JP7002228B2 - Space equipment adapters and space transport aircraft and artificial satellites - Google Patents

Description

The present invention relates to a space equipment adapter that supports a space device (for example, an artificial satellite, etc.) inside the space transport device for outer space, and a transport machine or an artificial satellite equipped with the space device adapter.

Various fixed structures have been proposed for adapters for space equipment. As an example, a method for constructing a spacecraft and an adapter used for a spacecraft have been proposed, for example, a structure in which a carrier rocket and a load such as an artificial satellite can be attached by the adapter (see Patent Document 1).

Special Table 2005-521590

In an adapter structure for space equipment such as Patent Document 1, if the structure is complicated in pursuit of high rigidity, it becomes difficult to reduce the weight, and conversely, if the pursuit of weight reduction is too much, it becomes difficult to secure the rigidity. It is difficult to achieve both high rigidity and light weight.

The present invention provides a space equipment adapter, a space transporter, and an artificial satellite that can realize weight reduction while ensuring desired rigidity.

The present invention is a space equipment adapter that supports space equipment inside a transport machine for outer space, and is configured by joining a plurality of divisions divided in the circumferential direction in an annular shape, and each of the divisions is configured. A through hole that penetrates the plate-shaped member constituting the divided body in the thickness direction, and a rib formed by a part of the plate-shaped member so as to surround the opening of the through hole at the peripheral edge of the opening of the through hole. It is characterized by having a structural portion.

According to the present invention, it is possible to provide a space equipment adapter, a space transporter, and an artificial satellite that realizes weight reduction while ensuring desired rigidity.

The coupling diagram of the example of the space equipment adapter in one Embodiment of this invention. The coupling diagram of the example of the space equipment adapter in one Embodiment of this invention. FIG. 6 is a cross-sectional view of a coupling diagram of an example of a space equipment adapter according to an embodiment of the present invention. The coupling diagram of the example of the space equipment adapter in one Embodiment of this invention. The development view of the space equipment adapter in one Embodiment of this invention. The development view of the space equipment adapter in one Embodiment of this invention. An enlarged view of a main part of a space equipment adapter according to an embodiment of the present invention. Sectional drawing of the space equipment adapter in one Embodiment of this invention. An enlarged view of a main part of a space equipment adapter according to an embodiment of the present invention. An enlarged view of a main part of a space equipment adapter according to an embodiment of the present invention. A perspective view and a sectional view of a space equipment adapter according to another embodiment of the present invention. Enlarged sectional view of a main part of a space equipment adapter according to another embodiment of the present invention. The perspective view of the space equipment adapter in another embodiment of this invention. Exploded perspective view of the space equipment adapter in another embodiment of the present invention. The side view which shows the coupling state of the space equipment adapter in another embodiment of this invention.

Hereinafter, the present invention will be described in detail based on the embodiments.
(First Embodiment)
The space equipment adapter according to the first embodiment of the present invention will be described with reference to FIGS. 1 to 10.

As shown in FIG. 1, one end of the space equipment adapter (hereinafter, also referred to as an adapter) 100 of the present embodiment is fixed to the main body 1a side of the space transport machine 1 such as a rocket, and is fixed to the main body 1a of the space transport machine 1. On the other hand, it is used for the connection structure of the connection portion with the artificial satellite 2 mounted separably.

Specifically, the adapter 100 of the present embodiment is composed of a first structure 10 connected to the artificial satellite 2 and a second structure 20 connected to the main body 1a of the space transporter 1. The structure 10 and the second structure 20 are integrally (inseparable) bonded.

Here, the first structure 10 has a tubular shape of a substantially polygonal pyramid (a substantially hexagonal pyramid in the present embodiment) that forms an internal space as a whole, with respect to the bottom portion 11 of the hexagon on the space transporter 1 side. The upper surface on the artificial satellite 2 side has a hexagonal shape that is relatively smaller than the bottom portion 11. That is, the side wall of the first structure 10 is composed of a polyhedral structure having an inclined surface inclined from the artificial satellite 2 side toward the space transporter 1 side.

The first structure 10 of the present embodiment has a hexagonal pyramid-shaped three-dimensional structure to increase the rigidity as a whole, but may be, for example, a triangular pyramid, a quadrangular pyramid, or another polygonal pyramid. Details of the configuration of the first structure 10 will be described later.

