Stress analysis and fatigue analysis design solutions  

Aerospace structural design engineers are key on gas turbine aero engines programmes, for example, the Rolls Royce Trent programme.

Design, structural analysis and validation are important to BR700 series aero engines, helicopter Gearboxes, Tail Rotor Drive Systems, Westland Helicopters transmissions.

Structural design engineers employed in aerospace design offices, aim to progress to technical management or technical specialist. Typical destinations include BAE Systems, Airbus (UK and Europe), Dassault, Rolls-Royce plc, and Messier Dowty.

Modern aircraft have to have more lightweight and more durable structures. Aerospace vehicle structural design, includes stress analysis, finite element analysis, fatigue analysis, fracture mechanics, damage tolerance, aeroelasticity, crashworthiness and structural stability.

Finite element analysis typically includes

•Linear static analysis

•Non-linear analysis

•Geometric non-linearity (e.g. gaps and contacts)

•Non-linear material response

•Dynamic Analysis

•Normal modes

•Frequency response (application for Acoustic Fatigue  Analysis)

•Random vibration

We have extensive experience of analysing both metallic and composite structures/materials. Our modelling capabilities range from simple 2-D analyses to complete aircraft structures.

Formulating and applying appropriate mathematical and numerical models to predict the state of stress and deformation of one, two and three-dimensional aerospace structures, explaining the limitations of the models, assess their applicability to realistic configurations and estimate the errors resulting from their application, are all part of the routines.

Computational analysis of a structural design, applies energy and variational principles for the determination of deflections and internal loads in one-dimensional structural elements, applies Ritz Method for the approximate calculation of deflections and stresses in one-dimensional structural elements, explains the principles and implementation of the finite element method in linear static problems, applies the finite element method in the stress analysis of aerospace structural components, and designs a structural component of an aerospace structure with the aid of state of the art finite element techniques. Structural design criteria will account for stiffness, strength, toughness and useful life considerations.

Aircraft Structural Design

of modifications and aircraft reconfiguration

In practice, for aircraft modification, the design phase is not only critical, but it eliminates unproductive and redundant engineering costs that occur unexpectedly during the certification phase.

The analysis of a wide variety of aircraft repairs and modifications by combining traditional analytical techniques with the most advanced computer software technology available, will achieve tasks such as:

•Interior monument stress analysis

•Damage tolerance analysis for aircraft skin penetrations (antenna), bulkhead feed through and other significant fuselage cutout or expansions (e.g. cargo doors, jump doors, etc)

•Analysis of high stress zones such as engine mounts, engine nacelle environment

•Analysis of avionic rack installations, crew/passenger seats (both static and dynamic)