• 대한기계학회:학술대회논문집
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• 대한기계학회 2003년도 추계학술대회
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• pp.1578-1583
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• 2003

Time-Optimal solutions for attitude control with reaction wheels as well as with thrusters are studied. The suggested varying-time-sharing ratio thrusting is found to reduce the maneuvering time enormously. The hybrid control such as sequential hybrid and simultaneous hybrid with reaction wheels and thrusters are considered. The results show that simultaneous hybrid method reduces the maneuver time very much. Spacecraft model is KOrea Multi-Purpose SATellite(KOMPSAT)-II, which is being developed by KARI in KOREA as an agile maneuvering satellite.

• Journal of Mechanical Science and Technology
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• 제19권9호
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• pp.1695-1705
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• 2005

Reaction wheels and thrusters are commonly used for the satellite attitude control. Since satellites frequently need fast maneuvers, the minimum time maneuvers have been extensively studied. When the speed of attitude maneuver is restricted due to the wheel torque capacity of low level, the combinational use of wheel and thruster is considered. In this paper, minimum time optimal control performances with reaction wheels and thrusters are studied. We first identify the features of the maneuvers of the satellite with reaction wheels only. It is shown that the time-optimal maneuver for the satellite with four reaction wheels in a pyramid configuration occurs on the fashion of single axis rotation. Pseudo control logic for reaction wheels is successfully adopted for smooth and chattering-free time-optimal maneuvers. Secondly, two different thrusting logics for satellite time-optimal attitude maneuver are compared with each other: constant time-sharing thrusting logic and varying time-sharing thrusting logic. The newly suggested varying time-sharing thrusting logic is found to reduce the maneuvering time dramatically. Finally, the hybrid control with reaction wheels and thrusters are considered. The simulation results show that the simultaneous actuation of reaction wheels and thrusters with varying time-sharing logic reduces the maneuvering time enormously. Spacecraft model is Korea Multi-Purpose Satellite (KOMPSAT)-2 which is being developed in Korea as an agile maneuvering satellite.

• 제어로봇시스템학회논문지
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• 제17권7호
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• pp.704-713
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• 2011

For many years, many pilots lost their lives and aircrafts due to GLOC(Gravity-induced Loss Of Consciousness). Due to the emergence of high-gravity maneuvering aircraft such as the F-16, F-15 and T-50, the automatic GLOC detection and recovery systems are necessary to increase the aircraft safeties even when the pilot loses his consciousness due to high-G maneuvering. This paper addresses the design of GLOC detection, warning and recovery algorithm based on a model of supersonic jet trainer. The system is solely controlled by the pilot's control input (i.e., control stick force) and aircraft status such as attitude, airspeed, altitude and so forth. And, moreover, it does not depend upon any pilot physiological condition. The test evaluation results show that the developed system supports the recovery of an aircraft from the unusual aircraft attitude and improves the aircraft safeties even when the pilot loses his consciousness due to high-G maneuvering.

• 한국항해항만학회지
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• 제40권5호
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• pp.231-239
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• 2016

In general, the attitude of a high-speed planning boat changes following a speed change. Since the hydrodynamic forces acting on a ship differ according to the change of its underwater shape, it is difficult to estimate its hydrodynamic force compared to that of a large commercial ship. In this paper, 6 Degrees Of Freedom (DOF) equations of motion that express the maneuvering motion of a planning boat are modeled by analyzing its motion characteristics based on various sea trial tests. Finally, a maneuvering simulation is carried out and a validation of the equations of motion is confirmed with the results of sea trial tests.

• 항공우주시스템공학회지
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• 제13권3호
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• pp.23-31
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• 2019

현대의 위성들의 설계요구조건은 운용되는 목적에 따라 다양해진다. 기존 중/대형 위성과는 달리 저궤도에서 운용되는 소형위성의 경우 군사적인 목적을 나타내기도 한다. 그렇기 때문에 고해상도의 사진 및 영상 수요가 증가하며 다표적 관측이 중요하게 된다. 이에 다표적 관측을 하기 위해서 위성의 기동성은 중요한 설계변수이다. 기동성이 증가하기 위해서 소형화가 되면 전체 질량관성모멘트가 감소하기 때문에 위성의 강성을 높여야한다. 본체에 비해서 강성이 낮은 태양전지판의 경우 진동이 발생하기 때문에 영상획득에 큰 영향을 미친다. 이러한 진동특성을 확인하기 위하여 본 연구에서는 위성을 축소모델로 제작하여 자세기동을 모사하기 위한 실험 치구를 도입하였고, 위성의 강성을 모사하기 위한 모사장치를 제시하였다. 또한 실험방식은 스텝모터를 이용하여 와이어의 감는 길이에 따라 위성의 기동각을 모사하였으며, 기동실험 시 발생되는 위성의 본체 및 태양전지판에 대하여 진동특성을 실험적으로 검증하고자 한다.

