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Seiya Ueno,Ryuichi Watanabe 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
This paper treats with the calculation procedure of reference trajectory to be applied to emergency guidance and control law for future reusable space transportation systems, such as spaceplane. The reusable transportation system is required to return to the landing area safely even if unexpected malfunction causes and the mission is aborted. Low computational load is necessary lor the emergency guidance law because reference trajectory must be calculated through an onboard computer within a short time. And also the reference trajectory is required to be followed by a spaceplane with low performance in maneuver. Thus it is desired that the reference trajectory is provided as a solution of minimum curvature problem, which is an optimal control problem. This paper proposes the calculation procedure of optimal control problem without iterative calculation. Homotopy method is applied to solve optimal control problems. Numerical results show that calculation of define integral provides three dimensional optimal trajectory.
Real-Time Guidance Law for Quasi-Minimum Time Maneuver for a Missile
Seiya Ueno,Seiji Yamaoka 제어로봇시스템학회 2009 제어로봇시스템학회 국제학술대회 논문집 Vol.2009 No.8
Minimum time guidance is often required to real systems. However, optimal control problem is not solved inthe guidance system because of computational load. This paper proposed one design procedure for minimum time guidance law using multiple design points. The results show that the guidance law satisfies the design criteria, but the guidance law is solution at a local minimum point. The improvement on design criteria is necessary.
Minimum-Time Guidance and Control Law for High Maneuvering Missile
Seiji Yamaoka,Seiya Ueno 한국항공우주학회 2009 International Journal of Aeronautical and Space Sc Vol.10 No.1
This paper deals with design procedure of online guidance and control law for future missiles that requires agile maneuverability. For the purpose, the missile with high powered side thruster is proposed. The guidance and control law for such missiles is discussed from a point of view of optimal control theory in this paper. Minimum time problem is solved for the approximated system. It is derived that bang-bang control is optimal input from the necessary conditions of optimal solution. Feedback guidance without iterative calculation is useful for actual systems. In this paper, multiple design point method is applied to design feedback gains and feed forward inputs of the guidance and control law. The numerical results show that the proposed guidance and control law has a high-performance for wide-ranging boundary conditions.
Conflicts of Collision Avoidance Control Law for Aircrafts with Time Delay
Takehiro Higuchi,Seiya Ueno 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
This paper is on collision avoidance control law for aircrafts with time delay. Conventional traffic alert and collision avoidance system only give the pilot idea to avoid in vertical direction. This paper expands the avoidance control system lor the full automated avoidance for actual use in aviation. Based on the fuzzy based collision avoidance control Jaw introduced in previous study, this paper loads the control law for both aircraft approaching and seeks the problem including the time delay. The results show that the ability of the control law lowers when the time delay is occurred. The problem of this time delay can be improved by configuring the membership functions according to the value of time delay where they call be obtained by the set or data showing when the information is obtained and the present time.
Study on Minimum Time Maneuver Problem for High Maneuvering Missile
Seiji Yamaoka,Seiya Ueno 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
the authors have been studying an application of Multidisciplinary Design Optimization (MDO) to the future missiles. For the purpose, a new design procedure on guidance and control system is proposed in this paper. For the future missiles, high maneuvering and high responsiveness are required. Then, the authors have been studying on guidance and control system design of the missile that uses the useful side thruster method for the high maneuvering and high responsiveness in the future missile. The side thruster method has an independent gas generator. The maximum thrust does not depend on dynamic pressure and is enabled even in the low-speed region immediately after launching or the high altitude area. It is expected that this method is useful in high maneuvering and high responsiveness in the future missiles. It is assumed that the side thruster device can change the amplitude of thrust continuously in this paper. In our previous studies, we solved the minimum time problem with the open loop and calculated optimal solution. The optimum thrust is no bang-bang control, but intermediate value is also used. The numerical results verified the usefulness. In this paper, we propose the closed-loop control system which is calculated inputs in real time due to aim toward the guidance and control system of more realistic missiles, verified by simulation.
Naoya Kataoka,Shota Yoshida,Seiya Ueno,Takashi Minemoto 한국물리학회 2014 Current Applied Physics Vol.14 No.5
The output energy of photovoltaic (PV) modules under outdoor conditions is greatly influenced by the spectral irradiance distribution of the solar spectrum. To analyze this effect on PV modules, the spectral irradiance distribution, which is one-dimensional data, has to be represented by a zero-dimensional index. The average photon energy (APE) is an index for spectral irradiance distributions, which represents the average energy per photon in a spectrum. We have previously analyzed the uniqueness of the shape of the solar spectrum in the wavelength range of 350e1050 nm, and one corresponding value of APE showed a specific shape of spectral irradiance distribution. In this study, new indexes were calculated for a limited wavelength range of 350e750 nm and multiple bands of 450e500 nm and 800 e850 nm of the solar spectrum for easy measurement and calculation. The result shows the uniqueness of new indexes to the shape of measured solar spectrum and the standard deviations were found to be quite small. This indicates that the new indexes are reasonable for representing the spectral irradiance distribution and its effect on PV performance.