JP2016161123A - Impact absorption material - Google Patents

Abstract

PROBLEM TO BE SOLVED: To dampen impact added to a structure such as a spacecraft or an aircraft when the structure performs landing, splashdown or impact shock.SOLUTION: An impact absorption material 20 comprises frame parts 22, cubic space parts 24 of each of the cells with the frame parts 22 being applied as side walls and foam materials 26 filled in the cubic space parts 24. The frame parts 22 are constituted by cubic shapes in which their plan view shapes are extended in a main impact absorbing direction (Z-axis direction). The impact absorption material 20 comprises, at a first cutting plane C1, a first impact absorbing layer L11 including a first foam material filling part 31 filled with foam materials 26 and a cell clearance part 30C not filled with foam materials 26. In addition, the impact absorption material 20 comprises, at a second cutting plane C2, a second impact absorbing layer L21 including a second foam material filling part 32 filled with the foam materials 26. An area A2 of the second foam material filling part 32 at the second cutting plane C2 is formed to be wider than an area A1 of the first foam material filling part 31 at the first cutting plane C1.SELECTED DRAWING: Figure 3

Description

  The present invention relates to a shock absorber, for example, a shock absorber used for space equipment, an outer wall of an aircraft structure, an underfloor structure, or the like.

  Patent Document 1 (Japanese Patent Laid-Open No. 10-316096) discloses a honeycomb cushion material for a hot air balloon that protects a person or an article loaded on a hot air balloon gondola from an impact at the time of a hot air balloon crash. Yes.

  The honeycomb cushion material for hot air balloons described in Patent Document 1 is attached between the lower surface of the gondola and the lower surface of the gondola, with the cell axis direction of the honeycomb structure directed vertically. Yes. When the hot air balloon falls, the cell wall of the honeycomb structure buckles due to the impact load accompanying the landing. The shock energy applied to the gondola can be absorbed and buffered.

  Patent Document 2 (Japanese Patent Application Laid-Open No. 2009-6838) discloses an impact absorbing structure in which a side impact pad having a lattice-shaped reinforcing material is provided on the inner side of an automobile door. The space of the lattice reinforcing material of the side-impact pad described in Patent Document 2 is filled with a highly rigid foam material. It has been described that the rigidity of the grid-like reinforcing material is increased by this high-rigid foam material.

  Patent Document 3 (Japanese Patent Application Laid-Open No. 2003-64629) discloses a vehicle collision buffer device in which a plurality of buffer materials having an aluminum honeycomb structure are arranged. The collision buffer device for a vehicle described in Patent Document 3 is provided at an end portion of a road separation zone, and effectively gives an impact at the time of a collision without giving excessive deceleration acceleration to a vehicle that collides. The purpose is to absorb.

  In the vehicular collision shock absorber described in FIG. 8 of Patent Document 3, the shock absorber disposed at the front (front) of the plurality of shock absorbers is wider in the left-right direction than the shock absorber disposed at the rear. Is small.

Japanese Patent Laid-Open No. 10-316096 JP 2009-6838 A JP 2003-64629 A

  The impact applied to the structure at the time of landing, landing or collision of a structure such as a space device or an aircraft is mitigated.

  The means for solving the problem will be described below using the numbers used in the (DETAILED DESCRIPTION). These numbers are added to clarify the correspondence between the description of (Claims) and (Mode for Carrying Out the Invention). However, these numbers should not be used to interpret the technical scope of the invention described in (Claims).

  In one aspect of the present invention, the shock absorber (20) includes at least one of the three-dimensional space portion (24) of each cell having the skeleton portion (22) and the skeleton portion (22) as side walls, and the three-dimensional space portion (24). And a foam material (26) filled in the part. The skeleton part (22) has a three-dimensional shape obtained by extending one or more planar figures in the main shock absorption direction (Z-axis direction). The shock absorbing material (20) is a first foam material filling portion in which the foam material (26) is filled at the first cut surface (C1) perpendicular to the main shock absorbing direction (Z-axis direction). (31) and a first shock absorbing layer (L11) having a cell gap (30C) not filled with the foam material (26). Further, the shock absorbing material (20) is a second foam material filling portion in which the foam material (26) is filled at the second cut surface (C2) perpendicular to the main shock absorbing direction (Z-axis direction). And a second shock absorbing layer (L21 or first filling layer L12) having (32). The area (A2) of the second foam filling portion (32) in the second cut surface (C2) is the area (A1) of the first foam filling portion (31) in the first cut surface (C1). Is more widely formed.

  In one aspect of the present invention, the shock absorber (20) is filled in the three-dimensional space portion (24) of each cell having the skeleton portion (22) and the skeleton portion (22) as side walls, and the three-dimensional space portion (24). Foam material (26). The skeleton part (22) has a three-dimensional shape obtained by extending one or more planar figures in the main shock absorption direction (Z-axis direction). The shock absorber (20) includes a first shock absorber (201) having a first plane area (A1) at a cut surface perpendicular to the main shock absorption direction (Z-axis direction), and the main shock absorption. The second shock absorber (202) having a second plane area (A2) larger than the first plane area (A1) at the cut surface perpendicular to the direction (Z-axis direction) is the main impact. They are stacked in the absorption direction (Z-axis direction).

  In one aspect of the present invention, the shock absorber (20) is filled in the three-dimensional space portion (24) of each cell having the skeleton portion (22) and the skeleton portion (22) as side walls, and the three-dimensional space portion (24). Foam material (26). The skeleton part (22) has a three-dimensional shape obtained by extending one or more planar figures in the main shock absorption direction (Z-axis direction). The shock absorber (20) includes a first height shock absorber (301) having a first height (H1) with respect to a main shock absorption direction (Z-axis direction), and a main shock absorption direction (Z-axis direction). ) And a second height shock absorber (302) having a second height (H2) lower than the first height (H1) and perpendicular to the main shock absorption direction (Z-axis direction). It is arranged in the direction to.

  The three-dimensional space portion (24) in the shock absorbing material (20) can be configured such that there is no cell void portion (30C) that is not filled with the foam material (26).