• 한국군사과학기술학회지
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• 제12권1호
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• pp.44-50
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• 2009

In this study, the relationship between military pilot's spatial ability and unusual attitude recovery was investigate. MRT(Mental Rotation Test) was measured with spatial ability whereas recovery time and error rates were mearsured with respect to 11 unusual attitudes. Eight fighter pilots and eight rear cockpit pilots of F-4E participated in this study. The results showed that MRT response time was significantly correlated with unusual attitude recovery time. The regression equation showed that unusual attitude recovery time was linearly related to MRT response time and could be explained by MRT response time more than 66%. In conclusion, it is recommended that a training is needed to improve the mental rotation ability in a visually restricted environments during maneuvering.

• 항공우주기술
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• 제1권1호
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• pp.65-71
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• 2002

다목적 실용위성의 자세제어계 mode는 크게 Sun, Maneuver, Science Mode로 나누어진다. 이중 Manuever Mode는 다시 Attitude Hold submode 와 Δ-V Burn submode로 나누어진다. 본 논문은 지상으로 송신된 playback 데이터를 이용하여 자세제어계 Maneuver Mode의 동작상태를 주로 분석하였다. Maneuver Mode중 attitude hold submode에서의 nadir pointing performance, 그리고 Δ-V Burn submode에서의 pitch/ roll 90도 maneuver 후 추력기 점화 과정에 대한 성능 분석을 수행하였으며 자세제어계 서브시스템 설계 규격을 만족함을 검증하였다.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2001년도 ICCAS
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• pp.141.6-141
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• 2001

This paper presents the attitude algorithm using Fuzzy technique to mix gyro information with accelerometer. The attitude angle calculated by the low-cost gyros only increases its error with time rapidly because of the integration process of the algorithm and large sensor error. It is known that the accelerometer output includes the attitude information of a vehicle and its information is more effective during low dynamic maneuver. Therefore it is needed to combine two information appropriately for obtaining the attitude information from low-cost MEMS inertial sensors. Because Fuzzy logic is very effective to make a decision of maneuvering state, it is applied to the mixed algorithm. It is shown by experiment ...

• 한국인공지능학회지
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• 제12권3호
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• pp.9-15
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• 2024

This paper addresses the critical need for quadcopters in GPS-denied indoor environments by proposing a novel attitude control mechanism that enables autonomous navigation without external guidance. Utilizing AR marker detection integrated with a dual PID controller algorithm, this system ensures accurate maneuvering and positioning of the quadcopter by compensating for the absence of GPS, a common limitation in indoor settings. This capability is paramount in environments where traditional navigation aids are ineffective, necessitating the use of quadcopters equipped with advanced sensors and control systems. The actual position and location of the quadcopter is achieved by AR marker detection technique with the image processing system. Moreover, in order to enhance the reliability of the attitude PID control, the dual closed loop control feedback PID control with dual update periods is suggested. With AR marker detection technique and autonomous attitude control, the proposed quadcopter system decreases the need of additional sensor and manual manipulation. The experimental results are demonstrated that the quadrotor's autonomous attitude control and operation with the dual closed loop control feedback PID controller with hierarchical (inner-loop and outer-loop) command update period is successfully performed under the non-GPS aided indoor environment and it enhanced the reliability of the attitude and the position PID controllers within 17 seconds. Therefore, it is concluded that the proposed attitude control mechanism is very suitable to GPS-denied indoor environments, which enables a quadcopter to autonomously navigate and hover without external guidance or control.

• 우주기술과 응용
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• 제3권4호
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• pp.322-332
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• 2023

Satellite attitude-control actuators are equipped with a reaction wheel for three-axis attitude control. The reaction wheel rotates a motor inside the actuator to generate torque in the vector direction. When using the reaction wheel, there are restrictions on the torque values generated as the motor rotates. The torque value of the reaction wheels mounted on small satellites is approximately 10 mNm, and high values are not used. Therefore, three-axis attitude control of a small satellite is possible using a reaction wheel, but this method is not suitable for missions that require rapid attitude control at a specific time. As a technology to overcome the small torque value of the reaction wheel, the control moment gyro (CMG) is currently in wide use as a rapid attitude-control actuator in space satellites. The CMG has an internal gimbal mounted at a right angle to the rotation motor and generates a large torque value. In general, when the gimbal operates, a torque value approximately 100 times greater is generated, making it suitable for rapid posture maneuvering. Currently, we are developing a technology for mounting a controlled moment gyro on a small satellite, and here we share the development status of an 800 mNm CMG.