• Journal of the Korean Institute of Intelligent Systems
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• v.20 no.2
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• pp.304-310
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• 2010

Chronic pain and herniated disk is a common disease that 80% of adults are experienced. There diseases rates of caused by the physical shock, such as the traffic accident, and the accidental fall is about 10%. And the most of these diseases is caused by having habitual incorrect position. People know that incorrect position would cause to accumulate continuous stress, but it is not easy to correct position. Because it does not recognize incorrect position repeated habitual consequently. This system collects data of user position after sensors that could measure position attach on use and presumes correct position used by position presumption algorithms. Its system purpose is continuing incorrect position could be aware to user and lead to change to correct position to prevent habituation of incorrect position. If habitual of correct position continues through accurate measurement and repeating cognitive learning, it would help for children and chronic patience.

• Aerospace Engineering and Technology
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• v.10 no.2
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• pp.121-127
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• 2011

In the attitude and orbit control subsystem design, the moment of inertia of the satellite is the major contributor to be considered. Satellites equipped with large solar arrays need to measure the moment of inertia accurately to avoid the interference of the thruster actuation period with its flexible mode. In this paper, the in-orbit tests of COMS to measure the moment of inertia are described. Then, the differences between the measured through in-orbit test and the predicted are compared. Finally, it is verified that the differences are below uncertainty bounds considered in the critical design of COMS attitude and orbit control subsystem.

• Aerospace Engineering and Technology
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• v.6 no.2
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• pp.1-7
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• 2007

The control design for attitude and yaw rate of 40 % scaled SMART UA Vhas been performed. Analytic selection method for a control gain is proposed to meet the design specification of desired time response considering stability margin. The sliding mode attitude controller is also proposed and compared with the simulation results of a linear controller. Additionally, a velocity and height tracking controller is devised to prepar for the flight test.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.6
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• pp.455-462
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• 2017

In recent decades, many researchers have been struggling to developing the compound aircraft that is capable high speed and VTOL flight. And in recent years, multi-copters are very popular because of having advantages of VTOL and easy handling, but they are lack of doing long-range mission. Therefore, we presents simple aircraft architecture which is equipped fixed wing, multi propellers and no control surfaces. In this paper, we designed the attitude control for the compound aircraft prototype and measured the attitude control performance with flight test for validating prototype's performance. We analysed the attitude control test result comparing with similar size of a fixed wing aircraft. The performance was almost same as fixed wing aircraft.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.6
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• pp.537-544
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• 2009

This paper concerns analysis technique on determining of attitude control gain in the low frequency region using stability area. The stability area is defined by the D-Decomposition method, which was designed by Neimark. In this paper, it is introduced D-Decomposition method from reference paper and design attitude control gain of generic launch vehicle during first stage flight phase. For selecting PD control gain, it is considered the system parameter uncertainty about whole first-stage flight phase, represented the stability area boundary on each case. After deciding the PD control gain using stability area method, it is applied to launch vehicle linear model, and checking the stability margin requirement, frequency response characteristics.

• Journal of Advanced Navigation Technology
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• v.8 no.2
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• pp.112-119
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• 2004

This paper proposes an attitude determination GPS/INS integrated system scheme for a UAV and presents experimental flight test results. The proposed system is designed as a part of an autopilot system and comprises a GPS attitude determination receiver, an off-the-shelf inertial measurement unit (IMU), and a navigation computer unit (NCU). UAV requires accurate attitude information for stable automatic flight control. The proposed system can provide accurate attitude information for the flight control computer (FCC) so that stable automatic flight control can be achieved. In order to verify the performance of the proposed scheme, an integrated navigation system has been developed. In order to evaluate the developed navigation system, the flight test has been performed. In the flight test, the developed system was shown to provide the position, the velocity and the attitude satisfactorily enough for stable flight control. The accuracy of the attitude information of the developed system was confirmed by comparing attitude of vertical gyro.

• Journal of the Institute of Convergence Signal Processing
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• v.20 no.2
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• pp.99-104
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• 2019

Recently, modern people are increasing the incidence of various musculoskeletal diseases due to wrong posture. Prevention is possible through proper posture habit, but it is not easy to recognize posture by oneself. Various studies have been conducted to monitor persistent posture in daily life, but most studies using constrained measurement methods and high-cost measurement equipment are not suitable for daily life. In this paper, we implemented a posture discrimination system using a FSR sensor array that can induce posture correction spontaneously through sitting posture monitoring in daily life. The implemented system is designed as a cushion type so it is easy to apply to existing chair. In addition, it can identify five most common postures in everyday life, and can monitor real-time through Android-based smart-phone monitoring application. For the performance evaluation of the implemented system, each posture was measured 50 times repeatedly. As a result, 97.6% accuracy was confirmed.

• ICROS
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• v.3 no.2
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• pp.34-40
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• 1997

우리별 1, 2호의 제작과 운용을 통하여 위성 설계에 필요한 기본적인 지식과 기술을 습득할 수 있었다. 소형 위성이기 때문에 전체 시스템을 비교적 쉽게 이해하고 우리별 3호 설계에 많은 밑 바탕이 되었다. 4년 동안의 위성 운용 경험은 새로운 시스템 제작에 있어 많은 새로운 아이디어와 접근방법을 제공해 주었다. 자세 제어적인 측면에서 볼 때 우리별 3호는 매우 진보적인 구조와 성능을 가지고 있다. 따라서 계속적인 시스템 분석과 실험을 통하여 신뢰도를 높이는 작업이 요구된다.

• Proceedings of the Korean Information Science Society Conference
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• 2001.04a
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• pp.118-120
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• 2001

본 논문에서는 GPS(Global Positioning System)와 관성 항법 시스템(INS: Inertial Navigation System 이하 INS)을 혼합 구성한 수신보드의 운영을 위한 Embedded 운영체제를 설계하고 구현하였다. 이 운영체제는 실시간으로 인공위성과 IMU로부터 수신되어지는 Raw Measurement 획득, GPS 항법, 자세 결정, 통합항법, 위성 추적을 수행하는 태스크들을 우선순위 기반으로 처리하는 선점형(Premptive) 스케줄링 방식을 채택한 실시간 운영 체제이다. 본 논문에서는 자세 결정용 GPS와 INS를 이용한 통합시스템보드를 위한 실시간 운영체제의 개발 환경, 운영체제의 구조, 개발 내용과 실험내용에 대해 언급하였다.

• Korean Architects
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• no.5 s.337
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• pp.33-65
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• 1997

WTO(세계무역기구)출범 이후 국제적인 설계시장 개방 및 교류가 점차 증가하고 있는 상황에서 국내 건축계도 그동안 이에 대한 다양한 대응방안을 모색해 왔다. 그러나 대부분의 경우 외국건축사의 국내진출과 시장잠식을 우려한 수세적 자세에 머물러 왔으며, 이를 적극적인 자세에서 국내건축사의 해외진출을 확대할 수 있는 기회로 활용하는데에는 소홀히 해온 듯하다. 본지는 이와같은 배경에서 '국내건축사의 해외진출 방안'이라는 주제로 기획특집을 마련, 한국건축의 해외 설계시장 진출상황과 잠재력, 바람직한 접근방향 및 활성화 방안등을 살펴봄으로써 개방화ㆍ국제화를 국내건축계의 새로운 도약을 위한 발판으로 삼을 수 있는 계기를 마련하고자 한다.