PET/CT에서 재구성 프로그램의 성능 평가

임정진,윤석환,김종필,남궁식,신성화,윤상혁,김영석,이형진,이홍재,김진의,우재룡,Lim, Jung Jin,Yoon, Seok Hwan,Kim, Jong Pil,Nam Koong, Sik,Shin, Seong Hwa,Yoon, Sang Hyeok,Kim, Yeong Seok,Lee, Hyeong Jin,Lee, Hong Jae,Kim, Jin Eui,Woo, 대한핵의학기술학회 2012 핵의학 기술 Vol.16 No.2

암의 조기검진 및 수술 전후 추적검사에 유용하게 이용되고 있는 PET/CT는 영상의 질을 향상시키기 위하여 기계적인 성능 향상과 더불어 영상 재구성방법도 발전되어 왔다. 본 연구는 Time of Flight (TOF)를 기반으로 한 재구성 프로그램들에 대하여 영상의 질을 평가하고자 한다. Gemini TF, Biograph mCT, Discovery 690을 이용하여 phantom 영상을 동일한 조건으로 2분 동안 영상을 획득 후 Astonish TF, ultraHD PET, SharpIR을 적용한 것과 적용하지 않은 것에 대하여 영상을 재구성하였다. Flangeless Esser PET phantom 의 내부에는 $^{18}F$-FDG 1.11 kBq/ml (30 ${\mu}Ci/ml$)를 채우고 4개의 열소 원통(8, 12, 16, 25 mm)에는 8.88 kBq/ml (240 ${\mu}Ci/ml$)를 채워서 배후 방사능과 열소 원통 방사능의 비율이 1:8이 되도록 제작하였고 triple line phantom의 내부에는 $^{18}F$-FDG 37 MBq (1 mCi)를 채우고 세 개의 line에는 0.37 MBq/ml (100 uCi)를 주입하여 제작하였다. Flangeless Esser PET phantom을 사용한 재구성 영상에서 contrast ratio와 background variability를 구하였고, triple line phantom을 사용한 재구성 영상에서 resolution을 측정하였다. Phantom lid 크기가 8, 12, 16, 25 mm에서의 contrast ratio는 Astonish TF를 적용하지 않은 영상에서 8.69, 12.28, 19.31, 25.80%, 적용한 영상에서는 6.24, 13.24, 19.55, 27.60%, ultraHD PET를 적용하지 않은 영상에서 4.94, 12.68, 22.09, 30.14%, 적용한 영상에서는 4.76, 13.23, 23.72, 31.65%, SharpIR를 적용하지 않은 영상에서 13.18, 17.44, 28.76, 34.67%, 적용한 영상에서는 13.15, 18.32, 30.33, 35.73%로 나타났다. Background variability는 Astonish TF를 적용하지 않은 영상에서 5.51, 5.42, 7.13, 6.28%, 적용한 영상에서는 7.81, 7.94, 6.40, 6.28%, ultraHD PET를 적용하지 않은 영상에서 6.46, 6.63, 5.33, 5.21%, 적용한 영상에서는 6.08, 6.08, 4.45, 4.58%, SharpIR를 적용하지 않은 영상에서 5.93, 4.82, 4.45, 5.09%, 적용한 영상에서는 4.80, 3.92, 3.63, 4.50%로 나타났다. Phantom line 위치가 upper, center, right에서의 resolution은 Astonish TF를 적용하지 않은 영상에서 10.77, 11.54, 9.34 mm, 적용한 영상에서는 9.54, 8.90, 8.88 mm, ultraHD PET를 적용하지 않은 영상에서 7.84, 6.95, 8.32 mm, 적용한 영상에서는 7.51, 6.66, 8.27 mm, SharpIR를 적용하지 않은 영상에서 9.35, 8.69, 8.99 mm, 적용한 영상에서는 9.88, 9.18, 9.00 mm로 나타났다. TOF를 기반으로 하여 영상의 질을 향상시키기 위한 재구성 프로그램 사용 시 전반적으로 영상의 질적 향상이 이루어짐을 알 수 있었다. 또한 제조사별 재구성 프로그램 비교에 대해서는 어느 정도의 결과 값의 차이를 보였지만 이는 제조사별 장비의 특성과 재구성 알고리즘의 차이로 인한 결과라고 생각된다. 따라서 각 병원에서는 영상의 질을 향상시키기 위해 사용되는 재구성 프로그램을 이용함에 있어서 프로그램에 맞는 적절한 재구성 조건을 찾기 위한 추가적인 연구가 필요할 것으로 사료된다. Purpose : PET/CT is widely used for early checking up of cancer and following up of pre and post operation. Image reconstruction method is advanced with mechanical function. We want to evaluate image quality of each reconstruction program based on time of flight (TOF). Materials and Methods : After acquiring phantom images during 2 minutes with Gemini TF (Philips, USA), Biograph mCT (Siemens, USA) and Discovery 690 (GE, USA), we reconstructed image applied to Astonish TF (Philips, USA), ultraHD PET (Siemens, USA), Sharp IR (GE, USA) and not applied. inside of Flangeless Esser PET phantom (Data Spectrum corp., USA) was filled with $^{18}F$-FDG 1.11 kBq/ml (30 Ci/ml) and 4 hot inserts (8. 12. 16. 