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Andri Agus Rahman
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INDONESIA
Indonesian Journal of Aerospace
Published by Badan Riset dan Inovasi Nasional
ISSN : -     EISSN : 30320895     DOI : https://doi.org/10.55981/ijoa
Core Subject : Science, Engineering,
Aerospace Engineering Astronomy
Indonesian Journal of Aerospace provides a broad opportunity for the scientific and engineering community to report research results, disseminate knowledge, and exchange ideas in various fields related to aerospace science, technology, and policy. Topics suitable for publication in the IJoA include (but are not limited to) Space science (astrophysics, heliophysics, magnetospheric physics, ionospheric physics, etc.), Aeronautics technology (dynamic, structure, mechanics, avionics, etc.), Space technology (rocket, satellite, payload system, control, etc.), Propulsion and energetic technology (propellant, rocket static-test, thermodynamics of propulsion system, etc.), Aeronautics and space policy, and Application of aerospace science and technology.
Arjuna Subject : Ilmu Bumi dan Planet (semua kategori) - Ruang Angkasa dan Ilmu Planet
Articles 13 Documents
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Search results for , issue "Vol. 19 No. 2 (2021)" : 13 Documents clear
The Effect of Payload Weight to Mean Coil Diameter of Helical Compression Spring for Payload Separation Laksono , Shandi Prio
Indonesian Journal of Aerospace Vol. 19 No. 2 (2021)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3565

Abstract

Weight is one of major factors in sounding rocket or launch vehicle design. Indeed, payload weight contributes to the rocket weight. Sounding rocket release the payload in the upper atmosphere at the certain altitude. Sounding rocket is intended to carry the payload as much as possible. In payload jettison/separation system, helical compression spring is commonly used. The previous study result show that in order to avoid mechanical failure of the spring, if the payload weight was 60 kg, the minimum wire diameter of helical compression spring must be 8 mm with mean coil diameter of 80-96 mm. Based on the previous study result, this study investigated the effect of payload weight to mean coil diameter of helical compression spring for payload separation. The numerical method was used in this study. In order to increase the payload weight, the mean coil diameter must be decreased. The results obtained show that the maximum payload weight that can be used was 77 kg with the maximum mean coil diameter of 80 mm, and free length of 0.417 m. In addition, safety factor of 1.65 and energy storing of 81.8 N.m was obtained.
Three-Dimensional (3D) Flight Planning Optimization Using Genetic Algorithm Considering FCOM Data Nugraha, Calvarico Bima; Ruseno, Neno
Indonesian Journal of Aerospace Vol. 19 No. 2 (2021)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3607

Abstract

Flight Planning is a document prepared by airline which consist of aircraft information, planned route, required fuel, carried load, weather forecast, etc. It needs to be submitted to ATC to get approval and then it will be used by pilot to guide the flight to reach the destination. Optimization in flight planning route is one of the essential factors in reducing fuel consumption to reduce cost and emission. The aim of this research is to optimize the flight planning route in Three-Dimensional approach using Genetic algorithm. Genetic algorithms (GA) are widely used in optimizations that includes many parameters, thus it could be used in flight planning optimization. The concept of GA is a heuristic search approach that inspired by Darwin’s theory of natural evolution which mimics “Survival of the fittestâ€. The method starts with a hexagon size containing nodes of possible points connecting departure and arrival airports. In this research the nodes are extracted using Dijkstra algorithm from previous research. The algorithm used population size of 500 individuals that generated with 0.01 mutation rate, 100 generation cycle, and 20 elite size. The case study covers routes in area of Indonesia which are flights of Jakarta – Tanjung Pinang, Jakarta – Makassar, and Jakarta – Manado. The different aircraft gross weights are analyzed to study the effect of aircraft weight to the resulted flight route. The aircraft performance database from Flight Crew Operating Manual (FCOM) of A320 aircraft was used to calculate the fuel burn. It is concluded that the algorithm able to find the optimal flight route as the best individual with range of cruise altitude from 35,000 to 39,000 ft. Results from Jakarta - Tanjung Pinang showed an average of fuel reduction of around 2.29% followed by Jakarta - Makassar with 13.28% and Jakarta - Manado with 15.68%. Although, the resulted altitude profile shows a fluctuation in the middle of route, in average it is a climb.
Full Pages JTD Vol 19 No.2 December 2021 Tekgan, Editorial Jurnal
Indonesian Journal of Aerospace Vol. 19 No. 2 (2021)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar

Abstract

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