  The shape of the plane figure of the skeleton part (22) includes a polygonal shape, a circular shape, or a wave shape.

  One or more buckling promoting openings (28) are formed in the side wall of the skeleton (22).

  In one aspect of the present invention, the shock absorber (20) fills the skeleton part (22), the three-dimensional space part (24) of each cell having the skeleton part (22) as side walls, and the three-dimensional space part (24). Foamed material (26). The skeleton part (22) has a three-dimensional shape obtained by extending one or more planar figures in the main shock absorption direction (Z-axis direction). One or more buckling promoting openings (28) are formed in the side wall of the skeleton (22).

  The buckling promoting opening (28) is an opening communicating with the side walls of the plurality of skeleton parts (22).

  In another embodiment, the structure outer wall (15) used in the space device (8) or the aircraft (9) includes a shock absorber (20), an inner wall (14), and an outer wall (16). The shock absorber (20) is disposed between the inner wall (14) and the outer wall (16).

  Impact comprising a skeleton part (22), a three-dimensional space part (24) of each cell having the skeleton part (22) as a side wall, and a foam material (26) filled in at least a part of the three-dimensional space part (24) The manufacturing method of the absorbent material (20) includes a skeleton part raw material roll cutting step (S10), a skeleton part sheet lamination step (S12), a work forming step (S14), a stretching step (S16), and a foam filling step. (S18). The skeleton part raw material roll cutting step (S10) is a step of cutting a skeleton part raw material roll (22R) to form a plurality of skeleton part sheets (22S) having a predetermined length. In the skeleton part sheet stacking step (S12), a part of the plurality of skeleton part sheets (22S) is joined to each other at a predetermined interval parallel to the main shock absorption direction (Z-axis direction), so that a plurality of skeleton parts are joined. This is a step of forming a skeleton block (22B) in which the partial sheets (22S) are laminated. The process forming step (S14) is a step of opening a buckling promoting opening (28) in the stacking direction in the skeleton block (22B). The stretching step (S16) is a step of stretching the skeleton block (22B) to form a three-dimensional space portion (24) having the same spatial cross section in the main shock absorption direction (Z-axis direction). The foam material filling step (S18) is a step of filling the three-dimensional space portion (24) with the foam material (26).

  The impact applied to the structure at the time of landing, landing or collision of a structure such as a space device or an aircraft can be reduced.

FIG. 1 is an external perspective view of a space device such as an atmospheric re-entry capsule and is a diagram illustrating a part of an outer wall portion of a structure including a shock absorber. FIG. 2 is an external front view of an aircraft such as a helicopter, and is a diagram illustrating the underfloor structure including the shock absorber and a part of the outer wall portion of the structure including the shock absorber. FIG. 3 is a cross-sectional view illustrating each layer of the shock absorbing material inserted into the outer wall of the structure or the shock absorbing material disposed in the underfloor structure. FIG. 4 is a cross-sectional view showing a state cut along the KK cross section (first cut surface C1) shown in FIG. FIG. 5 is a perspective view for explaining a shock absorbing material having a honeycomb structure having a hexagonal plane figure. FIG. 6 is a diagram illustrating the relationship between the displacement Z and the load W corresponding to a decrease in the distance between the outer wall and the inner wall of the outer wall portion of the structure. FIG. 7 is a cross-sectional view for explaining each layer of the shock absorbing material inserted into the outer wall of the structure or the shock absorbing material arranged in the underfloor structure, and mainly includes a plurality of shock absorbing materials having different plane areas. It is a figure explaining the structure laminated | stacked on the shock absorption direction. FIG. 8 is a cross-sectional view for explaining each layer of the shock absorbing material inserted into the outer wall of the structure or the shock absorbing material arranged in the underfloor structure, and a plurality of shock absorbing materials having different heights are arranged. It is a figure explaining the performed structure. FIG. 9 is a perspective view for explaining an impact absorbing material having a honeycomb structure having a quadrangular plan view. FIG. 10 is a perspective view for explaining a shock absorbing material having a honeycomb structure having a circular plane figure. FIG. 11 is a perspective view for explaining a shock absorbing material having a honeycomb structure having a triangular plane figure. FIG. 12 is a perspective view for explaining an impact absorbing material having a honeycomb structure having a corrugated plan view. FIG. 13 is a flowchart for explaining a method of manufacturing the shock absorbing material. FIG. 14 is an external view for explaining a skeleton part raw material roll cutting process and a skeleton part sheet laminating process. FIG. 15 is an external view for explaining the processing and forming step and the stretching step.

  With reference to an accompanying drawing, the form for carrying out an impact-absorbing material is explained below.

(Shock absorber mounting example 1)
With reference to FIG. 1, the example of attachment of the shock absorber 20 is demonstrated. FIG. 1 is an external perspective view of a space device 8 such as an atmospheric re-entry capsule, in which a part of an outer wall portion 15 of a structure including a shock absorber 20 is cut and described.

  With reference to FIG. 1, the structure outer wall 15 of the space device 8 is a wall that partitions the room 10 and the outdoor 12 of the space device 8. The structure outer wall 15 includes an inner wall 14, an outer wall 16, a heat shield 18, a shock absorber 20, and a gap 30 (or a cell gap 30C described later).

  The inner wall 14 is a member that forms a wall in the room 10 of the space device 8. The outer wall 16 is a member that forms a wall in the outdoor 12 of the space device 8.

  The heat shield 18 is a member that protects the room 10 by making it difficult for the heat generated when the outer wall 16 is heated to a high temperature when the space device 8 re-enters the atmosphere.

  The shock absorber 20 is a member for reducing the impact applied to the structure when the space device 8 (structure) re-entering the atmosphere lands on the ground or lands on the sea. Since the gap 30 is formed in a part of the layer of the shock absorber 20, the gap 30 is applied when a force is applied to the shock absorber 20 in the main shock absorption direction (Z-axis direction). A large stress is applied to the shock absorber 20 arranged on the side of the shock absorber 20 so that the shock absorber 20 is easily deformed. Therefore, the layer of the shock absorbing material 20 having more voids 30 is deformed by the load W in the relatively weak main shock absorbing direction (Z-axis direction), so that the initial load increase rate θ applied to the space device 8 is increased. Can be reduced. Further, the peak value WP of the load W applied to the space device 8 can be reduced. The temporal change of the load W applied to the space device 8, the load increase rate θ, and the peak value WP of the load W will be described later with reference to FIG.

