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RISS 인기검색어
- 검색키워드
- 저자 : Koichi Yonemoto (검색결과 6 건)
- 무료
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H<SUB>∞</SUB> Control of Winged Rocket and Its Flight Test
Koichi Yonemoto,Shigeru Kaji 제어로봇시스템학회 2009 제어로봇시스템학회 국제학술대회 논문집 Vol.2009 No.8
H∞ theory is one of the advanced design methodologies of attitude control law with robustness. There have been many application studies of H∞ theory on the actual flight vehicles, but the problem of insufficient performance of controllability and poor adaptability to flight environmental conditions such as dynamic pressure or flight Mach number have been always in questions. In addition to the design problem, the selection of weighting function for loop-shaping to achieve appropriate control with robustness and controllability by try and error requires and controllability by try and error requires the designers a lot of labor. This paper discusses the applicability of H∞ theory, which employs feed forward controller and dynamic pressure attenuator, to the design of the attitude control law of a small winged rocket developed by Kyushu Institute of Technology and its flight test.
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Experiment and Numerical Calculation on Air-Water Phased Propulsion Flow of Water Rocket
Koichi Yonemoto,Takehiro Himeno,Yusuke Oshikata 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
Water rocket is propelled by ejecting water using pressurized air. When the quantity of water decreases, the water and the air are ejected simultaneously in two phased flow. Experimental and numerical studies of this kind of air-water phased ejection are few .Therefore it is not yet completely clear about the flow and thrust generation characteristics. In this study, a measurement equipment was prepared to obtain the time history of air-water propulsive characteristics. Photos of air-water phased propulsion flow were also taken using a high-speed digital video camera to examine the thrust generation mechanism. A recent paper reported that a fully disturbed and mixed air-water phased flow is established at about 0.3 seconds after water ejection start. But the present experiment tells us that an air column grows from the upper surface of water to penetrate the nozzle flow. This air-water phased nozzle flow is not fully disturbed as reported previously, but is clearly separated into the air column flow and the cylindrical water flow. A whirl airflow may occur in a certain water amount and air pressure condition. Typical flow parameters are obtained to find that the air column penetrates faster than the water ejection. Numerical calculations are conducted to clarify the air-water phased flow characteristics. The growth of the air column is well simulated as the experiment.
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Hybrid Optimal Trajectory Generation Using Genetic Algorithm and Sequential Quadratic Programming
Koji Okuda,Koichi Yonemoto,Tomoki Akiyama 제어로봇시스템학회 2009 제어로봇시스템학회 국제학술대회 논문집 Vol.2009 No.8
The maximum performance is required for the space plane which will be realized in future. Thus, the efficient real-time calculation method for the trafectory optimization is required. The Space Systems Laboratory of Kyushu Institute of Technology has been studying the winged rocket development program as a research subject of fully reusable space transportation systems. This paper proposes an optimization trajectory method for winged rocket aiming at onboard real-time calculation. The present optimization employs a technique to solve the equations of motion directly with the control input function, which has variable coefficients for optimization. As the results, the optimization variables are reduced and the initial conditions are satisfied. GA(Genetic Algorithm) provides an initial solution of variable coefficients of the control input function for SQP(Sequential Quadratic Programming) method. This optimization algorithm using GA for initial solution and SQP for fine solution reduces the total calculation time and improves the accuracy.
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Trajectory Optimization of Winged Rocket Using GA/SQP Algorithm
Tomoki AKIYAMA,Koichi YONEMOTO 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
The maximum performance is required for the space plane which will be realized in future. Thus, the efficient real-time calculation method for the trajectory optimization is required. The Space Systems Laboratory of Kyushu Institute of Technology has been studying the winged rocket development program as a research subject of fully reusable space transportation systems. This paper proposes an optimization trajectory method for winged rocket aiming at onboard real-time calculation. The present optimization employs a technique to solve the equations of motion directly with the control input function. which has variable coefficients for optimization. As the results, the optimization variables are reduced and the initial conditions are satisfied. GA (Genetic Algorithm) provides an initial solution of variable coefficients of the control input function for SQP (Sequential Quadratic Programming) method. This optimization algorithm using GA for initial solution and SQP for fine solution reduces the total calculation time and improves the accuracy.
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Masaaki Murakami,Koichi Yonemoto,Takahiro Fujikawa 한국항공우주학회 2022 International Journal of Aeronautical and Space Sc Vol.23 No.4
To achieve high-range capability, reusability, and aircraft-like operability in spaceplanes, the latter have been investigated actively. One of the critical technologies for spaceplanes is the flexible guidance methodology, which can accommodate various mission requirements and constraints. The application of an evolutionary algorithm to the real-time optimization of longitudinal ascent guidance trajectories is presented herein. The combination of the engine gimbal and aerodynamic control surfaces is considered to improve the design flexibility of the trajectories and mitigate the elevator hinge moment. The range of guidance commands for the engine gimbal angle and the angle of attack that satisfy the longitudinal trim condition are identified in advance and stored as tabular data. The performance of the proposed guidance algorithm is evaluated via a flight simulation of a subscale flight demonstrator.
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Experimental Flight of KIT Student’s Rocket in France
Koji Okuda,Yuji Ujimoto,Yuta Otsuka,Takaya Sato,Takuya Shidooka,Daijiro Semba,Kenichi Tominaga,Junichi Fukuda,Yuta Yamamoto,Kazuki Wada,Shinichi Sagara,Koichi Yonemoto 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
KIT Student's Rocket has been developed by a student group of Kyushu Institute of Technology lor rocket launch campaign held at La Courtine in France since 2006. This paper introduces the newest design of rocket. The rocket has the body length of 2120㎜, and weighs 14.6㎏ and can reach to an altitude of about 700㎜ by a solid rocket motor provided by CNES (the French Centre National D’Etudes Spatiales). The rocket is controlling rolling attitude during ascent phase and then deploying a parafoil at the apogee of the trajectory for recovery guidance to an aiming point.
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