• Proceedings of the Korean Society for Agricultural Machinery Conference
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• 2002.02a
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• pp.35-41
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• 2002

본 연구는 기존 벼 펠렛종자 제조장치의 제조성능 및 제조 벼 펠렛종자 품질향상을 위하여 펠렛재료 공급부, 성형부, 펠렛종자 배출부를 개선 설계 제작하여 그 성능과 제조 벼 펠렛종자 특성을 구명함으로써 직파용 벼 펠렛종자 대량생산을 위한 제조장치 개발의 기초 자료를 얻고자 수행하였으며 그 주요 결과를 요약하면 다음과 같다. 펠렛재료의 일정한 공급과 펠렛재료가 성형 홈으로부터의 이탈하는 것을 줄이고, 펠렛종자의 완전한 배출이 가능하도록 한 벼 펠렛종자 제조장치를 설계·제작하였으며, 벼 펠렛종자 제조장치를 상토 종자혼합비, 성형롤의 회전속도에 따라 실험한 결과 벼 펠렛종자 제조 능력은 성능 개선 전의 펠렛종자 제조장치에 비하언 약 1.7배 향상된 제조능력을 보였으며, 성형률은 최대 약 89 %로 나타나 개선 전의 71%에 비해 18 %정도 성형률이 향상되었다. 그러나, 벼 종자손실률은 약 24% ∼ 49%로 거의 비슷한 수준인 것으로 나타났다. 제조된 벼 펠렛종자의 특성을 분석한 결과 펠렛종자의 구형률은 99.1%로 거의 구형으로 제조됨을 알 수 있었으며, 무게는 제조 직후에는 약 1.70 g, 완전 건조 후에는 1.31 g으로 나타났고, 직경은 약 12.03 mm에서 건조 후 11.53 mm로 축소되었다. 개선 전에 비해 직경과 무게가 약간씩 증가한 것으로 나타났다. 이러한 결과는 재선된 제조장치에서 펠렛재료가 성형롤의 성형 홈에 압축 공급되고, 펠렛재료의 손실도 적었기 때문으로 판단된다. 제조된 한 개의 벼 펠렛종자 내에 포함된 완전 벼 종자의 개수는 상토 종자혼합비가 커질수록 성형롤의 회전속도가 낮을수록 많아지는 것으로 분석되었으며, 모두 펠렛종자 당 평균 약 3 개 이상의 완전 벼 종자를 포함하고 있는 것으로 나타났다. 개선 전에 비하여 펠렛종자 내에 포함된 평균 완전 종자수도 증가하였으며, 3개 이상 완전 종자를 포함한 펠렛종자의 비율도 증가하여 유압에 의한 펠렛재료 공급과 성형롤의 개선효과가 있었던 것으로 보인다. 음지 건조 후 벼 펠렛종자의 압축강도는 약 132 N ∼ 152 N으로 조사되었으며, 개선전에 비하면, 약 30 %가 증가한 것으로 나타났다. 출아율 실험 결과 상토 종자혼합비 6 : 1, 성형롤 회전속도 7 rpm에서 건답직파는 100%, 답수직파는 97 %의 출아율을 보여 만족할 만한 결과를 얻었으나, 그 외의 경우는 거의 90 % 이하의 출아율을 보여 출아율을 높이기 위한 방안이 필요한 것으로 보인다. 본 연구의 벼 펠렛종자 제조장치의 적정운전 조건은 제조된 벼 펠렛종자의 특성과 출아율을 고려해 볼 때 상토 종자혼합비 6 : 1, 성형롤 회전속도 약 7 rpm으로 판단되며, 이 때 제조능력은 시간당 약 65 Kg(펠렛종자 약 39,000 개), 성형률 약 87 %, 종자손실률은 약 30 %, 펠렛종자 내 평균 종자수는 약 5.5 개, 완전 벼 종자 3개 이상 포함 펠렛종자 비율은 약 100 %가 될 것으로 보인다.

• Proceeding of EDISON Challenge
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• 2016.11a
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• pp.4-8
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• 2016

본 연구에서는 플라잉 디스크를 이용하여 회전 운동의 유무에 따른 공력특성의 변화를 비교 분석하였다. 회전 운동이 발생하면 표면에 비대칭적으로 압력이 분포하기 때문에 롤링 모멘트가 발생하고 마그너스 효과로 측력이 발생하고 피칭모멘트, 회전감쇠모멘트가 발생하고 롤 안정성이 증가한다.

