WO2015049898A1 - 継手及び航空機構造 - Google Patents

継手及び航空機構造 Download PDF

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Publication number
WO2015049898A1
WO2015049898A1 PCT/JP2014/065864 JP2014065864W WO2015049898A1 WO 2015049898 A1 WO2015049898 A1 WO 2015049898A1 JP 2014065864 W JP2014065864 W JP 2014065864W WO 2015049898 A1 WO2015049898 A1 WO 2015049898A1
Authority
WO
WIPO (PCT)
Prior art keywords
joint
base material
strength
plane
inclined portion
Prior art date
Application number
PCT/JP2014/065864
Other languages
English (en)
French (fr)
Inventor
阿部　俊夫
清嘉 ▲高▼木
小山　貴之
和昭 岸本
齋藤　浩一
隆司 石田
Original Assignee
三菱重工業株式会社
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 三菱重工業株式会社 filed Critical 三菱重工業株式会社
Priority to US14/916,311 priority Critical patent/US10040538B2/en
Priority to CA2923152A priority patent/CA2923152C/en
Priority to EP14851251.0A priority patent/EP3029339A4/en
Priority to CN201480048925.1A priority patent/CN105518315B/zh
Priority to BR112016004953A priority patent/BR112016004953A2/pt
Priority to RU2016107659A priority patent/RU2632552C1/ru
Publication of WO2015049898A1 publication Critical patent/WO2015049898A1/ja

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
    • B29C65/5057—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like positioned between the surfaces to be joined
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
    • B29C65/5064—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like of particular form, e.g. being C-shaped, T-shaped
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
    • B29C65/5064—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like of particular form, e.g. being C-shaped, T-shaped
    • B29C65/5071—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like of particular form, e.g. being C-shaped, T-shaped and being composed by one single element
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
    • B29C65/5064—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like of particular form, e.g. being C-shaped, T-shaped
    • B29C65/5085—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like of particular form, e.g. being C-shaped, T-shaped and comprising grooves, e.g. being E-shaped, H-shaped
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/11—Joint cross-sections comprising a single joint-segment, i.e. one of the parts to be joined comprising a single joint-segment in the joint cross-section
    • B29C66/112—Single lapped joints
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/11—Joint cross-sections comprising a single joint-segment, i.e. one of the parts to be joined comprising a single joint-segment in the joint cross-section
    • B29C66/114—Single butt joints
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/12—Joint cross-sections combining only two joint-segments; Tongue and groove joints; Tenon and mortise joints; Stepped joint cross-sections
    • B29C66/124—Tongue and groove joints
    • B29C66/1244—Tongue and groove joints characterised by the male part, i.e. the part comprising the tongue
    • B29C66/12443—Tongue and groove joints characterised by the male part, i.e. the part comprising the tongue having the tongue substantially in the middle
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/12—Joint cross-sections combining only two joint-segments; Tongue and groove joints; Tenon and mortise joints; Stepped joint cross-sections
    • B29C66/124—Tongue and groove joints
    • B29C66/1246—Tongue and groove joints characterised by the female part, i.e. the part comprising the groove
    • B29C66/12463—Tongue and groove joints characterised by the female part, i.e. the part comprising the groove being tapered
    • B29C66/12464—Tongue and groove joints characterised by the female part, i.e. the part comprising the groove being tapered being V-shaped
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/13—Single flanged joints; Fin-type joints; Single hem joints; Edge joints; Interpenetrating fingered joints; Other specific particular designs of joint cross-sections not provided for in groups B29C66/11 - B29C66/12
    • B29C66/131—Single flanged joints, i.e. one of the parts to be joined being rigid and flanged in the joint area
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/301—Three-dimensional joints, i.e. the joined area being substantially non-flat
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/40—General aspects of joining substantially flat articles, e.g. plates, sheets or web-like materials; Making flat seams in tubular or hollow articles; Joining single elements to substantially flat surfaces
    • B29C66/41—Joining substantially flat articles ; Making flat seams in tubular or hollow articles
    • B29C66/43—Joining a relatively small portion of the surface of said articles
    • B29C66/434—Joining substantially flat articles for forming corner connections, fork connections or cross connections
    • B29C66/4344—Joining substantially flat articles for forming fork connections, e.g. for making Y-shaped pieces
    • B29C66/43441—Joining substantially flat articles for forming fork connections, e.g. for making Y-shaped pieces with two right angles, e.g. for making T-shaped pieces, H-shaped pieces
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
    • B29C66/51—Joining tubular articles, profiled elements or bars; Joining single elements to tubular articles, hollow articles or bars; Joining several hollow-preforms to form hollow or tubular articles
    • B29C66/52—Joining tubular articles, bars or profiled elements
    • B29C66/524—Joining profiled elements
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
    • B29C66/51—Joining tubular articles, profiled elements or bars; Joining single elements to tubular articles, hollow articles or bars; Joining several hollow-preforms to form hollow or tubular articles
    • B29C66/53—Joining single elements to tubular articles, hollow articles or bars
    • B29C66/532—Joining single elements to the wall of tubular articles, hollow articles or bars
    • B29C66/5326—Joining single elements to the wall of tubular articles, hollow articles or bars said single elements being substantially flat
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • 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
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B11/00—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding
    • F16B11/006—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding by gluing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/12—Joint cross-sections combining only two joint-segments; Tongue and groove joints; Tenon and mortise joints; Stepped joint cross-sections
    • B29C66/124—Tongue and groove joints
    • B29C66/1244—Tongue and groove joints characterised by the male part, i.e. the part comprising the tongue
    • B29C66/12441—Tongue and groove joints characterised by the male part, i.e. the part comprising the tongue being a single wall
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B29C66/7212—Fibre-reinforced materials characterised by the composition of the fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
    • B29L2031/3076—Aircrafts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/12—Construction or attachment of skin panels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • 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
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B11/00—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding

Definitions

  • the present invention relates to a joint and an aircraft structure.
