• 제어로봇시스템학회:학술대회논문집
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• 1993.10b
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• pp.480-485
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• 1993

A method for obtaining optimal orbital maneuvers of a space vehicle has been developed by combining feedback linearization method with the elegance of the Lambert's theorem. To obtain solutions to nonlinear orbital maneuver problems. The full nonlinear equations of motion for space vehicle in polar coordinate system are transformed exactly into a controllable linear set in Brunovsky canonical form by using feedback linearization by choosing position vector as fully observable output vector. These equations are used to pose a linear optimal tracking problem with a solutions to Lambert's problem and a linear analytical solution of continuous low thrust problem as reference trajectories.

• Journal of Advanced Marine Engineering and Technology
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• v.10 no.3
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• pp.119-125
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• 1986

By using the least square input estimator and a likelihood ratio technique, an one-dimensional tracking problem is presented. A Kalman tracking filter based on constant-velocity model is used to track a target and the filtered estimate is updated with an input estimate when a maneuver is detected. The simulation results show that there are significant improvements using the scheme presented here.

• Journal of the Korean Society of Safety
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• v.14 no.4
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• pp.85-92
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• 1999

Vehicle rollover is an important issue for the traffic safety. Rollover can occur from the driver's action, the vehicle characteristics, or the road condition. This study is about the rollover propensity analysis of a jeep vehicle using the steering and braking maneuver, which is the combined result by the driver and the vehicle. Simple equations of roll motion is used to analyze the roll motion and a special purpose vehicle dynamics program is used to simulate the rollover of the jeep vehicle. From the simulation, an incipient rollover motion of the vehicle was found. However, the more complete rollover propensity analysis would require further investigation using roll dynamic sensitivity study.

• Bulletin of the Korean Space Science Society
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• 2004.04a
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• pp.60-60
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• 2004

인공위성 편대 비행은 하나의 대형 위성을 쏘아 올리는 것보다 비용면에서 절약효과를 볼 수 있을 뿐만 아니라 우주 공간상에서 간섭계의 구현이 가능하다는 장점이 있다. 우주 간섭계의 구현은 위성 편대의 재배치 기동(Reconfiguration maneuver)을 통하여, 원하는 관측대상으로의 지향을 자유로이 할 수 있으며, 기저선의 크기에 제약을 받지 않으므로 간섭계의 효과를 극대화시키는 것이 가능하다. (중략)

• 제어로봇시스템학회:학술대회논문집
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• 2005.06a
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• pp.979-984
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• 2005

In this study, we suggest a tilt rotor aircraft and attempt to apply a nonlinear model matching control method for its maneuver. The proposed method is very simple and useful to construct the control law for the complicated nonlinear system such as aircraft motion.

• The Transactions of the Korean Institute of Electrical Engineers
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• v.35 no.11
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• pp.519-528
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• 1986

By using a least-square input estimator and likelihood ratio technique, a tracking problem is presented. A Kalman tracking filter based on constant-velocity, straight-line model is used to track a target and the filtered estimate is updated using an input estimate when a maneuver is detected. Track residuals at each scan are sensed by a detector to guard against unexpected corrections of the filter. The simulation results show there are significant improvements using the scheme presented.

• 제어로봇시스템학회:학술대회논문집
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• 1995.10a
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• pp.376-379
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• 1995

To force an aircraft to track the specified path, the generation of the smooth desired trajectory is essential. In this paper, the cubic spline function is used to generate the trajectory which passes through the specified intercept points. The simulation results show that the desired trajectory generated by the spline interpolation is very smooth and the aircraft tracks it with small position errors.

• Journal of Astronomy and Space Sciences
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• v.17 no.2
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• pp.249-256
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• 2000

It has been developed to calculate fuel budget for a geostationary communication and broadcasting satellite. It is quite essential that the pre-launch fuel budget estimation must account for the deterministic transfer and drift orbit maneuver requirements. After on-station, the calculation of satellite lifetime should be based on the estimation of remaining fuel and assessment of actual performance. These estimations step from the proper algorithms to produce the prediction of satellite lifetime. This paper concentrates on the fuel estimation method that was studied for calculation of the propellant budget by using the given algorithms. Applications of this method are discussed for a communication and broadcasting satellite.

• Proceedings of the KIEE Conference
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• 2002.07d
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• pp.2659-2661
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• 2002

The development of guided missile requires complex guidance schemes and hardware units because of high maneuver, delicate and variable missions. In this point of view, simulation systems and facilities which test missile hardwares and softwares are needed. This paper introduces the hardware-in-the loop simulation system and facilities which include the real-time computation systems and 3 Axis FMS(Flight Motion Simulator).

• Bulletin of the Korean Space Science Society
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• 2004.10b
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• pp.101-101
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• 2004