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Jurnal Teknologi Dirgantara
Published by Lembaga Penerbangan dan Antariksa Nasional
ISSN : 14128063     EISSN : 25977849     DOI : https://doi.org/10.30536
Core Subject : Science, Engineering,
Aerospace Engineering Chemical Engineering, Chemistry & Bioengineering Computer Science & IT Mechanical Engineering Physics
Jurnal Teknologi Dirgantara (Journal of Aerospace Technology) is an Indonesian accredited scientific publication that covers topics of Rocket, satellite, and aeronautics technology, as well as a spin-off from aerospace technology, such as aerodynamics, astronautics, aerospace structure, power and thermal system of satellites, flight controls. Propulsion and energetic technologies, such as propellant, rocket static-test, thermodynamics of propulsion system. Launch vehicle technology and space operations, such as satellite telecommunication systems, space payloads, and ground station technologies.
Arjuna Subject : Teknik (semua kategori) - Teknik Ruang Angkasa
Articles 333 Documents
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Full Pages JTD Vol 19 No.2 December 2021 Editorial Jurnal Tekgan
Jurnal Teknologi Dirgantara Vol 19, No 2 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3738

Abstract

Design and experimental Verification of Vibration Testing Fixture for Flight Control Panel Yusuf Giri Wijaya; Nur Mufidatul Ula
Jurnal Teknologi Dirgantara Vol 19, No 2 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3701

Abstract

In this research, experimental design and testing of the vibration test fixture were carried out. The designed vibration test fixture is used to test the FCP, which is one of the components of avionics in aircraft. FCP vibration testing is carried out using the DO-160 test standard. The test has a test frequency range from 5 to 500 Hz. Therefore, the vibration test fixture must have a natural frequency above 600 Hz. The vibration test fixture is designed using a T-type model with modifications to get optimal results. The raw material used to make the test fixture is aluminum. The test fixture has a natural frequency value above 500 Hz, and both were tested using FEM simulation and experimental tests. Therefore, the vibration test fixture that is made meets the requirements for vibration testing on FCP. The difference in the natural frequency value from the FEM simulation and experimental test results on the vibration test fixture is 14.61% on the Z-axis, 10.61% on the X-axis, and 9.74 on the Y-axis.
Study on The Development of Guidance System Technology for 122-140 mm Artillery Rocket Ahmad Riyadl; Widianto Nugroho; Ahmad Novi Muslimin; Zaenal Asiqin; Rudi Setiawan; Robertus Heru Triharjanto; Yoni Herdian Yogaswara
Jurnal Teknologi Dirgantara Vol 19, No 2 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3691

Abstract

The increase in rocket Artillery accuracy means there will be fewer rockets to be used to destroy a target. This could reduce the needed budget and risk of weapon mobilization. Therefore, this research investigates the advancement in the guidance system technology for Artillery rockets, especially for 122-140 mm caliber. The objective of the research is to find a direction for the development guidance system for the Indonesian Artillery rocket (RHAN). The research use the descriptive-analytic method, in which data was collected from literature studies and inductive analysis was performed. The data shows two kinds of actuators were used, a canard and thrusters. In canard mode, 2 strategies were used, i.e. with bearing to isolate the roll from the rocket, in which 5 control algorithms were used, and without bearing, which 2 control algorithms were used. In thruster mode, there was 5 control algorithms used. Further analysis shows that the best performance is obtained from 2 modes of the canard strategy with bearing, and 2 modes of the thruster strategy. Therefore, it is concluded that the 4 modes can be used to be implemented in RHAN which needs to be added to the control system.
Full Pages JTD Vol 18 No.1 Juni 2020 Editor Jurnal
Jurnal Teknologi Dirgantara Vol. 18 No.1 Juni 2020
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2020.v18.a3711

Abstract

Full Pages JTD Vol 19 No.1 June 2021 Editorial Jurnal
Jurnal Teknologi Dirgantara Vol 19, No 1 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3740