  • CFRP Carbon-Fiber-Reinforced plastic
  • the member inserted into the joint is bonded by an adhesive, and the joint and the base material are also bonded by the adhesive. Thereby, a member is joined to a base material.
  • the plate material to be joined to the base material must be positioned with high accuracy. That is, when the joint is previously provided on the base material, the plate material needs to be positioned with high accuracy with respect to the joint.
  • Patent Document 1 a positioning pin (projection) is provided on the side surface of the plate material, a notch in which the pin is fitted is provided on the side surface of the joint, and the plate material is inserted so that the pin of the plate material fits in the notch of the joint.
  • a positioning pin projection
  • a notch in which the pin is fitted is provided on the side surface of the joint, and the plate material is inserted so that the pin of the plate material fits in the notch of the joint.
  • the bonding surface between the joint and the base material is a load (surface that pulls the member with respect to the surface of the base material to which the joint is joined).
  • a load surface that pulls the member with respect to the surface of the base material to which the joint is joined.
  • the bonding surface between the member and the base material is flat. However, if the bonding surface is flat, it may not have sufficient strength for the out-of-plane load.
  • the present invention has been made in view of such circumstances, and an object of the present invention is to provide a joint and an aircraft structure that can further increase the strength of the joint surface between the joint and the base material.
  • the joint and aircraft structure of the present invention employ the following means.
  • the joint according to the first aspect of the present invention is a joint for joining a member to a base material, and an inclined portion that is inclined with respect to a plane orthogonal to a direction in which a tensile load is applied to the member is the base material.
  • the inclined portion is embedded in the base material and bonded to the base material.
  • the joint according to this configuration is to join a member to a base material.
  • an inclined portion is formed on the bonding surface with the base material.
  • the inclined portion is inclined with respect to a plane orthogonal to a direction in which a tensile load on the member is applied. In other words, the inclined portion is inclined toward the base material.
  • the bonding surface of the base material with the joint is formed with a dug portion corresponding to the shape of the inclined portion so that the inclined portion of the joint is embedded. As a result, the inclined portion of the joint is embedded in the base material and bonded to the base material.
  • the adhesive strength there is an out-of-plane strength that is a strength in a direction of pulling the member (out-of-plane direction). That is, the out-of-plane strength is a strength against a tensile load (out-of-plane direction load) applied to the member.
  • the adhesive strength is classified into an in-plane strength that is a strength in a shearing direction (in-plane direction) with respect to the bonding surface.
  • the out-of-plane strength and the in-plane strength are orthogonal.
  • the theoretical adhesive strength against the out-of-plane direction load is the out-of-plane direction strength.
  • the in-plane strength has a strength component in the out-of-plane direction.
  • the theoretical adhesive strength with respect to the out-of-plane direction load is a strength obtained by adding the sine component of the in-plane adhesive strength to the out-of-plane adhesive strength.
  • the bonding strength is stronger than when the bonding surface is flat.
  • the peak stress at the end of the bonded surface when subjected to an out-of-plane load is reduced as compared to the case where the inclined portion is not formed. Therefore, this configuration can further increase the strength of the bonding surface between the joint and the base material.
  • the surface opposite to the adhesive surface is inclined toward the end so that the thickness is thinner than the central portion.
  • the difference in rigidity between the joint and the base material is small compared to when the opposite surface is not inclined with respect to the adhesive surface, that is, when the end of the joint is perpendicular to the base material, for example.
  • strength of the edge part of a joint falls because an opposite surface inclines with respect to an adhesion surface.
  • the inclined portion is formed on the bonding surface, the peak stress at the end of the joint when subjected to an out-of-plane load is reduced, so that damage to the end of the joint is suppressed.
  • the inclined portion is formed by a plurality of inclined surfaces.
  • the bonding strength of the bonding surface can be made uniform.
  • the inclined portion is formed of a plurality of inclined surfaces having different angles with respect to the base material.
  • the strength of the adhesive surface can be adjusted by varying the angle according to the load expected to be applied to the joint.
  • the inclined portion is formed by one inclined surface.
  • the strength of the bonding surface between the joint and the base material can be increased with a simple configuration.
  • An aircraft structure includes the above-described joint, and a base material in which a dug portion corresponding to the shape of the inclined portion is formed so that the inclined portion of the joint is embedded. And the joint is embedded in the base material and bonded by adhesion.
  • FIG. 1 is a perspective view showing a main wing of an aircraft with a part broken away. It is a side view which shows the shape of the coupling and base material which concern on embodiment of this invention. It is the side view which the joint and base material which concern on embodiment of this invention joined. It is an enlarged view of the area
  • FIG. 1 is a perspective view showing a partially broken main wing 1 of an aircraft.
  • the main wing 1 includes an upper skin 3, a lower skin 5, a front spar 7, a rear spar 9, and a plurality of ribs 11.
  • the upper skin 3 and the lower skin 5 are thin plates that constitute the outer shape of the main wing 1 and also serve as an aerodynamic surface. It is responsible for part of the load.
  • the front spar 7 and the rear spar 9 are structural members that extend in the blade length direction of the main wing 1 and are disposed between the upper skin 3 and the lower skin 5.
