JP6461781B2 - Payload fairing - Google Patents

Description

  The present invention relates to a payload fairing that is provided in a launch vehicle and accommodates a payload such as an artificial satellite.

  The payload fairing is usually provided at the tip (head) of the launch rocket and accommodates a payload such as an artificial satellite. Payload fairing has the role of protecting the internal payload from various external influences (for example, loud sound or vibration during launch, or frictional heat during flight in the atmosphere). Payload fairing is also referred to as satellite fairing, especially if the payload is a satellite.

  Taking the case where the payload is an artificial satellite as an example, the artificial satellite is launched in a state of being accommodated in a satellite fairing, and is transported to a target altitude and orbit by a launch rocket. If the artificial satellite reaches a sufficient altitude during the transfer, the satellite fairing is usually separated into two fairing pieces and separated from the rocket head. The separated fairing pieces fall to a safe area of the surface of the earth, such as the sea.

  Payload fairing is required not only to have durability to protect the internal payload from external influences, but also to reduce the weight of the payload fairing in the rocket launchable weight as much as possible (weight reduction). From the viewpoint of achieving both durability and weight reduction, for example, as shown in Patent Document 1, a sandwich panel using a honeycomb core as a base material (honeycomb sandwich panel) is often employed for payload fairing. .

  Each fairing piece is composed of one or more honeycomb sandwich panels. A honeycomb sandwich panel is generally manufactured by bonding a plurality of honeycomb cores with a water-impermeable adhesive and further bonding a surface material on both sides. Since the honeycomb core has a structure in which a plurality of hollow cells are connected, the honeycomb core itself joined by a non-permeable adhesive also has a structure in which the hollow cells are connected.

  As described above, the payload fairing can be separated into a plurality of fairing pieces, and each fairing piece is composed of one or more honeycomb sandwich panels. Here, although the plurality of hollow cells constituting the honeycomb core are connected to each other, the individual hollow cells are not normally connected to each other. Therefore, in the fairing piece (that is, inside the honeycomb core), air is held by a number of connected hollow cells. Therefore, after the fairing piece falls on the sea and lands, it basically floats on the water.

  Since the floating fairing piece has a concern of affecting the navigation of the ship, it is currently collected by, for example, a collection ship. However, recovery by a recovery ship is expensive and recovery may be difficult if the weather is bad.

  Thus, for example, on pages 2 to 3 of Non-Patent Document 1, a configuration is proposed in which slots are provided in the hollow cells constituting the honeycomb core in order to submerge the separated fairing pieces in the sea. According to this configuration, seawater enters the honeycomb core through the slots, and air inside the core is released through the slots. Therefore, it is possible to submerge the floating fairing piece and suppress the influence on the navigation of the ship.

JP 2010-105455 A

Seiji NISHIO, Naruhiko CHIKU, Makihito OZAKI, Yoichi HORIE, Yoshihiko KOMADA, Atsushi HIRANO, Takayuki IMOTO and Kyoichi UI, "Preliminary Design of the payload fairing for the Epsilon Launch Vehicle", The 28th International Symposium on Space Technology and Science (28th ISTS ), June 5 to 12, 2011, ID: 2011-g-05

  As described above, the configuration in which the communication portion such as the slot is provided in the hollow cell is very effective from the viewpoint of introducing seawater into a large number of hollow cells that are the internal structure of the fairing piece (honeycomb sandwich panel). However, from the viewpoint of submerging the entire fairing piece, in addition to introducing seawater into individual hollow cells, it is necessary to consider introducing seawater well into the honeycomb core constituted by these hollow cells. . In other words, if seawater cannot be introduced satisfactorily from the outside to the inside of the honeycomb core, seawater cannot be satisfactorily introduced into many hollow cells constituting the honeycomb core. Therefore, for payload fairing, there is room for further technical consideration regarding submergence.

  The present invention has been made to solve such problems, and an object of the present invention is to provide a payload fairing that can submerge a fairing piece that has fallen on the sea even better.

  In order to solve the above-described problem, a payload fairing according to the present invention is configured by detachably connecting a plurality of fairing pieces, and has a storage space for storing a payload therein, and the fairing piece Is composed of a honeycomb sandwich panel having a base material formed by bonding a plurality of honeycomb cores with an adhesive layer, and the honeycomb core has a communication portion for communicating a plurality of hollow cells constituting the honeycomb core with each other Is provided, and the adhesive layer is provided with a gap that allows the hollow cells to communicate with each other between the bonded honeycomb cores.

  According to the said structure, a fairing piece is comprised by the honeycomb sandwich panel and the honeycomb sandwich panel is comprised by joining several honeycomb cores. And each honeycomb core is mutually joined by the adhesive bond layer which has a space | gap part. The hollow cells constituting the honeycomb core are provided with communication portions (for example, slots) that communicate with each other. Thus, when the payload fairing reaches the water, water enters the inside of an arbitrary honeycomb core through the communication portion, and further, water is introduced into the inside of the adjacent honeycomb core through the gap portion. Become. Therefore, since continuous water permeation and exhaust between adjacent honeycomb cores are possible, the fairing pieces can be effectively submerged and the fairing pieces can be submerged more quickly.

  In the payload fairing having the above-described configuration, the gap may be configured such that an adhesive is not partially filled in a region serving as a joint between the honeycomb cores.

  Moreover, in the payload fairing of the said structure, the structure formed by embedding a hollow member in the said adhesive bond layer may be sufficient.

  Further, the payload fairing having the above-described configuration may be configured such that a blocking member that prevents an adhesive from flowing into a region that becomes the gap is provided around the gap.

  Further, in the payload fairing having the above-described configuration, when the gap is filled with the adhesive in a region serving as a joint portion between the honeycomb cores, or an adhesive filled in the region serving as the joint portion is used. The structure formed when making it harden | cure may be sufficient.

  Further, in the payload fairing having the above-described configuration, the honeycomb sandwich panel is provided with an opening for inundation exhaust communicating with the inside at a position to be an inner surface of the fairing piece or a joint portion between the fairing pieces. It may be a configuration.

  In this invention, there exists an effect that the payload fairing which can submerge the fairing piece which fell on the sea more satisfactorily by the above structure can be provided.

(A)-(C) are typical side views which respectively show the typical structural example of the satellite fairing which is an example of the payload fairing which concerns on embodiment of this invention. (A) is a schematic perspective view showing a schematic configuration in which the honeycomb sandwich panel constituting the satellite fairing shown in FIGS. 1 (A) to (C) is flattened, and (B) is shown in (A). It is a schematic diagram explaining the internal structure of a honeycomb sandwich panel and the structure of the opening part for submerged exhaust. It is a schematic perspective view which shows typically the typical structure (it is comprised by one honeycomb sandwich panel) of the fairing piece which comprises the satellite fairing shown to FIG. 1 (A), and the submerged condition. FIG. 2 is a schematic perspective view schematically showing a typical configuration (configured by a plurality of honeycomb sandwich panels) of a fairing piece constituting the satellite fairing shown in FIG. (A) is typical sectional drawing which shows schematic structure of the panel coupling | bonding frame with which the fairing piece shown in FIG. 4 is provided, (B) is a schematic part which shows the other structural example of the panel coupling | bonding frame shown in FIG. It is a perspective view. It is a perspective view explaining the typical structural example of the honeycomb core which comprises a honeycomb sandwich panel, and the opening part for immersion exhaust. (A) is a schematic diagram illustrating an example in which seawater enters the inside of the honeycomb core from the submerged exhaust opening shown in FIG. 2 (B) based on the longitudinal cross-sectional structure of the honeycomb sandwich panel. FIG. 5 is a schematic diagram illustrating an example in which seawater intrusion is hindered in the core splice portion shown in FIG. 3 or FIG. 4 based on the longitudinal sectional structure of the honeycomb sandwich panel, and (C) is an example shown in (B). It is a schematic diagram demonstrated based on a cross-sectional structure. (A)-(C) are the schematic diagrams explaining the structural example of the space | gap part provided in the adhesive bond layer of the core splice part shown in FIG. 3 or FIG. 4 based on the cross-sectional structure of a honeycomb sandwich panel. (A) and (B) are schematic diagrams illustrating an example of forming the adhesive layer shown in FIGS. 8 (A) and (B) based on the cross-sectional structure of a honeycomb sandwich panel. (A), (B) is a schematic diagram explaining the intrusion of seawater and the discharge of air when the fairing piece shown in FIG. 3 or FIG. 4 is submerged.

