포발사 탄약에 적합한 비례항법 유도법칙 연구

신승제,김환우 대한전자공학회 2018 전자공학회논문지 Vol.55 No.2

이 논문에서는 포탄의 운동특성 분석을 통해 포탄의 타격 정확도를 향상 시키는 개선된 유도항법제어 기법을 제안하고자 한다. 이 기법은 포탄의 유도기법으로 많이 연구되고 있는 궤적성형 기법과 비례항법제어를 활용하여 포탄의 속도가 낮아 유도 입력의 크기가 제한적인 비행영역에서는 궤적성형 기법을 통해 제어입력을 최소로 하고, 포탄의 고도 저하에 따라 속도가 높아지면 비례항법제어를 통해 제어입력의 크기를 높여 충돌각 및 충돌정확도를 높이는 기법이다. 시뮬레이션을 통해 비례항법유도(Proportional Navigation, PN) 및 충돌점 예측기법(Impact Point Prediction, IPP)과 비교하여 제안한 기법의 제어입력 적절성 및 표적 수직타격 우수성을 확인하였으며, 표적타격 정확도는 원형 공산 오차(Circular Error Probability, CEP)를 통해 확인하였다. In this paper, we propose an improved guided navigation control technique that improves the accuracy of hitting the ammunition by analyzing the motion characteristics of the ammunition. This technique uses the trajectory shaping technique and the proportional navigation control, which have been studied extensively in the guidance technique of the ammunition, to minimize the control input through the trajectory forming technique in the gliding region where the guidance input magnitude is limited due to the low speed of the ammuniton, when the speed increases with the decrease of altitude, proportional navigation control increases the size of the control input to increase the collision angle and collision accuracy. The simulation results show that the proposed method has superior control input suitability and target vertical striking superiority compared with Proportional Navigation (PN) and Impact Point Prediction (IPP). And the target hit accuracy improvement was confirmed by Circular Error Probability (CEP).

HERO 시험평가 기법 연구

신승제,Shin, Seung-Je 한국군사과학기술학회 2007 한국군사과학기술학회지 Vol.10 No.2

This report presents the test technique using optic thermal sensor for the HERO evaluation of equipment installed EED. The calibration method of EED-thermal sensor assembly is explained by relation between the current in bridge wire and voltage in thermal sensor. And the HERO test and evaluation method is indicated based on MIL-STD-464A and MIL-STD-331C. The safety and reliability levels of EED-thermal sensor assembly are evaluated when exposed in the electromagnetic environment.

활공형 탄약의 비행모사 시뮬레이터를활용한 조건별 최대사거리 연구

신승제,김환우 한국멀티미디어학회 2018 멀티미디어학회논문지 Vol.21 No.6

When the new ammunition is designed, it is necessary to confirm in advance how long the target distance is depends on the shape and weight of the designed ammunition. Therefore we can use commercial software such as PRODAS to predict the target distance in the design stage. This commercial software has aerodynamic data for various ammunition shape and calculates the target range by calculating the kinetic equations of the ammunition using the aerodynamic data most similar to the designed ammunition. The ammunition for predicting the target distance through software such as PRODAS is a non-guided ammunition that has no control after launch but the glide type ammunition is guided and control ammunition. So it is predicts the state of ammunition after the launch. A new type of simulator is needed to analyze the maximum range and to verify the onboard guided and control algorithm. The simulator constructed in this paper is an optimized simulator for glide type ammunition. Unlike unmanned aircraft and guided missiles. The rotation characteristics of the ammunition are considered and the navigation initialization algorithm is applied. The constructed simulator confirmed the performance by performing maximum range analysis of glide type ammunition.

Fournier 괴저 중증도지수를 이용한 Fournier 괴저와 음낭 농양의 예후인자의 비교

신승제,류동수 대한요로생식기감염학회 2013 Urogenital Tract Infection Vol.8 No.1

Purpose: To evaluate effective factors in the survival of patients with Fournier’s gangrene (FG) and scrotal abscess, and to determine the validity of the Fournier’s gangrene severity index (FGSI), which was designed for determining disease severity in these patients. Materials and Methods: Twenty-eight men who treated for FG were enrolled. The data were evaluated about medical history, extent of body surface area involved (%), and the FGSI, which index presents patients’ vital signs (body temperature, heart and respiratory rates) and metabolic parameters (serum sodium, potassium, creatinine, bicarbonate, hematocrit, and white blood cell count). All the patients had antibiotic treatment and radical surgical debridement. The data were assessed according to whether the patient of FG survived or died, and also compared in patients with scrotal abscess (n=26). Results: Of the evaluated 28 FG patients, 6 died (21.4%). The difference in median age between survivors (57.5 years) and those who died (69.0 years) was not significant (p=0.18). Escherichia coli is the most common pathogen in 25% of FG and 15% of scrotal abscess patients. The median extent of the body surface area involved in patients who survived and died was 2.5% and 3.5%, respectively (p =0.13). However, the median FGSI scores for nonsurvivors and survivors of FG, and patients of scrotal abscess were 10.0±3.6, 3.3±2.6, and 0.9±2.6, respectively (p<0.01). The heart rate and serum creatinine level at the admission were significant prognostic parameters in patients with FG. Conclusions: The FGSI score appeared to be predicts the disease severity and the patient's survival in patients with FG and scrotal abscess.