25 mm) were filled with 8.88 kBq/ml (240 ${\mu}Ci/ml$) the ratio of background activity and hot inserts activity was 1 : 8. Inside of triple line phantom (Data Spectrum corp., USA) was filled with $^{18}F$-FDG 37 MBq/ml (1 mCi). Three of lines were filled with 0.37 MBq (100 ${\mu}Ci$). Contrast ratio and background variability were acquired from reconstruction image used Flangeless Esser PET phantom and resolution was acquired from reconstruction image used triple line phantom. Results : The contrast ratio of image which was not applied to Astonish TF was 8.69, 12.28, 19.31, 25.80% in phantom lid of which size was 8, 12, 16, 25 mm and it which was applied to Astonish TF was 6.24, 13.24, 19.55, 27.60%. It which was not applied to ultraHD PET was 4.94, 12.68, 22.09, 30.14%, it which was applied to ultraHD PET was 4.76, 13.23, 23.72, 31.65%. It which was not applied to SharpIR was 13.18, 17.44, 28.76, 34.67%, it which was applied to SharpIR was 13.15, 18.32, 30.33, 35.73%. The background variability of image which was not applied to Astonish TF was 5.51, 5.42, 7.13, 6.28%. it which was applied to Astonish TF was 7.81, 7.94, 6.40 6.28%. It which was not applied to ultraHD PET was 6.46, 6.63, 5.33, 5.21%, it which was applied to ultraHD PET was 6.08, 6.08, 4.45, 4.58%. It which was not applied to SharpIR was 5.93, 4.82, 4.45, 5.09%, it which was applied to SharpIR was 4.80, 3.92, 3.63, 4.50%. The resolution of phantom line of which location was upper, center, right, which was not applied to Astonish TF was 10.77, 11.54, 9.34 mm it which was applied to Astonish TF was 9.54, 8.90, 8.88 mm. It which was not applied to ultraHD PET was 7.84, 6.95, 8.32 mm, it which was applied to ultraHD PET was 7.51, 6.66, 8.27 mm. It which was not applied to SharpIR was 9.35, 8.69, 8.99, it which was applied to SharpIR was 9.88, 9.18, 9.00 mm. Conclusion : Image quality was advanced generally while reconstruction program which is based on time of flight was used. Futhermore difference of result compared each manufacture reconstruction program showed up, however this is caused by specification of instrument of each manufacture and difference of reconstruction algorithm. Therefore we need further examination to find out appropriate reconstruction condition while using reconstruction program used for advance of image quality.

비행 임무에 따른 조종사 스트레스 차이에 대한 연구

이동호,조영진 한국항공운항학회 2022 한국항공운항학회지 Vol.30 No.2

This study is a study to analyze the stress difference of pilots according to the category of aircraft. According to previous studies, pilot stress is affected by several factors such as flight time, fatigue regulation, and operating environment, and it is known that stress also affects cardiac variability. In this paper, we analyzed that there is a difference in stress according to the operating environment through airline pilots and pilots of educational institutions, and then tested the difference in stress between airplane pilots and helicopter pilots. This study differs in that it is a study that has almost no empirical research on pilot fatigue and stress considering the role of flight crew members and operational conditions for each mission. If we expand and verify the sample of the results for the stress difference in the future, it will be a great contribution to practical aviation safety research in connection with the fatigue risk management system in the future.

