Development of hardware-in-the-loop simultion for rocket guidance system

Hadi, Yulyan Wahyu; Trilaksono, Bambang Riyanto

doi:10.1109/iceei.2015.7352502

Cited by 2 publications

(2 citation statements)

References 6 publications

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“…One of these control problems is the control of guided missiles; where the aerodynamics flight parameters are continuously changing. There are many researches done using robust control techniques, H-infinity control and robust control (Lungu and Lungu, 2014;Hui et al, 2014;Kaur and Ohri, 2014;Roy and Barai, 2013;Ouda, 2017), nominal operating point selection (Schultz et al, 2016), and hardware-in-the-loop (Hadi and Bambang, 2015;Hashemi and Montazeri, 2014;Louali et al, 2017) in order to enhance the performance of the guided missile system for example. Mohammadi et al (2016) investigated an independent design for a roll channel autopilot in order to eliminate the effects of the induced and control cross coupling roll moments.…”

Section: Introductionmentioning

confidence: 99%

Nominal model selection and guidance computer design for antitank guided missile

Ouda

Sheikh

Elhalwagy

et al. 2019

IJAAC

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The great developments in applied mathematics and computational capabilities facilitate the design and implementation of robust control. Among the real applications are the guided missiles especially the antitank guided missile systems which are commanded to the line of sight (CLOS) against ground and short-range targets. The present work is concerned with improving the performance of an antitank guided missile system belonging to the first generation via robust synthesis of guidance systems. The selection of nominal model is required to design the guidance computer for the system. This paper is devoted to the quantitative analysis to select a nominal plant which used to design a guidance computer that has a successful flight path trajectory against different types of uncertainties. The design and analysis necessitate somehow accurate model with different uncertainties for the system. The flight path is evaluated considering the HIL environment.

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Section: Introductionmentioning

confidence: 99%

Nominal model selection and guidance computer design for antitank guided missile

Ouda

Sheikh

Elhalwagy

et al. 2019

IJAAC

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“…It also does not need a large memory capacity to store the program code. Moreover, most of the HILS use integrated hardware and software system which is not an open source, not a re-programmable nor having non-free license [8,9,10].…”

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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Development of hardware-in-the-loop simultion for rocket guidance system

Cited by 2 publications

References 6 publications

Nominal model selection and guidance computer design for antitank guided missile

Nominal model selection and guidance computer design for antitank guided missile

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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