  Hereinafter, preferred embodiments of the present invention will be described with reference to the drawings. In the following description, the same or corresponding elements are denoted by the same reference symbols throughout the drawings, and redundant description thereof is omitted.

[Payload fairing]
In the present embodiment, as a typical example of payload fairing according to the present invention, satellite fairing will be exemplified to specifically describe the present invention. First, a typical satellite fairing configuration will be specifically described with reference to FIGS. 1A to 1C and FIGS. 2A and 2B.

  As shown in FIG. 1 (A), FIG. 1 (B), or FIG. 1 (C), the satellite fairing 10A, 10B, or 10C has a substantially conical cylindrical shape, and is located at the head of a launch rocket (not shown). Attached and has a storage space inside. In this storage space, an artificial satellite 40A or 40B (illustrated by a dotted line in the figure) as a payload is stored.

  A satellite fairing 10A shown in FIG. 1 (A) is composed of three parts of a nose cap part 11, a nose cone part 12, and a cylinder part 13 in order from the front end. The nose cap portion 11 is located at the front end of the satellite fairing 10A and is formed in a substantially hemispherical shape. The nose cone portion 12 is located on the rear side when viewed from the nose cap portion 11 and is formed in a substantially conical shape. The cylinder part 13 is located on the rear side when viewed from the nose cone part 12 and is formed in a substantially cylindrical shape.

  A satellite fairing 10B shown in FIG. 1B has a nose cap part 11, a nose cone part 12, a cylinder part 13 and a rear cone part 14 in order from the front end. The configuration of the nose cap part 11, the nose cone part 12 and the cylinder part 13 is the same as that of the satellite fairing 10A, but the rear cone part 14 is located on the rear side when viewed from the cylinder part 13 and has an outer diameter larger than that of the cylinder part 13. Is formed in an inverted truncated cone shape.

  A satellite fairing 10C shown in FIG. 1C has a nose cap part 11, a nose cone part 12, a cylinder part 13 and a rear cone part 15 in order from the front end. The configuration of the nose cap part 11, the nose cone part 12 and the cylinder part 13 is the same as that of the satellite fairing 10A or 10B. The rear cone portion 15 is located on the rear side when viewed from the cylinder portion 13, similarly to the rear cone portion 14 of the satellite fairing 10 </ b> B, but is formed in a truncated cone shape having an outer diameter larger than that of the cylinder portion 13.

  Each of the satellite fairings 10A to 10C is configured by connecting two fairing pieces 110 to each other in a separable manner. The fairing pieces 110 are formed in a shape that substantially divides the satellite fairings 10A to 10C in the longitudinal direction (longitudinal direction), and these fairing pieces 110 are detachably coupled by a separation mechanism (not shown).

  In the satellite fairing 10 </ b> A, one fairing piece 110 a is composed of a nose cap part 11, a vertical half of the nose cone part 12, and a vertical half of the cylinder part 13, and the other fairing piece 110 b is the nose cone part 12. It consists of a vertical half and a vertical half of the cylinder part 13. In the satellite fairing 10B, one fairing piece 110a is composed of a nose cap part 11, a vertical half of the nose cone part 12, a vertical half of the cylinder part 13, and a vertical half of the rear cone part 14, and the other fairing piece 110b. Is composed of a vertical half of the nose cone portion 12, a vertical half of the cylinder portion 13, and a vertical half of the rear cone portion 14. In the satellite fairing 10C, one fairing piece 110a is composed of a nose cap portion 11, a vertical half of the nose cone portion 12, a vertical half of the cylinder portion 13, and a vertical half of the rear cone portion 15, and the other fairing piece 110b. Is composed of a vertical half of the nose cone portion 12, a vertical half of the cylinder portion 13, and a vertical half of the rear cone portion 15.

  In the satellite fairings 10A to 10C shown in FIGS. 1A to 1C, the nose cap portion 11 is configured to remain on one fairing piece 110a, but the satellite fairings 10A to 10C. This configuration is not limited to this, and the nose cap portion 11 may also be divided into two halves and may constitute a part of the other fairing piece 110b.

  The fairing piece 110 (that is, the satellite fairings 10A to 10C) is configured by a honeycomb sandwich panel 20 (hereinafter, abbreviated as “honeycomb panel 20” as appropriate) as schematically shown in FIG. The honeycomb panel 20 has a sandwich structure in which a skin material 22 as a surface material is bonded to both surfaces of a honeycomb core 21 as a base material. Further, the honeycomb panel 20 is provided with submerged exhaust openings 25A and 25B communicating with the honeycomb core 21 inside. The actual honeycomb panel 20 includes a curved structure or the like according to the specific shape of the fairing piece 110 (that is, the specific shape of the payload fairing) (see FIG. 3 or FIG. 4). In FIG. 2 (A), the structure of the honeycomb panel 20 is schematically illustrated in a flat plate shape for convenience.

  In the honeycomb panel 20 having a schematic configuration shown in FIG. 2A, a plurality of (three in FIG. 2A) honeycomb cores 21 are joined to form a single base material. The skin material 22 (two in the example of the surface of FIG. 2 (A)) is connected, and the single surface material is comprised. In other words, in the honeycomb panel 20, a base material composed of a plurality of honeycomb cores 21 is sandwiched between double-sided layers composed of a plurality of skin materials 22.

  A separation mechanism housing 31 is attached to the panel end portion 26 of the honeycomb panel 20. As will be described later, the fairing piece coupling portion 111 is constituted by the panel end portion 26 and the separation mechanism housing 31. The separation mechanism housing 31 is a constituent member for attaching a separation mechanism for detachably connecting the fairing pieces 110 to the fairing piece coupling portion 111, and is attached to the panel end portion 26 by a fastener member such as a bolt (not shown). ing.

  In the honeycomb panel 20, a portion where the honeycomb cores 21 are connected is the core splice portion 23, and a portion where the skin materials 22 are connected is the skin splice portion 24. The core splice part 23 is configured by joining the end faces of the honeycomb core 21 with an adhesive. Further, as shown in FIG. 2A, for example, the skin splice portion 24 is formed by stacking the same material as that of the skin material 22 with an adhesive or a fastening member (bolt or the like). Although not shown, it is configured by directly overlapping and joining the end portions of the skin material 22. In addition, the specific structure of the core splice part 23 and the skin splice part 24 is not specifically limited, What is necessary is just to be comprised using a well-known method or material in the field | area of a spacecraft.