가변스팬 모핑 항공기 종방향 운동의 준선형 파라미터 변이 모델링

이지훈(Jihoon Lee),정승윤(Seungyun Jung),김성훈(Seong-hun Kim),이한나(Hanna Lee),김유단(Youdan Kim) 한국항공우주학회 2017 한국항공우주학회 학술발표회 논문집 Vol.2017 No.11

Lateral Vehicle Control Based on Active Flight Control Technology

Seo Young-Bong,Choi Jae-Weon,Duan Guang Ren The Korean Society of Mechanical Engineers 2006 JOURNAL OF MECHANICAL SCIENCE AND TECHNOLOGY Vol.20 No.7

In this paper, a lateral vehicle control using the concept of control configured vehicle (CCV) is presented. The control objectives for the lateral dynamics of a vehicle include the ability to follow a chosen variable without significant motion change in other specified variables. The analysis techniques for decoupling of the aircraft motions are utilized to develop vehicle lateral control with advanced mode. Vehicle lateral dynamic is determined to have the steering input and control torque input. The additional vehicle modes are also defined to using CCV concept. We use right eigenstructure assignment techniques and command generator tracker to design a control law for an lateral vehicle dynamics. The desired eigenvectors are chosen to achieve the desired decoupling (i.e., lateral direction speed and yaw rate). The command generator tracker is used to ensure steady-state tracking of the driver's command. Finally, the developed design is utilized by using the lateral vehicle dynamic with four wheel.

Lateral Vehicle Control Based on Active Flight Control Technology

Young Bong Seo,Jae Weon Choi,Guang Ren Duan 대한기계학회 2006 JOURNAL OF MECHANICAL SCIENCE AND TECHNOLOGY Vol.20 No.7

In this paper, a lateral vehicle control using the concept of control configured vehicle (CCV) is presented. The control objectives for the lateral dynamics of a vehicle include the ability to follow a chosen variable without significant motion change in other specified variables. The analysis techniques for decoupling of the aircraft motions are utilized to develop vehicle lateral control with advanced mode. Vehicle lateral dynamic is determined to have the steering input and control torque input. The additional vehicle modes are also defined to using CCV concept. We use right eigenstructure assignment techniques and command generator tracker to design a control law for an lateral vehicle dynamics. The desired eigenvectors are chosen to achieve the desired decoupling (i.e., lateral direction speed and yaw rate). The command generator tracker is used to ensure steady-state tracking of the driver's command. Finally, the developed design is utilized by using the lateral vehicle dynamic with four wheel.

Variable stability system control law development for in-flight simulation of pitch/roll/yaw rate and normal load

Ko, Joon Soo,Park, Sungsu The Korean Society for Aeronautical and Space Scie 2014 International Journal of Aeronautical and Space Sc Vol.15 No.4

This paper describes the development of variable stability system (VSS) control laws for the KFA-i to simulate the dynamics of KFA-m aircraft. The KFA-i is a single engine, Class IV aircraft and was selected as an in-flight simulator (IFS) aircraft, whereas the KFA-m is a simulated aircraft that is based on the F-16 aircraft. A 6-DoF math model of KFA-i aircraft was developed, linearized, and separated into longitudinal and lateral motion for VSS control law synthesis. The KFA-i aircraft has five primary control surfaces: two flaperons, two all movable horizontal tails, and one rudder. Flaperons are used for load control, the horizontal tails are used for pitch and roll rate control, and the rudder is used for yaw rate control. The developed VSS control law can simulate four parameters of the KFA-m aircraft simultaneously, such as pitch, roll, yaw rates, and load. The simulation results show that KFA-i follows the responses of KFA-m with high accuracy.

