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ANALISIS DEFLEKSI DAN TEGANGAN STRUKTUR ROKET RX-320 PADA WAKTU HANDLING DENGAN METODE ELEMEN HINGGA (FEM) Sugiarmadji HPS; - Setiadi
Jurnal Teknologi Dirgantara Vol 7, No.2 Desember (2009)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Analisis kekuatan struktur pada waktu handling roket perlu dilakukan, seperti ketika akan menjalani penimbangan untuk mencari letak c.g (center of gravity) roket ataupun ketika roket diletakkan di atas launcher. Roket biasanya diangkat dengan menggunakan katrol yang dilengkapi dua buah clamp. Analisis defleksi dan tegangan yang terjadi akan dilakukan dengan menggunakan bantuan perangkat lunak berbasis Metoda Elemen Hingga (Finite Element Methods/FEM). Hasil analisis defleksi dan tegangan struktur roket RX-320, menunjukkan terjadinya tegangan geser maksimum sebesar maks = 85.188,71 Pa. Oleh karena itu bahan tabung masih aman sekali terhadap beban yang bekerja. Tegangan geser ini dapat mempengaruhi lapisan liner dan propelan roket. Besarnya defleksi maksimum pada struktur roket adalah sebesar 5.1903E-3 mm yang terjadi pada nodal no. 25373. Lokasi ini berada di ujung struktur nose cone. Besarnya defleksi di daerah struktur tabung, harganya relatif kecil. Oleh karena itu, pengaruh terjadinya defleksi terhadap propelan dan liner masih bisa diabaikan. Namun demikian, selama menjalani handling, roket harus diperlakukan dengan hati-hati, sehingga propelan dan liner tidak mengalami keretakan.
RANCANGAN KAPAL UDARA (AIRSHIP) UNTUK VIDEO MONITORING DARI UDARA - Sugiarmadji HPS; Robertus Heru T; - Setiadi; - Ediwan
Jurnal Teknologi Dirgantara Vol 1, No.1 Juni(2003)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Remotely controlled non rigid helium airship type is chosen in airship design criteria for video monitoring. The design consists of airship dimensions and volume determination, maximum take of weight (MTOW) and W (weight empty plus payload) calculations, weight and structures analysis, airship stabilization analysis, airship guidance system, power plant system, position monitoring system, material and process, and payload systems. Here, Helium gas will be filled for generating a lift that is equal to the weight of the displaced air. An Airship Demonstrator Model LPN-01 is built to represent the design results. The model has length of L=8.5 m and 2.2 m diameter, so that the envelope volume is of 20 m. This Demonstrator Model will be used for studying capability or performance of airship, especially on ascent and descent manuever, airship's stability, position monitoring and payloads.
ANALISIS MODUS NORMAL DAN KEKUATAN STRUKTUR SIRIP ROKET-168 DARI BAHAN AL-PLATE - Sugiarmadji; - Setiadi
Jurnal Teknologi Dirgantara Vol 2, No.1 Juni (2004)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2004.v2.a793

Abstract

Structural strength analysis on Motor Rocket-168 fins was carried out to determine static stresses due to aerodynamic loadings. Here, 90 mm of the root chord area from leading edge was unclamp (free). The analysis results showed the maximum value of von Mises stress is Q von mises = 42.40 MPa. For 90 mm condition un clamp (free) we obtained the safety factor of the material for fins structures made of Al-Plate is SF=3.39. For 67.5 mm of 90 mm root chord area constrainted at 12456 directions, it was found Qvm equal 11,26 MPa and has higher safety factor. Eigenvalues and eigenvectors of the fins structures. The results showed that the eigenvalues of the fin structures are Q1 equal 198,47 Hz, Q2 equal 616,34 Hz, Q3 equal 1080,97 Hz, Q4 equal 1704,33 Hz, Q5 equal 2386,82 Hz, dan Q6 equal 2770,94 Hz.
Co-Authors - Ediwan - Sugiarmadji - Sugiarmadji HPS Robertus Heru T Sugiarmadji HPS