• Journal of Astronomy and Space Sciences
• /
• v.25 no.4
• /
• pp.347-360
• /
• 2008

In this paper, a Hardware-In-the-Loop simulator to simulate attitude control of space craft using momentum wheels is developed. The simulator consists of a spherical air bearing system allowing rotation and tilt in all three axes, three momentum wheels for actuation, and an AHRS (Attitude Heading Reference System). The simulator processes various types of data in PC104 and wirelessly communicates with a host PC using TCP/IP protocol. A simple low-cost momentum wheel assembly set and its drive electronics are also developed. Several experiments are performed to test the performance of the momentum wheels. For the control performance test of the simulator, a PID controller is implemented. The results of experimental demonstrations confirm the feasibility and validity of the Hardware-In-the-Loop simulator developed in the current study.

• Advances in Automotive Engineering
• /
• v.1 no.1
• /
• pp.123-141
• /
• 2018

Hardware-in-the-loop (HiL) simulation is a very powerful tool to design, test and verify automotive control systems. However, well-validated and high degree of freedom vehicle models have to be utilized in these simulations in order to obtain realistic results. In this paper, a vehicle dynamics model developed in the Carsim Real Time program environment and its validation has been performed using experimental results. The developed Carsim real time model has been employed in the Tofas R&D hardware-in-the-loop simulator. Experimental and hardware-in-the-loop simulation results have been compared for the standard FMVSS No. 126 test and the results have been found to be in good agreement with each other. Two electronic stability control (ESC) algorithms, named the Basic ESC and the Integrated ESC, taken from the earlier work of the authors have been tested and evaluated in the hardware-in-the-loop simulator. Different evaluation methods have been formulated and used to compare these ESC algorithms. As a result, the Integrated ESC system has been shown superior performance as compared to the Basic ESC algorithm.

• 제어로봇시스템학회:학술대회논문집
• /
• 1997.10a
• /
• pp.1334-1337
• /
• 1997

A spacecraft attitude control ground hardware simulator development is discussed in the paper. The simulator is called KT/KARI HILSSAT(Hardware-In-the Loop Simulator Single Axis Testbed), and the main structure consists of a single axis bearing and a satellite main body model on the bearing. The single axis tabel as ans experimental hardware simulator that evaluates performance and applicability of a satellite before evolving and/or confirming a mew or and old control logic used in the KOREASAT is developed. Attitude control of spaceraft by using reaction wheel is performed.

• Proceedings of the KIEE Conference
• /
• summer
• /
• pp.117-119
• /
• 2004

An optimal flight motion simulator path generation method is proposed for hardware in the loop simulation of high maneuverable missile. The proposed method consists of open loop and closed loop path calculation algorithm based on the energy optimal control strategies. The optimal angle command is able to protect the simulator from high acceleration shock at initial control phase.

• Transactions of the Korean Society of Automotive Engineers
• /
• v.6 no.2
• /
• pp.155-167
• /
• 1998

The prevalence of microprocessor-based controllers in automotive systems has greatly increased the meed for tools which can be used to validate and test control systems over their full range of operation. The objective of this paper is to develop a real time simulator of an anti-lock braking system and the methodology of using hardware-in-the-loop simulation based on a personal computer. By use of this simulator, the analyses of a commercial electronic control unit as well as the validation of the developed control logics for ABS were performed successfully. The simulator of this research can be traction applied to development of more advanced control system, such as traction control systems, vehicle dynamic control system and so forth.

• Journal of the Korean Society for Precision Engineering
• /
• v.16 no.5 s.98
• /
• pp.83-90
• /
• 1999

The prevalence of microprocessor-based controllers in automotive system has greatly increased the need for tools which can be used to validate and test control system over their full range of operation. The objective of this paper is to develop a real time simulator of an anti-lock braking system and traction control system by the methodology of using hardware-in-the-loop simulation based on a personal computer. By use of this simulator, the analyses of commercial electronic control units and components for ABS/TCS were performed successfully. The simulator of this research can be applied to development of more advanced control system(such as vehicle dynamic control system) and other automotive system.

• Transactions of the Korean Society of Automotive Engineers
• /
• v.7 no.5
• /
• pp.194-205
• /
• 1999

The prevalence of microprocessor-based controllers in automotive systems has greatly increased the need for tools which can be used to validate and test control systems over their full range of operation. The objective of this paper is to develop a real time simulator of traction control system by the methodology of using hardware-in-loop simulation based on a personal computer. By use of this simulator, the analysis of commercial electronic control units and components for TCS were performed successfully. The simulator of this research can be applied to development of more advanced control systems(suck as vehicle dynamics control system) and other automotive system.

• Journal of Astronomy and Space Sciences
• /
• v.26 no.1
• /
• pp.47-58
• /
• 2009

In this study, a Hardware-In-the-Loop (HIL) simulator using thrusters is developed to validate the spacecraft attitude system. To control the attitude of the simulator, eight cold gas thrusters are aligned with roll, pitch and yaw axis. Also linear actuators are applied to the HIL simulator for automatic mass balancing to compensate the center of mass offset from the center of rotation. The HIL simulator consists of an embedded computer (Onboard PC) for simulator system control, a wireless adapter for wireless network, a rate gyro sensor to measure 3-axis attitude of the simulator, an inclinometer to measure horizontal attitude, and a battery set to supply power for the simulator independently. For the performance test of the HIL simulator, a bang-bang controller and Pulse-Width Pulse-Frequency (PWPF) modulator are evaluated successfully. The maneuver of 68 deg. in yaw axis is tested for the comparison of the both controllers. The settling time of the bang -bang controller is faster than that of the PWPF modulator by six seconds in the experiment. The required fuel of the PWPF modulator is used as much as 51% of bang-bang controller in the experiment. Overall, the HIL simulator is appropriately developed to validate the control algorithms using thrusters.

• ICROS
• /
• v.7 no.6
• /
• pp.26-31
• /
• 2001

• Proceedings of the Korean Nuclear Society Conference
• /
• 1999.05a
• /
• pp.222-222
• /
• 1999