On the other hand, in the present embodiment, for example, the second structure 20 has a hexagonal through hole 210 corresponding to the internal space of the first structure 10 corresponding to the connection shape with the space transporter 1 to outer space. Is provided, and the whole is provided in a ring shape. The bottom 11 side of the first structure 10 described above is connected to the upper end 20a of the ring-shaped second structure 20. The first structure 10 and the second structure 20 can be joined by, for example, bonding or welding.

Further, by forming the outer shape of the second structure 20 into a ring shape, as shown in FIG. 3, the end portion of the dome-shaped motor case (fuel case) M or the like as the main body configuration on the space transporter 1 side. The second structure 20 can be attached so as to surround and accommodate the inside. That is, the second structure 20 is attached so as to overlap the end of the motor case M on the space transporter 1 side. As a result, the end portion of the motor case M is inserted into the internal space of the first structure 10 and the second structure 20, so that the total length of the space transport machine 1 can be shortened by that amount, or the artificial satellite 2 or the like can be used. The mounting space can be expanded.

The adapter 100 having such a configuration may be attached to the main body 1a side of the space transport machine 1 by integrating the first structure 10 and the second structure 20 in advance, or the main body 1a of the space transport machine 1. After fixing the second structure 20 on the side, the first structure 10 may be mounted on the second structure 20. Further, an electronic device A such as a circuit board is mounted on the side wall of the first structure 10 of the adapter 100.

Further, since the artificial satellite 2 is finally separated from the space transport machine 1, a separation device is interposed between the artificial satellite 2 and the adapter 100 or between the adapter 100 and the main body of the space transport machine 1. .. In the present embodiment, the separation device 30 is arranged between the artificial satellite 2 and the adapter 100. As a result, after the artificial satellite 2 is separated, the adapter 100 remains on the main body 1a side of the space transport machine 1.

In any case, the adapter 100 of the present embodiment is connected to the space transporter 1 for outer space via the second structure 20 until the artificial satellite 2 is separated, and is artificially connected via the first structure 10. Supports loads such as satellite 2 or other space equipment.

Here, the configuration of the first structure 10 constituting a part of the adapter 100 of the present embodiment described above will be described in detail.

As shown in FIG. 5, in the first structure 10 of the present embodiment, the side surface portions constituting the six side walls radially with respect to each side of the hexagonal upper surface portion 12 on which the artificial satellite 2 is mounted are divided. It is integrally provided as a 13 and has a structure developed into one plate-shaped member. That is, the connecting portion between the upper surface portion 12 and the side surface portion (divided body 13) becomes a bent portion 12a and becomes a non-divided portion, but the ends of the adjacent divided bodies 13 are separated from each other, and the ends thereof have a three-dimensional structure. When they are joined to each other.

That is, in this one plate-shaped member, each divided body 13 is bent at the bent portion 12a forming each side of the upper surface portion 12, and the adjacent side surface portions (divided bodies 13) are joined to each other. As shown in FIGS. 1 to 4, 7, and 8, a substantially hexagonal pyramid-shaped three-dimensional structure is formed in which the bottom portion 11 facing the upper surface portion 12 is a hexagonal opening.

The first structure 10 is formed of, for example, in the present embodiment, a plate-shaped member made of a metal material such as aluminum. Such a plate-shaped member can be manufactured, for example, by partially bending and joining a structure composed of a single aluminum plate as shown in FIG. 5, but the divided body is divided as shown in FIG. May be combined and produced. Alternatively, it may be manufactured as an integral piece by carving or the like. Further, the material forming the divided body 13 is not limited to the metal material described above, but may be another material such as carbon fiber, or may be composed of a composite obtained by combining a plurality of different materials.

Further, in the present embodiment, each of the above-mentioned divided bodies 13, that is, each side surface portion as a three-dimensional structure is provided with a through hole 130 penetrating in the thickness direction, and the upper surface portion 12 is also provided with a thickness. A through hole 120 penetrating in the direction is provided. In the present embodiment, the through hole 130 is formed small in the portion provided by the electronic device A on the side wall of the first structure 10. Further, a rib structure portion 135 protruding in the thickness direction (penetration direction) is provided at the opening peripheral edge portion of the through hole 130 provided in the divided body 13. The rib structure portion 135 of the present embodiment is vertically erected in the thickness direction of the divided body 13, that is, in the direction parallel to the penetrating direction of the through hole 130. Hereinafter, the divided body 13 forming such a rib structure portion 135 will be described.

