Protective Facility ISSN:3058-7816(Print) 3058-8618(Online) 방호시설

This study evaluates the structural stability of windows in a Light Armed Helicopter (LAH) under representative operational conditions. The analysis focused on the windshield, cockpit windows, and cabin windows using structural and thermal simulations. Key environmental factors considered include bird strike, foreign object damage (FOD), aerodynamic pressure, vibration loads, and thermal effects. The bird strike simulation indicated that the composite windshield (glass–TPU–PET) prevented penetration and limited fragment dispersion, ensuring pilot visibility. FOD analysis showed that impacts from small steel particles produced negligible displacement, posing no risk of failure. Under aerodynamic pressure loading, with internal-external differential pressures of +3,850 Pa and –4,900 Pa, all windows exhibited stable elastic behavior without plastic deformation. Vibration analysis confirmed that the natural frequencies of the windows (23.8–210.1 Hz) were well above the main rotor excitation frequency (4.5 Hz), avoiding resonance.Overall, the results demonstrate that LAH windows can withstand combined environmental loads while maintaining structural integrity. These findings provide a technical basis for design validation and future optimization of helicopter window structures.