  For example, as shown in FIG. 2B, the honeycomb core 21 has a configuration in which a plurality of hollow cells 211 having a predetermined cross-sectional shape are arranged in parallel in a planar shape. In the configuration shown in FIG. 2B, the hollow cell 211 has a hexagonal core whose hollow cross-sectional shape is a hexagon. In addition, the hollow cell 211 is provided with, for example, a slot 210 as a communication portion that allows adjacent hollow cells 211 to communicate with each other. Thereby, the many hollow cells 211 constituting the honeycomb core 21 are communicated as a whole.

  In addition, the specific structure of the honeycomb core 21 is not specifically limited, What is necessary is just a structure provided with the hollow cell 211 which has a well-known cross-sectional shape. As a specific hollow cell 211, for example, a hexagonal core as shown in FIG. 2 (B), a flexible core (registered trademark) whose hollow cross-sectional shape is T-shaped, a hollow cross-sectional shape is a hexagonal cross section. Examples thereof include an OX core (registered trademark) having a cross section that extends in one direction, and a double flexible core (registered trademark) having a hollow cross section that has a substantially star-shaped cross section.

  As described above, the submerged exhaust openings 25 </ b> A and 25 </ b> B are openings that communicate with the honeycomb core 21 inside the honeycomb panel 20, and are formed on the inner surface side of the fairing piece 110 or the side surface of the honeycomb panel 20. The submerged exhaust openings 25A and 25B are configured to expose the hollow cells 211 of the honeycomb core 21. For example, as shown in FIG. For example, the submerged exhaust opening 25B is provided in a frame body such as the separation mechanism housing 31 as shown in FIG. The specific configuration of the submerged exhaust openings 25A and 25B will be described in detail later. In the present embodiment, as described later, the submerged exhaust opening 25 </ b> B also serves as the bolt hole 35.

[Fairing piece]
Next, an example of a specific configuration of the fairing piece 110 constituting the satellite fairings 10A to 10C will be described with reference to FIGS.

  As the fairing piece 110, for example, as shown in FIG. 3, one constituted by a single honeycomb panel 20A can be exemplified. In other words, in the configuration shown in FIG. 3, one honeycomb panel 20 </ b> A is one fairing piece 110. The honeycomb panel 20A is composed of a total of 20 honeycomb cores 21. Ten honeycomb cores 21 are joined in the longitudinal direction (vertical direction) of the fairing piece 110, and two in the circumferential direction (lateral direction). The honeycomb core 21 is joined. In addition, in FIG. 3, the core splice part 23 is shown with the broken line.

  Moreover, as a structural example of the other fairing piece 110, as shown in FIG. 4, what was comprised by the honeycomb panel 20B-20D of multiple sheets (for example, 3 sheets) can be mentioned. The fairing piece 110 shown in FIG. 4 is basically composed of 20 honeycomb cores 21 as in the fairing piece 110 shown in FIG. 3, and these honeycomb cores 21 are made of 3 honeycomb panels. The honeycomb panels 20 </ b> B to 20 </ b> D are joined to each other by a panel joining frame 16. In other words, in the configuration shown in FIG. 4, the three honeycomb panels 20 </ b> B to 20 </ b> D are joined together via the panel joining frame 16 to constitute one fairing piece 110.

  As shown in FIG. 4, the honeycomb panels 20B to 20D are arranged in parallel along the longitudinal direction (longitudinal direction) of the fairing piece 110, and the honeycomb panel 20B and the honeycomb panel 20C are coupled to the panel coupling frame 16 to form the honeycomb. The panel 20 </ b> C and the honeycomb panel 20 </ b> D are joined by the panel joining frame 16.

  The honeycomb panel 20B constitutes the nose cone portion 12 that is the tip side of the fairing piece 110. In the example shown in FIG. 4, the honeycomb panel 20B is constituted by joining eight honeycomb cores 21. The honeycomb panel 20 </ b> C constitutes most of the cylinder portion 13 that is the trunk portion of the fairing piece 110. In the example illustrated in FIG. 4, the honeycomb panel 20 </ b> C is configured by joining eight honeycomb cores 21. The honeycomb panel 20D constitutes the rear end side (side coupled to the rocket) of the cylinder portion 13 of the fairing piece 110. In the example shown in FIG. 4, the honeycomb panel 20D is constituted by joining four honeycomb cores 21. Yes.

  In any of the honeycomb panels 20B to 20D, two honeycomb cores 21 are joined in the circumferential direction. Therefore, the honeycomb panel 20B and the honeycomb panel 20C have four honeycomb cores 21 joined in the longitudinal direction, and the honeycomb panel 20D has two honeycomb cores 21 joined in the longitudinal direction. The configuration of the fairing piece 110 is not limited to the configuration shown in FIG. 3 or FIG. 4. For example, the number of the honeycomb cores 21 is set in accordance with the size of the artificial satellites 40A and 40B that are payloads in both the longitudinal direction and the circumferential direction. Can be set. Moreover, as shown in FIG. 4, when the fairing piece 110 is comprised by the several honeycomb panel 20, it is not limited to three sheets, Four or more sheets may be sufficient and two sheets may be sufficient.

  The panel coupling frame 16 is attached to the edges of the honeycomb panels 20B to 20D. As shown in FIG. 5A, the panel coupling frames 16 are connected to each other through a fastener member 162, for example. Thereby, honeycomb panel 20B-20D can be mutually couple | bonded. In the configuration example shown in FIG. 5A, the panel coupling frame 16 is attached to the panel edge 20a of the honeycomb panel 20 so as to cover the outside of the edge, and the panel coupling frame 16 and the panel edge 20a are attached. A fastener member 161 is inserted so as to penetrate therethrough. Thereby, the panel coupling frame 16 is fixed to the panel edge portion 20a.

  In addition, the site | part which comprises the fairing piece coupling | bond part 111 among the site | parts of the honeycomb panel 20, ie, the site | part couple | bonded with the honeycomb panel 20 which comprises the other fairing piece 110 is called the panel edge part 26. FIG. On the other hand, as shown in FIG. 4, when the fairing piece 110 is composed of a plurality of honeycomb panels 20, a portion that connects the honeycomb panels 20 is referred to as a panel edge 20 a as described above. Shall.

  Here, in the configuration example shown in FIG. 5A, the panel edge portion 20 a is not inserted deeply so as to fill the interior of the panel coupling frame 16, and the frame inner space 163 is located inside the panel coupling frame 16. Has occurred. However, the mounting structure of the panel coupling frame 16 is not limited to this. For example, the panel coupling frame 16 may be fixed by the fastener member 161 in a state where the panel edge portion 20a is inserted to the back of the panel coupling frame 16 so that the intra-frame space 163 does not occur.

  Further, when the honeycomb panels 20 are bonded to each other, the side surfaces (the peripheral surfaces of the panel edge portions 20a) of the respective honeycomb panels 20 are abutted and connected. Since the panel coupling frame 16 is provided on the panel edge portion 20a, the side surface of the honeycomb panel 20 is covered with the panel coupling frame 16. Therefore, as shown in FIG. 5A, the outer surfaces (corresponding to the side surfaces of the honeycomb panel 20) of the panel coupling frame 16 are abutted with each other, and the fastener member 162 is inserted so as to penetrate the outer surfaces. Thereby, the honeycomb panels 20 can be bonded to each other via the panel bonding frame 16.

