Papers by Herma Yudhi Irwanto
Latvian Journal of Physics and Technical Sciences/Latvian journal of physics and technical sciences, Mar 30, 2024
Progress in electromagnetics research M. Pier M, 2024
AIP Conference Proceedings, Dec 31, 2022
AIP Conference Proceedings, Dec 31, 2022
Journal of Physics: Conference Series, 2018
After development of simulation system in laboratory tests has been completed, before implementin... more After development of simulation system in laboratory tests has been completed, before implementing an autonomous flight control system directly in a high speed UAV, the system needs to be tested in a 'transitional' vehicle namely Clouds aeromodeling, to make sure all devices of the control system function well in manual mode, stability and auto pilot by way point. Compatibility of setting gain PID in the simulation test with the real flight test becomes a challenge to ensure the success of the vehicle in flying, as probability of flight failures or target missing is reduced. This research has successfully proven the compatibility of the gain PID in an auto pilot by way point flight condition.
AIP Conference Proceedings, 2020
Jurnal RESTI (Rekayasa Sistem dan Teknologi Informasi)
The success of a research is highly dependent on the method adopted, especially research related ... more The success of a research is highly dependent on the method adopted, especially research related to dangerous and expensive matters which will certainly require special handling in the development or maintenance steps. One of them is research related to space technology such as aviation and rocketry technology, which is very dependent on the design model of the flying vehicle and, in general, will always use simulation to ensure that the entire system being built is carried out safely and can be implemented properly according to plan. In the development of the prototype flying vehicle, especially the development of the avionics and flight control system, the vehicle will go through sequential simulation steps from Software in the Loop Simulation (SILS), Hardware in the Loop Simulation (HILS), and Ready-to-Fly System (RTFS). In this paper, the simulation steps will be described with the intention of facilitating integration and testing of each sub-system being developed, testing the ...
Jurnal Lemhannas RI
Kemandirian alutsista nasional dalam memproduksi alat pertahanan dan keamanan dalam suatu negara ... more Kemandirian alutsista nasional dalam memproduksi alat pertahanan dan keamanan dalam suatu negara akan dapat memberikan efek deterrent dalam pergaulan antar negara secara regional maupun internasional. Perbedaan cara dalam mengelola industri pertahanan oleh negara-negara maju dan negara-negara berkembang dapat dijadikan acuan untuk meningkatkan performa industri pertahanan negara dengan menerapkan beberapa hal yang dapat dilakukan dengan penyesuaian kondisi lingkungan berjalan. Disamping itu, mengacu pada sejarah pendirian dan proses berkembangnya industri pertahanan di Indonesia, diperlukan konsistensi pemerintah melalui KKIP dengan pengimplementasikan undang-undang tentang industri pertahanan yang telah dibuat serta evaluasi secara terus menerus terhadap hasil juga akan dapat meningkatkan siklus hidup industri pertahanan itu sendiri. Sehingga hasil pembelajaran pengelolaan industri pertahanan oleh negara-negara maju digabungkan dengan implementasi undang-undang dalam industri perta...