  • a plurality of stringers, which are auxiliary members extending in the blade length direction of the main wing 1, are disposed on the inner surface of the upper skin 3 or the lower skin 5 between the front spar 7 and the rear spar 9.
  • the rib 11 is a structural member that extends in the width direction of the main wing 1 and is disposed between the upper skin 3 and the lower skin 5 as shown in FIG.
  • the rib 11 is a structural member extending in a direction substantially orthogonal to the front spar 7 and the rear spar 9, and is a plate-like member formed in the cross-sectional shape of the main wing 1.
  • the joint 20 is, for example, a joint between the upper skin 3 and the front spar 7 or the rear spar 9, It is used for joining, joining of the rib 11 and the front spar 7 or the rear spar 9.
  • the joint 20 may be used for structures other than the main wing 1 of an aircraft.
  • FIG. 2 is a side view showing the shapes of the joint 20 and the base material 22 according to the present embodiment
  • FIG. 3 is a side view in which the joint 20 and the base material 22 are joined
  • FIG. FIG. 5 is a perspective view showing the shapes of the joint 20 and the base material 22.
  • the joint 20 according to the present embodiment is a so-called pi ( ⁇ ) -type joint provided on the base material 22 and having a groove 24 formed therein.
  • the joint 20 is used in an aircraft body structure as described above, and a member (a plate material 26 as an example in the present embodiment) constituting a part of the body structure is inserted into the groove portion 24.
  • the front spar 7 and the rear spar 9 are the base material 22, and the rib 11 is the plate material 26.
  • the plate material 26 is bonded to the joint 20 by filling the gap between the plate material 26 and the groove 24 with an adhesive.
  • the joint 20 is bonded to the base material 22 with an adhesive.
  • the bonding method between the base material 22 and the joint 20 and the bonding method between the joint 20 and the plate material 26 are not particularly limited. As described above, the plate material 26 is bonded to the base material 22 without using a fastener by bonding using the joint 20.
  • the material of the joint 20, the base material 22, and the plate material 26 is, for example, a composite material such as carbon-fiber-reinforced plastic (CFRP).
  • CFRP uses carbon fiber as a reinforcing material and synthetic resin as a matrix.
  • CFRP carbon-fiber-reinforced plastic
  • the present invention is not limited thereto, and a metal such as an aluminum alloy may be used as the material of the joint 20, the base material 22, and the plate material 26.
  • the inclined portion 28 is formed on the bonding surface 25 with the base material 22.
  • the inclined portion 28 is inclined with respect to a plane (horizontal direction, direction B in FIG. 3) orthogonal to a direction (vertical direction, direction A in FIG. 3) in which a tensile load is applied to the plate material 26.
  • the inclined portion 28 is inclined toward the base material 22.
  • the inclined portion 28 according to the present embodiment is inclined from the end portion 30 of the joint 20.
  • the inclined portion 28 is formed by two inclined surfaces 28A and 28B.
  • the inclined surfaces 28 ⁇ / b> A and 28 ⁇ / b> B intersect to form the corner portion 32.
  • the corner 32 extends in the longitudinal direction of the joint 20, that is, parallel to the end 30 of the joint 20. Further, a surface 34 (hereinafter referred to as “opposite surface”) opposite to the bonding surface 25 of the joint 20 is inclined in a tapered shape toward the end portion 30 so that the thickness is thinner than the central portion of the joint 20. ing.
  • the base material 22 is formed with a digging portion 38 corresponding to the shape of the inclined portion 28 so that the inclined portion 28 of the joint 20 is embedded in the bonding surface 36 with the joint 20.
  • the inclined portion 28 is embedded in the base material 22 and bonded to the base material 22.
  • the angle of the inclined surfaces 28A and 28B with respect to the B direction is defined as an inclination angle ⁇ .
  • the adhesive surface 25 of the joint 20 and the adhesive surface 36 of the base material 22 are collectively referred to as an adhesive layer.
  • adheresive strength the strength of the adhesive layer (hereinafter referred to as “adhesive strength”) will be described with reference to FIGS.
  • FIG. 6 is a schematic diagram showing the adhesive strength of the adhesive layer in the base material 22 where the digging portion 38 is not formed.
  • FIG. 7 is a schematic diagram showing the adhesive strength of the adhesive layer in the base material 22 in which the digging portion 38 is formed.
  • out-of-plane direction strength Ptall which is a strength in a direction in which the plate material 26 is pulled (A direction in FIGS. That is, the out-of-plane direction strength Ptall is a strength against a tensile load (hereinafter referred to as “out-of-plane direction load”) applied to the plate material 26.
  • the in-plane strength Psall which is the strength in the direction of shearing the adhesive layer (the B direction in FIGS. 6 and 7, hereinafter referred to as “in-plane direction”). It is divided into.
  • the in-plane direction strength Psall is a strength component in the out-of-plane direction.
  • the theoretical bond strength Pall with respect to the out-of-plane direction load is a strength obtained by adding the sine component (Psall ⁇ sin ⁇ ) of the in-plane bond strength Psall to the out-of-plane bond strength Ptall as shown in the equation (2).
  • Pall Ptall + Psall ⁇ sin ⁇ (2) That is, when the dug portion 38 is formed in the base material 22 and the adhesive layer is inclined, the adhesive strength is stronger than when the adhesive layer is flat.
  • FIG. 8 is an overall view of the numerical analysis model 50
  • FIG. 9 is an enlarged view of a region B in FIG.
