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All Journal Indonesian Journal of Aerospace
Dewi, Wiwiek Utami
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Aerospace Engineering Astronomy

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Effects of Bleeder Schedule to Fiber Mass Fraction and Composites Surface Topography on Wet Lay-up Manufacturing Process Dewi, Wiwiek Utami; Sutrisna, Rizky; Sutrisno, Sutrisno
Indonesian Journal of Aerospace Vol. 19 No. 1 (2021)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3572

Abstract

The thermal protector materials of the rocket’s motor are made by a wet lay-up manufacturing process. Since the fiber mass fraction of the product is low, several experiments were conducted to solve this problem including changing the type of the epoxy resin and selecting the most suitable bleeder schedule. Bleeder cloth application results in increasing the fiber mass fraction. The fiber mass fraction of thermal protector material manufactured by hand lay-up can reach a maximum of 56,78%, whereas vacuum bagging can reach a maximum of 66,43%. Peel ply and breather fabric combination are the best bleeder schedule for the hand lay-up method meanwhile perforated release film and breather fabric are the best bleeders for the vacuum bagging method. Composite surface topography obtained from peel ply is visible on the surface. The imprints of the nylon peel ply weave are visible through SEM analysis. Meanwhile, the surface topography obtained from the perforated release film is not visible. The vacuum bagging method helped reduce the number of voids and ductile polymer fractures from the composite surface. This paper recommends peel ply usage in the thermal protector manufacturing process to replace the sanding or filling method that the author use nowadays.
OPTIMASI SISTEM LINING MOTOR ROKET PADAT RX1220 MELALUI PERUBAHAN KOMPOSISI MATERIAL LINER DAN METODE LINING (OPTIMIZATION OF LINING SYSTEM FOR RX1220 SOLID ROCKET MOTOR THROUGH IMPROVEMENT OF LINER MATERIAL COMPOSITION AND LINING METHOD) Dewi, Wiwiek Utami
Indonesian Journal of Aerospace Vol. 12 No. 1 Juni (2014): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

