• The Journal of Korea Robotics Society
• /
• v.4 no.4
• /
• pp.327-333
• /
• 2009

This paper describe the riding robot system named by "RideBot" which is a riding robot like as a horse. In order to simulate the riding motions, we develope the saddle mechanism which can generate 3 DOF motions including pitch, roll, and bounce movement, and also we controlled the riding motions and the intention of horseman. To generate the riding motions with the bodily sensation, we developed Novel Washout Filter and the algorithms for motion control. And also, we developed some health care service for the health care of horseman. A body state index was proposed that evaluates the personal health state from both the measured physiological variables and the surveyed questions. The physiological variables such as weight, blood pressure, heart rate variability (HRV), accelerated state photoplethysmograph(APG), body fat, and happiness index were measured by the specially designed bio-handle system and survey questions. The efficiency of the proposed ride robot is evaluated in the experiments.

• 제어로봇시스템학회:학술대회논문집
• /
• 2001.10a
• /
• pp.156.5-156
• /
• 2001

Stabilized tracking platform in a missile consisting of a flat planar antenna, pitch/yaw gimbals, gear trains, and current controlled DC drive motors for pitch and yaw gimbal must have a capability to track a target as an inertial sensor in the presence of missile body motion such as maneuvering and vibration. Because of this reason, tracking a target from dynamic platform requires a servo architecture that includes a outer tracking loop(position loop) and inner rate loop that stabilizes the line of sight(LOS). This paper presents a gimbaled platform model including nonlinear phenomena due to viscous and Coulomb friction based on experimental data and torque equilibrium equation, the design concept for the inner tacholoop having P controller structure ...

• The Bulletin of The Korean Astronomical Society
• /
• v.37 no.2
• /
• pp.198.2-198.2
• /
• 2012

태양 전지판의 전개 여부는 저궤도 위성의 발사 성공 여부를 판단하는 가장 중요한 항목 중 하나이다. 태양 전지판이 성공적으로 전개되어야만 태양 지향 자세제어에 의해 위성 운용에 필요한 전력 생성이 가능하기 때문이다. 그러므로 발사 후 지상국 교신을 통해 최우선적으로 태양 전지판의 전개 여부를 판단한다. 태양 전지판의 전개 여부는 다양한 실패 상황에 가정해 총 5가지 조건을 통해 판단한다. 첫째, SAR1, SAR2의 입력 전류가 모두 0.8A보다 커야 한다. 만약 하나라도 0.8A 미만이라면 한 개 이상의 태양 전지판이 전개되지 않고 1번 태양 전지판이 태양 지향을 하지 못하는 상황이다. 둘째, SAR1 입력 전류와 SAR2 입력 전류의 값이 유사해야 한다. 만약 입력 전류 값이 크게 차이가 난다면 2번과 3번 태양 전지판 중 하나만 태양 지향을 하는 경우이다. 셋째, CSSA#5 출력 전류가 3.2mA보다 커야 한다. 만약 3.2mA보다 작다면 2번과 3번 태양 전지판의 전개가 실패하고 1번 태양 전지판이 태양 지향을 하는 경우 또는 1번 태양 전지판이 전개 실패하고 태양 지향을 하는 경우이다. 넷째, S/C Roll, Pitch, Yaw rate이 모두 0.2 deg/sec 보다 작아야 한다. 만약 body rate이 크다면 1번 태양 전지판의 전개 실패 상황을 예상할 수 있다. 다섯째, 각 태양 전지판의 온도 차이가 $35^{\circ}C$ 보다 작아야 한다. 만약 온도 차이가 크다면 1번 태양 전지판 전개 실패 상황에서 2번과 3번 태양 전지판이 태양 지향을 하는 경우이다. 총 다섯 가지의 조건을 모두 만족해야만 태양 전지판이 성공적으로 전개되었다고 판단한다. 태양 전지판의 전개 판단은 위성이 발사체에서 분리되고 약 4500초 이후 시점에 스발바드 지상국과의 교신을 통해 확인되었다. 이 시점의 SAR1 입력 전류는 약 2.00A, SAR2 입력 전류는 약 1.93A였기 때문에 모두 0.8A보다 크고 서로 유사한 값임을 확인했다. CSSA#5의 출력 전류는 약 3.5mA의 값을 나타냈다. S/C Roll rate은 -0.0084 deg/sec, Pitch rate은 -0.0072 deg/sec, Yaw rate은 -0.0303 deg/sec의 값을 나타냈다. 각 태양 전지판의 최대 온도 차이는 $7.7^{\circ}C$의 값을 나타냈다. 5가지 조건을 모두 만족함으로써 태양 전지판 전개는 성공적으로 수행된 것으로 판단했다.