As described above, each of the divided bodies 13 is provided with a substantially rectangular (here, trapezoidal) through hole 130 as shown in FIGS. 1 and 2, and the opening peripheral edge of the through hole 130 is annular. The rib structure portion 135 is integrally provided. Further, in the present embodiment, the shape of the through hole 130 provided in each of the divided bodies 13 is the same in the set of the divided bodies 13 facing each other in the penetrating direction, but they may have different structures.

Here, each of the divided bodies 13 of the present embodiment is formed by punching or molding a part of a plate-shaped member having a thickness capable of processing such as bending to form a through hole 130. By performing a convex bending process such as by integrally drawing the opening peripheral edge of the through hole 130, a continuous annular rib structure 135 is formed along the opening peripheral edge of the through hole 130. There is. The thickness of the plate-shaped member constituting each of the divided bodies 13 may be formed to be thinner than the thickness of the rib structure portion 135, but may be formed to have the same thickness.

The divided body 13 of the present embodiment has a thin plate shape as a whole, but the plurality of divided bodies 13 are connected in an annular shape, so that the rigidity is uniformly increased without variation in strength, and the through hole 130 is further formed. Since a plurality of holes 120 are provided and the upper surface portion 12 is also provided with through holes 120, it also contributes to weight reduction. That is, in the present embodiment, the weight can be adjusted by the size of the through holes 130 and 120, and the strength can be adjusted by the height, thickness, and the like of the rib structure portion 135. Further, in the present embodiment, since the outer shape of the divided body 13 is trapezoidal, the shape of the through hole 130 and the rib structure portion 135 is also trapezoidal. Can be enhanced.

Further, as shown in FIG. 9, each rib structure portion 135 is provided so as to surround the substantially trapezoidal through hole 130, so that the rib structure portions 135a and 135b on the short side and the long side parallel to each other are provided. The rib structure portions 135c on the hypotenuse connecting the short side and the rib structure portions 135a and 135b on the long side are integrally connected by the rib structure portions 135d at the four corners.

As a result, in a state where the divided bodies 13 are joined in an annular shape and integrated like the first structure 10, a substantially hexagonal pyramid structure is formed. Therefore, when the artificial satellite 2 is mounted on the upper surface portion 12, the artificial satellite 2 is mounted. The weight and the like are supported by each of the divided bodies 13 that serve as the side walls. At this time, since the rib structure portion 135 is provided in each of the divided bodies 13, the rib structure portion 135 is reinforced, and further, since the divided bodies 13 are connected in an annular shape, the rib structure portion 135 as a whole is reinforced. ..

Specifically, as shown in FIG. 9, the rib structure portion 135c on the diagonal side provided in each division body 13 has a beam structure along the connecting portion (joining portion) 13a of the division body 13 on the side wall of the first structure 10. On the other hand, both ends of the rib structure portions 135a and 135b on the short side and the long side are connected to the rib structure portion 135c on the diagonal side to form a beam structure in the circumferential direction of the first structure 10, and such a rib structure portion 135 is formed. Since a plurality of the first structure portions 1 are juxtaposed in the circumferential direction and the four corners of the rib structure portions 135 are connected to each other by the rib structure portions 135d, the rigidity of the first structure portion 10 can be significantly improved.

Further, in each rib structure portion 135 of the present embodiment, the shape of the four corners is R-shaped, that is, the rib structure portion 135d composed of the corners of the arc shape causes the rib structure portions 135a and 135b on the short side and the long side and the hypotenuse. It has a structure in which the rib structure portion 135c of the above is connected to each other. This makes it possible to prevent the stress from concentrating at the four corners of each rib structure portion 135 when an external stress is applied, that is, to disperse the stress. The present invention is, of course, not limited to this, and the four corners of each rib structure portion 135 may be connected at right angles or may be divided so as to be discontinuous.

