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Sugiarmadji HPS
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ANALISIS DEFLEKSI DAN TEGANGAN STRUKTUR ROKET RX-320 PADA WAKTU HANDLING DENGAN METODE ELEMEN HINGGA (FEM) Sugiarmadji HPS; Setiadi
Indonesian Journal of Aerospace Vol. 7 No. 2 (2009): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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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.
KARAKTERISTIK DINAMIKA STRUKTUR SATELIT MIKRO LAPAN-TUBSAT Triharjanto, Robertus Heru; Sugiarmadji HPS
Indonesian Journal of Aerospace Vol. 3 No. 2 (2005): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2005.v3.a814

Abstract

The TUBSAT-LAPAN micro satellite is planned to be launched using PSLV rocket. The design constraints of the mechanical system of the satellite are able to accomodate structural requirment for PSLV, which are first resonance frequency in the rocket longitudinal axis 90 Hz and first resonance frequency in the lateral axis 45 Hz. Therefore, the structural dynamic characteristic data of the satellite is important to be evaluated, such as natural frequency and mode shapes of the satellite structures, The normal modes analysis made is done usingh Finite Element Methods commercial software NASTRAN. To simplify the FEM modeling the satellite components inside the compartmens is replaced by a dummy load simulating their contribution to satellite mass, centerof gravity and inertia, which was made by the same material as the satellite's structure, i.e. Al-Alloy 2024T351. Meanwhile, the FEM modeling for both the UHF antena used the Stainless Steel materials as the real antena. The analysis results show that the lowest local natural frequency of the satellite occurs on the UHF antena. The first natural frequency of the antena structures in lateral direction is 52,29 Hz. The first natural frequency of the satellite in lateral direction 151.47 Hz completing the satellite integration, vibration test was done to the satellite. The test shows that the first global frequency is 72-75 Hz in the lateral direction and 148 Hz in longitudinal direction. Structural dynamic characteristic of TUBSAT_LAPAN micro satellite in free flying condition are also analyzed using no-constraint condition to check the safe separation clearance scenario. The results show that the first natural frequencies for satellite structures (combination) become very small, less than 0.00032 Hz. But, the lowest of the first natural frequency for UHF antena structures is almost constant, 52.30 Hz in lateral direction.
RANCANGAN KAPAL UDARA (AIRSHIP) UNTUK VIDEO MONITORING DARI UDARA Sugiarmadji HPS; Robertus Heru T; Setiadi; Ediwan
Indonesian Journal of Aerospace Vol. 1 No. 1 (2003): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

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 HPS; Setiadi
Indonesian Journal of Aerospace Vol. 2 No. 1 (2004): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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 Robertus Heru T Setiadi Triharjanto, Robertus Heru