  In general, when the space equipment 8 lands on the ground, when re-entry, the parachute is opened and decelerated after landing or landing, or when the space equipment 8 descends near the ground, a reverse injection rocket is injected to air. There is a case of landing using the cushion effect. By adding the shock absorber 20 to the structure outer wall 15 of the space device 8, it is possible to further reduce the unexpected shock when the space device 8 lands.

(Shock absorber mounting example 2)
Next, another example of attachment of the shock absorber 20 will be described with reference to FIG. FIG. 2 is an external front view of the aircraft 9 such as a helicopter, and is a diagram illustrating a part of the underfloor structure including the shock absorber 20 and a part of the structure outer wall 15 including the shock absorber 20. In addition, about the site | part which has the same function as the site | part shown in FIG. 1, the same code | symbol is attached | subjected and some description is abbreviate | omitted.

  Referring to FIG. 2, structural body outer wall portion 15 of aircraft 9 is a wall that partitions indoor 10 and outdoor 12 of aircraft 9. The structure outer wall 15 includes an inner wall 14, an outer wall 16, a shock absorber 20, and a gap 30 (or a cell gap 30C described later). In addition, the shock absorbing material 20 can be disposed in the underfloor structure below the inner wall 14 ′ (floor material) of the aircraft 9.

  The inner wall 14 is a member that forms a wall in the interior 10 of the aircraft 9. The outer wall 16 is a member that forms a wall in the outdoor 12 of the aircraft 9. The inner wall 14 ′ is a floor material for a space on which an occupant of the aircraft 9 is boarded or a space on which cargo is loaded.

  The shock absorbing material 20 is a member for alleviating an impact applied to a structure, a passenger, a cargo or other mounted object when the aircraft 9 (structure) lands on the ground at an unexpectedly high descending speed. Since the gap 30 is formed in a part of the layer of the shock absorber 20, the gap 30 is applied when a force is applied to the shock absorber 20 in the main shock absorption direction (Z-axis direction). A large stress is applied to the shock absorber 20 arranged on the side of the shock absorber 20 so that the shock absorber 20 is easily deformed. Therefore, since the layer of the shock absorbing material 20 having more voids 30 is deformed with a relatively weak load W, the initial load increase rate θ applied to the aircraft 9 can be reduced. Further, the peak value WP of the load W applied to the aircraft 9 can be reduced.

(First configuration example of the shock absorber 20)
A first configuration example of the shock absorber 20 will be described with reference to FIGS. 3 to 5. FIG. 3 is a cross-sectional view illustrating each layer of the shock absorber 20 that is inserted into the structure outer wall 15 or the shock absorber 20 that is disposed in the underfloor structure. FIG. 4 is a cross-sectional view showing a state cut along the KK cross section (first cut surface C1) shown in FIG. FIG. 5 is a perspective view for explaining a shock absorber 20 having a honeycomb structure having a hexagonal plane figure. In addition, about the site | part which has the same function as the site | part shown in FIG.1 and FIG.2, the same code | symbol is attached | subjected and the description is partially omitted.

  The shock absorber 20 includes a skeleton part 22, a three-dimensional space part 24, a foam material 26, and a cell gap part 30C.

  The skeleton part 22 has a three-dimensional shape (FIGS. 4 and 5 shown in FIG. 4 and FIG. 5) obtained by extending one or more plane figures (hexagonal plane figures in the embodiment shown in FIGS. 4 and 5) in the main shock absorption direction (Z-axis direction). In the embodiment shown, it is composed of a hexagonal prism-shaped honeycomb structure. Thereby, as for the frame | skeleton part 22, the some cut surface orthogonal to the main impact absorption direction (Z-axis direction: cell axis direction) is mutually the same shape. In FIG. 4, the hexagonal planar shape is described only in a part of the upper left, and description of other parts is omitted.

  When a large force is applied to the skeleton part 22 in the main shock absorption direction (Z-axis direction: the direction in which the outer wall 16 and the inner wall 14 are compressed), the skeleton part 22 having a honeycomb structure is buckled and deformed. By this deformation, the impact applied to the outer wall 16 can be absorbed.

  The three-dimensional space portion 24 is a space of each cell having the skeleton portion 22 as a side wall, and in the embodiment shown in FIGS. 4 and 5, is a hexagonal prism-shaped space that is long in the main shock absorption direction (Z-axis direction). At least a part of the three-dimensional space 24 shown in FIGS. 3 to 5 is filled with a foam material 26 to improve the shock absorption while increasing the buckling strength in the main shock absorption direction (Z-axis direction). . The cell gap portion 30C of the first structural example of the shock absorbing material 20 shown in FIG. 3 is composed of a three-dimensional space portion 24 of each cell having a skeleton portion 22 not filled with the foam material 26 as a side wall.

  As the material of the skeleton part 22, materials such as aluminum alloy, iron, titanium alloy, meta-aramid fiber, paper, resin, composite material, wood, concrete and the like can be used. A polyolefin material such as polyethylene or polypropylene can be used as the resin material. As the composite material, fiber reinforced plastics such as carbon fiber reinforced plastic, glass fiber reinforced plastic, aramid fiber reinforced plastic, boron fiber reinforced plastic, polyethylene fiber reinforced plastic, and Zylon reinforced plastic can be used.

  As a material of the foam material 26, a foam material such as foam resin or foam metal can be used. As the material of the foamed resin, materials such as foamed urethane, foamed polyethylene, and foamed styrene can be used. Materials such as aluminum alloy and iron can be used as the material for the foam metal. As the length of one side of the hexagonal planar shape of the skeleton part 22, for example, a dimension of 5 mm or more and 40 mm or less can be used. Moreover, the thickness of the skeleton part 22 can use a material of 0.05 mm or more and 1 mm or less.