  • the numerical analysis model 50 is formed by a base material model 52 in which the digging portion 38 is formed and a joint model 54 in which the inclined portion 28 is formed.
  • the joint model 54 is a model in which the joint 20 and the plate material 26 are combined.
  • both ends (ends A and B) of the base material model 52 were constrained, and a load (out-of-plane direction load) was applied to the joint model 54 in the Y direction which is an out-of-plane direction.
  • E about 60000 MPa as a composite material constituting the base material model 52 and the joint model 54
  • E about 40000 MPa for the gap filler model 56
  • E about 3000 MPa for the adhesive layer model 58.
  • E is a longitudinal elastic modulus (Young's modulus).
  • FIG. 10 is a graph showing the numerical analysis results.
  • a broken line in FIG. 10 indicates a numerical analysis result of the numerical analysis model 50 in which the dug portion 38 is not formed in the base material 22.
  • the solid line indicates the numerical analysis result of the numerical analysis model 50 in which the dug portion 38 is formed in the base material 22.
  • the horizontal axis in FIG. 10 is the X direction of the numerical analysis model 50, the coordinate A indicates the end of the adhesive layer model 58, and the coordinate CL indicates the center of the adhesive layer model 58 (see also FIG. 9).
  • the vertical axis indicates the magnitude of stress generated by receiving an out-of-plane load.
  • peak stress was generated at the end portion (coordinate A) of the adhesive layer model 58 by receiving an out-of-plane load.
  • the numerical analysis model 50 in which the dug portion 38 is not formed has a smaller peak stress at the end portion (coordinate A) of the adhesive layer model 58 than the numerical analysis model 50 in which the dug portion 38 is formed. This is because the difference in rigidity between the base material 22 and the joint 20 is smoothed by forming the digging portion 38.
  • the stress at the end of the adhesive layer model 58 is reduced by about 60% compared to the case where the digging portion 38 is not formed. Thereby, the adhesive strength due to the formation of the dug portion 38 is improved by about 2.5 times as a whole.
  • the opposite surface 34 is inclined toward the end portion 30.
  • the joint 20 according to this embodiment has a smaller rigidity difference between the joint 20 and the base material 22 than when the end 30 is perpendicular to the base material 22, for example.
  • strength of the edge part 30 falls because the edge part 30 inclines.
  • the inclined portion 28 is formed in the joint 20 and embedded in the base material 22, the peak stress at the end portion 30 when receiving an out-of-plane load is reduced as shown in FIG. Even if the opposite surface 34 is inclined toward the end portion 30, damage to the end portion 30 is suppressed.
  • the joint 20 according to the present embodiment is formed by the two inclined surfaces 28A and 28B, the adhesive strength of the adhesive surface 25 can be made equal on the left and right.
  • the joint 20 is for joining the plate material 26 to the base material 22 and is inclined with respect to a plane orthogonal to the direction in which the tensile load on the plate material 26 is applied.
  • a portion 28 is formed on the bonding surface 25 with the base material 22.
  • the base material 22 is formed with a dug portion 38 corresponding to the shape of the inclined portion 28 so that the inclined portion 28 of the joint 20 is embedded. Then, the joint 20 is embedded in the base material 22 and joined by adhesion.
  • the joint 20 according to this embodiment can further increase the strength of the bonding surface between the joint 20 and the base material 22.
  • FIG. 11 is a side view showing the shapes of the joint 20 and the base material 22 according to the first modification
  • FIG. 12 is an enlarged view of a region C shown in FIG. 11 and 12 that are the same as those in FIGS. 3 and 4 are given the same reference numerals as in FIGS.
  • the joint 20 according to the first modification is formed with flat portions 60A and 60B from the end 30 of the adhesive surface 25 toward the center of the joint 20, and the flat portions 60A and 60B.
  • Inclined surfaces 28A and 28B are formed in the center direction from the end portion of each.
  • FIG. 13 is a side view showing the shapes of the joint 20 and the base material 22 according to the second modification
  • FIG. 14 is an enlarged view of a region D shown in FIG. 13 and 14 that are the same as those in FIGS. 3 and 4 are assigned the same reference numerals as in FIGS.
  • the inclined portion 28 according to the third modification is formed of a plurality of inclined surfaces 28A, 28B, 28C, and 28D having different inclination angles. 13 and 14, the inclined surface 28A and the inclined surface 28B have the same inclination angle, and the inclined surface 28C and the inclined surface 28D have the same inclination angle.
  • the present invention is not limited to this, and the inclined portion 28 may be formed of four or more inclined surfaces.
  • the inclination angle can be varied according to the load expected to be applied to the joint 20, and the strength of the adhesive surface 25 can be adjusted.
  • FIG. 15 is a side view showing the shapes of the joint 20 and the base material 22 according to the third modification.
  • the inclined part 28 according to the third modification is formed by one inclined surface.
  • FIG. 16 is a side view showing the shapes of the joint 20A and the base material 22 according to the fourth modification.
  • the joint 20A according to the fourth modification is not a pie-shaped joint described above but a T-shaped joint.
  • FIG. 17 is a side view showing the shapes of the joint 20B and the base material 22 according to the fifth modification.
  • the joint 20B according to the fifth modification is not an above-described pie-shaped joint but an L-shaped joint.
