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Ginting, Salam
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Aerospace Engineering Astronomy

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ANALISA AERODINAMIKA KENDALI CANARD ROKET RKX 250 Ginting, Salam
Indonesian Journal of Aerospace Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007)
Publisher : BRIN Publishing

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In the framework of guided missile development in LAPAN, Center of Technology has been rocket designed, constructed and then performed a guided missile trial launching in Pameungpeuk in May 2002. However the result was still far from expectation. It has been realized that numerous of factors played a part in the failure of the missile trial launching, which are structure strenght, propulsion, propellant, guidance system and aerodynamic stability. From all the above factors, aerodynamic static stability is the initial requirement which has to be validated before stepping to the next design process. Based on the above situation, it has been carried out a analysis un RKX 250 rocket aerodynamic static stability with canard guidance which configuration is almost similiar with the one that was launched in Pameungpeuk. To find out the rocket's aerodynamic static stability, a research on lift coefficient and drag coefficient must be done first. From the lift coefficient data, a conduction the center pressure of aerodynamics rocket. Method that is used in this research is the ine which was developed by quadrature multhopp which is analytical method (Krasnov N.F.1978).
ANALISA PERUBAHAN STATIC MARGIN PERANCANGAN ROKET KENDALI RKX 70 MM Ginting, Salam; Ismail, Maryono
Indonesian Journal of Aerospace Vol. 7 No. 1 Juni (2009): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Roket ini dirancang untuk roket kendali sehingga dibutuhkan gerakan manuver yang lincah, cepat, dan akurat. Roket ini dilengkapi dengan 4 kontrol canard dipasang pada bagian depan dan 4 buah sirip dipasang di bagian nozel roket. Nilai statik margin roket ini positif sehingga roket ini dapat digolongkan jenis unstable missile. Sistem kendalinya sudah aktif saat roket lepas dari peluncur mengikuti program pengendalian yang sudah tersedia. Titik berat roket ditetapkan pada titik 0,7 kali panjang roket terhitung dari nose cone. Pusat tekanan aerodinamikanya dihitung setelah diperoleh koefisien aerodinamika gaya angkat roket menggunakan metode Quadrature Multhopp, yang lazim digunakan dalam perancangan aerodinamika roket. Tulisan ini merupakan hasil dari perancangan aerodinamika roket secara teoritis yang harus divalidasi dengan hasil penelitian yang sudah baku yakni penelitian NACA Report untuk roket yang sejenis.
ANALISIS HASIL PENGUJIAN DAN PREDIKSI TEORITIS AERODINAMIKA ROKET RX 300 Ginting, Salam
Indonesian Journal of Aerospace Vol. 5 No. 2 (2007): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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LAPAN has a supersonic wind tunnel facility which could be used for research of rocket model to get aerodynamics characteristic of the model through testing with various speeds within supersonic range. The research on the RX 300 rocket model has been carried out in the above facility at velocity range of 1,5-3 Mach. Some aerodinamic are obtained from this research. Such as lift drag and moment ceofficients. Aerodynamic coefficient is shown in the curve as a function of Mach and angle of attack. This result will be compared with the theoretical calculation and the result is higher around 5 percent than theory. The approach of Quadrature Multhopp is method use in this analysis. The RX 300 rocket model is equipped with foru flaps at the back part of the rocket as a stabilizer when the rocket is launched. This rocket is designed for being able to carry a payload with dimention of 25 cm diameter and 45 cm length. Keywords: Aerodynamic rocket, Wind tunnel.
Co-Authors Ismail, Maryono