지능형 유도 탄약의 신뢰성 향상을 위한 항법센서 고장탐지 및 대응기법

신승제(Seung-Je Shin),김환우(Whan-Woo Kim) 대한전자공학회 2018 전자공학회논문지 Vol.55 No.7

포발사 유도 탄약은 유도탄과 달리 발사초기 강한 물리적 충격을 받게 된다. 유도 탄약 내부에 장착된 항법센서(INS, Inertia Navigation System)인 가속도계 및 자이로가 포발사 충격에 손상되지 않는다면, 비행중 항법 초기화가 가능하게 되고 일반적인 순수 항법알고리즘을 이용하여 탄의 현재상태를 추측하여 유도조종을 수행할 수 있으며 최종적으로 표적타격 정확도를 향상시킬 수 있다. 하지만 탑재된 항법센서의 일부 또는 전체에서 고장이 발생한다면 표적오차를 증가시키는 방향으로 유도조종을 수행할 확률이 매우 높아진다. 이 논문에서는 포발사 유도 탄약에 장착된 항법센서(가속도계 및 자이로)의 고장 상황에서 탄약의 표적타격 정확도를 최대한 유지하기 위해, 가용한 센서 정보를 이용한 근사적인 항법해를 도출하는 알고리즘을 제안 하였다. 이를 위해 각각의 센서 출력값 변화에 따라 센서의 정상/성능저하/고장을 판단하였으며, 이 정보를 이용하여 성능저하 상황에서는 센서 측정치와 시스템 예측값을 조합하여 탄약의 현재 상태를 추정하고 고장상황에서는 정상 측정되는 타센서의 정보를 이용하여 근사적 항법해를 도출하는 시스템을 설계하였다. 마지막으로 제안한 알고리즘의 적용을 통해 항법센서 고장에 따른 포발사 유도 탄약의 성능저하가 효과적으로 개선됨을 확인하였다. Unlike guided missiles, guided ammunitions are subject to strong physical shocks at launch. If the accelerometer and gyroscope (INS, Inertia Navigation System) installed in the guided ammunition are not damaged by the impact of the shooter, it will be possible to initialize the navigation in flight and estimate the current state of the ammunition using general basic navigation algorithm guided controls can be performed, and finally the target striking accuracy can be improved. However, if a fault occurs in some or all of the mounted navigation sensors, the probability of performing the guided control in the direction of increasing the target error becomes very high. In this paper, we propose an new algorithm to derive an approximate navigation solution using the available sensor information in order to maintain the target hit accuracy of the ammunition in the fault situation of the some navigation sensor (accelerometer and gyro) mounted on the guided ammunition. For this purpose, the normal / performance deterioration / fault of the sensor was determined according to the change of each sensor output value. In the case of performance degradation using this information, the current state of the ammunition is estimated by combining the sensor measurement value and the system predictive value. In the case of fault, the system is designed to derive an approximate navigation solution using information from other sensors. Finally, it was confirmed that the deterioration of ammunition performance due to the failure of the navigation sensor was effectively improved through the application of the proposed algorithm.

지능형 유도탄약의 회전각 추정기법

신승제(Seung-Je Shin),김경훈(Gyeong-Hun Kim),김환우(Whan-Woo Kim) 대한전자공학회 2019 전자공학회논문지 Vol.56 No.3

