WO2011132292A1 - エネルギー吸収構造体 - Google Patents
エネルギー吸収構造体 Download PDFInfo
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- WO2011132292A1 WO2011132292A1 PCT/JP2010/057157 JP2010057157W WO2011132292A1 WO 2011132292 A1 WO2011132292 A1 WO 2011132292A1 JP 2010057157 W JP2010057157 W JP 2010057157W WO 2011132292 A1 WO2011132292 A1 WO 2011132292A1
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- WIPO (PCT)
- Prior art keywords
- energy
- contact portion
- energy absorbing
- energy absorption
- displacement
- Prior art date
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F7/00—Vibration-dampers; Shock-absorbers
- F16F7/12—Vibration-dampers; Shock-absorbers using plastic deformation of members
- F16F7/121—Vibration-dampers; Shock-absorbers using plastic deformation of members the members having a cellular, e.g. honeycomb, structure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F2224/00—Materials; Material properties
- F16F2224/02—Materials; Material properties solids
- F16F2224/0225—Cellular, e.g. microcellular foam
Definitions
- the present invention relates to an energy absorbing structure for absorbing impact energy.
- a shock absorbing device for absorbing impact energy for example, a landing shock absorbing device for a rotary wing aircraft described in Patent Document 1 below is known.
- a landing shock absorbing device for a rotary wing aircraft described in Patent Document 1 below is known.
- a seat lower portion located below the seat and a floor plate are connected in a separable state by a shear pin, and an impact absorbing means comprising a honeycomb core is arranged below the seat lower portion.
- the lower portion of the seat When a predetermined impact load is applied to the landing impact absorbing device, the lower portion of the seat is separated from the floor plate and lowered by the shear pin breaking, and is supported by the honeycomb core.
- the honeycomb core is plastically deformed to absorb impact energy.
- this invention aims at providing the energy absorption structure which can suppress that an energy absorption member falls when a load is added to the energy absorption structure, and can absorb load energy effectively. To do.
- the energy absorption structure according to the present invention includes an energy absorption member that is installed adjacent to the first member and absorbs energy, and a displacement suppression member that suppresses relative displacement between the first member and the energy absorption member.
- the displacement suppressing member connects the first member and the energy absorbing member.
- the displacement suppressing member that connects the first member and the energy absorbing member suppresses the relative displacement between the first member and the energy absorbing member.
- the energy absorbing member can be prevented from falling and load energy can be effectively absorbed.
- the displacement suppressing member is disposed so as to straddle the contact portion between the first member and the energy absorbing member.
- the contact part is not only a mode in which the first member and the energy absorbing member are in direct contact, but the first member and the energy absorbing member are interposed between the first member and the energy absorbing member via another member.
- the aspect which contacts indirectly is also included.
- the first member is an aircraft fuselage frame
- the displacement suppressing member is a side surface of the fuselage frame adjacent to the contact portion between the fuselage frame and the energy absorbing member, and the contact portion. What connects the side surface of the energy absorption member adjacent to is suitable.
- An aircraft often has a curved surface, and even if the aircraft does not tilt, a component force that tries to defeat the energy absorbing member may be generated. According to the present invention, such an aircraft is used. In this case, the energy absorbing member can be prevented from falling and load energy can be effectively absorbed.
- the displacement suppressing member has a maximum thickness at the contact portion and becomes thinner as the distance from the contact portion increases. Therefore, since it is possible to improve the connection strength while suppressing an increase in weight, the relative displacement between the first member and the energy absorbing member can be efficiently suppressed, and the energy absorbing member can be effectively prevented from falling. Load energy can be absorbed.
- the displacement suppression member is a fibrous member, and one end of the displacement suppression member is the first member so as to cover a contact portion between the first member and the energy absorption member. It is preferable that the side surface of the displacement suppressing member is radially expanded and disposed, and the other end of the displacement suppressing member is radially expanded on the side surface of the energy absorbing member.
- the first member is an aircraft fuselage frame
- the energy absorbing member has a honeycomb structure in which a plurality of hollow columnar cells extending from a contact portion with the fuselage frame are formed.
- the displacement suppression member is a plurality of fibrous members, and one end of the displacement suppression member is radially on the side surface of the fuselage frame adjacent to the contact portion with the end portion of the contact portion as a central point. It is preferable that the other end of the displacement suppressing member is radially extended from the center point to the side surface of the cell.
