PENGUJIAN DAN ANALISIS PADA KOMPOSIT KARBON/EPOXY UD DAN FABRIC YANG DIBUAT DALAM BEBERAPA KONFIGURASI LAPISAN AKIBAT IMPACT KECEPATAN RENDAH

• Main Author: Romadon, Haroen
• Format: Theses
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/33437
• Institution: Institut Teknologi Bandung

Laminate as structure or component on the aircraft is very risky for the impact caused by the mechanism of mechanical loading during maintenance and flight. The important things in the use of Carbon Fiber Reinforced Composite on aircraft structures is the occurrence of Low Velocity Impact (LVI) loads which often cause invisible damage (Barely Visible Impact Damage – BVID), but significant damage occurs in the inside of the structure, that is delamination between layers. The damage caused by the impact on the inside of the structure can be detected by Non Destructive Inspection, Through Transmission Ultrasonic – TTU. Delamination damage can cause decreased of compression strength on the composite plate. CAI (Compression After Impact) test can provide the magnitude of the composite plate strength decrease before and after being affected by LVI. For more efficiently design composite aircraft structures, there are recommendations for design inputs; the composite plates with the composition of UD fibers and fabric of two different configurations..