Abstract

Effect of Hybridization on Tensile, Shear and Compressive Properties of Carbon Based Fiber Reinforced Composites Kosim Abdurohman
Jurnal Teknologi Dirgantara Vol 19, No 2 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3575

Abstract

The high specific stiffness and strength of composites make them widely used   in defence, marine, and aerospace applications. Hybrid composites have increased use in high-tech applications. The glass/carbon and KC/carbon hybrid composites manufactured by vacuum assisted resin infusion methods are used in this study. The matrix used for both composites are vinylester resin. The glass/carbon and KC/carbon hybrid laminates arrangement is [G/C/G2/C/G2/C]s and [(KC)2/C3]s, respectively. The mechanical properties are evaluated according to ASTM standards. Fracture micrograph analysis are investigated using SEM. The comparison of mechanical properties and surface fracture of both hybrid composites have been investigated. The tensile and compressive strength of KC/carbon are higher than glass/carbon hybrid composites. However, the shear strength of KC/carbon is lower than glass/carbon hybrid composites. SEM micrograph exhibits that the KC/carbon has a good fiber/matrix and interlayer bond better than glass/carbon hybrid composites.
The Effect of Payload Weight to Mean Coil Diameter of Helical Compression Spring for Payload Separation Shandi Prio Laksono
Jurnal Teknologi Dirgantara Vol 19, No 2 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

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.
The effect of Impact Angle on Dynamic Response of 19 Passenger Commuter Aircraft Windshield against Bird Strike Budi Aji Warsiyanto
Jurnal Teknologi Dirgantara Vol 19, No 2 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3560

Abstract

This paper's objective was to determine the dynamic response of a 19 passenger commuter aircraft windshield to impact angle variations. The phenomenon was performed using the finite element method, and the smoothed particle hydrodynamics (SPH) was chosen as a method for modeling bird material. The elastic-plastic polymethyl methacrylate (PMMA) material with the maximum principal strain failure criterion was used to model the windshield's dynamic response. The variation of the impact angle consists of 15°, 0°, -8°, and -15°, which are measured of the longitudinal axis of the aircraft. The simulation result showed that the impact angle that causes the windshield's dynamic response in the elastic, plastic deformation, and the greatest failure is the angle -15°. The upper end of the windshield (fixed) is the weakest part due to the stress concentration.
Design Optimization of A Conventional Rocket Nozzle Using Coupled Thermo-Structural Analysis M Dito Saputra; Novi Andria
Jurnal Teknologi Dirgantara Vol 19, No 2 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3570

Abstract

Thrust in a rocket is gained by expelling the combustion gas through a nozzle.  This rocket nozzle is a vital component during the conversion of chemical energy into kinetic energy. Consequently, it is exposed to extreme temperature and pressure resulted from gas combustion. Therefore to ensure a successful rocket operation, the nozzle must be able to maintain structural integrity when exposed to such environment. On the other hand, its structural weight must be kept minimum to reduce the overall weight of the rocket. Due to these circumstances, the nozzle design phase is very important since the nozzle significantly affects the whole rocket performance. LAPAN is currently developing some solid propellant based rocket. Each rocket’s nozzle is still designed using conventional configuration, consisting of a metal case and graphite insert. The nozzle relies on a thick structure geometry to maintain structural integrity. This approach induces a heavy-weight nozzle that burdens the rocket performance. This paper is attempted to optimize LAPAN’s conventional solid rocket nozzle design. A series of procedures are proposed to generate a lighter nozzle design. RX-450 rocket’s nozzle will be used as the studied model in this paper.  Coupled thermo-structural analysis forms the main procedure to evaluate the proposed nozzle geometry structural integrity. The study succesfully provided an optimized nozzle geometry with sufficient strength and reduced weight. 
Three-Dimensional (3D) Flight Planning Optimization Using Genetic Algorithm Considering FCOM Data Calvarico Bima Nugraha; Neno Ruseno
Jurnal Teknologi Dirgantara Vol 19, No 2 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

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 fittest”. 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.

Page 32 of 34 | Total Record : 333

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