• Journal of Animal Environmental Science
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• v.11 no.1
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• pp.11-16
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• 2005

The round bale wrappers are generally used for rice straw after the harvesting of low land rice by combine harvester. In this situation, the bale wrappers should be well adapted under the travelling over raised borders and temporary ditches in soft soil of narrow rice fields. The study was conducted to improve the performance of bale wrapper through the new design for compact size, lowered gravity center and lowered power consumption. The prototype of round bale wrapper had been designed and assembled to tractor with three point hitch mounted. The machine type is one roll driving system with one roll for rotating and one roll for wrapping. The driving torque and work performance of the machines were measured and analysed. The torque requirement of the prototype and conventional type was 6kgf-m and 12kgf-m, respectively. The prototype shaved less friction resistance between bale driving roll and round bale. and the power requirement can also be reduced from 12kgf-m in the conventional to 6kgf-m in the prototype. The work efficiency of the new bale wrapper was $45\%$ higher than the conventional wrapper, and the working cost of the prototype can be reduced $17\%$ than that of the conventional.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.3
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• pp.220-228
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• 2008

In this study the aerodynamic characteristics of a canard-controlled missile with freely spinning tailfins were investigated by using a semi-empirical method and a CFD code. The mean aerodynamic coefficients for the rolling and roll damping moments were first calculated and then used to predict the roll-rate of freely spinning tailfins. The calculation of roll-rate in the CFD code was carried out by combining a Chimera overset grid system and 6-DOF analysis module. The predicted roll-rate was in good agreement with the experimental data for the roll and yaw canard control inputs. It was also shown that the results are in good agreement with the prediction by a CFD code. This indicates that the semi-empirical method can be used to predict the roll-rate of a canard-controlled missile with freely spinning tailfins.

• Journal of Aerospace System Engineering
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• v.16 no.6
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• pp.114-122
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• 2022

This paper explores three-dimensional unsteady computational fluid dynamic (CFD) analyses with an overset grid technique to analyse the wake effect created by a rotating propeller on a hand-launched unmanned aerial vehicle (UAV). Additionally, the influence of actual aileron deflection on the equilibrium condition of the rolling moment is examined in various hand-launched take-off conditions. The results of this study demonstrate the importance of initial aileron deflection in increasing the initial rolling stability during the hand-launched take-off process. Furthermore, an aerodynamic database is constructed to rapidly predict the aileron set values required for different take-off speeds and angle-of-attacks.

• Journal of the Korean Institute of Illuminating and Electrical Installation Engineers
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• v.19 no.8
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• pp.122-130
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• 2005

For silent operation, Roll-Screen has been designed by using piezolelectric ultrasonic motor. To drive the ultrasonic motor, a digitally controlled drive system has been designed by using PLD. And to measure the position and velocity of Roll-Screen, encoder with 36 pulse/revolution is used. This paper proposed a new method for a precise velocity control of ultrasonic motor, in spite of using low-level encoder. The proposed method use a non-fixed sampling time and compensate the initial nonlinear characteristics of ultrasonic motors.

• Proceedings of the Korean Society for Agricultural Machinery Conference
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• 2000.02a
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• pp.272-277
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• 2000

• Journal of Advanced Navigation Technology
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• v.22 no.6
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• pp.500-506
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• 2018

In this paper, we considered the one-shot alignment using master inertial navigation system (MINS) and slave inertial navigation system (SINS) in the missile to find the exact posture of a missile. In order to perform one-shot alignment, the tilt angle between MINS and SINS must be obtained, which can be compensated by obtaining the tilt angle between missile round and SINS. The tilt angle was calculated by using the roll rotation of missile round, jig for rotating the missile round and interface structure to measure the horizontal state by using a horizontal angle meter were constructed. As a result of the tilt angle save (TAS) inspection, the tilt angle ${\alpha}$, ${\beta}$, ${\gamma}$ is normal range and it is possible to perform one-shot alignment by compensating this value.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.3
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• pp.221-228
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• 2014

In this paper, the operational concept and the navigation algorithms for the gliding guided artillery munition are studied. The gliding guided artillery munition has wings for gliding; therefore spin of the munition should be eliminated. The previous navigation algorithms assumed a spinning munition with constant angular velocity; hence, they cannot be applied for the gliding munition. Moreover, lateral stability becomes worse due to decrease of angular momentum. Therefore, side force should be controlled to improve the stability, and the munition should maneuver, then the previous navigation algorithms for typical fixed-wing aircraft cannot be applied. In this paper, we apply the previous navigation algorithms for the spinning munition. Spin is eliminated and wings are deployed based on the estimation results, and the advanced navigation algorithm for the non-spinning munition is introduced.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.1
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• pp.1-10
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• 2011

Combustion and extinction limits in heat-recirculating excess enthalpy reactors employing both gas-phase and catalytic reaction have been examined with an emphasis Reynolds number (Re) effects and possible application to microscale combustion devices. In this paper, geometrically similar reactors of different physical sizes and different numbers of turns were tested with the aim of estimating for combustor characteristics. Combustion efficiency is estimated by measuring exhausted gases through the gas chromatograph. From these results the effect of scale and number of turns are demonstrated and optimal operating conditions for Swiss roll combustors are identified.