  In addition, the specific structure of the fastener members 161 and 162 is not particularly limited, and a known member can be suitably used. Further, the configuration for fixing the panel coupling frame 16 to the honeycomb panel 20 is not limited to the configuration in which the fastener member 161 is penetrated in the thickness direction of the honeycomb panel 20, and various known fixing configurations can be employed. Similarly, the configuration for coupling the panel coupling frames 16 to each other is not limited to the configuration for penetrating the fastener member 162, and various known coupling configurations can be employed.

  As described above, the fairing piece 110 is combined with the other fairing pieces 110 to form the satellite fairings 10A to 10C. The satellite fairings 10A to 10C are attached to the tip of the rocket. Therefore, as shown in FIG. 3 or FIG. 4, the fairing piece 110 has a fairing piece coupling portion 111 for coupling to another fairing piece 110 and a rocket coupling portion 112 for coupling to a rocket. doing. Each of the fairing piece coupling portion 111 and the rocket coupling portion 112 includes a separation mechanism (not shown in FIG. 3 or FIG. 4), and is connected to the other fairing piece 110 or the tip of the rocket via this separation mechanism. Combined.

  As before, the fairing piece 110 is composed of one or a plurality of honeycomb panels 20. Therefore, the attachment site of the separation mechanism in the fairing piece coupling part 111 or the rocket coupling part 112 can be a part of the panel side surface of the honeycomb panel 20. Further, as shown in FIG. 3 or FIG. 4, the honeycomb panels 20 </ b> A to 20 </ b> D are provided with a submerged exhaust opening 25 </ b> A at a position that becomes the inner surface of the fairing piece 110 and the fairing piece coupling portion 111. A submerged exhaust opening 25B is provided.

[Submerged exhaust opening]
Next, the submerged exhaust openings 25A and 25B provided in the fairing piece 110 will be specifically described with reference to FIGS. 5B and 6 in addition to FIGS. 2A to 5A. explain.

  As described above, the fairing piece 110 is composed of one or a plurality of honeycomb panels 20, and the honeycomb panel 20 is composed of a base material obtained by joining a plurality of honeycomb cores 21. Each honeycomb core 21 is provided with submerged exhaust openings 25 </ b> A and 25 </ b> B that communicate with the honeycomb core 21 at positions that become the inner surface of the fairing piece 110 or the fairing piece coupling portion 111.

  As described above, the honeycomb core 21 is provided with the slots (communication portions) 210 that allow the plurality of hollow cells 211 constituting the honeycomb core 21 to communicate with each other. Therefore, the entire inside of the honeycomb core 21 communicates with the slot (communication portion) 210 and the inside of the honeycomb core 21 communicates with the outside through the submerged exhaust openings 25A and 25B. become. Further, as described above, the honeycomb panel 20 is obtained by joining a plurality of honeycomb cores 21 via the core splice portion 23.

  For example, as shown in FIG. 6, the core splice portion 23 is provided on a side surface of the honeycomb core 21 other than the panel end portion 26, and is configured by joining the honeycomb cores 21 with an adhesive layer 33. In FIG. 6, for convenience of explanation, the adhesive layer 33 is illustrated with emphasis. The adhesive layer 33 is a joined portion that joins the honeycomb cores 21 and has no water permeability. Therefore, the submerged exhaust openings 25 </ b> A and 25 </ b> B are basically provided in each honeycomb core 21 divided by the core splice part 23.

  However, as will be described later, by providing a gap in the adhesive layer 33, water permeability can be secured in the adhesive layer 33. Therefore, since seawater can be circulated between the adjacent honeycomb cores 21 via the gaps, it is possible to improve the degree of freedom of positions where the submerged exhaust openings 25A and 25B are provided. The details of the adhesive layer 33 and the gap will be described later.

  As shown in FIGS. 2 (A) to 4, 5 (B), and 6, the submerged exhaust opening 25 </ b> A is formed on the inner surface of the fairing piece 110 (i.e., inside the storage space of the satellite fairings 10 </ b> A to 10 </ b> C). Provided). Therefore, the submerged exhaust opening 25A can be expressed as a “panel inner surface opening”. The submerged exhaust opening 25A is formed by notching the skin material 22 as schematically shown in FIG. 2B, but is not limited to this, as shown in FIG. The coupling frame 16 may be formed.

  Here, for example, if the formation position of the submerged exhaust opening 25A is a position where the panel coupling frame 16 and the panel edge 20a overlap (see FIG. 5A), the submerged exhaust opening 25A is Both the skin material 22 and the panel coupling frame 16 may be cut out. In addition, if the formation position of the submerged exhaust opening 25A is only the panel coupling frame 16, that is, the position corresponding to the frame internal space 163 (see FIG. 5A), the submerged exhaust opening 25A can be It is only necessary to cut out only the coupling frame 16.

  As shown in FIGS. 2A and 6, the submerged exhaust opening 25 </ b> B is provided in the separation mechanism housing 31 attached to the panel end 26. The panel end portion 26 and the separation mechanism housing 31 constitute a fairing piece coupling portion 111 (see an area surrounded by a dotted line in FIG. 6), and the panel end portion 26 to which the separation mechanism housing 31 is attached has a honeycomb core. 21 is an open end where the hollow cells 211 are exposed. Therefore, the submerged exhaust opening 25 </ b> B is communicated with the hollow cell 211 by forming the submerged exhaust opening 25 </ b> B in the separation mechanism housing 31. In addition, as schematically shown in FIG. 2A, the separation mechanism housing 31 forms a panel side surface in the honeycomb panel 20. Therefore, the submerged exhaust opening 25B can be expressed as a “panel side opening”.

  The specific configuration of the submerged exhaust openings 25A and 25B is not particularly limited. For example, as shown in FIGS. 2A to 6, the shape of the submerged exhaust openings 25 </ b> A and 25 </ b> B may be circular, but of course is not limited to this, and is a rectangle or a polygon more than a pentagon. Also good. Further, the shape or opening diameter (inner diameter) of the submerged exhaust openings 25A and 25B is not particularly limited. The submerged exhaust openings 25A and 25B can satisfactorily introduce seawater into the honeycomb panel 20 constituting the fairing piece 110 when the fairing piece 110 reaches the sea as will be described later. Any shape or opening diameter may be used.

  For example, the submerged exhaust opening 25A formed on the inner surface of the panel is preferably a shape or an opening diameter that can expose one or more hollow portions of the hollow cell 211. For example, in the configuration shown in FIG. 6, the submerged exhaust opening 25 </ b> A is formed by notching the skin material 22 so as to expose the inner surface side end of the hollow cell 211 (see FIG. 2B). Therefore, if the submerged exhaust opening 25A has a larger opening than the cross section of the hollow cell 211, seawater intrusion or air exhaust, which will be described later, easily occurs.

  As for the submerged exhaust opening 25B formed on the side surface of the panel, a bolt hole 35 provided in the separation mechanism housing 31 can be used as shown in FIG. Specifically, for example, when the separation mechanism operates, the bolt hole 35 of the separation mechanism housing 31 is opened. At this time, since the panel end portion 26 is an open end, the slot (communication portion) 210 of the hollow cell 211 is open so as to be exposed. Accordingly, the panel end portion 26 of the honeycomb core 21 can communicate with the outside air through the bolt holes 35. Therefore, the bolt hole 35 of the separation mechanism housing 31 can be used with the submerged exhaust opening 25B.