As described above, the adapter 100 of the present embodiment is integrated with the first structure 10 having the rib structure portion 135 and the first structure 10 connected to the second structure 20, and this is integrated into the artificial satellite 2. By adopting it in the connection structure between the space transport machine 1 and the space transport machine 1, it is possible to realize weight reduction while ensuring desired rigidity. That is, the desired rigidity was mainly realized by providing the plurality of rib structure portions 135 in the first structure 10, and the weight reduction was mainly achieved by providing the plurality of through holes 130 in the first structure 10. In addition, the rib structure portion 135 is provided to reduce the thickness of the plate-shaped member constituting the first structure 10. Therefore, the adapter 100 of the present embodiment can realize a structure capable of achieving both desired rigidity and weight reduction.

In the first structure 10, the through hole 130 shown in FIG. 4 has an advantage that, for example, not only the weight is reduced but also the area arranged in the internal space of the first structure 10 is easily accessed. There is also.

Further, in the present embodiment, as shown in FIG. 10, since the second structure 20 employs an annular member having a plurality of holes 201a and 201b, the weight is reduced. In the present embodiment, such a second structure 20 is formed of, for example, a metal material such as aluminum. However, in order to reduce the weight while maintaining rigidity, the second structure 20 is not limited to the above-mentioned metal material, but carbon fiber or the like. It may be another material, or it may be composed of a composite obtained by combining a plurality of different materials.

Further, in the adapter 100 of the present embodiment, the first structure 10 and the second structure 20 are separately configured, but of course, the present invention is not limited to this, and the adapter 100 is integrated with the same material such as metal casting or carbon fiber. It may be configured by molding. Even in this case, by forming the rib structure portion 135 and the through hole 130 at least in the first structure 10, it is possible to reduce the weight while ensuring the desired rigidity.

(Other embodiments)
Although the present invention has been described in detail based on the first embodiment, the present invention is not limited to the above-mentioned first embodiment. For example, in the above-mentioned first embodiment, the rib structure portion 135 is composed of the rib structure portions 135a and 135b on the short side and the long side, the rib structure portion 135c on the hypotenuse side, and the rib structure portion 135d at the four corners. Of course, the present invention is not limited to this, and for example, the rib structure portion may be formed only by the rib structure portion on the hypotenuse side.

Further, as shown in FIG. 11, in the through hole 120 provided in the upper surface portion 12 of the first structure 10 of the first embodiment described above, the rib structure 125 having the opening peripheral portion convex inward is provided. It may be provided in the same manner as the rib structure 135 provided in the divided body 13 in the first embodiment described above. As a result, the strength of the first structure 10 is further increased.

Further, in the first embodiment described above, a structure in which the rib structure portion 135 having a convex shape is provided in a direction parallel to the thickness direction (perpendicular) of the divided body 13 has been described, but the present invention is, of course, not limited to this. For example, as shown in FIGS. 12 (a) and 12 (b), the rib structure portion 135 may be bent in a direction intersecting the thickness direction of the divided body 13 (penetration direction of the through hole 130). However, as shown in FIG. 12A, the angle formed by one surface of the split body 13 on the convex side and the rib structure 135 is a sharp angle, that is, the rib structure 135 is the split body 13. By making the structure inclined to one side, the strength of the divided body 13 can be increased.

The present invention is not limited to the adapter (space equipment adapter) described above, but is also applicable to a space transporter equipped with such an adapter or an artificial satellite provided with an adapter.

(Second Embodiment)
FIG. 13 shows the space equipment adapter according to the second embodiment of the present invention, and FIG. 14 shows a perspective exploded view thereof. Since the basic structure in this embodiment is the same as that in the first embodiment, only the differences will be described and the others will be omitted. The same reference numerals as those in the first embodiment may be used as reference numerals in the drawings.

FIG. 13 shows a perspective view of the space equipment adapter according to the present embodiment. The space adapter according to this embodiment is intended to be applied to a carrier rocket or the like having a larger diameter than that of the first embodiment, and has a plurality of rib structure portions 135 in order to secure the rigidity of the divided body 13 and improve accessibility. It is provided.

The divided body 13 has a connecting portion 301 equivalent to that of the second structure 20 connected to the space transport machine in the first embodiment, and is designed to be lightweight while ensuring rigidity.

It is preferable to provide the through hole 130 in a large size in order to reduce the weight, but it is difficult to secure the rigidity. Therefore, in the second embodiment shown in FIG. 13, the through hole 130 having a triangular structure provided with the rib structure portion 135 is provided. Is provided so that the outer peripheral shape thereof is substantially triangular along the outer shape of the divided body 13, and the support portion 302 for ensuring the rigidity is formed between the through holes 130 thereof to obtain the desired rigidity. Is secured.