포발사 지능형 유도탄약은 일반 유도탄과 달리 극한의 초기발사조건 때문에 탄약의 초기자세 설정이 불가능하다. 또한 발사초기 강한 물리적 충격을 받으므로 유도탄약 내부에 장착된 GPS(Global Position System) 및 관성항법장치(INS, Inertia Navigation System)는 전원이 인가되지 않은 상태에서 발사가 되고, 비행 중 항법 초기화를 통해 탄의 현재 상태를 추정하여 유도조종을 수행할 수 있으며 최종적으로 표적타격 정확도를 향상시킬 수 있다. 하지만 포발사 탄약의 특성에 따라 포강의 강선에 의해 발생하는 초당 20∼30회의 회전력 때문에 탄약의 회전각을 추정하는 것은 매우 어려우면서도 많은 오차요인을 가지고 있다. 선진국에서 개발 완료된 지능형 유도탄약인 M982(엑스켈리버)의 경우 GPS 수신강도 변화와 회전율을 이용하여 회전각을 추정한다. 이 방법은 회전율이 일정시간 동안 일정하게 유지되지 않으면 추정 정확도가 떨어지는 등 문제가 있다. 이 논문에서는 지능형 유도탄약에 탑재된 GPS 측정치의 미분/회전변환 후 INS의 가속도 데이터와 비교하거나 INS 측정치의 적분/회전변환 후 GPS 속도 데이터와 비교함으로써 회전각을 예측하는 기법을 제안 하였다. 제안한 기법은 유도탄약의 성능분석프로그램을 통해 획득한 모의데이터를 통해 기능을 확인 하였으며, 실제 포발사 시험에서 획득된 원격측정장치 데이터를 이용하여 성능을 검증하였다. Unlike conventional guided missiles, the intelligence gun-guided ammunition cannot set the initial position because of initial conditions of an extremity that is subject to a strong physical shock at the beginning of launch. Therefore the GPS and INS installed inside the intelligence guided ammunition are launched without power applied. The current state of the ammunition is estimated by the navigation initialization during the flight. After that, the ammunition has undergo guided control and finally the target striking accuracy can be improved. However, it is very difficult to estimate the rotation angle of the ammunition because of the 20∼30 rotations per second caused by the rifling inside the gun bore due to the characteristics of cannon launch ammunition. In the case of the M982(excalibur), an intelligence guided ammunition developed in the U.S. the rotation angle is estimated using the signal intensity of GPS and rotation rate. This method has a problem in that the roll angle estimation accuracy is significantly lowered unless the rotation rate is maintained constant for a certain period of time. In this paper, we propose a method to estimate rotation angle by comparing the acceleration data of INS after differential/rotation conversion of GPS measurements or by comparing the velocity data of GPS after integration/rotation conversion of INS measurements mounted on intelligent guided ammunition. The proposed algorithm was verified by simulation data obtained form the performance analysis program of ammunition and once again verified using telemetry data obtained from actual cannon launch test.

좌표계 변환을 통한 롤 각 추정기법의 적용가능성 연구

신승제(Seung-Je Shin),김철영(Chul-Young Kim) 대한전자공학회 2020 전자공학회논문지 Vol.57 No.10

항법/유도조종이 가능한 지능형 탄약은 발사초기 열악한 환경(충격, 회전)을 극복하기 위한 내고충격 전자장치를 내장하고 있다. 하지만 짧은 순간에 강한 충격과 고속 회전이 인가되기 때문에 항법 수행을 위한 초기정렬은 불가능 하고 발사 직후 충격량에 의해 작동하는 열전지에 의해 전원인가 및 초기화가 이루어진다. 위성항법장치(GPS, Global Positioning System)와 관성항법장치(INS, Inertial Navigation System)를 이용한 비행 중 항법 초기화를 위해 가장 필요한 것은 롤 각 추정이다. 포강의 강선에 의해 발생하는 초당 20∼30회의 회전력 때문에 롤 각을 추정하는 것은 매우 어려우며 많은 오차를 발생시킨다. 선진국에서 개발 완료된 지능탄약인 M982(Excalibur)의 경우 GPS 수신강도 변화와 회전율을 이용하여 롤 각을 추정한다. 이 방법은 회전율이 일정시간 동안 일정하게 유지되지 않으면 추정 정확도가 떨어지는 등 문제가 있다. 이러한 문제를 개선하기 위해 회전율에 관계없는 새로운 롤 각 추정기법을 제안한바 있다[14]. 이 논문에서는 기 제안한 롤 각 추정기법의 오차가 지능형 탄약의 통합항법과 유도조종에 미치는 영향을 확인하였으며 최종 탄착 정확도 분석을 통해 적용 가능성함을 확인하였다. 이를 위해 성능분석 시스템을 구성하였으며 다양한 유도 기법에서 성능저하가 없음을 확인 하였다. The intelligent ammunition capable of navigation/guided control has built-in high-impact electronics to overcome strong impact and high-speed rotation at the beginning of launch. However, since strong shock and high-speed rotation are applied in a short moment, initial alignment for navigation is impossible, and power is applied and initialized by a thermoelectric battery operated by the amount of shock immediately after launch. The roll angle estimation is the most necessary for initializing navigation during a flight using a Global Positioning System(GPS) and Inertial Navigation System(INS). It is very difficult to estimate the roll angle due to the rotational force of 20 to 30 times per second caused by the steel wire of the gun barrel, and it causes many errors. In the case of M982(Excalibur), an intelligent ammunition developed in united states, the roll angle is estimated by using the change in GPS reception intensity and rotation rate. This method has problems such as poor estimation accuracy if the rotation rate is not kept constant for a certain period of time. To solve this problem, a new roll angle eestimation technique was proposed that is independent of the rotation rate<SUP>[14]</SUP>. In this paper, it was confirmed that the error of the recently proposed roll angle estimation technique does not affect the integrated navigation and guided control of intelligent ammunition, and further confirmed the applicability through the final target hitting accuracy analysis. For this, performance analysis was constructed and it was confirmed that there was no performance degradation in various guidance techniques.

