• Nuclear Engineering and Technology
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• v.39 no.1
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• pp.63-74
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• 2007

In this paper, a reconfigurable controller consisting of a normal controller and a standby controller is designed to control the thermoelectric (TE) power in the SP-100 space reactor. The normal controller uses a model predictive control (MPC) method where the future TE power is predicted by using support vector regression. A genetic algorithm that can effectively accomplish multiple objectives is used to optimize the normal controller. The performance of the normal controller depends on the capability of predicting the future TE power. Therefore, if the prediction performance is degraded, the proportional-integral (PI) controller of the standby controller begins to work instead of the normal controller. Performance deterioration is detected by a sequential probability ratio test (SPRT). A lumped parameter simulation model of the SP-100 nuclear space reactor is used to verify the proposed reconfigurable controller. The results of numerical simulations to assess the performance of the proposed controller show that the TE generator power level controlled by the proposed reconfigurable controller could track the target power level effectively, satisfying all control constraints. Furthermore, the normal controller is automatically switched to the standby controller when the performance of the normal controller degrades.

• 한국HCI학회:학술대회논문집
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• 2009.02a
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• pp.855-861
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• 2009

This paper presents the concept of dynamically reconfigurable space by introducing smart building components. Thanks to the advances in ubiquitous computing and ITC technology, we are able to expect, in the near future, the aspects of future buildings which may transform their appearance and states to perform specific functions. In other words, it is certain that the building space will actively reconfigure itself to accommodate user's needs once we acquire proper technologies. Based on the assumption that building components may not be transformed through the magical process, but change its physical states (e.g. transparency, illumination, display contents, etc.) and functions of embedded devices (e.g. audio, actuators, sensors, etc.), we can envision a dynamically reconfigurable smart space. In order to conceptualize such spaces, critical surveys have been conducted on current works of leading architects. When the room needs to be used as a specific function room, the components need to change theirs states or to behave in a certain manner to create an optimum environment. Our model defines the relationships and elements to describe the mechanism of reconfigurable space. We expect this model provides a conceptual guideline for developing a smart building components based on spatial service scenarios. Therefore, a future smart spaces implemented by integrating various technologies are not designed in deterministic manner, so that spatial functions are expanded without constrained by physical existence.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.7
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• pp.660-665
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• 2011

Reconfigurable Flight Simulator for an airborne tactical mission based on virtual reality technology is developed as a software configurable cockpit with computer display as virtual instruments. It can simulate F-15K, KF-16, T/A-50 class fighter and depending on simulated cockpit, control stick and throttle are replaceable. For effective immersion, Video See-Through type HMD is applied.

• International Journal of Aeronautical and Space Sciences
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• v.18 no.2
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• pp.290-299
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• 2017

Reconfigurable flight control using various kinds of adaptive control methods has been studied since the 1970s to enhance the survivability of aircraft in case of severe in-flight failure. Early studies were mainly focused on the failure of actuators. Recently, studies of reconfigurable flight controls that can accommodate complex damage (partial wing and tail loss) in conventional aircraft were reported. However, the partial wing loss effects on the aerodynamics of conventional type aircraft are quite different to those of BWB(blended wing body) aircraft. In this paper, a reconfigurable flight control algorithm was designed using a direct model reference adaptive method to overcome the instability caused by a complex damage of a BWB aircraft. A model reference adaptive control was incorporated into the inner loop rate control system enhancing the performance of the baseline control to cope with abrupt loss of stability. Gains of the model reference adaptive control were polled out using the Liapunov's stability theorem. Outer loop attitude autopilot was designed to manage roll and pitch of the BWB UAV as well. A 6-DOF dynamic model was built-up, where the normal flight can be made to switch to the damaged state abruptly reflecting the possible real flight situation. 22% of right wing loss as well as 25% loss for both vertical tail and rudder control surface were considered in this study. Static aerodynamic coefficients were obtained via wind tunnel test. Numerical simulations were conducted to demonstrate the performance of the reconfigurable flight control system.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.3
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• pp.67-73
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• 2006

In this paper, a reconfigurable model following flight control method is proposed based on direct adaptive scheme using parameter estimation. Adaptive control scheme updates the control gains to make the system output follow the reference output even when fault occurs. By adopting the frequency domain parameter estimation method, system changes by the fault can be estimated. Recursive Fourier transformation is used for system identification. Using recursive Fourier transform, the proposed adaptive control algorithm guarantees the system stability and improves the system characteristics. To evaluate the performance of proposed control method, numerical simulations are performed.

• The KIPS Transactions:PartA
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• v.11A no.5
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• pp.303-312
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• 2004

In this paper, we propose a methodology solving the problem of the hardware-software partitioning in reconfigurable systems using a Y-chart design space exploration and implement a simulator according to the methodology. The methodology generates a mapping set between tasks and hardware elements using the hardware element model and the application model. We evaluate the throughput by simulating cases in each mapping set. With the throughput evaluation result, we can select the mapping case with the highest throughput. We also propose an heuristic improving the simulation time by reducing the mapping set on the basis of the relationship between workload and parallelism. Simulation results show that we can reduce the size of mapping set which poses difficulties on hardware-software partitioning by up to 80%.

• Proceedings of the IEEK Conference
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• 2002.07b
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• pp.924-927
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• 2002

In this paper we proposed the design space exploration environment of re-configurable hybrid systems and evaluate the performance by changing design parameters. With this, we analyzed the effect of various scheduling methods which determine how we allocate hardware/software resources to application program. A simple static (fixed) mapping strategy produces almost the same performance compared with a sophisticated dynamic mapping strategy especially when a CPU is already busy with its pre-assigned own tasks.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.7
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• pp.35-44
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• 2006

When control surface failure occurs, it is conventional to correct a current control or to transform to other control. In this paper, instead of adopting a conventional way, a reconfiguration method which compensate the failure with alternative control surface deflection, depending on the level of failure, by using neural network and PCH(Pseudo-Control Hedging). The Conroller is designed of inner-loop(SCAS : Stability Command Augmentation System) with DMI(Dynamic Model Inversion) and outer-loop with Y axis acceleration feedback for a coordinate turn. Additionally, double PCH method was adopted to prevent actuator saturation and input command was generated to compensate for failure. At the end, The feasibility of the method is validated with randomly selected failure scenarios.

• International Journal of Aeronautical and Space Sciences
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• v.4 no.1
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• pp.1-8
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• 2003

In this paper, a reconfigurable flight control system is designed by applying the sliding mode control scheme. The sliding mode control method is a nonlinear control method which has been widely used because of its merits such as robustness and flexibility. In the sliding mode controller design, the signum function is usually included, but it causes the undesirable chattering problem. The chattering phenomenon can be avoided by using the saturation function instead of signum function. However, the boundary layer of the sliding surface should be carefully treated because of the use of the saturation function. In contrast to the conventional approaches, the thickness of the boundary layer of our approach does not need to be small. The reachability to the boundary layer is guaranteed by the sliding mode controller. The fault detection and isolation process is operated based on a sliding mode observer. To evaluate the reconfiguration performance, a numerical simulation using six degree-of-freedom aircraft dynamics is performed.

• The Transactions of the Korea Information Processing Society
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• v.6 no.1
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• pp.66-74
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• 1999

A linear quadtree representation as a way to store a quadtree is efficient to save space compared with other representations. It , therefore, has been widely studied to develop efficient algorithms to execute operations related with quadtrees. In this paper, we present algorithm to find neighbor blocks of binary images represented by linear quadtrees, using three-dimensional n${\times}$n${\times}$n processors on RMESH(Reconfigurable MESH). Pur algorithm have O(1) time complexity.