The Experts below are selected from a list of 9 Experts worldwide ranked by ideXlab platform
John Wang - One of the best experts on this subject based on the ideXlab platform.
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on the certification of bonded repairs to Primary Composite aircraft components
Journal of Adhesion, 2015Co-Authors: A A Baker, Andrew J Gunnion, John WangAbstract:Airworthiness certification is required when bonded repairs are made to Primary Composite Structure in situations where damage has reduced or has the potential to reduce residual strength to below the design ultimate strength. Generally, certification of bonded Primary Structure poses many difficulties. As most repairs are one-off events meeting these certification requirements is especially challenging since demonstration by testing will generally not be possible or cost-effective. This paper discusses options for addressing the two key issues relating to certification: (a) how to validate initial and enduring bond strength of adhesive bonds, mainly given the inability of conventional non-destructive inspection to provide this assurance and (b) how to develop acceptable generic design allowables for bonded repairs which represent actual failure modes – especially for cyclic loading, since validation by testing of simulated repairs will generally be infeasible. It is concluded that proof testing of bonded...
Byji Varughese - One of the best experts on this subject based on the ideXlab platform.
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integrity evaluation of feature level test specimen of an aircraft Primary Composite Structure
2018Co-Authors: S Venkatesh, S C Lakshminarayana, Byji VarugheseAbstract:It is well known to the aircraft designers that the design of Structure using only metals or only Composite materials can be realized with higher confidence level based on the database or tools available present in their aircraft design bureau. However, data availability for design of Primary structural element/joint using metal, Composites, and mechanical fasteners is minimal, and many of them are proprietary; moreover, they are depending on type of design. There is a need to design and test a feature level test specimen with appropriate boundary and loading conditions, which simulates behavior of full-scale component. Primary structural joint for actuator mounting on the Composite fin has been considered for feature level testing. The purpose of the tests was to demonstrate the validity of the structural joint by applying static limit and ultimate loads. The feature level test specimen consists of Composite and metal joints was successfully loaded to the ultimate design load without evidence of failure. The global behavior predicted by the finite element (FE) model of the test arrangement was in close agreement with the experimental results as evidenced by the strain and displacement results. The success of the testing program demonstrated the importance of feature level test in the design stage of Primary Composite structural joints of a civil transport aircraft.
A A Baker - One of the best experts on this subject based on the ideXlab platform.
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on the certification of bonded repairs to Primary Composite aircraft components
Journal of Adhesion, 2015Co-Authors: A A Baker, Andrew J Gunnion, John WangAbstract:Airworthiness certification is required when bonded repairs are made to Primary Composite Structure in situations where damage has reduced or has the potential to reduce residual strength to below the design ultimate strength. Generally, certification of bonded Primary Structure poses many difficulties. As most repairs are one-off events meeting these certification requirements is especially challenging since demonstration by testing will generally not be possible or cost-effective. This paper discusses options for addressing the two key issues relating to certification: (a) how to validate initial and enduring bond strength of adhesive bonds, mainly given the inability of conventional non-destructive inspection to provide this assurance and (b) how to develop acceptable generic design allowables for bonded repairs which represent actual failure modes – especially for cyclic loading, since validation by testing of simulated repairs will generally be infeasible. It is concluded that proof testing of bonded...
Saul Ledesma - One of the best experts on this subject based on the ideXlab platform.
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thermal numerical analysis of the Primary Composite Structure of a cubesat
Aerospace, 2019Co-Authors: Saul Piedra, Mauricio Torres, Saul LedesmaAbstract:A thermal computational analysis for the Composite Structure of a CubeSat is presented. The main purpose of this investigation is to study the thermal performance of carbon fibre/epoxy resin Composite materials with Zinc Oxide nanoparticles in order to be used in the panels of the Primary Structure of a CubeSat. The radiative heat fluxes over each Composite panel are computed according to the orbit trajectory and they are utilized as boundary conditions for the analysis. The direct solar, albedo and Earth infrared radiation fluxes are considered in this study. The model implementation, including the computation of the orthotropic thermal conductivity of the Composite material is presented. The thermal simulations were performed for three different orbit inclination angles: the selected mission ( β = 57 ∘ ), the worst hot ( β = 90 ∘ ) and the worst cold ( β = 0 ∘ ). The temperature ranges in the electronic boards are analyzed in order to show that are into the operating limits of each electronic component.
S Venkatesh - One of the best experts on this subject based on the ideXlab platform.
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integrity evaluation of feature level test specimen of an aircraft Primary Composite Structure
2018Co-Authors: S Venkatesh, S C Lakshminarayana, Byji VarugheseAbstract:It is well known to the aircraft designers that the design of Structure using only metals or only Composite materials can be realized with higher confidence level based on the database or tools available present in their aircraft design bureau. However, data availability for design of Primary structural element/joint using metal, Composites, and mechanical fasteners is minimal, and many of them are proprietary; moreover, they are depending on type of design. There is a need to design and test a feature level test specimen with appropriate boundary and loading conditions, which simulates behavior of full-scale component. Primary structural joint for actuator mounting on the Composite fin has been considered for feature level testing. The purpose of the tests was to demonstrate the validity of the structural joint by applying static limit and ultimate loads. The feature level test specimen consists of Composite and metal joints was successfully loaded to the ultimate design load without evidence of failure. The global behavior predicted by the finite element (FE) model of the test arrangement was in close agreement with the experimental results as evidenced by the strain and displacement results. The success of the testing program demonstrated the importance of feature level test in the design stage of Primary Composite structural joints of a civil transport aircraft.