  The thickness of the shock absorber 20 shown in FIGS. 3 and 5 in the main shock absorption direction (Z-axis direction) is L0, and is disposed on the first shock absorption layer L11 disposed on the inner wall 14 side and the outer wall 16 side. It has the 1st filled layer L12. As shown in FIG. 3, the first filling layer L12 has a second shock absorbing layer L21 and a second filling layer L22. Among these, the first shock absorbing layer L11 is a shock absorbing layer having a first cut surface C1 perpendicular to the main shock absorbing direction (Z-axis direction), and the first shock absorbing layer L11 is filled with the foam material 26. And a cell gap portion 30 </ b> C composed only of the three-dimensional space portion 24 not filled with the foam material 26.

  The second shock absorbing layer L21 is a shock absorbing layer having a second cut surface C2 perpendicular to the main shock absorbing direction (Z-axis direction), and is a second foamed material filled with the foamed material 26. Both the filling portion 32 and the cell gap portion 30 </ b> C configured only from the three-dimensional space portion 24 not filled with the foam material 26 are included.

  The second filling layer L22 shown in FIG. 3 is composed of only the third foam material filling portion 33 filled with the foam material 26, and is an impact absorbing layer in which the cell gap portion 30C does not exist.

  As shown in FIGS. 3 and 4, the area A2 of the second foam filling portion 32 in the second cut surface C2 (second shock absorbing layer L21) is equal to the first cut surface C1 (first shock absorbing layer). L11) is wider than the area A1 of the first foam filling portion 31. Further, the area A3 of the third foam filling portion 33 in the third cut surface C3 (second filling layer L22) is larger than the area A2 of the second foam filling portion 32 (second shock absorbing layer L21). Widely formed.

  When a large load W is applied to the shock absorbing material 20 shown in FIGS. 3 and 4 in the main shock absorbing direction (Z-axis direction: for example, the direction in which the outer wall 16 and the inner wall 14 are compressed), the skeleton portion 22 having a honeycomb structure. However, in a layer with a small area filled with the foam material 26 (for example, the first shock absorbing layer L11), buckling starts with a relatively small load W. Then, in a layer having a large area filled with the foam material 26 (for example, the second filling layer L22), buckling starts with a relatively large load W. In this manner, by changing the filling height of the foam material 26, the buckling load can be easily adjusted while using the structural material of the single skeleton part 22.

  Therefore, by disposing the shock absorber 20 on the outer wall 15 of the structure of the space device 8 or the aircraft 9, the relative speed when the space device 8 or the aircraft 9 is landed on the ground or landing on the water is reduced. At the initial stage, the first shock absorbing layer L11 starts buckling, thereby reducing the relative speed with a small load W, and then the second shock absorbing layer L21 starts buckling so that the medium load is reached. The load W can be gradually increased by decreasing the relative speed with W and finally buckling the second packed bed L22.

  The shock absorbing material 20 shown in FIG. 5 has a buckling promoting opening 28 on the side wall of the skeleton part 22. The buckling promoting opening 28 reduces the buckling load when a load W is applied to the skeleton portion 22 in the main shock absorption direction (Z-axis direction), and the skeleton portion 22 is buckled with a smaller load W. It is an opening for starting. The buckling promoting opening 28 can be opened on the side wall of the skeleton part 22 filled with the foam material 26 or the side wall of the skeleton part 22 having the cell gap part 30C according to the required buckling load. In general, the buckling load of the skeleton part 22 filled with the foam material 26 is larger than the buckling load of the skeleton part 22 having the cell gap part 30C. By opening a buckling promoting opening 28 on the side wall of the skeleton portion 22 filled with the foam material 26, the buckling load of the skeleton portion 22 filled with the foam material 26 and the seat of the skeleton portion 22 having the cell gap portion 30C. A buckling load intermediate to the bending load can be obtained. Further, the buckling promoting opening 28 can be an opening that communicates the side walls of the plurality of skeleton parts 22 (for example, an opening that communicates the side walls of the plurality of skeleton parts 22 in a straight line), and is opened in all directions. be able to.

  Further, as shown in the embodiment of FIG. 5, the number of buckling promoting openings 28 can be changed according to the height in the main shock absorption direction (Z-axis direction). For example, in the embodiment shown in FIG. 5, the number of buckling promoting openings 28 is decreased at a ratio of 4: 2: 1 at each of the heights D1, D2, and D3. In other words, the number of the buckling promoting openings 28 is configured to decrease stepwise as the outer wall 16 is approached in the main shock absorption direction (Z-axis direction). Moreover, you may change the opening area of a buckling promotion opening part according to an opening position. The shock absorber 20 shown in FIG. 5 is shown for an embodiment that includes both the cell gap 30C and the buckling promoting opening 28. Of the cell gap 30C or the buckling promoting opening 28, A configuration having only one of them can also be used.

  Next, transition of the deformation amount (displacement Z) when a load W is applied to the structure outer wall 15 will be described with reference to FIG. FIG. 6 is a diagram showing a relationship between the displacement W corresponding to a decrease in the distance between the outer wall 16 and the inner wall 14 of the structure outer wall portion 15 and the load W.

  The displacement characteristic W0 shown in FIG. 6 represents the relationship between the displacement Z and the load W when the shock absorber 20 is not disposed on the structure outer wall 15. When the shock absorber 20 is not disposed on the outer wall 15 of the structure, the maximum load is WP0 and the initial load increase rate is θ0. The displacement characteristic W1 represents the relationship between the displacement Z and the load W when the shock absorber 20 is disposed on the structure outer wall 15. When the shock absorber 20 is disposed on the outer wall 15 of the structure, the maximum load is reduced by ΔWP to WP1. When the shock absorber 20 is disposed on the outer wall 15 of the structure, the initial load increase rate is also decreased by Δθ to θ1.

  As shown in FIG. 6, by placing the shock absorber 20 on the structure outer wall 15 or the underfloor structure, the maximum load W applied to the structure and the inside of the structure when the space equipment 8 or the aircraft 9 is landed and the initial stage The load increase rate can be reduced.

