多段ロケット等の宇宙機体の分離装置の構造（継手構造）などにも展開可能である。   Here, in the spacecraft structure of the first embodiment described above, the coupling pin 5 included in the coupling member 3 shown in FIG. 12 from the state in which the structures 1 and 2 are coupled by the coupling member 3 as shown in FIG. Can be disconnected by means of gunpowder, motor, manual operation, etc., and the structures 1 and 2 can be separated as shown in FIG. Such a connection / separation mechanism can be applied to the structure of a joint structure separation device in a spacecraft in which two artificial satellites 7 and 8 are connected as shown in FIGS. 14 and 15, and a spacecraft such as a multistage rocket. It can also be applied to the structure of a separating device (joint structure).

Claims (7)

宇宙空間へ輸送される宇宙機体構造物であって、
互いの内部空間が一方向に連通するように連結される一対の円筒状胴体と、
前記一対の円筒状胴体を構成する各胴体の内周面にそれぞれ接合されて前記胴体を補強する補強部材と、を備え、
前記補強部材は、前記補強部材を構成する板状部材を厚さ方向に貫通する貫通孔と、前記貫通孔の開口周縁部において前記貫通孔の開口を取り囲むように前記板状部材の一部で形成されたリブ構造部とを有することを特徴とする宇宙機体構造物。 A spacecraft structure transported to outer space,
A pair of cylindrical bodies connected so that their internal spaces communicate in one direction;
A reinforcing member that reinforces the body by being joined to the inner peripheral surface of each body constituting the pair of cylindrical bodies,
The reinforcing member is a part of the plate-like member so as to surround the opening of the through-hole in the through-hole penetrating the plate-like member constituting the reinforcing member in the thickness direction and the opening peripheral edge of the through-hole. A spacecraft structure characterized by having a rib structure portion formed. 前記補強部材には、複数の前記貫通孔が等間隔で設けられたことを特徴とする請求項１に記載の宇宙機体構造物。   The spacecraft structure according to claim 1, wherein the reinforcing member is provided with a plurality of through holes at equal intervals. 前記リブ構造部は、前記貫通孔の開口を取り囲むように連続的に設けられた環状の凸部により構成されることを特徴とする請求項１又は２に記載の宇宙機体構造物。   3. The spacecraft structure according to claim 1, wherein the rib structure portion includes an annular convex portion that is continuously provided so as to surround the opening of the through hole. 前記リブ構造部の四隅は、弧形状の隅部で連結されていることを特徴とする請求項３に記載の宇宙機体構造物。   The spacecraft structure according to claim 3, wherein the four corners of the rib structure portion are connected by arc-shaped corner portions. 前記一対の円筒状胴体の厚みは、前記板状部材の厚みより薄いことを特徴とする請求項１乃至４のいずれか１項に記載の宇宙機体構造物。   The spacecraft structure according to any one of claims 1 to 4, wherein a thickness of the pair of cylindrical bodies is thinner than a thickness of the plate member. 前記補強部材は、複数の板状部材を環状に連結することで構成されたことを特徴とする請求項１乃至５のいずれか１項に記載の宇宙機体構造物。   The spacecraft structure according to any one of claims 1 to 5, wherein the reinforcing member is configured by connecting a plurality of plate-like members in an annular shape. 請求項１乃至６のいずれか１項に記載の宇宙機体構造物を分離装置として備えた宇宙機体。

A spacecraft comprising the spacecraft structure according to any one of claims 1 to 6 as a separation device.

JP2016166274A 2016-07-06 2016-08-26 Spacecraft body structure and spacecraft body Pending JP2018030556A (en)

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JP2016166274A JP2018030556A (en) 2016-08-26 2016-08-26 Spacecraft body structure and spacecraft body
PCT/JP2017/024865 WO2018008730A1 (en) 2016-07-06 2017-07-06 Uncoupling device
EP17824333.3A EP3483461B1 (en) 2016-07-06 2017-07-06 Uncoupling device
US16/233,639 US11518550B2 (en) 2016-07-06 2018-12-27 Coupling/uncoupling device

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2021535857A (en) * 2018-05-24 2021-12-23 ザ ヨーロピアン ユニオン、リプレゼンテッド バイ ザ ヨーロピアン コミッションThe European Union, represented by the European Commission Concept of efficient satellite structure for single or stacked launches

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2021535857A (en) * 2018-05-24 2021-12-23 ザ ヨーロピアン ユニオン、リプレゼンテッド バイ ザ ヨーロピアン コミッションThe European Union, represented by the European Commission Concept of efficient satellite structure for single or stacked launches
JP7145975B2 (en) 2018-05-24 2022-10-03 ザ ヨーロピアン ユニオン、リプレゼンテッド バイ ザ ヨーロピアン コミッション Efficient satellite architecture concepts for single or stacked multiple launches
US11827384B2 (en) 2018-05-24 2023-11-28 The European Union, Represented By The European Commission Efficient satellite structure concept for single or stacking multiple launches

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