  Thereby, seawater can be easily infiltrated into the honeycomb core 21 from the bolt hole 35 (submerged exhaust opening 25B) of the panel end portion 26 through the slot (communication portion) 210, and the slot (communication portion). The air in the honeycomb core 21 can be exhausted through 210. It should be noted that a known frame material other than the separation mechanism housing 31 may be attached to the panel end portion 26 in order to maintain a good state in which the honeycomb core 21 is exposed.

  The formation positions of the submerged exhaust openings 25A and 25B are not particularly limited, but the submerged exhaust openings 25A and 25B have fairing pieces in each of the honeycomb cores 21 in order to allow seawater to enter the respective honeycomb cores 21. 110 is preferably provided at a position that is an end in the circumferential direction and the longitudinal direction. Thereby, the four corner vicinity of the honeycomb core 21 will be open | released, and many parts of the honeycomb core 21 can be immersed in favorable water. For example, as shown in FIG. 6, the submerged exhaust openings 25 </ b> A and 25 </ b> B may be formed at or near the circumferential and longitudinal ends of the honeycomb core 21 constituting the honeycomb panel 20.

  In the example shown in FIG. 6, since the separation mechanism housing 31 is attached to one end of the honeycomb core 21 in the circumferential direction, the submerged exhaust opening 25 </ b> B is provided at one end of the honeycomb core 21, and the submerged exhaust is provided at the other end of the honeycomb core 21. An opening portion 25A is provided. Or although not shown in figure, the opening 25A for immersion exhaust may be provided also in the panel inner surface adjacent to the end of the honeycomb core 21. FIG. Furthermore, as schematically shown in FIG. 5B, the submerged exhaust opening 25 </ b> A may be formed by cutting out a part of the panel coupling frame 16. Further, as schematically shown in FIG. 2 (A), when the honeycomb panel 20 is composed of three or more honeycomb cores 21 in the circumferential direction, both ends in the circumferential direction and the longitudinal direction of each honeycomb core 21 The submerged exhaust openings 25A and 25B may be formed in the vicinity of the portion.

  If the inside of the honeycomb core 21 can be satisfactorily immersed, the submerged exhaust openings 25A and 25B are provided at at least one of the circumferential end and the longitudinal end of the fairing piece 110. Just do it. That is, it is preferable that the submerged exhaust openings 25A and 25B are provided at both the end in the circumferential direction and the end in the longitudinal direction, but seawater can be satisfactorily introduced into the honeycomb core 21. For example, it may be provided only at the end in the circumferential direction, or may be provided only at the end in the longitudinal direction.

  In addition, the submerged exhaust openings 25A and 25B are located on the inner surface of the fairing piece 110 or the fairing piece coupling portion 111 as described above from the viewpoint of isolating the storage space for the payload fairing from the outside. It may be provided at a position where it is not exposed to outside air or outer space.

  The inner surface of the fairing piece 110 is a surface that determines a storage space for storing the artificial satellites 40A and 40B as payloads, but the outer surface of the fairing piece 110 is a surface that is exposed to the outside air or outer space. Therefore, the submerged exhaust opening 25A is formed on the inner surface of the fairing piece 110 from the viewpoint of isolating the storage space from the outside air or outer space. In addition, when the fairing pieces 110 are coupled by the separation mechanism to form the satellite fairings 10A to 10C, the fairing pieces 110 are coupled by abutting the fairing piece coupling portions 111 to each other. Is in a state of being. For this reason, by providing the submerged exhaust opening 25B at a position where the fairing piece coupling portion 111 is not exposed to the outside air or outer space, it is possible to avoid the possibility of affecting the isolation of the storage space.

  The formation position of the submerged exhaust opening 25A on the inner surface of the fairing piece 110 is not particularly limited as long as it is provided at a position corresponding to the portion 113 indicated by the alternate long and short dash line in FIG. 3 or FIG. This portion 113 is a central portion in the circumferential direction on the inner side of the fairing piece 110 and is a region extending in the longitudinal direction. Therefore, for convenience, this portion 113 is referred to as an “inner surface central portion 113”. Although the cross section in the circumferential direction (lateral direction) of the fairing piece 110, that is, the shape of the cross section is substantially arc-shaped, the inner surface central portion 113 corresponds to the apex of the convex portion or the concave portion in the cross section of the fairing piece 110. It becomes an area to do.

  Here, a specific range (width of the inner surface central portion 113) of the inner surface central portion 113 is not particularly limited, and at least two submerged exhaust openings 25A are provided in the vicinity of the apex of the concave portion or the convex portion. Any width that can be provided may be used. In the example shown in FIG. 3 or FIG. 4, the circumferential direction of the fairing piece 110 is configured by two honeycomb cores 21. In this case, the vicinity of the apex of the concave portion or the convex portion is between the end faces of the honeycomb cores 21. Corresponds to the position where the two are joined together. The submerged exhaust opening 25A is provided at an end (one end) near the apex. Therefore, in this example, the inner surface central portion 113 only needs to be wide enough to provide at least two submerged exhaust openings 25A in the circumferential direction.

  Although not shown, if the circumferential direction of the fairing piece 110 is constituted by one honeycomb core 21 or is constituted by three or more honeycomb cores 21, the fairing piece 110 is near the apex of the fairing piece 110. It is possible to employ a configuration in which at least one submerged exhaust opening 25A is provided in the circumferential direction at the position, and submerged exhaust openings 25A are provided at both ends in the circumferential direction of the honeycomb core 21, respectively. Further, even in the example shown in FIG. 3 or FIG. 4, if the end faces of the two honeycomb cores 21 that are brought into contact with each other are connected to each other, only one submerged exhaust opening 25 </ b> A is provided in the vicinity of the apex. It can also be provided. In these cases, the width of the inner surface central portion 113 may be a width that allows at least one submerged exhaust opening 25A to be provided in the circumferential direction.

  Therefore, the lower limit of the width of the inner surface central portion 113 only needs to be such that one or two submerged exhaust openings 25A can be provided in the circumferential direction. On the other hand, the upper limit of the width of the inner surface central portion 113 may be a width that includes the apex and is about ¼ to ３ of the circumferential length of the fairing piece 110. If the width of the inner surface central portion 113 is within this range, the submerged exhaust opening 25A can be provided at a position that can be regarded as the vicinity of the apex.

  Thus, when the fairing piece 110 is used as a reference, the submerged exhaust opening 25A is a position corresponding to the inner surface central portion 113 (inner side of the fairing piece 110 and the central portion in the circumferential direction) of the honeycomb core 21. Is preferably provided. However, the portion of the fairing piece 110 where the submerged exhaust opening 25A is provided is not limited to the inner surface central portion 113. For example, in the fairing piece 110, the submerged exhaust opening 25 </ b> A may be provided in another part together with the inner surface central part 113, or the submerged exhaust opening 25 </ b> A may be provided in a part other than the inner surface central part 113. .