(Second configuration example of the shock absorber 20)
Next, a second configuration example of the shock absorber 20 will be described with reference to FIG. FIG. 7 is a cross-sectional view for explaining each layer of the shock absorber 20 inserted into the structure outer wall 15 or the shock absorber 20 arranged in the underfloor structure, and a plurality of shock absorbers having different plane areas. It is a figure explaining the structure which laminated | stacked the material in the main impact absorption direction (Z-axis direction). In addition, about the site | part which has the same function as the site | part shown in FIG. 3, the same code | symbol is attached | subjected and the description is partially omitted.

  The cell gap portion 30 </ b> C of the first configuration example shown in FIG. 3 is composed of a three-dimensional space portion 24 of each cell having the skeleton portion 22 not filled with the foam material 26 as a side wall. On the other hand, the skeleton part 22 does not exist in the gap part 30 of the second configuration example shown in FIG.

  The shock absorber 20 shown in FIG. 7 includes a first shock absorber 201 disposed on the inner wall 14 side, a second shock absorber 202, and a third shock absorber 203 disposed on the outer wall 16 side. It is composed of The first shock absorbing material 201, the second shock absorbing material 202, and the third shock absorbing material 203 each include a skeleton portion 22, a three-dimensional space portion 24, and a foam material 26.

  The second shock absorber 202 is laminated in the main shock absorbing direction (Z-axis direction) by forming a gap 30 in a part of the upper part of the third shock absorber 203 layer. Similarly, the first shock absorber 201 is laminated in the main shock absorption direction (Z-axis direction) by forming a gap 30 in a part of the upper portion of the second shock absorber 202 layer. In the example illustrated in FIG. 7, the gap portion 30 is not formed in the layer of the third shock absorber 203. Further, in the embodiment shown in FIG. 7, the cell gap portion 30 </ b> C is provided in the skeleton portion 22 of each shock absorber (first shock absorber 201, second shock absorber 202, and third shock absorber 203). Does not exist. For this reason, it is possible to easily perform the filling operation of the foam material 26 in the skeleton portion 22 (for example, the delicate operation of performing the filling operation of the foam material 26 while leaving the cell gap portion 30C is unnecessary). ).

  The third planar area A3 of the third shock absorber 203 at the third cut surface C3 perpendicular to the main shock absorption direction (Z-axis direction) of the shock absorber 20 laminated in this way is It is larger than the second plane area A2 of the second shock absorber 202 at the two cut planes C2. Similarly, the second plane area A2 of the second shock absorber 202 at the second cut surface C2 is larger than the first plane area A1 of the first shock absorber 201 at the first cut plane C1. Is also big.

  Therefore, by placing the shock absorber 20 shown in FIG. 7 on the outer structure 15 of the structure of the space device 8 or the aircraft 9 or the underfloor structure, the space device 8 or the aircraft 9 is landed on the ground or on the water. When reducing the relative speed when water is applied, the first shock absorber 201 starts buckling at the initial stage to reduce the relative speed with a small load W, and then the second shock absorber 202 is By starting buckling, the relative speed can be decreased with a moderate load W, and finally the third shock absorber 203 can be buckled to gradually increase the load W. Thus, by combining the shock absorbers having the same height, the buckling load can be easily adjusted while using a small number of types of shock absorbers.

  By using the shock absorber 20 shown in FIG. 7, the structure and the maximum load W applied to the inside of the structure and the initial load increase rate can be reduced when the space device 8 or the aircraft 9 is landing or landing. . 5 is opened in the skeleton 22 of the first shock absorber 201, the second shock absorber 202, or the third shock absorber 203 shown in FIG. be able to.

  In addition, the space | gap part 30 may be comprised from the solid space part 24 (For example, cell space | gap part 30C shown in FIG. 5, etc.) of each cell which makes the frame | skeleton part 22 in which the foaming material 26 is not filled as a side wall. Further, the first shock absorbing material 201 and the second shock absorbing material 202 are composed of only the shock absorbing material filled with the foam material 26 and not having the cell gap 30C, and the skeleton portion 22 not filled with the foam material 26. The shock absorbers may be formed by arranging them in a direction perpendicular to the main shock absorption direction (Z-axis direction).

(Third configuration example of the shock absorber 20)
Next, a third configuration example of the shock absorber 20 will be described with reference to FIG. FIG. 8 is a cross-sectional view for explaining each layer of the shock absorber 20 inserted into the structure outer wall 15 or the shock absorber 20 arranged in the underfloor structure, and a plurality of shock absorbers having different heights. It is a figure explaining the structure which arranged the material. In addition, about the site | part which has the same function as the site | part shown in FIG. 3, the same code | symbol is attached | subjected and the description is partially omitted.

  In the second configuration example shown in FIG. 7, the gap portion 30 is formed by laminating a plurality of shock absorbing materials having different plane areas in the main shock absorbing direction (Z-axis direction). On the other hand, in the third configuration example shown in FIG. 8, the gap portion 30 is formed by arranging a plurality of shock absorbing materials having different heights in a direction perpendicular to the main shock absorbing direction (Z-axis direction). ing. In the third configuration example illustrated in FIG. 8, the skeleton portion 22 does not exist in the gap portion 30, as in the second configuration example illustrated in FIG. 7.

  The shock absorber 20 shown in FIG. 8 includes a first height shock absorber 301 inserted between the inner wall 14 and the outer wall 16 and a second height shock absorber 302 disposed on the outer wall 16 side. And a third height shock absorber 303. The shock absorber 20 shown in FIG. 8 is configured by arranging shock absorbers having different heights in the main shock absorption direction (Z-axis direction). The first height shock absorber 301, the second height shock absorber 302, and the third height shock absorber 303 are respectively the skeleton part 22, the three-dimensional space part 24, the foam material 26, Is provided.

  The height of the first shock absorber 301 in the main shock absorption direction (Z-axis direction) is the highest first height H1. The height of the second shock absorber 302 in the main shock absorption direction (Z-axis direction) is the second height H2. The height of the third height shock absorber 303 in the main shock absorption direction (Z-axis direction) is a third height H3. As shown in FIG. 8, the gaps 30 can be formed in the shock absorber 20 by alternately arranging shock absorbers having different heights. Further, in the embodiment shown in FIG. 8, the skeleton part 22 of each shock absorbing material (first height shock absorbing material 301, second height shock absorbing material 302, third height shock absorbing material 303). There is no cell gap 30C. For this reason, it is possible to easily perform the filling operation of the foam material 26 in the skeleton portion 22 (for example, the delicate operation of performing the filling operation of the foam material 26 while leaving the cell gap portion 30C is unnecessary). ).