2022 IEEE 8th Information Technology International Seminar (ITIS)
2016 International Seminar on Intelligent Technology and Its Applications (ISITIA), 2016
Development of auto pilot system for high-speed UAV, RKX-200TJ, started in 2013. Currently, as th... more Development of auto pilot system for high-speed UAV, RKX-200TJ, started in 2013. Currently, as the guided and control system for UAV, the FPGA (Field Programmable Gate Array), in order to flexibility in management of inputs and outputs facilitate many modules, which are processed simultaneously. So the control and stability of the UAV is improved and easy to handle by the processor. Testing on this controller capacity in receiving 4 different inputs and 2 outputs module should be done in an integrated simulation with flight simulator (XPlane) to make sure that all programs run according to plan. Moreover, in this research, HILS (Hardware in the Loop Simulation) is activated to initiate IMU (inertial measurement unit), which is located on top of hexapod to illustrate the close loop programming (PID) between the vehicle attitude, which is seen in hexapod movement and IMU issuing sensor data and received by processor. Integrated development of HILS involves three computer units, i.e. dynamic computer (XPlane), monitoring computer (to control hexapod and to serve as GCS / Ground Control System) and a computer controller that is connected with the main onboard computer (NI MyRIO). All three computers are connected with the UDP (User Datagram Protocol). Meanwhile, the controller computer accesses the main board computer using the facility of ‘shared memory’. With these connections, the flying simulation of RKX-200TJ can run smoothly without interruption of time lag. Vehicle simulation models created in XPlane Maker. Vehicle dimensions, engine specification, control geometry and setting of weight and balance are very influential in this simulation. The vehicle model should be made as similar as possible to the actual vehicle. It should include data input of real measurement of the center of gravity (CG), with both X axis and Z axis should be used as a reference model of the vehicle. In this simulation the booster rocket is modeled in JATO (Jet Assisted Take Off) with the firing angle leads to CG, according to the result of real measurement. Simulation of auto take off and auto pilot system went well; describing RKX-200TJ hovered early with booster for 1 sec, and was subsequently taken over by the auto pilot system. The takeover happened when the vehicle speed had reached 250 km/h or 600 m altitude based on the program installed. The auto pilot system would maneuver with a maximum of 30 deg banking and stabilization that maintained speed and altitude to reach the target way point.
The use of fixed wing UAVs has been widely well known. There are a lot of advantages that can be ... more The use of fixed wing UAVs has been widely well known. There are a lot of advantages that can be reached using this aerial vehicle such as suitable for surveillance, remote inspection and disaster support missions. This kind of vehicle typicallny has nonlinear behavior, yet it is not as complex as an unmanned small scale helicopter. In this research, nonlinear modeling and linearization of this model were done. These dynamic system and linear model were carried out to develop an autonomous control system. This paper focuses on the development of a fixed wing uav control system which was validated through real time simulation for further flight test application. LQR Optimal control was chosen to accomplish the trajectory following mission. This control design was validated through hardware in the loop simulation based on Matlab/Simulink and XPlane Environment.
2015 4th International Conference on Instrumentation, Communications, Information Technology, and Biomedical Engineering (ICICI-BME), 2015
Started in 2013, research development on RKX-200TJ had given promising results. As the research w... more Started in 2013, research development on RKX-200TJ had given promising results. As the research was conducted, the rocket needed some improvement so that it could be used as a spinoff of defense system by Indonesian National Armed Force (TNI). The improvement needed was increasing potential weight in its payload, so RKX-200TJ had at least payload weight 25 kilogram. Thus, a rocket booster launcher was needed to replace the existing pneumatic launcher. However, the safety of the rocket booster had to be confirmed by calculating the stability of the vehicle at the switch of Cg location in Z axis at the time of booster launch and release. This research was done by using Integrated Simulation System (ISS) and the result was compared directly with the data from flight test RKX-200TJ Dummy Booster. The vehicle was designed to cruise at a speed of 250 km/hour, auto pilot by way points, using turbine jet as the main launcher (thrust max 20 kgf) and rocket booster as the initial launcher (average thrust 120 kgf). The crucial thing in this discussion was the one second when the booster was burning. Before flying, the vehicle had ZCg minus 6 cm, but when it was burning out, the booster was released and ZCg went back to 0. Such condition needed to be anticipated by locating the booster in the right angle. The right angle could be found by a simulation using XPlane repeatedly with different variations of angles. The result was later compared to the real flying data. The simulation result showed more details on the vehicle's pitch tendency with different angles of booster location. The significant result was separated within 0.1 deg of booster location, which might produce unsafe pitch up and pitch down if had not been recognized properly in the real flight test. The comparison between simulation result and flight test data showed that the simulation was quite reliable for different condition of ZCg for each vehicle fabrication which was done manually.
