Services
-> Detailed Design and Guidance (Closely supporting the design process to ensure optimal structural solution is converged upon within minimal design iterations)
-> Material Selection
-> Design of Metallic Structures
-> Composite Structure Design (Honeycomb structures and CFRP laminates , optimised for loading envelopes)
-> Building of Finite Element Models (from component level to global Spacecraft / Aircraft level)
-> Quasi-Static analysis (Limit, Ultimate)
-> Vibroacoustic analysis (Random Vibration, Acoustic cases, Harmonic Sine)
-> Analysis of structural response to Thermal load cases (structural failure modes as well as sensor pointing under thermal expansion/warping)
-> Assessment of Transport, Lift, Handling and Part Build cases.
-> Shock analysis
-> Non-linear analysis, geometric, material, contact, progressive failure.
-> Transient response analysis (Linear and Non-linear).
-> Structural Optimization (by Finite Element Analysis)
-> Fluid Structure Interaction.
-> Sizing and Failure modes analysis for metallic structures, composite structures (CFRP and Honeycomb) and joints (preloaded bolted joints, bonded joints, rivets etc.)
-> Buckling (Linear and Non-Linear)
-> Equipment environmental response calculation.
-> Fatigue analysis for service spectra (for example fuselage pressurisation cycles) in addition to dynamic loading scenarios including harmonic sine, random vibration and acoustic.
-> Damage Tolerance Analysis, crack propagation modelling and residual strength calculations.
-> Structural Qualification Test support (from Unit level to spacecraft/aircraft level)
-> Correlation of Finite Element Models against measured test data.
-> Generation of condensed models (Craig Bampton) to support CLA (Coupled Loads Analysis) in accordance with launch agency requirements.
>>> Some analysis examples are shown below <<<
Example 1: Solar Array Deployment (Non-Linear Transient Analysis)
(Plots show solar array deployment and hinge lock-out , Isometric and Side Views)
Example 2: Modal Correlation of Spacecraft FEM against SQM Test Article
(Plot shows FEM displacements vs Test article Operational deformed shape , for 1g-Y lateral base excitation)
Example 3: Fluid-structure interaction, fuel sloshing within spherical tank.
Fuel sloshing modes within spherical tank (rubber diaphragm modelled)
Example 4: Progressive Failure of composite honeycomb sandwich panel
The example shows a honeycomb panel with a defective insert which is not potted into honeycomb core. The non-linear analysis shows peeling of top skin from honeycomb core when pull-out load is applied to the insert.
Example 5: Structural Opimization of Load Bearing Component
The plot shows a load bearing component that was mass optimized while still achieving the required stiffness.