  • the present invention is not limited to this, and the form in which the joint 20 is used for a structure other than an aircraft may be used.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Standing Axle, Rod, Or Tube Structures Coupled By Welding, Adhesion, Or Deposition (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)
  • Connection Of Plates (AREA)
  • Lining Or Joining Of Plastics Or The Like (AREA)
  • Laminated Bodies (AREA)

Abstract

継手（２０）は、板材（２６）を母材（２２）に接合させるためのものであって、板材（２６）に対する引っ張り荷重が加えられる方向と直交する面に対して傾斜する傾斜部（２８）が、母材（２２）との接着面（２５）に形成される。また、母材（２２）は、継手（２０）の傾斜部（２８）が埋め込まれるように、傾斜部（２８）の形状に応じた堀り込み部（３８）が形成される。そして、継手（２０）が母材（２２）に埋め込まれて接着により接合される。これにより、継手２０と母材２２との接着面の強度がより強くなる。

Description

継手及び航空機構造
　本発明は、継手及び航空機構造に関するものである。
　航空機の分野において、例えば炭素繊維強化プラスチック（Carbon-Fiber-Reinforced
Plastic：ＣＦＲＰ）等の複合材の適用範囲が一次構造へ拡大している。そして、複合材が軽量であるというメリットを生かして、構造の軽量化を達成するためにはファスナを用いない継手が好ましい。
　継手に差し込まれた部材は接着剤によって接着され、継手と母材も接着剤によって接着される。これにより、部材は、母材に接合される。
　そして、構造の組み立てにおいて、母材に接合される板材は高精度に位置決めされなければならない。すなわち、継手が予め母材に設けられている場合は、継手に対して板材が高精度に位置決めされる必要がある。
　特許文献１では、板材の側面に位置決め用のピン（突起物）を設け、継手の側面にこのピンが嵌め合わされる切欠きを設け、板材のピンが継手の切欠きに嵌るように板材を差し込むことで、位置決めを行うことが開示されている。
米国特許第８４０３５８６号明細書
　特許文献１に開示されている構造では、位置決めを行うことができるが、継手と母材との接着面は、継手が接合される母材の面に対して部材を引っ張る方向に働く荷重（面外方向荷重）に十分な強度を有していなければならない。
　部材と母材との接着面は、従来では平坦である。しかし、接着面が平坦であると、面外方向荷重に十分な強度を有しない場合がある。
　本発明は、このような事情に鑑みてなされたものであって、継手と母材との接着面の強度をより強くできる、継手及び航空機構造を提供することを目的とする。
　上記課題を解決するために、本発明の継手及び航空機構造は以下の手段を採用する。
　本発明の第一態様に係る継手は、部材を母材に接合させるための継手であって、前記部材に対する引っ張り荷重が加えられる方向と直交する面に対して傾斜する傾斜部が、前記母材との接着面に形成され、前記傾斜部が前記母材へ埋め込まれて前記母材と接着される。
　本構成に係る継手は、部材を母材に接合させるものである。また、本構成に係る継手は、母材との接着面に傾斜部が形成される。傾斜部は、部材に対する引っ張り荷重が加えられる方向と直交する面に対して傾斜する。換言すると、傾斜部は、母材へ向かって傾斜する。一方、母材における継手との接着面は、継手の傾斜部が埋め込まれるように、傾斜部の形状に応じた掘り込み部が形成される。これにより、継手は、傾斜部が母材へ埋め込まれて母材と接着される。
　ここで、接着強度として、部材を引っ張る方向（面外方向）の強度である面外方向強度がある。すなわち、面外方向強度は、部材に対する引っ張り荷重（面外方向荷重）に対する強度である。また、接着強度は、面外方向強度の他に、接着面に対してせん断する方向（面内方向）の強度である面内方向強度に分けられる。
　そして、接着面が平坦である場合、面外方向強度と面内方向強度は直交する。このため、面外方向荷重に対する理論接着強度は、面外方向強度となる。
　一方、本構成のように接着面に傾斜部が形成されている場合、面内方向強度は面外方向の強度成分を有する。このため、面外方向荷重に対する理論接着強度は、面外接着強度に面内接着強度の正弦成分が加算された強度となる。
　すなわち、接着面に傾斜部が形成されている場合の方が、接着面が平坦である場合に比べて、接着強度が強くなる。特に、面外方向荷重を受けたときの接着面の端部におけるピーク応力が、傾斜部が形成されない場合に比べて低減される。
　従って、本構成は、継手と母材との接着面の強度をより強くできる。
　上記第一態様では、前記接着面に対して反対の面が、中央部より厚みが薄くなるように端部に向かって傾斜している。
　本構成は、接着面に対して反対の面が傾斜していない場合、すなわち継手の端部が例えば母材に対して垂直になっている場合に比べ、継手と母材との剛性差が小さくなる。なお、接着面に対して反対の面が傾斜することで、継手の端部の強度が低下することが懸念される。しかし、接着面に傾斜部が形成されることで、面外方向荷重を受けたときの継手の端部におけるピーク応力が低減されるので、継手の端部の破損が抑制される。
