Customer Challenge

A major aircraft OEM required a design change for the fixed leading edge wing components to accommodate a new, heavier, and larger engine. The goal was to reduce fuel burn per seat by 14% through weight optimization and aerodynamic improvements, necessitating a redesign of the wing structural components.

Scope

  • Perform static stress analysis on Fixed Leading Edge components
  • Recommend design changes to accommodate the new engine

Solution

  • Conducted static strength analysis and factoring analysis
  • Identified low Reserve Factor (RF) zones and developed methods to mitigate them
  • Proposed necessary design changes
Solution

Benefits

  • Achieved faster design improvements
  • Enhanced aircraft performance

Results

  • Delivered improved design on time
  • Identified seven critical zones for design changes
  • Achieved a weight reduction of 189KG per wing set with First Time Right (FTR) deliverables

Features

  • Integrated design and stress analysis
  • Supported Preliminary Design Review (PDR) and Critical Design Review (CDR) approvals
  • Released certification dossiers for Sub-Spar and D-Nose components and FLE Ribs

This comprehensive redesign of the fixed leading edge wing components significantly improved aircraft performance, demonstrating our capability to meet critical engineering challenges efficiently and effectively.

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