• Journal of Korea Artificial Intelligence Association
• /
• v.2 no.1
• /
• pp.25-30
• /
• 2024

Kodály hand signs are symbols that intuitively represent pitch and note names based on the shape and height of the hand. They are an excellent tool that can be easily expressed using the human body, making them highly engaging for children who are new to music. Traditional hand signs help beginners easily understand pitch and significantly aid in music learning and performance. However, Kodály hand signs have distinctive features, such as the ability to indicate key changes or chords using both hands and to clearly represent accidentals. These features enable the effective use of Kodály hand signs. In this paper, we aim to investigate the changes in recognition rates according to the complexity of scales by creating a device for learning Kodály hand signs, teaching simple Do-Re-Mi scales, and then gradually increasing the complexity of the scales and teaching complex scales and children's songs (such as "May Had A Little Lamb"). The learning device utilizes accelerometer and bending sensors. The accelerometer detects the tilt of the hand, while the bending sensor detects the degree of bending in the fingers. The utilized accelerometer is a 6-axis accelerometer that can also measure angular velocity, ensuring accurate data collection. The learning and performance evaluation of the Kodály learning device were conducted using Python.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.37 no.10
• /
• pp.992-997
• /
• 2009

This paper focuses on the calculation of the missile angular velocity under the reduced sensor condition and its verification using the Flight Motion Simulator(FMS). The missile angular velocity is usually measured by the body gyroscopes, but we assume that the inertial sensors on the missile body are in the absence of pitch and yaw gyroscopes. Under this reduced sensor condition, this paper shows the missile angular velocity can be calculated by using the gimbal seeker gyroscope, the roll body gyroscope, the gimbal angle and its rate. The FMS experiment was carried out to verify the proposed algorithm.

• The Transactions of The Korean Institute of Electrical Engineers
• /
• v.60 no.6
• /
• pp.1204-1208
• /
• 2011

In this study, we proposed the system that calculates the algorithm with an accelerometer signal and detects the fall shock and it's direction. In order to gather the activity patterns of fall status and attach on the subject's body without consciousness, the device needs to be small. With this aim, it is attached on the right side of subject's waist. With roll and pitch angle which represent the activity of upper body, the fall situation is determined and classified into the posture pattern. The impact is calculated by the vector magnitude of accelerometer signal. And in the case of the elderly keep the same posture after fall, it can distinguish the situation whether they can stand by themselves or not. Our experimental results showed that 95% successful detection rate of fall activity with 10 subjects. For further improvement of our system, it is necessary to include tasks-oriented classifying algorithm to diverse fall conditions.

• Animal cells and systems
• /
• v.15 no.1
• /
• pp.85-90
• /
• 2011

In 2001, we conducted a study to assess the effects of differential arrival times and nest-site selection on reproductive performance in a mixed-species heronry consisting of six species in Taeseong-ri, Chungbuk, Korea. We recorded the arrival dates, nest heights, clutch sizes, and brood sizes after 15-20 days of the age of the birds' chicks. The grey herons and cattle egrets arrived first and last, respectively, on the colony site. In the homogenous vegetation structure of the breeding site, the pitch pine trees (Pinus rigida) were mainly used for building nests on 48 of the 50 pine trees (96%). The breeding species vertically stratifies the nest sites according to their body size, except for the cattle egrets and black-crowned night herons that nested at sites higher than those predicted from their body size. The mean nest success rates of the six species under study were positively correlated with the mean nest heights. Our findings suggest that aggressive interspecific interactions among neighbors influence nest-site selection to enhance breeding success.

• 제어로봇시스템학회:학술대회논문집
• /
• 2005.06a
• /
• pp.1978-1982
• /
• 2005

In this paper, a linear controller is designed for the longitudinal model of X-33 in TAEM (The Terminal Area Energy Management) phase. The CRA (Characteristic Ratio Assignment) is used as the continuous time design method such that the output response of X-33 control system tracks the reference command. The performance of the proposed controller is evaluated through the step response. Also simulation results show that the initial state of the plant is dominantly affected by the poles and zeros of the plant.

• The Journal of Korea Robotics Society
• /
• v.13 no.2
• /
• pp.103-112
• /
• 2018

In this paper, a high performance underwater vehicle which can be manufactured at low cost is designed and fabricated, and its performance is verified through experiments. To improve efficiency, the Myring equation is used to design the appearance and the duct structure including the thruster is planned to increase the propulsion efficiency while reducing the drag force. Through various methods, it is secured stable waterproof performance, and also is devised to have high speed movement and turning performance. The developed underwater vehicle is equipped with a high output BLDC motor to achieve a linear speed of up to 2 m/s and can change direction rapidly with stability through four rudders. The rudders are driven by coupling a timing belt and a pulley by extending the axis of a servo motor, and are equipped at the end of the body to turn heading. In addition, for stable posture control, the roll keeps its internal center of gravity low and maintains its stability due to restoring force. By controlling the four rudders, pitch and yaw are handled by the PID controller and show stable performance. To investigate the horizontal turning performance, it is confirmed that the yaw rate controller is designed and stable yaw rate control is performed.

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