yuzo shimada - Academia.edu (original) (raw)

Papers by yuzo shimada

Paper on target proximity and obstacle avoidance for the altitude control of spacecraft using pot... more Paper on target proximity and obstacle avoidance for the altitude control of spacecraft using potential function guidance methods.

한국항공우주학회 학술발표회 논문집, Nov 1, 2008

This is a preliminary report about our plan for a special-purpose flight simulator. The human-pow... more This is a preliminary report about our plan for a special-purpose flight simulator. The human-powered aircraft developed in Nihon University has achieved the Japanese flight distance record of 49.2 km in 2005. However, this Japanese record is still half the distance of the world record of 115.1 km that Massachusetts Institute of Technology achieved in 1988. Thus, the present goal for the development group of our university students is to break this world record. For this purpose, a research group for a human-powered flight support system was established to develop a special-purpose flight simulator for human-powered flight. The purpose of designing such a simulator is to provide the student pilot with a scientific and practical training facility and to feed the flight data and design factors back into an optimal design of the human-powered aircraft. That is, the simulator would be used to search for an optimal flight path planning, optimal power time-distribution program for the pilot, and the optimal configuration of the aircraft. To find the optimal flight path and optimal power distribution, an appropriate mathematical model for the pilot as a man-powered engine must also be analyzed and determined as well as a conventional pilot model in handling the control stick. The developed simulator would also be used to compare an ordinary student pilot with an athlete pilot. More details would be presented at the conference

제어로봇시스템학회 국제학술대회 논문집, Oct 1, 2003

The SICE Annual Conference 2013, 2013

In this paper, we present a fault-tolerant actuator control system with redundancy for a future s... more In this paper, we present a fault-tolerant actuator control system with redundancy for a future spaceplane. The control system based on model reference adaptive control is designed to maintain the control effects with respect to the vehicle rotational motion, even if some of the actuators develop problems or break down. A hardware-in-the-loop simulation involving real DC servo motors was carried out to show the effectiveness of the proposed system.

The Sice Annual Conference 2013, Sep 1, 2013

In this paper, we present a fault-tolerant actuator control system with redundancy for a future s... more In this paper, we present a fault-tolerant actuator control system with redundancy for a future spaceplane. The control system based on model reference adaptive control is designed to maintain the control effects with respect to the vehicle rotational motion, even if some of the actuators develop problems or break down. A hardware-in-the-loop simulation involving real DC servo motors was carried out to show the effectiveness of the proposed system.

Space Technology and Science, 1990

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2005

An optimal guidance law derived by solving the minimum-acceleration problem has been reported for... more An optimal guidance law derived by solving the minimum-acceleration problem has been reported for control of a lunar lander. In our past work, the guidance law was proved to enable vertical/soft landing. However, it was not robust against disturbance because there was a constraint condition relative to initial conditions in order to satisfy optimality. Therefore, if the constraint is not satisfied, the lunar lander must be controlled to track the reference trajectory generated by the optimal guidance law in order to be robust against disturbance. The control system makes the landing system complex and fuel consumption is increased in comparison to a guidance law without tracking control. Consequently, this study restructures the optimal control problem as a minimum-jerk problem to solve it. Jerk is a physical quantity defined as the time derivative of acceleration. The new optimal guidance law obtained has no constraints on the initial conditions. The results of computer simulation confirm the usefulness of the proposed guidance law.

In this paper, we present a new guidance law for a reusable launch vehicle (RLV) that lands verti... more In this paper, we present a new guidance law for a reusable launch vehicle (RLV) that lands vertically after reentry. In our past studies, a guidance law was developed for a vertical/soft landing to a target point. The guidance law, which is analytically obtained, can regenerate a trajectory against disturbances because it is expressed in the form of state feedback. However, the guidance law does not necessarily guarantee a vertical/soft landing when a dynamical system such as an RLV includes a nonlinear phenomenon owing to the atmosphere of the earth. In this study, we introduce a design of the guidance law for a nonlinear system to achieve a vertical/soft landing on the ground using the exact linearization method and solving the two-point boundary-value problem for the derived linear system. Numerical simulation confirmed the validity of the proposed guidance law for an RLV in an atmospheric environment.

The Proceedings of the Transportation and Logistics Conference, 2001

2007 International Conference on Control, Automation and Systems, 2007

We describe the application of model predictive control (MPC) using state mapping to the automati... more We describe the application of model predictive control (MPC) using state mapping to the automatic landing system of a spaceplane. The controller has to be designed to enable the vehicle to follow reference signals with respect to trajectory and velocity, which are expressed as functions of the downrange. To track the reference signals, a control input is generally designed so that one or more ideal transient responses are realized. We also have developed a flight control system based on this concept. However, it was not satisfactory for use as the controller of an actual vehicle due to the lack of consideration of the input and state constraints. A controller that considers these constraints can be designed by applying MPC. On the other hand, it is difficult to predefine the transient responses necessary to track the reference signals, which vary with the current downrange. In this paper, a new approach using state mapping and feedback linearization is proposed to improve the control performance of tracking the reference signals. State mapping is derived to describe a system in which the reference signals can be handled as a constant set point, and the described system is linearized using state feedback. The proposed system is applied to the Japanese automatic landing flight experiment (ALFLEX) vehicle. A numerical simulation is performed to verify the validity of the proposed method based on MPC.

2007 International Conference on Control, Automation and Systems, 2007

The formulation of an adaptive attitude control law with reduced number of estimated parameters i... more The formulation of an adaptive attitude control law with reduced number of estimated parameters is introduced for the automatic landing system of a spaceplane. Adaptive attitude control systems have been designed to obtain the control law by estimating the parameters that describe the dynamics of the vehicle and actuator. Despite the fact that the vehicle was well controlled so as

Paper on target proximity and obstacle avoidance for the altitude control of spacecraft using pot... more Paper on target proximity and obstacle avoidance for the altitude control of spacecraft using potential function guidance methods.