- FIG. 1 It is a schematic block diagram which shows the energy absorption structure which concerns on embodiment of this invention with an aircraft. It is an II-II arrow line view of FIG. It is a perspective view which shows the overlay collapse suppression member of the energy absorption structure shown in FIG. It is sectional drawing which shows the overlay collapse suppression member of the energy absorption structure shown in FIG. It is a perspective view which shows the roving fall suppression member of the energy absorption structure shown in FIG.
- FIG. 1 is a schematic configuration diagram showing an energy absorbing structure according to an embodiment of the present invention together with an aircraft.
- 2 is a view taken in the direction of arrows II-II in FIG. Note that FIG. 2 shows a structure only on one side in the aircraft width direction of the aircraft.
- an energy absorption structure 50 is mounted on an aircraft 2.
- This energy absorbing structure 50 is provided to absorb impact energy when the aircraft 2 collides with the ground 1 or the like due to emergency landing or the like, and is provided in front of and below the aircraft 2.
- the energy absorbing structure 50 includes an energy absorbing member (Energy Absorb member, hereinafter referred to as EA member) 3, an overlay collapse suppressing member (displacement suppressing member) 5, and a roving collapse suppressing member (displacement). (Suppression member) 6 is provided.
- the EA member 3 is for absorbing impact energy, and is installed adjacent to a fuselage frame (first member) 4 extending in the front-rear direction of the aircraft at the front and lower part of the aircraft 2. Specifically, the EA member 3 is installed adjacent to the bottom surface of the body frame 4, thereby forming a contact portion 8 between the body frame 4 and the EA member 3.
- the contact portion 8 is not limited to a mode in which the body frame 4 and the EA member 3 are in direct contact, but the body frame 4 and the EA member 3 are indirectly connected via a separate member between the body frame 4 and the EA member 3. It is also possible to make a mode of contact.
- the EA member 3 is configured by arranging a plurality of hollow columnar cells 30 extending from the contact portion 8 so as to form a honeycomb structure.
- a hollow quadrangular column as shown in FIG. 3 but also a hollow polygonal column such as a hollow hexagonal column or a hollow triangular column can be used.
- the EA member side surface 31 along the longitudinal direction of the body of the EA member 3 is connected to the frame side surface 41 along the longitudinal direction of the body of the fuselage frame 4 in a straight line or smoothly.
- the end surface of the EA member 3 opposite to the contact portion 8 is formed to have a shape along the body skin panel 7.
- the material of the EA member 3 is preferably a fiber reinforced plastic (hereinafter referred to as FRP material) such as a carbon fiber reinforced plastic that has a large effective stroke and excellent energy absorption characteristics and is lightweight, but aluminum or the like is used. May be. Further, instead of the member having the honeycomb structure, a foamed resin material, a foam metal, or the like may be used.
- FRP material fiber reinforced plastic
- a foamed resin material a foam metal, or the like may be used instead of the member having the honeycomb structure.
- FIG. 3 is a perspective view showing the overlay collapse suppressing member 5 of the energy absorbing structure shown in FIG.
- FIG. 4 is a cross-sectional view showing the overlay collapse suppressing member 5 of the energy absorbing structure shown in FIG.
- the overlay collapse suppression member 5 is for suppressing the relative displacement between the body frame 4 and the EA member 3 due to a collision, and connects the body frame 4 and the EA member 3. Specifically, as shown in FIG. 3, the overlay collapse suppression member 5 connects the frame side surface 41 of the body frame adjacent to the contact portion 8 and the EA member side surface 31 of the EA member 3 adjacent to the contact portion 8. is doing. That is, the overlay collapse suppression member 5 is disposed so as to straddle the contact portion 8 between the body frame 4 and the EA member 3.
- the overlay collapse suppression members 5 are provided on the outer side in the body width direction and on the inner side in the body width direction, respectively.
- the overlay collapse suppression member 5 is formed by adhesively bonding (ie, overlay bonding) the FRP material in layers so as to cover the frame side surface 41 and the EA member side surface 31.
- overlay bonding the thickness of the overlay collapse suppression member 5 is maximized at the contact portion 8 and directly covered with the frame side surface 41 and the EA member side surface 31 so that the thickness decreases as the distance from the contact portion 8 increases.
- the lower layer FRP material is made the largest, and the FRP material is made smaller step by step as it goes to the upper layer, so that stagger overlay is achieved.
- the body width of the EA member 3 is superposed by the superposition of the compressive force acting on the EA member 3 and the moment to try to collapse the EA member 3.
- the buckling of the EA member 3 that is likely to occur in the upper part in the direction can be suppressed.
- a metal plate may be used instead of the FRP material.