  The third plane area A3 of the third cut surface C3 having the third height H3 perpendicular to the main shock absorption direction (Z-axis direction) of the shock absorbers 20 arranged in this way is the second cut area. It is larger than the second planar area A2 on the surface C2. Similarly, the second plane area A2 in the second cut plane C2 is larger than the first plane area A1 in the first cut plane C1.

  Therefore, by placing the shock absorber 20 shown in FIG. 8 on the outer wall 15 of the structure of the space device 8 or the aircraft 9 or the underfloor structure, the space device 8 or the aircraft 9 is landed on the ground or on the water. When reducing the relative speed when water is applied, the impact absorbing material 301 of the first height starts buckling in the initial stage, thereby reducing the relative speed with a small load W, and then the impact of the second height. By starting the buckling together with the absorber 302, the relative speed is reduced at a moderate load W, and finally the impact absorber 303 of the third height is also buckled to gradually increase the load W. Can be increased. Since it is only the shock absorber 301 having the first height that is closely fitted between the inner wall 14 and the outer wall 16 in the outer wall 15 of the structure body, dimensional management is easy. The other impact absorbers 302 having the second height and the impact absorbers 303 having the third height are impact absorbers for forming the gap 30, and therefore, strict height tolerance management is not necessary.

  By using the shock absorber 20 shown in FIG. 8, the maximum load W applied to the inside of the structure and the structure and the initial load increase rate when the space device 8 or the aircraft 9 is landed can be reduced. It should be noted that the buckling promotion shown in FIG. 5 is applied to the skeleton 22 of the first height shock absorber 301, the second height shock absorber 302, or the third height shock absorber 303 shown in FIG. An opening 28 can be opened.

  It should be noted that the skeleton portion 22 not filled with the foam material 26 is formed in the gap portion 30 where the shock absorbing material formed above the second height shock absorbing material 302 and the third height shock absorbing material 303 does not exist. You may arrange | position the shock-absorbing material which consists only of.

(Fourth configuration example of the shock absorber 20)
Next, a fourth configuration example of the shock absorber 20 will be described with reference to FIG. FIG. 9 is a perspective view for explaining the impact-absorbing material 20 having a honeycomb structure having a square plane figure. In addition, about the site | part which has the same function as the site | part shown in FIG. 5, the same code | symbol is attached | subjected and some description is abbreviate | omitted.

  The plane figure of the skeleton part 22 in the first configuration example shown in FIG. 5 was a hexagon. On the other hand, as shown in FIG. 9, the plane figure of the skeleton part 22 in the fourth configuration example is a quadrangle, and the lattice-like skeleton part 22 is constituted by a three-dimensional shape extending in the main shock absorption direction (Z-axis direction). The As a result, the skeleton portion 22 is a quadrangle in which a plurality of cut surfaces perpendicular to the main shock absorption direction (Z-axis direction) are the same. In addition, the dimension and material of the skeleton part 22 in the 1st structural example shown in FIG. 5 can be used for the dimension and material of one side of the skeleton part 22. FIG.

  The three-dimensional space portion 24 shown in FIG. 9 is a space of each cell having the skeleton portion 22 as a side wall, and is a quadrangular prism-shaped space that is long in the main shock absorption direction (Z-axis direction). At least a part of the three-dimensional space portion 24 shown in FIG. 9 is filled with the foam material 26, so that the impact absorption can be improved while increasing the buckling strength in the main shock absorption direction (Z-axis direction). In addition, as shown in FIG. 5, one or more buckling promoting openings 28 can be opened on the side wall of the skeleton part 22.

  By forming the cell gap 30C or gap 30 shown in FIGS. 3, 7, and 8 using the shock absorber 20 shown in FIG. 9, the space device 8 or the aircraft 9 is landing or landing. The maximum load W applied to the inside of the structure and the structure and the initial load increase rate can be reduced.

(Fifth configuration example of the shock absorber 20)
Next, a fifth configuration example of the shock absorber 20 will be described with reference to FIG. FIG. 10 is a perspective view for explaining a shock absorbing material 20 having a honeycomb structure having a circular plane figure. In addition, about the site | part which has the same function as the site | part shown in FIG. 5, the same code | symbol is attached | subjected and some description is abbreviate | omitted.

  The plane figure of the skeleton part 22 in the fourth configuration example shown in FIG. On the other hand, as shown in FIG. 10, the plane figure of the skeleton part 22 in the fifth configuration example is circular, and the circular skeleton part 22 is constituted by a three-dimensional shape extending in the main shock absorption direction (Z-axis direction). . As a result, the skeleton portion 22 has a circular shape in which a plurality of cut surfaces perpendicular to the main shock absorption direction (Z-axis direction) are the same shape. In addition, the dimension and material of the diameter of the skeleton part 22 can use the dimension and material of the one side of the skeleton part 22 in the 1st structural example shown in FIG.

  The three-dimensional space portion 24 shown in FIG. 10 is a space of each cell having the skeleton portion 22 as a side wall, and is a cylindrical space that is long in the main shock absorption direction (Z-axis direction). At least a part of the three-dimensional space portion 24 shown in FIG. 10 is filled with the foam material 26, and the impact absorption can be improved while increasing the buckling strength in the main shock absorption direction (Z-axis direction). In addition, as shown in FIG. 5, one or more buckling promoting openings 28 can be opened on the side wall of the skeleton part 22.

  By forming the cell gap 30C or gap 30 shown in FIGS. 3, 7, and 8 using the shock absorber 20 shown in FIG. 10, the space device 8 or the aircraft 9 is landing or landing. The maximum load W applied to the inside of the structure and the structure and the initial load increase rate can be reduced.