한국형 공중 시뮬레이터 항공기 연구

고준수,안종민,박성수,Ko, Joon-Soo,Ahn, Jong-Min,Park, Sung-Su 한국군사과학기술학회 2011 한국군사과학기술학회지 Vol.14 No.6

This paper presented here contains development of variable stability system(VSS) control laws for the KIFS (Korean In-Flight Simulator) aircraft to simulate the dynamics of F-16 aircraft. Development of VSS Control law for pitch rate, roll rate, yaw rate simulation for three specified flight conditions using Model Following Technique with rate feedback autopilot for stability provision. The direct lift force controller was also added to the developed VSS control law to simulate the pitch rate and normal g-load simultaneously. The simulation results show high accuracy of F-16 aircraft's pitch, roll, yaw rate and g-load simulation.

항공기 지상이동시간 예측 연구

김준혁,서영성 한국교통연구원 2020 交通硏究 Vol.27 No.3

The accurate calculation of the variable taxi time(VTT) is to get efficient flow of aircraft at the airport. In this study, we propose models that can predict VTT. The regression model is used to predict VTT. FOIS(Flight Operation and Information System) data and ASDE(Airport Surface Detection System) data of Jeju international airport are used to generate the necessary data set for VTT prediction. An analysis of the factors that affect VTT is made. The effectiveness of the VTT prediction model is analyzed by comparing the predicted VTT with actual observations. 공항의 지상에서 이동하는 항공기의 흐름을 효율적으로 조절하고 항공기가 지상에서 점유하는 시간을 단축하기 위해서는 항공기 지상이동시간의 정확한 산정이 필요하다. 본 연구에서는 회귀모형을 이용한 항공기의 지상이동시간 예측 모형을 제안한다. 제주공항의 운항 및 비행정보시스템(Flight Operation and Information System, FOIS)의 자료와 공항지상감시레이더(Airport Surface Detection Equipment, ASDE)의 자료를 이용하여 항공기 지상이동시간 예측에 필요한 데이터 집합을 생성하고 항공기의 지상이동시간에 영향을 미치는 요소를 분석한다. 예측한 항공기 지상이동시간과 실제 관측치를 비교하여 본 연구에서 제안한 예측모형의 유효성을 분석한다.

Variable stability system control law development for in-flight simulation of pitch/roll/yaw rate and normal load

고준수,박성수 한국항공우주학회 2014 International Journal of Aeronautical and Space Sc Vol.15 No.4

This paper describes the development of variable stability system (VSS) control laws for the KFA-i to simulate the dynamics ofKFA-m aircraft. The KFA-i is a single engine, Class IV aircraft and was selected as an in-flight simulator (IFS) aircraft, whereasthe KFA-m is a simulated aircraft that is based on the F-16 aircraft. A 6-DoF math model of KFA-i aircraft was developed,linearized, and separated into longitudinal and lateral motion for VSS control law synthesis. The KFA-i aircraft has five primarycontrol surfaces: two flaperons, two all movable horizontal tails, and one rudder. Flaperons are used for load control, thehorizontal tails are used for pitch and roll rate control, and the rudder is used for yaw rate control. The developed VSS controllaw can simulate four parameters of the KFA-m aircraft simultaneously, such as pitch, roll, yaw rates, and load. The simulationresults show that KFA-i follows the responses of KFA-m with high accuracy.

Variable Stability System Control law Development for In-Flight Simulation of Pitch/Roll/Yaw Rate and Normal Load

Joon Soo Ko,Sungsu Park 한국항공우주학회 2014 International Journal of Aeronautical and Space Sc Vol.15 No.4

This paper describes the development of variable stability system (VSS) control laws for the KFA-i to simulate the dynamics of KFA-m aircraft. The KFA-i is a single engine, Class IV aircraft and was selected as an in-flight simulator (IFS) aircraft, whereas the KFA-m is a simulated aircraft that is based on the F-16 aircraft. A 6-DoF math model of KFA-i aircraft was developed, linearized, and separated into longitudinal and lateral motion for VSS control law synthesis. The KFA-i aircraft has five primary control surfaces: two flaperons, two all movable horizontal tails, and one rudder. Flaperons are used for load control, the horizontal tails are used for pitch and roll rate control, and the rudder is used for yaw rate control. The developed VSS control law can simulate four parameters of the KFA-m aircraft simultaneously, such as pitch, roll, yaw rates, and load. The simulation results show that KFA-i follows the responses of KFA-m with high accuracy.