　上記第一態様では、前記傾斜部が、複数の傾斜面で形成される。
　本構成によれば、接着面の接着強度を均等にできる。
　上記第一態様では、前記傾斜部が、前記母材に対する角度が異なる複数の傾斜面で形成される。
　本構成によれば、継手に加わると予想される荷重に応じて、角度を異ならせることで接着面の強度を調整できる。
　上記第一態様では、前記傾斜部が、一つの傾斜面によって形成される。
　本構成によれば、簡易な構成で、継手と母材との接着面の強度をより強くできる。
　本発明の第二態様に係る航空機構造は、上記記載の継手と、前記継手の前記傾斜部が埋め込まれるように、前記傾斜部の形状に応じた堀込み部が形成される母材と、を備え、前記継手が前記母材に埋め込まれて接着により接合される。
　本発明によれば、継手と母材との接着面の強度をより強くできる、という優れた効果を有する。
航空機の主翼を一部破断して示す斜視図である。 本発明の実施形態に係る継手及び母材の形状を示す側面図である。 本発明の実施形態に係る継手と母材とが接合した側面図である。 図３に示される領域Ａの拡大図である。 本発明の実施形態に係る継手及び母材の形状を示す斜視図である。 母材に掘り込み部が形成されていない接着層の接着強度を示す模式図である。 本発明の実施形態に係る接着層の接着強度を示す模式図である。 本発明の実施形態に係る接着層に生じる応力を算出するための数値解析モデルの構成図である。 図８に示される領域Ｂの拡大図である。 本発明の実施形態に係る数値解析結果を示すグラフである。 本発明の第１変形例に係る継手及び母材の形状を示す側面図である。 図１１に示される領域Ｃの拡大図である。 本発明の第２変形例に係る継手及び母材の形状を示す側面図である。 図１３に示される領域Ｄの拡大図である。 本発明の第３変形例に係る継手及び母材の形状を示す側面図である。 本発明の第４変形例に係る継手及び母材の形状を示す側面図である。 本発明の第５変形例に係る継手及び母材の形状を示す側面図である。
　以下に、本発明に係る継手及び航空機構造の一実施形態について、図面を参照して説明する。
　図１は、航空機の主翼１を一部破断して示す斜視図である。
　主翼１には、上側スキン３、下側スキン５、前側スパー７、後側スパー９、及び複数のリブ１１が備えられる。
　上側スキン３及び下側スキン５は、主翼１の外形を構成し、空力面も兼ねる薄板であり、前側スパー７、後側スパー９及びストリンガ（図示省略）とともに主翼１に働く引っ張り荷重や、圧縮荷重の一部を受け持つものである。
　前側スパー７及び後側スパー９は、図１に示されるように、主翼１の翼長方向に延びる構造部材であって、上側スキン３及び下側スキン５との間にわたって配置される部材である。
　前側スパー７と後側スパー９との間を、主翼１の翼長方向に延びる補助部材である複数のストリンガが上側スキン３又は下側スキン５の内側面に配置される。
　リブ１１は、図１に示すように、主翼１の翼幅方向に延びるとともに、上側スキン３及び下側スキン５の間にわたって配置される構造部材である。換言すると、リブ１１は、前側スパー７及び後側スパー９と略直交する方向に延びる構造部材であって、主翼１の断面形状に形成された板状の部材である。
　ここで、本実施形態に係る継手２０（図２等参照）は、例えば上側スキン３と前側スパー７や後側スパー９との接合、下側スキン５と前側スパー７や後側スパー９との接合、リブ１１と前側スパー７や後側スパー９との接合等に用いられる。なお、継手２０は、航空機の主翼１以外の構造に用いられてもよい。
　次に、本実施形態に係る継手２０の詳細について説明する。
　図２は、本実施形態に係る継手２０及び母材２２の形状を示す側面図であり、図３は、継手２０と母材２２とが接合した側面図であり、図４は、図３に示される領域Ａの拡大図であり、図５は、継手２０及び母材２２の形状を示す斜視図である。
　本実施形態に係る継手２０は、母材２２に設けられ、溝部２４が形成される所謂パイ（π）型継手である。
　継手２０は、例えば、上述のように航空機の機体構造に用いられ、機体構造の一部を構成する部材（本実施形態では一例として板材２６）が溝部２４に差し込まれる。例えば、前側スパー７や後側スパー９が母材２２であり、リブ１１が板材２６である。
　そして、板材２６と溝部２４との間隙に接着剤が充填されることにより、板材２６は継手２０に接着される。一方、継手２０は、母材２２に対して接着剤によって接着される。なお、母材２２と継手２０との接着方法及び継手２０と板材２６との接着方法は、特に限定されるものではない。
　このように、継手２０を用いた接着により、ファスナが用いられることなく、板材２６は母材２２に接合される。
　継手２０、母材２２、及び板材２６の材質は、例えば、炭素繊維強化プラスチック（Carbon-Fiber-Reinforced　Plastic：ＣＦＲＰ）等の複合材である。ＣＦＲＰは、補強材として炭素繊維が用いられ、マトリックスとして合成樹脂が用いられる。なお、これに限らず、継手２０、母材２２、及び板材２６の材質として、アルミ合金等の金属が用いられてもよい。
　そして、本実施形態に係る継手２０は、母材２２との接着面２５に傾斜部２８が形成される。傾斜部２８は、板材２６に対する引っ張り荷重が加えられる方向（垂直方向、図３のＡ方向）と直交する面（水平方向、図３のＢ方向）に対して傾斜する。換言すると、傾斜部２８は、母材２２へ向かって傾斜する。なお、本実施形態に係る傾斜部２８は、継手２０の端部３０から傾斜する。
　さらに、傾斜部２８は、二つの傾斜面２８Ａ，２８Ｂによって形成される。そして、傾斜面２８Ａ，２８Ｂが交わって角部３２を形成する。角部３２は、継手２０の長手方向、すなわち継手２０の端部３０と平行に延在する。