The through hole 131 is a hole provided for weight reduction, and is provided at a position corresponding to a central portion with respect to the three through holes 130 having a low contribution to strength. In order to secure a certain width of the support portion 302, it is preferable to install the support portion 302 in a triangular shape in which the direction of the triangle is opposite to that of the through hole 130.

As in the second embodiment shown in FIG. 13, it is essential that the frequency in the axial direction generated during the operation of the carrier rocket and the natural frequency of the space equipment adapter do not match, and generally, the space equipment adapter is used. It is preferable to increase the natural frequency of the universe, and a cone shape is suitable for weight reduction and ensuring a high natural frequency in the axial direction.

Further, in the above-mentioned cone shape, avionics, a thruster, a propellant storage tank and the like can be mounted in the internal space.

Further, for the connection between the upper surface body 12 and the divided body 13 and the divided bodies 13 shown above, a connection method having a desired strength such as rivet, welding (spot welding, TIG welding, etc.) and adhesion may be used. In this embodiment, it is fixed by a rivet 310.

Further, when the strength is insufficient by the above-mentioned connection method, it is preferable to arbitrarily use the above-mentioned connection method, such as the combined use of rivets and adhesives.

FIG. 15 shows an example of a space device to which the space device adapter in the present embodiment is applied. The artificial satellite 2 is mounted on the upper part of the adapter 100 via the separation device 30, and the main body 1a of the space transport machine 1 such as a rocket is connected to the lower part of the adapter 100 via the connection portion 301. ..

As shown in FIG. 15, a part of the propellant storage tank M of the space transport device 1 is housed inside the adapter 100. In the present embodiment, the electronic device A such as avionics is housed in the main body 1a of the space transport device 1, but the electronic device A may be provided in the space inside the adapter 100.

Further, in the present embodiment, a predetermined space is provided between the upper end portion of the adapter 100 and the propellant storage tank M. As shown in FIG. 15, a part of the pipe P connecting the propellant storage tank M and the thruster T is provided in this space. Further, in the present embodiment, the inclination angle formed by the divided body 13 is set so that a predetermined gap is formed from the upper portion of the pipe to the upper end portion of the adapter 100.

Further, as described above, a predetermined space may be provided above the adapter 100 for the purpose of not matching the natural frequency of the space transport device 1 with the natural frequency of the adapter 100, while the space transport device 1 may be provided. When the natural frequency of the adapter 100 and the natural frequency of the adapter 100 do not match, the divided body 13 is tilted so that the upper end of the container represented by the propellant storage tank M or the like is close to the upper end of the adapter 100. You may adjust the corners.

13 Split 130 Through hole 135 Rib structure 100 Adapter

Claims (6)

A space equipment adapter that supports space equipment inside a transport aircraft to outer space.
It is composed of a plurality of divided bodies divided in the circumferential direction and joined in an annular shape.
Each of the above-mentioned divided bodies
A through hole that penetrates the plate-shaped member constituting the divided body in the thickness direction,
A space equipment adapter comprising a rib structure portion formed of a part of the plate-shaped member so as to surround the opening of the through hole at the peripheral portion of the opening of the through hole. A first structure in which the plurality of divided bodies are connected in a cylindrical shape and the space equipment is detachably mounted.
The space equipment adapter according to claim 1, wherein the first structure and a second structure connecting the transport aircraft to each other are configured. The first structure has a polyhedral structure in which one surface is formed by each of the divided bodies.
2. The second structure is characterized in that the end portion of the first structure is connected and has a ring shape provided so as to surround the end portion on the transport aircraft side. The listed space equipment adapter. The space equipment adapter according to any one of claims 1 to 3 is fixed to the main body of a space transport machine that transports an artificial satellite to outer space, and the artificial satellite is detachably connected to the main body. A space transport machine characterized by being used for a connecting structure. The space equipment adapter according to any one of claims 1 to 3 is provided, and the space equipment adapter is mounted on a connection structure that is separably connected to the main body of the space transport machine. Satellite. The space equipment adapter according to any one of claims 1 to 3, wherein the through holes are provided in a plurality of outer peripheral shapes so as to follow the outer shape of the divided body.

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