ANALISIS DELAMINASI PADA ENTRY DAN EXIT SURFACE DENGAN
MATERIAL KOMPOSIT KARBON EPOXY
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
Listyo Rachmanto, Ashyadil
Subject
T Technology (General)
Datestamp
2024-02-15 08:15:08
Abstract :
Drilling was carried out to make holes in the components of the F1A glider aircraft which aimed to unite the fuselage and wing structural parts to create a strong and reliable structure. The drilling process on composite materials does not always go well which results in the composite being damaged during the drilling process. One punching defect is delamination (a measure of the damaged area around the hole). This study focused on delamination results with the composite materials used in aircraft, namely carbon fiber composites with an epoxy resin matrix. The method used to analyze the degree of delamination is by calculating the delamination factor (Fd), while to see the effect of the drilling treatment is used by using a two-way ANOVA based on hypothesis testing using the F distribution of the P-value. The drilling process is carried out using a CNC machine with the use of twist drill bits measuring 3mm and 6mm. Drilling treatment is very influential on the results of delamination. This is reinforced by ANOVA calculations with the result that the P value on the entry and exit surfaces is less than 0.05, indicating that the drilling treatment has an effect on the delamination results. -1.1983 and 1.2487 respectively. The highest delamination factor occurred on the entry and exit surfaces at RPM 3500 with direct drilling with values of 1.3328 and 1.3827 respectively. With this result, the higher the RPM value, the resulting delamination effect increases, both direct and gradual drilling.
Drilling was carried out to make holes in the components of the F1A glider aircraft which aimed to unite the fuselage and wing structural parts to create a strong and reliable structure. The drilling process on composite materials does not always go well which results in the composite being damaged during the drilling process. One punching defect is delamination (a measure of the damaged area around the hole). This study focused on delamination results with the composite materials used in aircraft, namely carbon fiber composites with an epoxy resin matrix. The method used to analyze the degree of delamination is by calculating the delamination factor (Fd), while to see the effect of the drilling treatment is used by using a two-way ANOVA based on hypothesis testing using the F distribution of the P-value. The drilling process is carried out using a CNC machine with the use of twist drill bits measuring 3mm and 6mm. Drilling treatment is very influential on the results of delamination. This is reinforced by ANOVA calculations with the result that the P value on the entry and exit surfaces is less than 0.05, indicating that the drilling treatment has an effect on the delamination results. -1.1983 and 1.2487 respectively. The highest delamination factor occurred on the entry and exit surfaces at RPM 3500 with direct drilling with values of 1.3328 and 1.3827 respectively. With this result, the higher the RPM value, the resulting delamination effect increases, both direct and gradual drilling.
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