• Proceeding of EDISON Challenge
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• 2016.03a
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• pp.566-570
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• 2016

본 연구에서는 플라잉 디스크를 이용하여 Pitching 운동 조건에서의 공력특성을 해석하였다. 본 해석에서 사용한 플라잉 디스크 모델은 프리원 151_140이며, 해석자로는 KFLOW_EDISON_2D_3DOF를 사용하였다. Pitching 운동이 있는 경우 받음각의 변화에 따른 공력특성을 비교 분석하였다. 기준 받음각의 변화에 따라 형상 아랫면과 뒷전 부근에 실속 와류가 다른 형태로 생겨 플라잉 디스크의 공력 특성에 영향을 준다는 것을 확인하였다. 또한, 기준 받음각이 증가 할수록 강한 실속 와류가 발생함을 알 수 있다.

• Journal of the Korea Institute of Military Science and Technology
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• v.2 no.2
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• pp.61-69
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• 1999

A dynamic stability test was performed to determine dynamic stability derivatives for the pure pitching motion of air-to-ground missile model in the low speed wind tunnel. The free vibration technique was employed to acquire oscillation characteristics of the model for damping coefficients. Damping coefficients are obtained by the method of logarithmic decrement. Results show good damping effects and stability capability at Mach numbers 0.1 and 0.2, with the angle of attack ranging from -15 to +20 degrees.

• The Transactions of The Korean Institute of Electrical Engineers
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• v.65 no.2
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• pp.335-341
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• 2016

In general, a yawing motion concept is used for the lateral control of one wheel robot where the gimbal system is located horizontally. In this paper, another concept of the vertically located gimbal system is presented for the same purpose. Although the vertical concept undergoes an instability more easily than the horizontal one, the pitching motion of the gyroscopic effect is considered. Firstly, the trade-off relation between two balancing concepts are investigated by comparing the gyroscopic mechanism. Secondly, the dynamic model for the problem of the proposed concept is derived using the oscillatory inverted stick model. Thirdly, the stability of the model is analyzed using the phase trajectory method. Finally, the control performance of the system by a vibration controller is simulated.

• Journal of the Korean Society of Mechanical Technology
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• v.13 no.2
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• pp.71-78
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• 2011

A kart is a vehicle without the suspension system and the differential gear. The kart frame as an elastic body plays the role of a spring. By the cornering of a kart, rolling, pitching and twisting motions are induced in the kart frame. Also the slip or noncontact of the wheel and a permanent deformation of the kart frame can be induced. In order to examine closely this phenomenon, measurement on height-displacements with various sensors and tracking system and analysis on the kart frame twisting characteristics with the rolling and pitching angle are needed. According to the measurement result, while driving in a curve at high speed the kart frame is quite twisted. Analysis on the measurement results shows that a kart used primarily in high speed requires a frame with low torsional stiffness and a frame material with high tensile strength and large elongation.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.12
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• pp.1-8
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• 2006

An experimental study was carried out in order to investigate the influence of Reynolds number on the near-wake of an oscillating airfoil. An NACA 0012 airfoil was sinusoidally pitched at the quarter chord point, and is oscillated over a range of instantaneous angles of attack of $\pm$6$^{\circ}$. An X-type hot-wire probe was employed to measure the near-wake of an oscillating airfoil, and the smoke-wire visualization technique was used to examine the flow properties of the boundary layer. The free-stream velocities were 1.98, 2.83 and 4.03 m/s and the corresponding chord Reynolds numbers were 2.3${\times}10^4$, 3.3$\times$104 and 4.8${\times}10^4$, respectively. The frequency of airfoil oscillation was adjusted to fix a reduced frequency of K=0.1. The results show that the properties of the boundary layer and the near-wake can dramatically be distinguished in the range of Reynolds numbers between 2.3${\times}10^4$ and 3.3${\times}10^4$, on the other hand, it is similar in the cases of Re=3.3$\times$104 and 4.8$\times$104. This is caused by that the unsteady separation point is dramatically delayed in case of Re= 2.3${\times}10^4$.