(Sixth configuration example of the shock absorber 20)
Next, a sixth configuration example of the shock absorbing material 20 will be described with reference to FIG. FIG. 11 is a perspective view for explaining a shock absorber 20 having a honeycomb structure having a triangular plane figure. In addition, about the site | part which has the same function as the site | part shown in FIG. 5, the same code | symbol is attached | subjected and some description is abbreviate | omitted.

  The plane figure of the skeleton part 22 in the fifth configuration example shown in FIG. 10 was circular. On the other hand, as shown in FIG. 11, the plane figure of the skeleton part 22 in the sixth configuration example is a triangle, and the triangular skeleton part 22 is constituted by a three-dimensional shape extending in the main shock absorption direction (Z-axis direction). . Thereby, the skeleton part 22 is a triangle in which a plurality of cut surfaces perpendicular to the main shock absorption direction (Z-axis direction) are the same shape. In addition, the dimension and material of one side of the skeleton part 22 in the first configuration example shown in FIG. 5 can be used as the dimension and material of one side of the skeleton part 22.

  The three-dimensional space portion 24 shown in FIG. 11 is a space of each cell having the skeleton portion 22 as a side wall, and is a triangular prism-shaped space that is long in the main shock absorption direction (Z-axis direction). At least a part of the three-dimensional space portion 24 shown in FIG. 11 is filled with the foam material 26, so that the impact absorption can be improved while increasing the buckling strength in the main shock absorption direction (Z-axis direction). In addition, as shown in FIG. 5, one or more buckling promoting openings 28 can be opened on the side wall of the skeleton part 22.

  By using the shock absorber 20 shown in FIG. 11 to form the cell gap 30C or the gap 30 shown in FIGS. 3, 7 and 8, the space device 8 or the aircraft 9 is landing or landing. The maximum load W applied to the inside of the structure and the structure and the initial load increase rate can be reduced.

(Seventh configuration example of the shock absorber 20)
Next, a seventh configuration example of the shock absorber 20 will be described with reference to FIG. FIG. 12 is a perspective view illustrating a shock absorber 20 having a honeycomb structure having a corrugated plan view. In addition, about the site | part which has the same function as the site | part shown in FIG. 5, the same code | symbol is attached | subjected and some description is abbreviate | omitted.

  The plane figure of the skeleton part 22 in the sixth configuration example shown in FIG. 11 is a triangle. On the other hand, as shown in FIG. 12, the plane figure of the skeleton part 22 in the seventh configuration example is constituted by a waveform and a linear shape, and the skeleton part 22 having the waveform and the linear shape is in the main shock absorption direction (Z-axis direction). It is comprised by the three-dimensional shape extended | stretched. As a result, the skeleton portion 22 has a plurality of cut surfaces perpendicular to the main shock absorption direction (Z-axis direction) having the same waveform and linear shape. In addition, the dimension and material of the side of the frame | skeleton part 22 in the 1st structural example shown in FIG. 5 can be used for the dimension and material of the space | interval between the peak part of the waveform of the frame | skeleton part 22. FIG.

  12 is a space of each cell having the skeleton portion 22 as a side wall, and is a space of each cell surrounded by a long waveform and a linear side wall in the main shock absorption direction (Z-axis direction). is there. At least a part of the three-dimensional space portion 24 shown in FIG. 12 is filled with the foam material 26, so that the shock absorption can be improved while increasing the buckling strength in the main shock absorption direction (Z-axis direction). In addition, as shown in FIG. 5, one or more buckling promoting openings 28 can be opened on the side wall of the skeleton part 22.

  By using the shock absorber 20 shown in FIG. 12 to form the cell gap 30C or the gap 30 shown in FIGS. 3, 7 and 8, the space device 8 or the aircraft 9 is landing or landing. The maximum load W applied to the inside of the structure and the structure and the initial load increase rate can be reduced.

(Manufacturing method of shock absorber 20)
Next, a manufacturing method of the shock absorber 20 in which the buckling promoting opening 28 is opened in the skeleton portion 22 of the hexagonal columnar honeycomb structure will be described with reference to FIGS. FIG. 13 is a flowchart for explaining a manufacturing method of the shock absorber 20. FIG. 14 is an external view for explaining a skeleton part raw material roll cutting process and a skeleton part sheet laminating process. FIG. 15 is an external view for explaining the processing and forming step and the stretching step. In addition, about the site | part which has the same function as the site | part shown in FIG. 5, the same code | symbol is attached | subjected and some description is abbreviate | omitted.

  In step S10 “skeleton part raw material roll cutting step” in FIG. 13, the operator cuts the skeleton part raw material roll 22R such as an aluminum alloy foil to a predetermined length by using a cutting machine or the like, and the skeleton part sheet 22S is cut. A plurality of moldings are performed (see FIG. 14).

  In step S12 “skeleton part sheet laminating step”, the operator uses a dispenser or the like to form an adhesive for forming the adhesive layer 23 between the skeleton part sheets 22S, which is necessary when forming the honeycomb structure. It is applied to the upper surface of the partial sheet 22S. The adhesive layer 23 is formed at a plurality of locations at predetermined intervals in parallel with the main shock absorption direction (Z-axis direction). (See FIG. 14). Note that folds and cuts for improving the flexibility of the skeleton part 22 at the time of expansion can be formed as necessary. And the newly cut | disconnected frame | skeleton part sheet | seat 22S is joined and laminated | stacked on the upper part of the frame | skeleton part sheet | seat 22S in which the contact bonding layer 23 was formed. Then, a new adhesive layer 23 is formed on the upper surface of the newly cut frame portion sheet 22S. This lamination is repeated a plurality of times to complete the skeleton block 22B (see FIG. 14).

  In step S14 “work forming step”, the operator opens one or a plurality of buckling promoting openings 28 in the stacking direction on the side wall of the skeleton part 22 of the skeleton part block 22B (see FIG. 15). More buckling promoting openings 28 are opened than the buckling promoting openings 28 shown in FIG. The buckling promoting opening 28 may be provided so as to penetrate the plurality of skeleton part sheets 22S. Moreover, the cutting which adjusts the width | variety and length of the frame | skeleton part block 22B suitably can also be performed in this process as needed.

