The Experts below are selected from a list of 45 Experts worldwide ranked by ideXlab platform

Chun H. Wang - One of the best experts on this subject based on the ideXlab platform.

  • Improved design methods for scarf repairs to highly strained Composite Aircraft Structure
    Composite Structures, 2006
    Co-Authors: Alex Harman, Chun H. Wang
    Abstract:

    This paper presents an analytical method to optimise the profile of the scarf joint between dissimilar modulus adherends so that adhesive stresses are approximately uniform along the joint. The optimised scarf repair is expected to enhance joint strength and reduce the amount of material removal. Finite element analyses have been performed to both validate the optimal solution and to evaluate the use of low stiffness patch to repair carbon epoxy Composites. In particular, the influence of patch lay-up on adhesive stresses has been investigated.

B Whittingham - One of the best experts on this subject based on the ideXlab platform.

  • micrographic studies on adhesively bonded scarf repairs to thick Composite Aircraft Structure
    Composites Part A-applied Science and Manufacturing, 2009
    Co-Authors: B Whittingham, A A Baker, A Harman, D Bitton
    Abstract:

    Abstract The hard-patch approach to scarf repairs involves adhesively bonding a pre-formed patch into the scarf cavity. This approach has several potential advantages compared with the conventional soft-patch approach, which involves forming the patch from pre-preg and co-bonding it with the adhesive during cure of the patch directly in the repair cavity. Two methods for producing the hard-patch were investigated. The first was the moulded approach where the patch was laid up in a mould and cured prior to bonding in the repair cavity. The development and implementation of the moulded hard-patch repair technique on an F/A-18 horizontal stabiliser is described. The second approach involves machining the patch from a Composite panel using digitised data obtained from the use of surface profiling equipment to capture the scarf cavity surface. Micrographic techniques were used to assess critical features of the bond-line produced from the different techniques. The results are compared with microscopic studies from a second F/A-18 horizontal stabiliser that was repaired much earlier using the soft-patch approach. Each repair is assessed in terms of the consolidation of plies along the bond-line and the conformity of the patch to the repair cavity as well as adhesive uniformity and porosity.

D Bitton - One of the best experts on this subject based on the ideXlab platform.

  • micrographic studies on adhesively bonded scarf repairs to thick Composite Aircraft Structure
    Composites Part A-applied Science and Manufacturing, 2009
    Co-Authors: B Whittingham, A A Baker, A Harman, D Bitton
    Abstract:

    Abstract The hard-patch approach to scarf repairs involves adhesively bonding a pre-formed patch into the scarf cavity. This approach has several potential advantages compared with the conventional soft-patch approach, which involves forming the patch from pre-preg and co-bonding it with the adhesive during cure of the patch directly in the repair cavity. Two methods for producing the hard-patch were investigated. The first was the moulded approach where the patch was laid up in a mould and cured prior to bonding in the repair cavity. The development and implementation of the moulded hard-patch repair technique on an F/A-18 horizontal stabiliser is described. The second approach involves machining the patch from a Composite panel using digitised data obtained from the use of surface profiling equipment to capture the scarf cavity surface. Micrographic techniques were used to assess critical features of the bond-line produced from the different techniques. The results are compared with microscopic studies from a second F/A-18 horizontal stabiliser that was repaired much earlier using the soft-patch approach. Each repair is assessed in terms of the consolidation of plies along the bond-line and the conformity of the patch to the repair cavity as well as adhesive uniformity and porosity.

A A Baker - One of the best experts on this subject based on the ideXlab platform.

  • micrographic studies on adhesively bonded scarf repairs to thick Composite Aircraft Structure
    Composites Part A-applied Science and Manufacturing, 2009
    Co-Authors: B Whittingham, A A Baker, A Harman, D Bitton
    Abstract:

    Abstract The hard-patch approach to scarf repairs involves adhesively bonding a pre-formed patch into the scarf cavity. This approach has several potential advantages compared with the conventional soft-patch approach, which involves forming the patch from pre-preg and co-bonding it with the adhesive during cure of the patch directly in the repair cavity. Two methods for producing the hard-patch were investigated. The first was the moulded approach where the patch was laid up in a mould and cured prior to bonding in the repair cavity. The development and implementation of the moulded hard-patch repair technique on an F/A-18 horizontal stabiliser is described. The second approach involves machining the patch from a Composite panel using digitised data obtained from the use of surface profiling equipment to capture the scarf cavity surface. Micrographic techniques were used to assess critical features of the bond-line produced from the different techniques. The results are compared with microscopic studies from a second F/A-18 horizontal stabiliser that was repaired much earlier using the soft-patch approach. Each repair is assessed in terms of the consolidation of plies along the bond-line and the conformity of the patch to the repair cavity as well as adhesive uniformity and porosity.

Alex Harman - One of the best experts on this subject based on the ideXlab platform.

  • Improved design methods for scarf repairs to highly strained Composite Aircraft Structure
    Composite Structures, 2006
    Co-Authors: Alex Harman, Chun H. Wang
    Abstract:

    This paper presents an analytical method to optimise the profile of the scarf joint between dissimilar modulus adherends so that adhesive stresses are approximately uniform along the joint. The optimised scarf repair is expected to enhance joint strength and reduce the amount of material removal. Finite element analyses have been performed to both validate the optimal solution and to evaluate the use of low stiffness patch to repair carbon epoxy Composites. In particular, the influence of patch lay-up on adhesive stresses has been investigated.