A review of composite product data interoperability and product life-cycle management challenges in the composites industry

A review of composite product data interoperability and product life-cycle management challenges is presented, which addresses “Product Life-cycle Management”, developments in materials. The urgent need for this is illustrated by the life-cycle management issues faced in modern military aircraft, where in-service failure of composite parts is a problem, not just in terms of engineering understanding, but also in terms of the process for managing and maintaining the fleet. A demonstration of the use of ISO 10303-235 for a range of through-life composite product data is reported. The standardization of the digital representation of data can help businesses to automate data processing. With the development of new materials, the requirements for data information models for materials properties are evolving, and standardization drives transparency, improves the efficiency of data analysis, and enhances data accuracy. Current developments in Information Technology, such as big data analytics methodologies, have the potential to be highly transformative

Failure of Blind Riveted Joint of Carbon Laminates

Thispaperdealswiththeexperimentalandnumericalinvestigationsofmechanicalbehavior of the single-lap joint of laminates consisting of TENAX-J IMS60 E13 24K carbon fibers and MSG L285 epoxy resin. TIBULB high-strength blind rivets having a diameter of 4.8 mm and 6.4 mm were used for the joint. Tension tests were performed to investigate the material parameters of the laminate and the clearance effect. The rivet clamping force was evaluated based on a torsion test. The finite element method model of the joint using non-linear shear stress-strain relations of a lamina and using Puck’s failure criterion for the 3D stress state was created. The model was used to analyze the failure of the joint under quasi-static loading. The maximum number of loading cycles leading to joint failure and the decrease in the joint load capacity and stiffness due to the cyclic loading were investigated

Integral Design and Optimisation Process for a Highly Flexible Generic Long Range Jet Transport with Flight Mechanic Derivative Constraints

Due to the increased application of carbon fibre reinforced plastics (CFRP) in the aircraft industry within the past decades, design of primary load carrying structures has vastly evolved. Ultimately, this led to weight saving and a wider design space as the result of reduced material density and the anisotropic nature of the composite. However, the aforementioned design space is currently limited by uncertainties such as material imperfections, open hole tensions or plate boarder stresses. These uncertainties are commonly overcome by applying large safety margins, limiting the benefit of replacing aluminium with carbon fibre. To investigate this matter, a highly flexible long range jet transport, resembling an Airbus A350- 900 or a Boeing 787-10 class aircraft, is taken as a reference. Its simulation model components are set up using an in-house model generator. In doing so, the main load carrying structure of the wing is optimised by the means of an comprehensive loads and optimisation tool chain built around MSC.Nastran. By applying an aeroelastic tailoring approach the flight mechanic stability of the aircraft is guaranteed, while the calculation of the sensitivities in the gradient based optimisation incorporates the change in the dimensioning loads. To obtain a highly flexible structure, a carbon fibre laminate optimisation is set up, using lamination parameters in combination with large strain allowables (up to 8000 µ in tension). The result is a highly flexible wing structure, featuring a vertical displacement of up to 10 % with respect to the semi-wingspan during cruise flight. Besides the impact of varying boundary conditions and optimisation strategies on the flexibility and the primary structural mass of the wing, the development of significant constraints and modal properties is investigated