• Journal of Korean Medical classics
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• v.13 no.2 s.17
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• pp.44-56
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• 2000

장개빈(張介賓)(1563-1640, 호시경악(號是景岳))시명말의학가이계승김원대의학전통적인물(是明末醫學家而繼承金元代醫學傳統的人物). 타재(他在) 류경도익(類經圖翼), 의역의(醫易義) 주장'의역동원'이논증의학여역학지회통성(主張'醫易同源'而論證醫學與易學之會通性). 타이성리학이론내연구의학(他以性理學理論來硏究醫學). 인이피칭위'유의'(因而被稱爲'儒醫'). 타광범지연구유가급제자백가지후(他廣範地硏究儒家及諸子百家之後), 이(以) 황제내경(黃帝內經) 여(與) 난경 위주(難經 爲主). 종합의가학설(綜合醫家學說). 타이(他以) '양상부족음본무여'지관념내설명인체내음양상태('陽常不足陰本無餘'之觀念來說明人體內陰陽狀態) 이반박주진형지자음론(而反駁朱震亨之滋陰論). 인이주장'부양억음'급'태극시명문'적학설(因而主張'扶陽抑陰'及'太極是命門'的學說). 타재(他在) 의역의(醫易義) 이부양억음내해설병리(以扶陽抑陰來解說病理). 관어태극-명문적론의야수성리학태극개념적영향(關於太極-命門的論議也受性理學太極槪念的影響). 단시(但是), 소위(所謂) '조원찬화'('調元贊化') '기사회생'적의학목적시속어도교양생론('起死回生'的醫學目的是屬於道敎養生論). 관어차점(關於此點), 연피칭위유의적성리학의가야병부예외(連被稱爲儒醫的性理學醫家也竝不例外). 일반인위 황제내경 시재전국 한대초기형성적(一般認爲 黃帝內經 是在戰國 漢代初期形成的). 야인위기의학체계반영저황로사상여음양오행론(也認爲其醫學體系反映著黃老思想與陰陽五行論). 장개빈수재성리학적립장내주장자기적이론(張介賓雖在性理學的立場來主張自己的理論). 단시대폭지접수도가급도교립장(但是大幅地接受道家及道敎立場). 타재(他在) 류경도익(類經圖翼), 태극도론(太極圖論), 이태극성위만물생명적근원(以太極成爲萬物生命的根源). 동시언급도도가여역위(同時言及到道家與易緯). 재장개빈(在張介賓), 태극시상통어도가발생론적개념(太極是相通於道家發生論的槪念). 야상통어태극적개념(也相通於太極的槪念). 재(在) 유경(類經), 섭생(攝生) 내간(來看). 타제요로장이외(他除了老莊以外). 우인용송대이후내단사상가강백단 이도순등적주장(又引用宋代以後內丹思想家强伯端 李道純等的主張), 인이전개자기적이론(因而展開自己的理論). 필자시위(筆者視爲), 장개빈재의학적양생방면상접수료이'성명쌍수'위기적송대이후내단사상(張介賓在醫學的養生方面上接受了以'性命雙修'爲基的宋代以後內丹思想). 병차타이연단적관점내이해부양억음(竝且他以煉丹的觀點來理解扶陽抑陰). 신위유의적장개빈능구장유도량자회통위일조의학체계적의거재어역학.(身爲儒醫的張介賓能구將儒道兩者會通爲一條醫學體系的依據在於易學). 장개빈재천인상응관념지하(張介賓在天人相應觀念之下), 용이음양변화지기구내변증천인관계(用以陰陽變化之機構來辨證天人關係). 재타적이론(在他的理論), 천지시속어 역(天地是屬於 易), 인시속어 의(人是屬於 醫), 단시양자귀위동일양적일리(但是兩者歸爲同一樣的一理). 재'원취제물(在'遠取諸物), 근취제신'적관점내강(近取諸身'的觀點來講), 타장'근취제신'적도리취어의학(他將'近取諸身'的道理取於醫學). 환유'원취제물'적도리취어역학(還有'遠取諸物'的道理取於易學), 인이모구귀납성일개원리(因而謀求歸納成一個原理). 타장자연현상적원리내재어인지생명(他將自然現象的原理內在於人之生命), 종여차정체적각도내간(從如此整體的角度來看). 가이설의학시상통어역학적(可以說醫學是相通於易學的). 역학대인여자연간적탐구(易學對人與自然間的探求), 비교측중어이론성(比較側重於理論性). 반이의학이역학이론위자(反而醫學以易學理論爲資). 관어자연여인지생명진일보지진행교구체성적연구(關於自然與人之生命進一步地進行較具體性的硏究). 총지(總之), 장개빈통과태극음양론(張介賓通過太極陰陽論), 부분유 도이참재'생명'적립장(不分儒 道而站在'生命'的立場), 광범지접납유도양가(廣範地接納儒道兩家). 유차(由此) 아문가이여도장개빈의서적가치병부한어의학가치(我們可以如道張介賓醫書的價値竝不限於醫學價値). 장개빈의서제시유 도량가가이회통어"생명사상"적철학상가능성(張介賓醫書提示儒 道兩家可以會通於"生命思想"的哲學上可能性).