　また、継手２０の接着面２５に対して反対の面（以下「反対面」という。）３４は、継手２０の中央部より厚みが薄くなるように、端部３０に向かってテーパ状に傾斜している。
　一方、母材２２は、継手２０との接着面３６に継手２０の傾斜部２８が埋め込まれるように、傾斜部２８の形状に応じた掘り込み部３８が形成される。
　これにより、継手２０は、傾斜部２８が母材２２へ埋め込まれて母材２２と接着される。
　なお、以下の説明において、傾斜面２８Ａ，２８ＢのＢ方向に対する角度を傾斜角θと定義する。また、以下の説明において、継手２０の接着面２５及び母材２２の接着面３６を総称して接着層という。
　次に、図６から図１０を参照して、接着層の強度（以下「接着強度」という。）について説明する。
　図６は、掘り込み部３８が形成されていない母材２２における接着層の接着強度を示す模式図である。図７は、掘り込み部３８が形成されている母材２２における接着層の接着強度を示す模式図である。
　接着強度として、板材２６を引っ張る方向（図６，７のＡ方向、以下「面外方向」という。）の強度である面外方向強度Ｐtallがある。すなわち、面外方向強度Ｐtallは、板材２６に対する引っ張り荷重（以下「面外方向荷重」という。）に対する強度である。
　また、接着強度は、面外方向強度Ｐtallの他に、接着層に対してせん断する方向（図６，７のＢ方向、以下「面内方向」という。）の強度である面内方向強度Ｐsallに分けられる。
　図６に示されるように接着層が平坦であると（傾斜角θ＝０°）、面外方向強度Ｐtallと面内方向強度Ｐsallは直交する。このため、母材２２に掘り込み部３８が形成されない場合における、面外方向荷重に対する理論接着強度Ｐallは、（１）式に示されるように、面外方向強度Ｐtallとなる。
　Ｐall＝Ｐtall　・・・（１）
　一方、図７に示されるように母材２２に掘り込み部３８が形成され、接着層が傾斜していると（傾斜角θ≠０°）、面内方向強度Ｐsallは面外方向の強度成分を有する。このため、面外方向荷重に対する理論接着強度Ｐallは、（２）式に示されるように、面外接着強度Ｐtallに面内接着強度Ｐsallの正弦成分（Ｐsall×sinθ）が加算された強度となる。
　Ｐall＝Ｐtall＋Ｐsall×sinθ　・・・（２）
　すなわち、母材２２に掘り込み部３８が形成され、接着層が傾斜している場合の方が、接着層が平坦である場合に比べて、接着強度が強くなる。
　次に、母材２２に掘り込み部３８が形成され、接着層が傾斜している場合における、接着層に生じる応力の数値解析結果について説明する。数値解析は、有限要素法を用いて行われた。
　図８は数値解析モデル５０の全体図であり、図９は図８の領域Ｂの拡大図である。
　図８，９に示されるように、数値解析モデル５０は、掘り込み部３８が形成された母材モデル５２と傾斜部２８が形成された継手モデル５４とで形成される。なお、継手モデル５４は、継手２０と板材２６とを組み合わせたモデルである。
　数値解析の条件として、母材モデル５２の両端（端部Ａ，Ｂ）を拘束し、継手モデル５４に対して面外方向であるＹ方向に荷重（面外方向荷重）を付与した。
　材料特性としては、母材モデル５２と継手モデル５４を構成する複合材としてＥ＝約６００００ＭＰａ、ギャップフィラーモデル５６をＥ＝約４００００ＭＰａ、接着層モデル５８をＥ＝約３０００ＭＰａとしている。なお、Ｅは、縦弾性係数（ヤング率）である。
　また、掘り込み部３８が形成されない母材モデル５２と傾斜部２８が形成されない継手モデル５４とで形成した数値解析モデル５０でも、同様の条件で数値解析を行った。
　図１０は、数値解析結果を示すグラフである。
　図１０における破線は、母材２２に掘り込み部３８が形成されない数値解析モデル５０の数値解析結果を示す。一方、実線は母材２２に掘り込み部３８が形成された数値解析モデル５０の数値解析結果を示す。また、図１０における横軸は数値解析モデル５０のＸ方向であり、座標Ａは接着層モデル５８の端部を示し、座標ＣＬは接着層モデル５８の中央部を示す（図９も参照）。一方、縦軸は面外方向荷重を受けることにより生じる応力の大きさを示す。
　図１０に示されるように、面外方向荷重を受けることにより、接着層モデル５８の端部（座標Ａ）にピーク応力が生じた。掘り込み部３８が形成されない数値解析モデル５０の方が、掘り込み部３８が形成された数値解析モデル５０に比べて、接着層モデル５８の端部（座標Ａ）におけるピーク応力が小さい。この理由は、掘り込み部３８が形成されることにより、母材２２と継手２０の剛性差が滑らかになるためである。
　母材２２に掘り込み部３８が形成されることにより、掘り込み部３８が形成されない場合に比べて、接着層モデル５８の端部の応力は、約６割低減される。これにより、掘り込み部３８が形成されることによる接着強度は、全体として約２．５倍向上する。
　また、本実施形態に係る継手２０は、反対面３４が端部３０に向かって傾斜している。これにより、本実施形態に係る継手２０は、端部３０が例えば母材２２に対して垂直になっている場合に比べ、継手２０と母材２２との剛性差が小さくなる。
　なお、端部３０が傾斜することで端部３０の強度が低下することが懸念される。しかし、継手２０に傾斜部２８が形成され、母材２２に埋め込まれることで、図１０に示されるように、面外方向荷重を受けたときの端部３０におけるピーク応力が低減されるので、反対面３４を端部３０に向かって傾斜させても、端部３０の破損が抑制される。
　また、本実施形態に係る継手２０は、二面の傾斜面２８Ａ，２８Ｂによって形成されるので、接着面２５の接着強度を左右で均等にできる。
