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Salam Ginting
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ANALISA AERODINAMIKA KENDALI CANARD ROKET RKX 250 Salam Ginting
Jurnal Teknologi Dirgantara Vol 5, No.1 Juni (2007)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

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). Keywords: Canard, Dinamika stabilitas, Statik stabilitas, Static margin, Pusat tekanan aerodinamika, Mach number.
ANALISA PERUBAHAN STATIC MARGIN PERANCANGAN ROKET KENDALI RKX 70 MM Salam Ginting; Maryono Ismail
Jurnal Teknologi Dirgantara Vol 7, No.1 Juni (2009)
Publisher : National Institute of Aeronautics and Space - LAPAN

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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.
Co-Authors Maryono Ismail