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.9
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• pp.712-722
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• 2018

This paper conducts parametric studies on flapping wing design, one of the most important design parameters of insect-mimicking aerial vehicles. Experimental study on wing shape was done through comparison and analysis of thrust, pitching moment, power consumption, and thrust-to-power ratio. A two-axis balance and hall sensor measure force and moment, and flapping frequency, respectively. Wing configuration is biplane configuration which can develop clap and fling effect. A reference wing shape is a simplified dragonfly's wing and studies on aspect ratio and wing area were implemented. As a result, thrust, pitching moment, and power consumption tend to increase as aspect ratio and area increase. Also, it is found that the flapping mechanism was not normally operated when the main wing has an aspect ratio or area more than each certain value. Finally, the wing shape is determined by comparing thrust-to-power ratio of all wings satisfying the required minimum thrust. However, the stability is not secured due to moment generated by disaccord between thrust line and center of gravity. To cope with this, aerodynamic dampers are used at the top and bottom of the fuselage; then, indoor flight test was attempted for indirect performance verification of the parametric study of the main wing.

• Journal of Aerospace System Engineering
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• v.15 no.5
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• pp.33-42
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• 2021

Modern aircraft fighters improve the maneuverability and performance with the RSS (Relaxed Static Stability) concept and therefore these aircrafts are susceptible to abrupt pitch-up in the transonic and moderate Angle-of-Attack (AoA) flight region where the shock wave is formed and the mean aerodynamic center is moved forward during deceleration. Also, the modeling of the aircraft flying in this flight region is very difficult due to complex flow filed and unpredictable dynamic characteristics and the model-based control design technique does not fully cover this problem. In this paper, we analyzed the performance of the TPMC (Transonic Pitching Moment Compensation) control based on the model-based IDI (Incremental Dynamic Inversion) and the Hybrid IDI based on the model and sensor based IDI during the SDT (Slow Down Turn) in transonic region. As the result, the Hybrid IDI had quicker response and the same maximum g suppression performance and provided the predictable flying qualities compared to the TPMC control. The Hybrid IDI improved the performance of the Over-G protection controller in the transonic and moderate AoA region

• KSCE Journal of Civil and Environmental Engineering Research
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• v.26 no.4D
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• pp.671-678
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• 2006

In this study, to describe vehicle-structure dynamic interaction phenomena with 1/4 vehicle model, nonlinear Hertzian contact spring and nonlinear contact damper are adopted. The external loads acting on 1/4 vehicle model are selfweight of vehicle and geometry information of running surface. The constraint equation on contact surface is implemented by the Penalty method with stabilization and the reaction from constraint violation. To describe pitching motion of various vehicles two types of the displacement constraint equations are exerted to connect between car bodies and between bogie frames, i.e., the rigid body connection and the rigid body connection with pin, respectively. For the time integration of dynamic equations of vehicles and structure Newmark time integration scheme is adopted. To reduce the error caused by inadequate time step size, adaptive time-stepping technique is also adopted. Thus, it is expected that more versatile dynamic interaction phenomena can be described by this approach and it can be applied to various railway dynamic problems with low computational cost.

• Aerospace Engineering and Technology
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• v.6 no.1
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• pp.35-44
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• 2007

In this study was made the flutter analysis for the export model of Firefly(Bandi-ho), the small canard aircraft. Stiffness model based on internal load generation finite element model was generated. Mass model based on the weight DB for weight control was generated. Aerodynamic model based on Doublet Lattice Method was generated. Preliminary flutter analysis was made. Based on it, major vibration modes are identified and experimentally obtained via the ground vibration test. The obtained normal mode frequencies were used to correlate the finite element model. Flutter analysis was made again and major flutter mechanisms were summarized. The most important flutter root was identified as a coupled root between rigid body roll mode and anti-symmetric wing pitching mode.