  As described above, the honeycomb core 21 is exposed in the submerged exhaust openings 25A and 25B, and the hollow cells 211 constituting the honeycomb core 21 are provided with the slots (communication portions) 210 as described above. This slot (communication part) 210 may be any one that allows adjacent hollow cells 211 to communicate with each other, can introduce seawater into the hollow cells 211, and can discharge the air within the hollow cells 211. Or size etc. are not specifically limited. However, the slot (communication portion) 210 is preferably formed at a position where the flow of seawater meanders in the hollow cell 211.

  For example, in the hollow cell 211 having a hexagonal cross section as shown in FIG. 2 (B), slots (communication portions) 210 are not formed on all the opposed surfaces of the three pairs of opposed surfaces constituting the hexagonal cylinder, The structure which forms the slot (communication part) 210 in two pairs of opposing surfaces can be mentioned, respectively. When the slot (communication portion) 210 is formed only on the pair of opposed surfaces, the seawater introduced from the submerged exhaust openings 25A and 25B flows in a straight line through the slot (communication portion) 210 on the opposed surface and does not meander. Therefore, if the slots (communication portions) 210 are formed on at least two pairs of facing surfaces, the seawater flowing into the hollow cell 211 can be meandered as much as possible.

  The hollow cells 211 only need to communicate with each other through a known communication portion, and the configuration of the communication portion is not limited to the slot 210 as shown in FIG. For example, although not shown, the hollow cell 211 may be formed with a drill hole instead of the slot 210 as a communicating portion. Various conditions, such as a formation method or formation position of a drill hole, are not specifically limited, For example, what is necessary is just to form a drill hole in a suitable location using a well-known drill apparatus.

[Core splice section]
Next, in addition to FIG. 6, about the specific structure of the core splice part 23 which is a junction part of honeycomb cores 21, FIG. 7 (A)-FIG. 7 (C), FIG. 8 (A)-FIG. This will be specifically described with reference to FIG. 9C and FIGS. 9A and 9B.

  As described above, the core splice portion 23 is a joint portion between the honeycomb cores 21, and as shown in FIG. 6, the core splice portion 23 is formed with the adhesive layer 33 that joins the side surfaces of the honeycomb core 21. ing. The adhesive layer 33 is basically impermeable to air and water.

  Here, as described later, when the fairing piece 110 has landed on the sea, seawater is introduced into the inside of the honeycomb core 21 constituting the honeycomb panel 20 from the submerged exhaust openings 25A and 25B of the fairing piece 110. Will be. For example, as shown by a block arrow A in FIG. 7A, seawater is introduced from the submerged exhaust opening 25A formed in the skin material 22 into the hollow cell 211 facing the submerged exhaust opening 25A. Is done. Since the slot (communication part) 210 is provided in the hollow cell 211, seawater invades one after another into the adjacent hollow cell 211 via the slot (communication part) 210. The air inside the honeycomb core 21 is exhausted from the submerged exhaust opening 25A or 25B). As a result, the honeycomb core 21 of the honeycomb panel 20 is filled with seawater.

  However, as shown in FIGS. 7B and 7C, the core splice portion 23 has an adhesive layer 33 through which air and water cannot permeate. Therefore, the seawater that has entered through the slot (communication portion) 210 is prevented from entering by the adhesive layer 33 as indicated by the block arrow D. 7A and 7B show a longitudinal section of the honeycomb panel 20 (a section along the extending direction of the hollow cell 211), and FIG. 7C shows a transverse section of the honeycomb panel 20 (a hollow cell). 2 is a sectional view taken along a sectional direction 211.

  Therefore, in the present invention, the adhesive layer 33 of the core splice portion 23 is partially free of adhesive so that the hollow cells 211 can communicate with each other between the bonded honeycomb cores 21. A gap (or the adhesive is removed) is provided. As a specific gap, for example, as shown in FIG. 8 (A) or FIG. 8 (B), a core splice opening 231 provided in a core splice 23 (a portion indicated by a dotted line in the figure), or FIG. Although the penetration pipe member 233 provided in the core splice part 23 is mentioned as shown to 8 (C), it is not specifically limited. It is sufficient that the gap portion is a path (water-permeable path or exhaust path) that allows air and water to flow (water-permeable and exhausted) between the adjacent honeycomb cores 21.

  The core splice opening 231 shown in FIG. 8A and FIG. 8B is formed by not being partially filled with an adhesive in a region to be a joint (adhesive filling region). In other words, the core splice opening 231 corresponds to a discontinuous portion of the adhesive layer 33. In the example shown in FIG. 8A, the core splice opening 231 is configured by not partially filling the adhesive layer 33 in the core splice 23 with the adhesive, but the example shown in FIG. Then, a blocking member 232 is provided around the core splice opening 231 so that the adhesive does not flow into the region that becomes the core splice opening 231 (so as to eliminate filling of the adhesive).

  In addition, the specific structure of the blocking member 232 is not particularly limited. As described later, the adhesive can be blocked well before curing, and the adhesive layer 33 after curing can be bonded well. Anything that can be fixed is acceptable. For example, the blocking member 232 may be a rod-like or linear member interposed between the honeycomb cores 21 as shown in FIG. 8B, or a sheet-like or plate-like member not shown. It may be. Moreover, the blocking member 232 may itself have adhesiveness. Thereby, the blocking member 232 itself can be fixed between the honeycomb cores 21. Further, since the adhesive used as the adhesive layer 33 is a general resin material (resin composition) as will be described later, the blocking member 232 is also a resin material that can be bonded and fixed with an adhesive. What is necessary is just to be comprised.

  Further, the through pipe member 233 shown in FIG. 8C is a tubular member having a hollow inside, and is provided so as to penetrate the adhesive layer 33 of the core splice portion 23. Thereby, the inside of the penetration pipe member 233 becomes a space part from which the adhesive is partially removed. In FIG. 8C, the through pipe member 233 is a tubular member having a diameter corresponding to one or two hollow cells 211, but the configuration of the gap is not limited to this, and the inside is Any hollow member that is hollow and capable of communicating the joined honeycomb cores 21 may be used. For example, the hollow member may not be tubular but may be an annular or rectangular frame member, or may be composed of a plurality of tubular members instead of a single tubular member as shown in FIG. Also good.

  Moreover, it does not specifically limit about the shape and size of a hollow member, The partial cavity part can be formed in the adhesive bond layer 33, and the flow of air and water should just be possible in the said cavity part. Similarly, the material of the hollow member is not particularly limited as long as it is a known material that can be bonded by the adhesive layer 33 and can maintain the hollow shape by the flow of air and water. Since the adhesive used as the adhesive layer 33 is a general resin material (resin composition) as will be described later, the hollow member may be a resin material that can be bonded and fixed with the adhesive.

  Moreover, the formation position of the void portion in the core splice portion 23 is not particularly limited as long as the adjacent honeycomb cores 21 can flow air and water to each other. For example, if a plurality of voids are provided at the center and the end of the honeycomb core 21, the inside of the honeycomb core 21 can be satisfactorily replaced with seawater while suppressing the remaining of air. Further, if voids are provided in all the core splice parts 23 included in the fairing piece 110, seawater can be satisfactorily introduced into all the honeycomb cores 21 constituting the fairing piece 110.

  The adhesive constituting the adhesive layer 33 is not particularly limited as long as it can satisfactorily join the honeycomb cores 21 together. As a typical adhesive, as shown schematically in FIG. 9 (A), a foamed adhesive 331 that foams by heating, or as shown schematically in FIG. 9 (B), it cures by a curing reaction. A liquid adhesive 332 can be given. As a typical foaming adhesive 331, for example, an epoxy-based foaming adhesive containing an epoxy resin can be cited, and as a typical liquid adhesive 332, an epoxy-based liquid adhesive containing an epoxy resin can be cited. it can.