한국항공우주학회 학술발표회 논문집, Nov 1, 2008

This is a preliminary report about our plan for a special-purpose flight simulator. The human-pow... more This is a preliminary report about our plan for a special-purpose flight simulator. The human-powered aircraft developed in Nihon University has achieved the Japanese flight distance record of 49.2 km in 2005. However, this Japanese record is still half the distance of the world record of 115.1 km that Massachusetts Institute of Technology achieved in 1988. Thus, the present goal for the development group of our university students is to break this world record. For this purpose, a research group for a human-powered flight support system was established to develop a special-purpose flight simulator for human-powered flight. The purpose of designing such a simulator is to provide the student pilot with a scientific and practical training facility and to feed the flight data and design factors back into an optimal design of the human-powered aircraft. That is, the simulator would be used to search for an optimal flight path planning, optimal power time-distribution program for the pilot, and the optimal configuration of the aircraft. To find the optimal flight path and optimal power distribution, an appropriate mathematical model for the pilot as a man-powered engine must also be analyzed and determined as well as a conventional pilot model in handling the control stick. The developed simulator would also be used to compare an ordinary student pilot with an athlete pilot. More details would be presented at the conference

제어로봇시스템학회 국제학술대회 논문집, Oct 1, 2003

The SICE Annual Conference 2013, 2013

In this paper, we present a fault-tolerant actuator control system with redundancy for a future s... more In this paper, we present a fault-tolerant actuator control system with redundancy for a future spaceplane. The control system based on model reference adaptive control is designed to maintain the control effects with respect to the vehicle rotational motion, even if some of the actuators develop problems or break down. A hardware-in-the-loop simulation involving real DC servo motors was carried out to show the effectiveness of the proposed system.

The Sice Annual Conference 2013, Sep 1, 2013

In this paper, we present a fault-tolerant actuator control system with redundancy for a future s... more In this paper, we present a fault-tolerant actuator control system with redundancy for a future spaceplane. The control system based on model reference adaptive control is designed to maintain the control effects with respect to the vehicle rotational motion, even if some of the actuators develop problems or break down. A hardware-in-the-loop simulation involving real DC servo motors was carried out to show the effectiveness of the proposed system.

Space Technology and Science, 1990

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 2005

An optimal guidance law derived by solving the minimum-acceleration problem has been reported for... more An optimal guidance law derived by solving the minimum-acceleration problem has been reported for control of a lunar lander. In our past work, the guidance law was proved to enable vertical/soft landing. However, it was not robust against disturbance because there was a constraint condition relative to initial conditions in order to satisfy optimality. Therefore, if the constraint is not satisfied, the lunar lander must be controlled to track the reference trajectory generated by the optimal guidance law in order to be robust against disturbance. The control system makes the landing system complex and fuel consumption is increased in comparison to a guidance law without tracking control. Consequently, this study restructures the optimal control problem as a minimum-jerk problem to solve it. Jerk is a physical quantity defined as the time derivative of acceleration. The new optimal guidance law obtained has no constraints on the initial conditions. The results of computer simulation confirm the usefulness of the proposed guidance law.

In this paper, we present a new guidance law for a reusable launch vehicle (RLV) that lands verti... more In this paper, we present a new guidance law for a reusable launch vehicle (RLV) that lands vertically after reentry. In our past studies, a guidance law was developed for a vertical/soft landing to a target point. The guidance law, which is analytically obtained, can regenerate a trajectory against disturbances because it is expressed in the form of state feedback. However, the guidance law does not necessarily guarantee a vertical/soft landing when a dynamical system such as an RLV includes a nonlinear phenomenon owing to the atmosphere of the earth. In this study, we introduce a design of the guidance law for a nonlinear system to achieve a vertical/soft landing on the ground using the exact linearization method and solving the two-point boundary-value problem for the derived linear system. Numerical simulation confirmed the validity of the proposed guidance law for an RLV in an atmospheric environment.

The Proceedings of the Transportation and Logistics Conference, 2001

2007 International Conference on Control, Automation and Systems, 2007

We describe the application of model predictive control (MPC) using state mapping to the automati... more We describe the application of model predictive control (MPC) using state mapping to the automatic landing system of a spaceplane. The controller has to be designed to enable the vehicle to follow reference signals with respect to trajectory and velocity, which are expressed as functions of the downrange. To track the reference signals, a control input is generally designed so that one or more ideal transient responses are realized. We also have developed a flight control system based on this concept. However, it was not satisfactory for use as the controller of an actual vehicle due to the lack of consideration of the input and state constraints. A controller that considers these constraints can be designed by applying MPC. On the other hand, it is difficult to predefine the transient responses necessary to track the reference signals, which vary with the current downrange. In this paper, a new approach using state mapping and feedback linearization is proposed to improve the control performance of tracking the reference signals. State mapping is derived to describe a system in which the reference signals can be handled as a constant set point, and the described system is linearized using state feedback. The proposed system is applied to the Japanese automatic landing flight experiment (ALFLEX) vehicle. A numerical simulation is performed to verify the validity of the proposed method based on MPC.

2007 International Conference on Control, Automation and Systems, 2007

The formulation of an adaptive attitude control law with reduced number of estimated parameters i... more The formulation of an adaptive attitude control law with reduced number of estimated parameters is introduced for the automatic landing system of a spaceplane. Adaptive attitude control systems have been designed to obtain the control law by estimating the parameters that describe the dynamics of the vehicle and actuator. Despite the fact that the vehicle was well controlled so as