  In step S16 “expansion step”, the operator expands the skeleton block 22B to a predetermined thickness, and has the same spatial cross section in the main shock absorption direction (Z-axis direction) (in the embodiment shown in FIG. 15, a hexagonal prism shape). .) Is formed.

  In step S18 “foaming material filling step”, the operator fills the foaming material 26 into a part or all of the three-dimensional space portion 24 formed in step S16.

  In step S20 “shock absorber stacking step”, the worker stacks a plurality of shock absorbers to form the gap 30 as in the second configuration example of the shock absorber 20 shown in FIG. In this way, the shock absorbing material 20 including the skeleton part 22, the three-dimensional space part 24 of each cell having the skeleton part 22 as a side wall, and the foam material 26 filled in at least a part of the three-dimensional space part 24 is completed. To do.

  The shock absorber according to the present invention has been described above with reference to the embodiment. However, the shock absorber according to the present invention is not limited to the above embodiment. Various modifications can be made to the above embodiment. It is possible to combine the matters described in the above embodiment with the matters described in the other embodiments.

  Note that the foam material 26 also generally has an effect of performing heat insulation against a temperature difference between the outer wall 16 and the inner wall 14. Therefore, by disposing the foam material 26 along the entire inner surface of the outer wall 16, the temperature of the outer wall 16 can be made difficult to be transmitted to the indoor 10 side.

8 ... Space equipment 9 ... Aircraft 10 ... Indoor 12 ... Outdoor 14 ... Inner wall 15 ... Structure outer wall 16 ... Outer wall 18 ... Heat shield 20 ... Shock Absorbing material 22 ... Skeletal part 22R ... Skeletal part raw material roll 22S ... Skeletal part sheet 22B ... Skeletal part block 23 ... Adhesive layer 24 ... Solid space part 26 ... Foam 28 ... Buckling promoting opening 30 ... Cavity 30C ... Cell gap 31 ... First foam filling part 32 ... Second foam filling part 33 ... Third Foam filling portion 201 ... first shock absorber 202 ... second shock absorber 203 ... third shock absorber 301 ... first height shock absorber 302 ... 2nd height shock absorber 303 ... 3rd height shock absorber A1 ... 1st plane area A2 ... 2nd plane area A3 ... 3rd plane area C1 ... First cut surface C2 ... second cut surface C3 ... third cut surface H1 ... first height H2 ... second height H3 ... third height L11 ... first shock absorbing layer L12 ... first filling layer L21 ... second shock absorbing layer L22 ... second filling layer

Claims (10)

A shock absorber comprising a skeleton part, a three-dimensional space part of each cell having the skeleton part as a side wall, and a foam material filled in at least a part of the three-dimensional space part,
The skeleton part is composed of a three-dimensional shape obtained by extending one or more planar figures in the main shock absorption direction,
A first cut surface perpendicular to the main shock absorption direction has a first foam filling portion filled with the foam material, and a cell gap portion not filled with the foam material. A shock absorbing layer;
A second shock absorbing layer having a second foam filling portion filled with the foam material at a second cut surface perpendicular to the main shock absorbing direction,
The area of the second foam filling portion in the second cut surface is formed wider than the area of the first foam filling portion in the first cut surface. A shock absorber comprising a skeleton part, a three-dimensional space part of each cell having the skeleton part as a side wall, and a foam material filled in the three-dimensional space part,
The skeleton part is composed of a three-dimensional shape obtained by extending one or more planar figures in the main shock absorption direction,
A first shock absorber having a first planar area at a cutting plane perpendicular to the main shock absorbing direction;
A shock absorbing material obtained by laminating a second shock absorbing material having a second plane area larger than the first plane area in a cut plane perpendicular to the main shock absorbing direction in the main shock absorbing direction. A shock absorber comprising a skeleton part, a three-dimensional space part of each cell having the skeleton part as a side wall, and a foam material filled in the three-dimensional space part,
The skeleton part is composed of a three-dimensional shape obtained by extending one or more planar figures in the main shock absorption direction,
A first height shock absorber having a first height relative to the main shock absorbing direction;
A shock absorber having a second height having a second height lower than the first height with respect to the main shock absorption direction and arranged in a direction perpendicular to the main shock absorption direction. The impact absorbing material according to claim 2 or 3, wherein the three-dimensional space portion does not include a cell gap portion that is not filled with the foam material. The impact-absorbing material according to any one of claims 1 to 4, wherein a shape of the plane figure of the skeleton has a polygonal shape, a circular shape, or a wave shape. The shock absorber according to any one of claims 1 to 5, wherein the side wall of the skeleton has one or more buckling promoting openings. A shock absorber comprising a skeleton part, a three-dimensional space part of each cell having the skeleton part as a side wall, and a foam material filled in the three-dimensional space part,
The skeleton part is composed of a three-dimensional shape obtained by extending one or more planar figures in the main shock absorption direction,
An impact absorbing material having one or more buckling promoting openings on a side wall of the skeleton. The shock absorbing material according to claim 6 or 7, wherein the buckling promoting opening is an opening that communicates with the side walls of the plurality of skeleton parts. The shock absorber according to any one of claims 1 to 8, an inner wall, and an outer wall,
An outer wall portion of a structure of a space device or an aircraft in which the shock absorbing material is disposed between the inner wall and the outer wall. A manufacturing method of an impact absorbing material comprising: a skeleton part; a three-dimensional space part of each cell having the skeleton part as a side wall; and a foam material filled in at least a part of the three-dimensional space part,
A skeleton part raw material roll cutting step of cutting a skeleton part raw material roll and forming a plurality of skeleton part sheets of a predetermined length;
A skeleton part sheet laminating step for forming a skeleton part block in which a part of the plurality of skeleton part sheets is joined at a plurality of positions with a predetermined interval parallel to the main shock absorption direction to form a skeleton part block. When,
A process of forming a buckling promoting opening in the stacking direction in the skeleton block; and
Extending the skeleton block to form a three-dimensional space having the same spatial cross section in the main shock absorption direction;
A foam absorbing material filling step of filling the three-dimensional space with a foam material.

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