포발사 탄약에 적합한 3차원 유도법칙의 성능개선 기법

신승제(Seung-Je Shin ),김환우(Whan-Woo Kim) 한국항공우주학회 2018 韓國航空宇宙學會誌 Vol.46 No.8

이 논문에서는 정밀유도 포탄의 성능향상을 위한 유도기법을 제안하였다. 본 논문에서 제안하는 기법은 탄의 운동특성분석 없이 탄도와의 오차를 최대한 줄여 탄약의 표적오차를 줄이기 위해서 고안한 기법이다. 이 기법은 탄약의 회전 및 세차운동으로 발생하는 탄내 장착 관성센서의 출력 변동폭을 줄이기 위해 신호처리 기법으로 많이 사용되는 이동평균필터 기법을 적절히 응용한 것으로 관성센서 출력값을 보정하는 것이 목적이다. 단순히 3차원 유도조종 기법을 적용한 경우와 개선기법을 포함하여 적용한 기법의 성능을 비교하였으며, 명확한 성능개선을 확인하였다. 이 기법의 적용으로 유도탄과는 달리 가혹한 환경조건 및 불규칙한 운동 특성을 가지는 포발사 탄약의 탄착 정확도가 개선되는 것을 확인하였다. In this paper, we propose a method to improve the performance by guidance technique and applying it to the precision guided ammunition. The proposed method is a technique designed to reduce the target error of ammunition by reducing the projectile error without analyzing the motion characteristics of the shot. This technique is applied to the moving average filter technique which is widely used as signal processing technique to reduce the fluctuation of the output of the inboard mounting inertial sensor caused by the rotation and the coning motion of the ammunition. In order to compare the performance of the applied technique including the simple 3D guided control technique and the proposed improvement technique. It is confirmed that the application of this technique improves the accuracy of impact of the cannon - launched ammunition with severe environmental conditions and irregular motion characteristics unlike the missile.

신장암에 대한 부분 신절제술 활용 경향 분석

신승제(Seung Jea Shin),김형준(Hyung Joon Kim),고광진(Kwang Jin Ko),성현환(Hyun Hwan Sung),전황균(Hwang Gyun Jeon),정병창(Byong Chang Jeong),서성일(Seong Il Seo),이현무(Hyun Moo Lee),최한용(Han Yong Choi),전성수(Seong Soo Jeon) 대한비뇨기종양학회 2015 대한비뇨기종양학회지 Vol.13 No.3

Purpose: Partial nephrectomy has a similar oncologic outcome to radical nephrectomy while reducing cardiac and metabolic morbidity. However, previous studies reported that partial nephrectomy had been underutilized. The purpose of this study is to analyze trends in the use of partial nephrectomy in Korea and evaluate which individual factors and hospital factor influenced the operative approach. Materials and Methods: Using URO-PDS database, 11560 patients underwent nephrectomy for renal cell carcinoma between 2006 and 2010 were identified. International Classification of Disease (ICD-9) diagnosis codes were applied to target subject of interest. Logistic regression was applied to identify determinants of partial nephrectomy. Results: Over the study period, the proportion of partial nephrectomies has steadily increased from 9.4% in 2006 to 30.4% in 2010 (p<0.001). Deviation of utilization in partial nephrectomy has been observed based on the area (p<0.001) and type of surgery (p<0.001). Individual of younger age, as well as male, were more likely to be treated with partial nephrectomy (p<0.001 for each). Furthermore, Patient treated at hospitals with higher nephrectomy volume were more prone to be treated with partial nephrectomy (p<0.001 for each). Conclusions: Partial nephrectomies have been increasingly performed over the study period but are still underutilized.

테이핑을 동반한 수정된 멀리건 기법 적용이 뇌졸중 환자의 견갑골 자세와 견관절 가동범위에 미치는 영향

김태근,신승제,전영길 대한정형도수물리치료학회 2016 대한정형도수물리치료학회지 Vol.22 No.2