- FIG. 5 is a perspective view showing the roving collapse suppressing member 6 of the energy absorbing structure shown in FIG.
- the roving collapse suppression member 6 is for suppressing the relative displacement between the body frame 4 and the EA member 3 due to a collision, and connects the body frame 4 and the EA member 3.
- the roving collapse suppression member 6 is a plurality of fibrous members, one end of which is radially spread over the frame side surface 41 of the body frame 4 so as to cover the contact portion 8, and the other end Are arranged radially on the cell side surfaces 32 and 33 of the cell 30 which is an energy absorbing member.
- the cell side surface 32 is a side surface along the airframe width direction that forms the outer periphery of the EA member 3 among the side surfaces of the cell 30, and the cell side surface 33 is a side surface along the airframe width direction that contacts the adjacent cell 30. It is.
- one end of the roving collapse suppression member 6 is arranged radially on the frame side surface 41 with the end portion of the contact portion 8 as a center point, and the other end is arranged from the same center point to the cell side surface 32 or the cell.
- the side surface 33 is radially expanded.
- the roving collapse suppressing member 6 is provided on the outer side in the body width direction and on the inner side in the body width direction.
- a string-like FRP roving material in which FRP material fibers are bundled is preferably used, but a thin metal wire or a synthetic resin string may be used.
- the roving collapse suppression member 6 is provided in the following process, for example.
- a cell 30 is formed by winding a FRP material prepreg sheet or the like around a core material such as silicon, and at the stage of stacking this to form the EA member 3, a string-like FRP roving material dipped in resin is added to the cell 30.
- a plurality of FRP roving materials are arranged so that the central portion is located at the center point described above, and one end of the FRP roving material is radially spread on the cell side surface 32 or the cell side surface 33 of the cell 30 so that the thickness of the FRP roving material is reduced.
- the other end of the FRP roving material is radially spread on the frame side surface 41 of the fuselage frame 4, laid up, and the fuselage frame 4 and the EA member 3 are integrally formed. In this way, the roving collapse suppression member 6 can be provided.
- a load F is applied to the aircraft 2. Since the bottom surface of the aircraft 2 has a curved surface shape, and the aircraft 2 collides with the ground 1 or the like with a forward speed, even if the aircraft 2 collides with the ground 1 without tilting, the EA member 3 is tilted against the load F.
- the component force (component force in the aircraft width direction and component force in the longitudinal direction of the aircraft) is included.
- the aircraft 2 tries to further defeat the EA member 3.
- the power to do works.
- the EA member 3 is more likely to fall down because the interior width is as narrow as about 1.2 m and the EA member 3 cannot be widened.
- the component force in the vertical direction of the fuselage is progressive progressive failure when the EA member 3 of the energy absorbing structure 50 is plastically deformed or the EA member 3 is a brittle material such as carbon fiber reinforced plastic.
- the component force in the body width direction tries to tilt the EA member 3 inward in the body width direction.
- the overlay collapse suppression member 5 is provided, so that the EA member 3 is prevented from being peeled from the fuselage frame 4 on the outer side in the body width direction.
- the EA member 3 On the inner side in the direction, the EA member 3 is prevented from being damaged from the corner. Therefore, the EA member 3 can be prevented from falling to the inner side in the body width direction, and load energy can be effectively absorbed.
- the aircraft 2 is a small aircraft, the effect is more easily exhibited.
- the EA member 3 since the thickness of the overlay collapse suppression member 5 is thinned as it leaves
- the moment generated by the component force in the machine width direction of the load F due to the tension of the roving collapse suppression member 6 is transmitted to the body frame 4. Therefore, the EA member 3 can be further suppressed from falling to the inner side in the body width direction, and load energy can be effectively absorbed. In addition, when the aircraft 2 is a small aircraft, the effect is more easily exhibited.
- the EA member 3 when the EA member 3 is plastically deformed to the position of the roving collapse suppression member 6 due to the component force of the load F in the vertical direction of the fuselage or when the EA member 3 is a brittle material such as carbon fiber reinforced plastic, Even so, since the roving collapse suppression member 6 is not arranged in a direction that greatly contributes to energy absorption, the energy absorption function of the EA member 3 is rarely impaired. Further, since the roving collapse suppression member 6 is arranged in the body width direction, the load F can be transmitted in the body width direction.
- the overlay collapse suppressing member 5 and the roving that connect the body frame 4 and the EA member 3 when a load is applied to the energy absorbing structure 50 Since the relative displacement between the body frame 4 and the EA member 3 is suppressed by the collapse suppressing member 6, it is possible to suppress the energy absorbing member from falling and effectively absorb the load energy.