2017 International Seminar on Sensors, Instrumentation, Measurement and Metrology (ISSIMM), 2017
Flight simulation of high speed UAV by using autonomous control system that is related to auto ta... more Flight simulation of high speed UAV by using autonomous control system that is related to auto take off and auto pilot by way points system had completed and succeeded with integrated HILS facility that had been developed previously. In this simulation, the ability of bank-to-turn controls the vehicle that reached 30 deg within speed of 250 km/h. However, the flight maneuver led to a rounding trajectory which was quite large and less effective. This research discusses the effort in maximizing control technology to gain the minimum time in reaching target, which is by combining maneuver strategy and vehicle speed. The result is time reduction by 23.6% of the reaching target, from 427 secs to 326 secs for 4 way points. Also, a very smooth maneuver and speed control in every flight condition reduce energy use significantly. Moreover, the maneuver successfully reaches the target accurately with target missing range below 80 m.
The main purpose of this research is to control the Unmanned Vehicle System (UAS), using Hardware... more The main purpose of this research is to control the Unmanned Vehicle System (UAS), using Hardware in Loop Simulation (HILS) for flight stability, navigation and autopiloting as well. This research includes setting the software for flight simulator, completely integrating hardware (micro processor, IMU, actuator and telemetry) for an UAV, and constructing a mobile ground station. HILS in the research is also developed as a mean to verify the UAV design and its implementation for both wind tunnel test and the real flight test. Each setup in HILS is equipped with a remote control setting, utilized to drive three kinds of flaps (aileron, elevator and rudder) and serving as a switch from manual flight to auto stability flight. Vehicle attitude data can be stored simultaneously in a flash disk, functioning as a logger that is sent through telemetry. All results from the process can be monitored in real time through a ground station, with a display that enables the user to analyze the resu...
Ground control system (GCS) was developed as tools to analyze a special purpose high speed UAV th... more Ground control system (GCS) was developed as tools to analyze a special purpose high speed UAV that capable of flying up to a minimum speed of 300 km/h, and this speed will continue to be improved for the next project. Using Hardware in the Loop Simulation (HILS) method between XPlane flight simulator and Labview as programming tools, all of attitude conditions, position in Google map and health monitoring of UAV can be monitored. Including setting the PID control and way points for auto pilot system can also be set easily. Making it easier for the pilot or the researchers to directly analyzing the current condition of the UAV maneuvers. Since all parameters are displayed in a user friendly views. In Hardware in the Loop Simulation (HILS), data communication is done using UDP / User Datagram Protocol to ensure that the data transfer will not interfere with monitoring / analysis conducted by the researchers, because this GCS has been extremes tested using F22 Raptor fighter up to spe...
Ground control system (GCS) was developed as tools to analyze a special purpose high speed UAV th... more Ground control system (GCS) was developed as tools to analyze a special purpose high speed UAV that capable of flying up to a minimum speed of 300 km/h, and this speed will continue to be improved for the next project. Using Hardware in the Loop Simulation (HILS) method between XPlane flight simulator and Labview as programming tools, all of attitude conditions, position in Google map and health monitoring of UAV can be monitored. Including setting the PID control and way points for auto pilot system can also be set easily. Making it easier for the pilot or the researchers to directly analyzing the current condition of the UAV maneuvers. Since all parameters are displayed in a user friendly views. In Hardware in the Loop Simulation (HILS), data communication is done using UDP / User Datagram Protocol to ensure that the data transfer will not interfere with monitoring / analysis conducted by the researchers, because this GCS has been extremes tested using F22 Raptor fighter up to spe...
International Journal on Advanced Science, Engineering and Information Technology
Jurnal Teknologi Dirgantara, Sep 17, 2018
The flight test of LAPAN's rockets and high speed Unmanned Aerial Vehicles (UAV), need monitoring... more The flight test of LAPAN's rockets and high speed Unmanned Aerial Vehicles (UAV), need monitoring system track their position and attitude. The objective of the research is to develop mobile ground control and tracking antenna system to support the LAPAN's flight test monitoring system. The system was built by utilizing the currently available equipment components into a ground control station (GCS) equipped with GPS based auto tracking antenna. This ground control system is equipped with automatic tracking antenna that always poin to the vehicle, so that the flying vehicle's attitude data will be maximally monitored, and analyzed directly with ease. This system has been tested on a laboratory scale related to testing using hardware in the loop simulation system, and therefore has been proven to be better than the previous flight test ground station, which only has manual tracking antenna.
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Papers by Herma Yudhi Irwanto