In 2013, as many as 21.42% of the RX1220 rocket motor production did not pass the radiographic testing due to air bubble presences within the liner layer (liner defects). In 2014, there are dimensional changes in the inside diameter of the rocket motor tube (107.5 mm to 107.1 mm). Lining process by using gravity casting method becomes more difficult to apply. Liner viscosity is considerably high for the lining method. The efforts to lower its viscosity had been done yet the result did not reach the expectation. The changes in liner composition and lining method were conducted to optimize the RX1220 lining process. The result was good. After the new compositionand improved method applied, no more liner defects in RX1220. All of RX1220 rocket motors were labeled QC pass from the radiographic testing.
EVALUASI KINERJA INSULINER BERBASIS EPOKSI MELALUI UJI STATIK MOTOR ROKET CASE BONDED (PERFORMANCE EVALUATION OF EPOXY BASED INSULINER OF CASE BONDED ROCKET MOTOR THROUGH STATIC TEST) Sutrisno; Rohman, Fathur; AH, Ronny Irianto; Dewi, Wiwiek Utami
Indonesian Journal of Aerospace Vol. 11 No. 1 Juni (2013): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Kegiatan penelitian yang telah dilakukan sebelumnya telah diperoleh material insuliner berbasis epoksi dan metode aplikasinya pada motor roket case bonded. Hasil penelitian ini juga telah diperoleh bahwa insuliner tersebut dapat direkomendasikan untuk digunakan pada motor roket case bonded yang menggunakan propelan radial burning sehingga perlu dibuktikan. Guna menguji kinerja insuliner tersebut telah dibuat dua unit motor roket case bonded mengggunakan insuliner berbasis epoksi dan satu unit motor roket free standing yang menggunakan insulasi termal berbasis epoksi dan lapisan fiber glass cloth untuk diuji statik. Tiga unit motor roket telah diuji statik. Berdasarkan pengujian diperoleh bahwa insuliner berbasis epoksi yang dibuat dapat berfungsi dengan baik. Kegagalan motor roket case bonded yang kedua tidak disebabkan oleh gagalnya insuliner tetapi oleh proses perakitan motor roket yang kurang sempurna.
PENGARUH PENAMBAHAN FILLER SIO2, CARBON BLACK, DAN TIO2 PADA SIFAT MEKANIK LINER EPOKSI POLISULFIDA MOTOR ROKET CASE BONDED (THE EFFECT OF SIO2, CARBON BLACK AND TIO2 FILLER ADDING TO MECHANICAL PROPERTIES OF EPOXY POLYSULFIDE LINER OF CASE BONDED MOTOR ROCKET) Dewi, Wiwiek Utami; Soegiono, Bambang
Indonesian Journal of Aerospace Vol. 11 No. 1 Juni (2013): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Liner epoksi polisulfida virgin (tanpa filler) tidak cukup kuat untuk menahan beban struktural dan kondisi yang ekstrem selama roket beroperasi oleh karena itu penambahan filler sangat penting dilakukan untuk meningkatkan kekuatan mekanik liner. SiO2, carbon black dan TiO2 telah dipilih sebagai filler untuk memperkuat matriks liner epoksi polisulfida pada motor roket case bonded Lapan. Pengaruh penambahan ketiga filler tersebut pada sifat mekanik liner telah diselidiki dalam penelitian ini. Sembilan jenis komposisi liner telah dibuat dan melalui beberapa proses pengujian sifat mekanik yang meliputi: kekerasan, tegangan tarik maksimum, regangan maksimum, dan kekuatan rekat (liner terhadap logam). Hasil penelitian menunjukkan bahwa nilai kekerasan liner sebanding dengan nilai tegangan tarik maksimum liner dan nilai kekuatan rekat liner terhadap logam sebanding dengan nilai regangan maksimum, sementara itu tegangan tarik maksimum liner memiliki hubungan polinomial dengan regangan maksimumnya. Regangan maksimum tertinggi (52%) dicapai pada nilai tegangan tarik maksimum 16,25 kg/cm2.
DEKOMPOSISI TERMAL PROPELAN KOMPOSIT BERBASIS AMONIUM PERKLORAT/HYDROXY TERMINATED POLYBUTADIENE (AP/HTPB) (THE THERMAL DECOMPOSITION ANALYSIS OF AMMONIUM PERCHLORATE/HYDROXYTERMINATED POLYBUTADIENE (AP/HTPB) COMPOSITE SOLID PROPELLANT) Dewi, Wiwiek Utami; Ismah, Yulia Azatil
Indonesian Journal of Aerospace Vol. 14 No. 1 Juni (2016): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2016.v14.a2944

Abstract

Thermal decomposition process of AP/HTPB solid propellant type RUM, 450 and 1220 were investigated by DTG60 (Differential Thermogravimetric) with operational parameters: temperature 30 – 400oC, nitrogen flow rate 50 ml/min, and heating rate 2.5 C/min. Thermal decomposition analysis will be the first step of decomposition kinetics research in determining life time of the propellant. TGA curve of propellant RUM was found to be two staged meanwhile the thermal decomposition of propellant 450 and 1220 has become one staged. The DTA curve/thermogram of propellant RUM show the formation of intermediate product before full-length decomposition. Unlike propellant RUM, DTA curves of propellant 450 and 1220 do not show the formation of intermediate product. Decomposition process of propellant 450 and 1220 accelerate by Al presence. The difference between AP modal on propellant 450 and 1220 show insignificance effect to the amount of decomposition energy consumption.
Co-Authors AH, Ronny Irianto Fathur Rohman, Fathur Ismah, Yulia Azatil Soegiono, Bambang Sutrisna, Rizky SUTRISNO Sutrisno, Sutrisno