- this invention is not limited to embodiment mentioned above,
- the overlay collapse suppression member 5 is provided so that the body front-back direction may be followed.
- it may be provided along the body width direction.
Abstract
Description
Claims (6)
- 第一部材に隣接して設置され、エネルギーを吸収するエネルギー吸収部材と、
前記第一部材と前記エネルギー吸収部材との相対変位を抑制する変位抑制部材とを備え、
前記変位抑制部材は、前記第一部材と前記エネルギー吸収部材とを連結する、
エネルギー吸収構造体。 - 前記変位抑制部材が、前記第一部材と前記エネルギー吸収部材との接触部をまたぐように配置される、
請求項1に記載のエネルギー吸収構造体。 - 前記第一部材は、航空機の胴体フレームであり、
前記変位抑制部材は、前記胴体フレームと前記エネルギー吸収部材との接触部に隣接した前記胴体フレームの側面と、前記接触部に隣接した前記エネルギー吸収部材の側面とを連結する、
請求項1に記載のエネルギー吸収構造体。 - 前記変位抑制部材の厚さが、前記接触部で最大となり、前記接触部から離れるに従い薄くなる、
請求項2または請求項3に記載のエネルギー吸収構造体。 - 前記変位抑制部材は、繊維状の部材であり、
前記第一部材と前記エネルギー吸収部材との接触部を覆うように、前記変位抑制部材の一方端が前記第一部材の側面に放射状に広げて配置され、前記変位抑制部材の他方端が前記エネルギー吸収部材の側面に放射状に広げて配置される、
請求項1に記載のエネルギー吸収構造体。 - 前記第一部材は、航空機の胴体フレームであり、
前記エネルギー吸収部材は、前記胴体フレームとの接触部から延びた複数の中空柱状のセルをハニカム構造となるように並設して構成され、
前記変位抑制部材は、複数の繊維状の部材であり、
前記変位抑制部材の一方端は、前記接触部の端部を中心点として前記接触部と隣接した前記胴体フレームの側面に放射状に広げて配置され、前記変位抑制部材の他方端は、前記中心点から前記セルの側面に放射状に広げて配置される、
請求項1に記載のエネルギー吸収構造体。
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2012511464A JPWO2011132292A1 (ja) | 2010-04-22 | 2010-04-22 | エネルギー吸収構造体 |
US13/634,756 US20130026289A1 (en) | 2010-04-22 | 2010-04-22 | Energy absorption structure |
PCT/JP2010/057157 WO2011132292A1 (ja) | 2010-04-22 | 2010-04-22 | エネルギー吸収構造体 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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PCT/JP2010/057157 WO2011132292A1 (ja) | 2010-04-22 | 2010-04-22 | エネルギー吸収構造体 |
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WO2011132292A1 true WO2011132292A1 (ja) | 2011-10-27 |
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PCT/JP2010/057157 WO2011132292A1 (ja) | 2010-04-22 | 2010-04-22 | エネルギー吸収構造体 |
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US (1) | US20130026289A1 (ja) |
JP (1) | JPWO2011132292A1 (ja) |
WO (1) | WO2011132292A1 (ja) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2013244791A (ja) * | 2012-05-24 | 2013-12-09 | Toyota Motor Corp | 衝撃吸収装置 |
JP2019043459A (ja) * | 2017-09-06 | 2019-03-22 | 本田技研工業株式会社 | フロアパネルのエネルギー吸収構造 |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN109850137A (zh) * | 2019-03-18 | 2019-06-07 | 西安爱生技术集团公司 | 一种伞降无人机可快速拆卸的后支点减震机构 |
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- 2010-04-22 WO PCT/JP2010/057157 patent/WO2011132292A1/ja active Application Filing
- 2010-04-22 US US13/634,756 patent/US20130026289A1/en not_active Abandoned
- 2010-04-22 JP JP2012511464A patent/JPWO2011132292A1/ja active Pending
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JP2013244791A (ja) * | 2012-05-24 | 2013-12-09 | Toyota Motor Corp | 衝撃吸収装置 |
JP2019043459A (ja) * | 2017-09-06 | 2019-03-22 | 本田技研工業株式会社 | フロアパネルのエネルギー吸収構造 |
Also Published As
Publication number | Publication date |
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JPWO2011132292A1 (ja) | 2013-07-18 |
US20130026289A1 (en) | 2013-01-31 |
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