  In addition, the adhesive layer 33 may be composed of only the foamed adhesive 331 or the liquid adhesive 332, or may be used in combination with another adhesive (or an adhesive member such as an adhesive tape). That is, in this Embodiment, the adhesive bond layer 33 may be comprised with one type of adhesive material, and may be comprised with two or more types of adhesive materials. For example, a sheet-like adhesive can be used together with the foamed adhesive 331 or the liquid adhesive 332. This sheet-like adhesive can be interposed between the foamed adhesive 331 or the liquid adhesive 332 and the end face of the honeycomb core 21. This sheet-like adhesive may also serve as the blocking member 232 described above.

  For example, a sheet-like adhesive may be provided so as to cover the tip portion of the foamed adhesive 331, and the foamed adhesive 331 may be heated and foamed after being interposed between the honeycomb cores 21. Thereby, the foaming region of the foaming adhesive 331 can be blocked with the sheet-like adhesive to form the core splice opening 231 and the honeycomb cores 21 are bonded to each other with both the foaming adhesive 331 and the sheet-like adhesive. be able to. In addition, the specific structure of a sheet-like adhesive is not specifically limited, A well-known thing can be used suitably.

  The formation method of the void portion shown in FIGS. 8A to 8C is also not particularly limited, and the void in which the side surfaces of the honeycomb core 21 can be sufficiently bonded to each other in the core splice portion 23 and air and water can flow. What is necessary is just to form the adhesive bond layer 33 so that a part can be maintained. If the adhesive constituting the adhesive layer 33 is a foamed adhesive 331 or a liquid adhesive 332, as schematically shown in FIG. 9A or FIG. What is necessary is just to form a space | gap part, when filling the adhesive agent to the splice object area | region 230 (area | region used as the core splice part 23), or when hardening the adhesive agent filled to the core splice object area | region 230.

  For example, in the example shown in FIG. 9A, the foamed adhesive 331 is disposed in the core splice target region 230 (the region between the two honeycomb cores 21 to be joined) excluding the region that becomes the core splice opening 231. The foamed adhesive 331 may be foamed and cured by heating. Further, in the example shown in FIG. 9B, a blocking member 232 is disposed around a region to be a core splice opening 231 (for convenience, a planned opening region) in the core splice target region 230, The planned opening area is isolated by the blocking member 232. After that, the core splice target region 230 is filled with the liquid adhesive 332 by the adhesive filling machine 41 schematically shown in FIG. After that, when the liquid adhesive 332 is cured by a curing reaction, the planned opening area isolated by the blocking member 232 becomes the core splice opening 231, and the adhesive layer 33 is formed in the other area.

  As described above, if the gap is provided in the adhesive layer 33, when seawater enters the inside of the honeycomb core 21 of the arbitrary honeycomb panel 20, the block arrow A in FIGS. 8A to 8C. As shown, the seawater can be introduced into the adjacent honeycomb core 21. Alternatively, as seawater enters from one of the submerged exhaust openings 25A and 25B, the air inside the honeycomb core 21 can be exhausted from the other submerged exhaust opening 25A and 25B. Therefore, for example, some of the fairing pieces 110 cannot contact seawater, or some of the submerged exhaust openings 25A and 25B of the fairing pieces 110 are blocked by floating matters on the sea. Even if seawater cannot be introduced into the interior from the honeycomb core 21 at the site, seawater can be introduced into the interior from the adjacent honeycomb core 21.

[Fairing piece submerged]
Next, regarding the submergence of the fairing piece 110 constituted by the honeycomb panel 20 having the above-described configuration, in addition to FIG. 2 (B), FIG. 3, FIG. 4, FIG. , (B) will be specifically described.

  The satellite fairings 10A to 10C are transported to a target altitude and orbit by a launch rocket. In the middle of this, in order to expose the artificial satellite 40A or 40B, the satellite fairings 10A to 10C are separated from the head of the rocket by opening and separating. The separated fairing piece 110 falls, for example, on the sea. For example, as shown in FIG. 10 (A), if the fairing piece 110 lands on the sea surface with the inner surface facing upward (a state where the storage space faces the upper atmosphere, a concave state), As indicated by a block arrow C in FIG. 4, seawater enters the fairing piece 110 from the rocket coupling portion 112 side (rear end side).

  In the example schematically shown in FIG. 10A, the honeycomb panel 20 constituting the fairing piece 110 has a configuration in which four honeycomb cores 21 are joined in the circumferential direction. For convenience of explanation, the two honeycomb cores 21A joined at the inner surface central portion 113 are referred to as “inner honeycomb core 21A”, and the remaining two honeycomb cores 21B joined to the outside of the inner honeycomb core 21A, respectively. Is referred to as "outer honeycomb core 21B". Further, a joint portion (core splice portion 23) between the inner honeycomb cores 21A is referred to as an “inner core splice portion 23A”, and a joint portion between the inner honeycomb core 21A and the outer honeycomb core 21B is referred to as an “outer core splice portion 23B”. .

  As described above, a plurality of submerged exhaust openings 25A are provided in the inner surface central portion 113 of the fairing piece 110 shown in FIG. Therefore, as shown by the block arrow A in FIGS. 3, 4, 5B, 6 and 10A, seawater enters the inner honeycomb core 21A from the submerged exhaust opening 25A.

  Here, in the inner honeycomb core 21A and the outer honeycomb core 21B constituting the fairing piece 110, the end portion of the outer honeycomb core 21B to which the separation mechanism housing 31 is attached is defined as “one end in the circumferential direction”, The end portion of the inner honeycomb core 21A is referred to as “the other end in the circumferential direction”. As described above, the inner honeycomb core 21 </ b> A and the outer honeycomb core 21 </ b> B are configured such that the plurality of hollow cells 211 communicate with each other through the slots (communication portions) 210. Therefore, seawater that has entered the inner honeycomb core 21 </ b> A from the submerged exhaust opening 25 </ b> A gradually fills the hollow cell 211 from the other end in the circumferential direction via the slot (communication portion) 210.

  Here, both the inner core splice portion 23A and the outer core splice portion 23B are provided with a core splice opening 231 as schematically shown in FIG. Further, in the outer honeycomb core 21B, a submerged exhaust opening 25B is provided on the side surface of the end portion that becomes the fairing piece coupling portion 111. The fairing piece coupling portion 111 includes a panel end portion 26 that is an open end and a separation mechanism housing 31 that is attached to the panel end portion 26, and the submerged exhaust opening 25 </ b> B is formed in the separation mechanism housing 31. Is formed.

  As described above, seawater gradually enters the inside of the inner honeycomb core 21 from the submerged exhaust opening 25 </ b> A located at the inner surface central portion 113. Therefore, as shown by a block arrow E2 in FIG. 10A, air moves from the inside of the inner honeycomb core 21A toward the outer honeycomb core 21B through the core splice opening 231, and finally the open end. Air is exhausted (discharged) from the submerged exhaust opening 25B through the panel end 26 (one end in the circumferential direction) (see also FIGS. 3, 4, 5B, and 6).

