Modelling and simulation of RKX200 rocket flight dynamics

Nurhafid, Alfi; Trilaksono, Bambang Riyanto; Sasongko, Rianto Adhy; Riyadl, Ahmad; Irwanto, Herma Yudhi

doi:10.1109/icici-bme.2013.6698498

Cited by 6 publications

(5 citation statements)

References 4 publications

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“…The family of UAV's linear model is derived using aerodynamic coefficients and equations described in [6]. All linear models derived in accordance to angle of attack and Mach parameters.…”

Section: Linear Modelmentioning

confidence: 99%

“…The autopilot gain value set is implemented using look-up table based on Mach speed and angle of attack. Stability of the system is inspected through a simulation using nonlinear model that has been developed in [6]. Autopilot system implemented using C-language code in MATLAB S-function module.…”

Section: Anti-windup Discretization and Time Delay Effectmentioning

confidence: 99%

“…This paper is a continuation of researches that discussed by [3] and [6]. By using the linear three-loop attitude design method described by [3], the method of gain-scheduling threeloop attitude autopilot design is discussed based on the UAV's model described in [6].…”

Section: Introductionmentioning

confidence: 99%

“…By using the linear three-loop attitude design method described by [3], the method of gain-scheduling threeloop attitude autopilot design is discussed based on the UAV's model described in [6]. The main contribution of this paper is to give an overview and additional references for readers who have an interest in gain-scheduling systems or three-loop attitude autopilot.…”

Section: Introductionmentioning

confidence: 99%

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Gain-scheduling design for three-loop attitude control system

Atman

Trilaksono

2014

2014 IEEE 4th International Conference on System Engineering and Technology (ICSET)

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This paper gives an overview of classical gainscheduling design applicable to three-loop attitude autopilot. Three-loop autopilot is a classic linear flight control scheme that is still being used nowadays. With the help of classical gainscheduling method it is expected that the implementation can help improve the response of the system. The scopes of this paper include design procedures and analysis from the model linear, design of linear autopilot, until the design of the gainscheduling autopilot. The addition of anti-windup and the effects of discretization and delay are also included in the discussion. The results showed that the designed gain scheduled autopilot is stable in nonlinear model testing and also in digital implementation and the effect of the delay.

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“…The family of UAV's linear model is derived using aerodynamic coefficients and equations described in [6]. All linear models derived in accordance to angle of attack and Mach parameters.…”

Section: Linear Modelmentioning

confidence: 99%

Section: Anti-windup Discretization and Time Delay Effectmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Gain-scheduling design for three-loop attitude control system

Atman

Trilaksono

2014

2014 IEEE 4th International Conference on System Engineering and Technology (ICSET)

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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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Comparison of Nonlinear and Linear Models’ Behaviour Regarding Rocket Stability

Miedziński

Głębocki

2022

Advances in Intelligent Systems and Computing

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Modelling and simulation of RKX200 rocket flight dynamics

Cited by 6 publications

References 4 publications

Gain-scheduling design for three-loop attitude control system

Gain-scheduling design for three-loop attitude control system

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

Comparison of Nonlinear and Linear Models’ Behaviour Regarding Rocket Stability

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