　以上説明したように、本実施形態に係る継手２０は、板材２６を母材２２に接合させるためのものであって、板材２６に対する引っ張り荷重が加えられる方向と直交する面に対して傾斜する傾斜部２８が、母材２２との接着面２５に形成される。また、母材２２は、継手２０の傾斜部２８が埋め込まれるように、傾斜部２８の形状に応じた堀り込み部３８が形成される。そして、継手２０が母材２２に埋め込まれて接着により接合される。
　従って、本実施形態に係る継手２０は、継手２０と母材２２との接着面の強度をより強くできる。
〔第１変形例〕
　以下、本発明の第１変形例について説明する。
　図１１は、本第１変形例に係る継手２０及び母材２２の形状を示す側面図であり、図１２は、図１１に示される領域Ｃの拡大図である。なお、図１１，１２における図３，４と同一の構成部分については図３，４と同一の符号を付して、その説明を省略する。
　本第１変形例に係る継手２０は、図１１，１２に示されるように接着面２５の端部３０から継手２０の中心方向へ向って平坦部６０Ａ，６０Ｂが形成され、平坦部６０Ａ，６０Ｂの端部から中心方向へ傾斜面２８Ａ，２８Ｂが形成される。
〔第２変形例〕
　以下、本発明の第２変形例について説明する。
　図１３は、本第２変形例に係る継手２０及び母材２２の形状を示す側面図であり、図１４は、図１３に示される領域Ｄの拡大図である。なお、図１３，１４における図３，４と同一の構成部分については図３，４と同一の符号を付して、その説明を省略する。
　本第３変形例に係る傾斜部２８は、傾斜角が異なる複数の傾斜面２８Ａ，２８Ｂ，２８Ｃ，２８Ｄで形成される。なお、図１３，１４の例では、傾斜面２８Ａと傾斜面２８Ｂは同じ傾斜角であり、傾斜面２８Ｃと傾斜面２８Ｄは同じ傾斜角である。なお、これに限らず、傾斜部２８は、４つ以上の傾斜面で形成されてもよい。
　これにより、継手２０に加わると予想される荷重に応じて傾斜角を異ならせることができ、接着面２５の強度が調整可能とされる。
〔第３変形例〕
　以下、本発明の第３変形例について説明する。
　図１５は、本第３変形例に係る継手２０及び母材２２の形状を示す側面図である。
　第３変形例に係る傾斜部２８は、一つの傾斜面によって形成される。
　これにより、第３変形例に係る継手２０は、簡易な構成で、継手２０と母材２２との接着面２５の強度をより強くできる。
〔第４変形例〕
　以下、本発明の第４変形例について説明する。
　図１６は、本第４変形例に係る継手２０Ａ及び母材２２の形状を示す側面図である。
　本第４変形例に係る継手２０Ａは、上述したパイ型の継手ではなく、Ｔ字型の継手とされる。
〔第５変形例〕
　以下、本発明の第５変形例について説明する。
　図１７は、本第５変形例に係る継手２０Ｂ及び母材２２の形状を示す側面図である。
　本第５変形例に係る継手２０Ｂは、上述したパイ型の継手ではなく、Ｌ字型の継手とされる。
　以上、本発明を、上記実施形態を用いて説明したが、本発明の技術的範囲は上記実施形態に記載の範囲には限定されない。発明の要旨を逸脱しない範囲で上記実施形態に多様な変更又は改良を加えることができ、該変更又は改良を加えた形態も本発明の技術的範囲に含まれる。
　例えば、上記実施形態では、継手２０を航空機構造に用いる形態について説明したが、本発明は、これに限定されるものではなく、継手２０を航空機以外の構造に用いる形態としてもよい。
　１　　　主翼
　２０　　継手
　２２　　母材
　２５　　接着面
　２６　　板材
　２８　　傾斜部
　３８　　掘り込み部

Claims (6)

  1. 　部材を母材に接合させるための継手であって、
    　前記部材に対する引っ張り荷重が加えられる方向と直交する面に対して傾斜する傾斜部が、前記母材との接着面に形成され、
    前記傾斜部が前記母材へ埋め込まれて前記母材と接着される継手。
  2. 　前記接着面に対して反対の面は、中央部より厚みが薄くなるように端部に向かって傾斜している請求項１記載の継手。
  3. 　前記傾斜部は、複数の傾斜面で形成される請求項１又は請求項２記載の継手。
  4. 　前記傾斜部は、前記母材に対する角度が異なる複数の傾斜面で形成される請求項３記載の継手。
  5. 　前記傾斜部は、一つの傾斜面によって形成される請求項１又は請求項２記載の継手。
  6. 　請求項１から請求項５の何れか１項記載の継手と、
    　前記継手の前記傾斜部が埋め込まれるように、前記傾斜部の形状に応じた堀込み部が形成される母材と、
    を備え、
    　前記継手が前記母材に埋め込まれて接着により接合される航空機構造。
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CA2923152A1 (en) 2015-04-09
CA2923152C (en) 2019-01-08
EP3029339A4 (en) 2016-09-14
CN105518315A (zh) 2016-04-20
CN105518315B (zh) 2018-07-06
EP3029339A1 (en) 2016-06-08
US20160194071A1 (en) 2016-07-07
BR112016004953A2 (pt) 2020-05-19
JP6169465B2 (ja) 2017-07-26
US10040538B2 (en) 2018-08-07
RU2632552C1 (ru) 2017-10-05
JP2015072041A (ja) 2015-04-16

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