HILS of auto take off system: For high Speed UAV using booster rocket

Irwanto, Herma Yudhi

doi:10.1109/isitia.2016.7828689

Cited by 8 publications

(3 citation statements)

References 6 publications

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“…Sari Bahari telah mulai mengembangkan rudal, untuk versi awal dinamai Rudal Petir. Teknologi kunci seperti yang disampaikan oleh (Irwanto, 2016) (EMI), rancang bangun embeded control system tahan vibrasi, penelitian dan pengembangan sistem tracking, penelitian dan pengembangan sistem sensor inersia, penelitian dan pengembangan sistem uji kontrol 3 dimensi, penelitian dan pengembangan flight simulator, penelitian dan pengembangan sistem separasi motor roket, penelitian dan pengembangan sistem aktuator rudal, rancang bangun sistem radar, rancang bangun sistem kendali terintegrasi untuk pemandu roket, pengembangan material untuk sensor infra-red, pengembangan nozzle coating untuk rudal, pengembangan binder untuk propelan, dan rancang bangun liner insulator tabung motor roket.…”

Section: Pendahuluanunclassified

Pengembangan Prototipe Rudal Petir dalam Rangka Meningkatkan Iptek di Bidang Rudal Pada Pemenuhan Alutsista dalam Negeri

Shofhani

Apriyanto

Jandhana

2022

SOSTECH

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Latar belakang: Pengembangan Prototipe Rudal Petir merupakan kegiatan pengembangan Prototipe Rudal Petir pada tahun 2017, yang sudah berhasil terbang autopilot mengikuti waypoint. Terkait hal ini Balitbang Kemhan melaksanakan Litbang Pengembangan Prototipe Rudal Petir ini bekerja sama dengan PT. Sari Bahari. Tujuan penelitian: Pada kegiatan Pengembangan Prototipe Rudal Petir tahap I – IV adalah bertujuan untuk meningkatkan jarak jangkau, kecepatan dan auto pilot system. Sedangkan pada tahap II – IV adalah pembuatan sistem Seeker, penggunaan Booster pada sistem peluncuran dan penggunaan warhead dengan model impact. Metode penelitian: Metode penelitian yang digunakan adalah penelitian dengan pendekatan kualitatif. Jenis pendekatan penelitian yang digunakan dalam penelitian ini adalah penelitian deskriptif analisis. Hasil penelitian: Diharapkan kegiatan ini akan meningkatkan Iptek di bidang rudal serta kemandirian nasional khususnya pemenuhan Alutsista dalam negeri sehingga perlu keberpihakan dari pemerintah pada pengembangan rudal petir ini untuk mendorong industri pertahanan nasional, dalam meningkatkan posisi tawar bangsa dan negara Indonesia di kawasan serta meningkatkan efek penggentar atau deterrence effect, juga dapat meningkatkan pemanfaatan tenaga ahli bangsa yang berpotensi dalam pengembangan dan pembuatan alutsista yang merupakan asset bangsa. Kesimpulan: Berdasarkan konsep desain yang telah dikembangkan pada rudal petir ini, berkaitan dengan kemandirian produk dan teknologi yang dikuasai sepenuhnya oleh bangsa Indonesia yang dihasilkan dari kemampuan dalam negeri, dengan beberapa komponen yang masih dibeli dari luar adalah komponen generik saja, yang dilakukan melalui integrasi untuk menjadi modul atas subsistem secara mandiri.

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Section: Pendahuluanunclassified

Pengembangan Prototipe Rudal Petir dalam Rangka Meningkatkan Iptek di Bidang Rudal Pada Pemenuhan Alutsista dalam Negeri

Shofhani

Apriyanto

Jandhana

2022

SOSTECH

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“…Presently, a significant number of researchers are engaged in investigating the complex interaction between booster rockets, turbojet engines, UAVs, launch pads during the launch phase [1,2,3,4], and auto takeoff systems [5]. Notably, Martel and Dudley [6] explored the impact of engine exhaust on booster rockets, leading to additional pitching moments.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Stability Study of Turbojet Engine During Unmanned Aerial Vehicle Assisted Taking Off Stage

Du,

Wu,

Wang

et al. 2023

J. Phys.: Conf. Ser.

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Rocket Assisted Take Off (RATO) technology is utilized for the takeoff phase of various types of UAVs. RATO creates heavy axial overload for a UAV system, which consequently increases the inlet pressure of the fuel pump of the UAV’s turbojet engine. This situation leads to an abrupt change in fuel supply for its combustor, eventually causing drastic changes in the operating state of the compressor system. In addition, it may potentially induce compressor surge. To resolve this problem, through an experimental investigation, this study delves into the dynamic response of the fuel system during the RATO phase. A two-zone dual-wave coupled compressor model has been established for the intake-turbojet engine system to scrutinize the aerodynamic stability of the turbojet engine during the RATO phase. The findings reveal that when the increase of fuel pump inlet pressure causes changes in the fuel flow rate, it is essential for the engine to re-establish aerodynamic equilibrium in order to mitigate the impacts of abrupt fuel flow step increases. Moreover, it has been observed that the more the ratio of the length of the intake and the cross-section area, the greater the contribution of the inertial force of airflow in the pipe it brings within the passage. This results in a stronger suppression of combustion chamber pressure and flow rate fluctuations induced by fuel step supply, thereby rendering the compressor less susceptible to surge. In summary, this research contributes valuable insights for appropriate matching of intakes, enhancing the ability of the turbojet engine against fuel step supply in the combustion chamber during the takeoff stage and augmenting the aerodynamic and thermodynamic overload resistance capability of the engine.

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“…Electric-Ducted Fan (EDF) rocket is one class of rocket that uses electric thruster as its main actuator [1]. It gains popularity for education and research purposes due its low cost and versatility.…”

Section: Introductionmentioning

confidence: 99%

Design and implementation of hardware in the loop simulation for electric ducted fan rocket control system using 8-bit microcontroller and real-time open source middleware

Yulnandi

Machbub

Prihatmanto

et al. 2017

J. Mechatron. Electr. Power Veh. Technol.

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Hardware in the Loop Simulation (HILS) is intended to reduce time and development cost of control system design. HILS systems are mostly built by integrating both controller hardware and simulator software where the software is not an open source. Moreover, implementing HILS by using manufactured system is costly. This paper describes the design and implementation of HILS for Electric Ducted Fan (EDF) rocket by using open-source platform for development with middleware. This middleware system is used to bridge the data flow between controller hardware and simulator software. A low-cost ATMEGA 2560 8-bit microcontroller is used to calculate rocket's attitude with Direction Cosine Matrix (DCM) algorithm and PID controller is employed to regulate rocket's dynamics based on desired specifications. X-Plane 10 simulator software is used for generating simulated sensory data. The test results validate that HILS design meets the defined specifications, i.e. angle difference of 0.3 degrees and rise time of 0.149 seconds on pitch angle.

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HILS of auto take off system: For high Speed UAV using booster rocket

Cited by 8 publications

References 6 publications

Pengembangan Prototipe Rudal Petir dalam Rangka Meningkatkan Iptek di Bidang Rudal Pada Pemenuhan Alutsista dalam Negeri

Pengembangan Prototipe Rudal Petir dalam Rangka Meningkatkan Iptek di Bidang Rudal Pada Pemenuhan Alutsista dalam Negeri

Aerodynamic Stability Study of Turbojet Engine During Unmanned Aerial Vehicle Assisted Taking Off Stage

Design and implementation of hardware in the loop simulation for electric ducted fan rocket control system using 8-bit microcontroller and real-time open source middleware

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