  In addition, since the core splice opening 231 is provided in the inner core splice portion 23A, seawater also flows inside the inner honeycomb cores 21A that are joined to each other as indicated by the bidirectional block arrow E1. It is possible. Therefore, for example, even if the submerged exhaust opening 25A of one inner honeycomb core 21A is blocked by an object floating on the sea surface, the core splice opening from the submerged exhaust opening 25A of the other inner honeycomb core 21A. Seawater can be introduced via H.231.

  10A and 10B illustrate the core splice opening 231 as a gap provided in the core splice 23 (see FIGS. 8A and 8B). However, the gap is not limited to this, and may be a through pipe member 233 (see FIG. 8C) or another configuration.

  On the other hand, as shown in FIG. 10 (B), if the fairing piece 110 lands on the sea surface with the inner surface facing downward (the storage space facing the lower sea surface, a convex state), the block arrow As shown to A, the fairing piece coupling | bond part 111 of the fairing piece 110 will be immersed in seawater. Therefore, seawater enters the outside honeycomb core 21B from the submerged exhaust opening 25B provided in the fairing piece coupling portion 111.

  As described above, since the plurality of hollow cells 211 constituting the honeycomb core 21 are provided with the slots (communication portions) 210, the hollow cells 211 are passed through the slots (communication portions) 210 from one end in the circumferential direction. Gradually fill with seawater. When the hollow cell 211 is filled with seawater, the air in the hollow cell 211 is exhausted through the slot (communication portion) 210. Further, as described above, the core splice opening 231 serving as a gap is provided in the outer core splice portion 23B, which is a joint portion between the outer honeycomb core 21B and the inner honeycomb core 21A. Therefore, as the inside of the outer honeycomb core 21B is gradually filled with seawater, the air inside the outer honeycomb core 21B is exhausted from the core splice opening 231 to the inner honeycomb core 21A (block arrow E3 ).

  Since the air in the inner honeycomb core 21A is exhausted to the outside through the submerged exhaust opening 25A in the inner surface central portion 113 (block arrow B), finally, the air inside the outer honeycomb core 21B and the inner honeycomb core 21A. Is finally exhausted from the submerged exhaust opening 25A located at the other end in the circumferential direction when viewed from the submerged exhaust opening 25B, and the inside of the honeycomb core 21 is replaced with seawater. As described above, since the core splice opening 231 is also provided in the inner core splice portion 23A, it is possible to exchange air inside and outside the inner honeycomb cores 21A (block arrow E4). ).

  Thus, by providing a void portion such as the core splice opening 231 in the adhesive layer 33 of the core splice portion 23, the hollow cells 211 communicate with each other between the honeycomb cores 21 joined to each other. It is possible. Therefore, for example, even when seawater enters only a part of the honeycomb cores 21 constituting the fairing piece 110, such as the submerged exhaust opening 25A of the inner surface central portion 113, the seawater adjoins through the gap. Seawater can be infiltrated into the honeycomb core 21, and the air inside the honeycomb core 21 is exhausted to the outside in accordance with the intrusion of seawater.

  Further, the submerged exhaust openings 25 </ b> A and 25 </ b> B provided in the fairing piece 110 communicate with the inside of the honeycomb panel 20 (the honeycomb core 21) constituting the fairing piece 110. Therefore, even if the fairing piece 110 lands on the sea surface in a concave state or on the sea surface in a convex state, the fairing piece 110 is fair by the submerged exhaust openings 25A and 25B and the gap portion provided in the core splice portion 23. The inside of the ring piece 110 (inside the hollow cell 211 constituting the honeycomb core 21) can be satisfactorily replaced with air from seawater. As a result, the fairing piece 110 that has landed on the sea can be smoothly submerged.

  As described above, in the payload fairing according to the present invention, the fairing piece is composed of a honeycomb panel having a base material obtained by joining a plurality of honeycomb cores with an adhesive layer. A slot is provided for communicating a plurality of hollow cells constituting the core with each other, and the adhesive layer is provided with a void portion that allows the hollow cells to communicate with each other between the bonded honeycomb cores. Yes.

  Therefore, the honeycomb cores to be joined can permeate and exhaust each other, so even if the number of submerged exhaust openings is small, the entire honeycomb cores constituting the fairing piece (honeycomb panel) can be formed. Sea water can be introduced. Further, if a part of the submerged exhaust opening has landed on the water surface, not only seawater can be introduced into the honeycomb core, but also seawater can be introduced into other adjacent honeycomb cores. As a result, the fairing piece can be effectively submerged. Furthermore, since water permeation and exhaust can be continuously performed between adjacent honeycomb cores, the fairing pieces can be submerged more quickly.

  It should be noted that the present invention is not limited to the description of the above-described embodiment, and various modifications are possible within the scope shown in the scope of the claims, and are disclosed in different embodiments and a plurality of modifications. Embodiments obtained by appropriately combining the technical means are also included in the technical scope of the present invention.

  The present invention can be widely and suitably used in the field of payload fairing for storing payloads such as artificial satellites.

10A-10C Satellite fairing (payload fairing)
DESCRIPTION OF SYMBOLS 11 Nose cap part 12 Nose cone part 13 Cylinder part 14,15 Rear cone part 16 Panel coupling frame 20 Honeycomb sandwich panel (honeycomb panel)
20A-20D Honeycomb sandwich panel (Honeycomb panel)
20a Panel edge portion 21 Honeycomb core 21A Inner honeycomb core 21B Outer honeycomb core 22 Skin material 23 Core splice portion 23A Inner core splice portion 23B Outer core splice portion 24 Skin splice portion 25A, 25B Submerged exhaust opening 26 Panel end portion 31 Separation Mechanism housing 33 Adhesive layer 35 Bolt hole 40A, 40B Satellite (payload)
41 Adhesive Filling Machine 110 Fairing Pieces 110a, 110b Fairing Piece 111 Fairing Piece Joining Part 112 Rocket Joining Part 113 Inner Surface Central Part 161, 162 Fastener Member 163 Space in Frame 210 Slot (Communication Part)
211 Hollow cell 331 Core splice opening (gap)
332 Blocking member 333 Through pipe member (gap)
334 Foam adhesive 335 Liquid adhesive

Claims (6)

A plurality of fairing pieces are connected to each other in a separable manner, and have a storage space for storing the payload inside
The fairing piece is composed of a honeycomb sandwich panel having a base material formed by bonding a plurality of honeycomb cores with an adhesive layer,
The honeycomb core is provided with a communication portion that communicates a plurality of hollow cells constituting the honeycomb core with each other,
Between the bonded honeycomb cores, the adhesive layer is provided with voids that allow the hollow cells to communicate with each other.
Payload fairing. The void portion is formed by not being partially filled with an adhesive in a region that becomes a joint portion between the honeycomb cores,
The payload fairing according to claim 1. The void is formed by embedding a hollow member in the adhesive layer,
The payload fairing according to claim 1. Around the gap, a blocking member that prevents the inflow of the adhesive to the area that becomes the gap is provided,
The payload fairing according to claim 2. The void portion is formed when the adhesive agent is filled in a region that becomes a joint portion between the honeycomb cores or when the adhesive agent filled in the region that becomes the joint portion is cured. To
The payload fairing according to any one of claims 1 to 4. The honeycomb sandwich panel is provided with a submerged exhaust opening that communicates with the inside of the fairing piece or at a position where the fairing piece is connected to each other.
The payload fairing according to any one of claims 1 to 5.