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변영환,허철준 건국대학교 산업기술연구원 1997 건국기술연구논문지 Vol.22 No.-
There are shock tunnel, gun tunnel, piston tunnel and expansion tube as ground-based hypersonic test facilities. Performances of these facilities depend on many things, but mainly characteristics of driver. These drivers are very important impulse facilities but hardly known for lack of theoretical analysis. Most of knowledges about drivers are based on facility developer's own experiences and experimental data. Characteristics of shock wave compression and piston compression have been studied in this reseach to study characteries of drivers of impulse test facilities. Change of ratio of driver pressure to stagnation pressure has been compared to well known results of other researches and it shows very similar trend. Shock wave compression is more effective than piston compression in low pressure, but piston compression is more effective than shock wave compression in high pressure. Results of our gas gun tests show that piston compression is more effective to get higher stagnation pressure in the region of the above 72 of driver pressue ratio.
Performance Optimization of Hypervelocity Launcher System using Experimental Data
Huh, Choul-Jun,Lee, Jin-Ho,Bae, Ki-Joon,Jeon, Kwon-Su,Byun, Yung-Hwan,Lee, Jae-Woo,Lee, Chang-Jin The Korean Society of Mechanical Engineers 2004 JOURNAL OF MECHANICAL SCIENCE AND TECHNOLOGY Vol.18 No.10
This study presents the performance optimization of hypervelocity launcher system by using the experimentall data. During the optimization, the RSM (Response Surface Method) is adopted to find the operating parameters that could maximize the projectile speed. To construct a reliable response surface model, 3 full factorial method is used with the selected design variables, such as piston mass and 2 driver fill pressure. Nine test data could successfully construct the reasonable response surface, which used to yield the optimal operational conditions of the system using the genetic algorithm. The optimization results are confirmed by the experimental test with a good accuracy. Thus, the optimization can improve the performance of the facility.
Performance Optimization of Hypervelocity Launcher System using Experimental Data
Choul-Jun Huh,Jin-Ho Lee,Ki-Joon Bae,Kwon-Su Jeon,Yung-Hwan Byun,Jae-Woo Lee,Chang-Jin Lee 대한기계학회 2004 JOURNAL OF MECHANICAL SCIENCE AND TECHNOLOGY Vol.18 No.10
This study presents the performance optimization of hypervelocity launcher system by using the experimental data. During the optimization, the RSM (Response Surface Method) is adopted to find the operating parameters that could maximize the projectile speed. To construct a reliable response surface model, 3 full factorial method is used with the selected design variables, such as piston mass and 2 driver fill pressure. Nine test data could successfully construct the reasonable response surface, which used to yield the optimal operational conditions of the system using the genetic algorithm. The optimization results are confirmed by the experimental test with a good accuracy. Thus, the optimization can improve the performance of the facility.
이진호(Jin-ho Lee),허철준(Choul-Jun Huh),배기준(Ki-Joon Bae),배영우(Yung-Woo Bae),변영환(Yung-Hwan Byun),이재우(Jae-Woo Lee),장조원(Jo-Won Chang) 한국항공우주학회 2004 韓國航空宇宙學會誌 Vol.32 No.8
본 연구에서 시험부 크기 30㎜×35.6㎜, Run Time 20초인 소형-저가의 초음속 풍동 을 개발하였다. 개발된 교육용 초음속 풍동은 단속적 불어내기식형이며, 노즐 블록 교체 형으로 설계되었다. 본 연구를 통하여 초음속 용동에 사용되는 대형-고가의 기계장비를 기존 소형의 상용 제품으로 대체하여 제작 단가를 낮추었다. 그리고 초음속 풍동의 핵심 기술인 노즐 설계를 비롯한 전체적인 초음속 풍동 설계 기술을 확보하였다. 풍동 시험부에서의 초음속 유동장 형성 및 유동 안정성에 대한 성능검증 실험을 수행하였다. A small size - low priced supersonic wind tunnel of which test section size is 30㎜ by 35.6㎜ and run time is 20sec is developed. This educational supersonic wind tunnel is an intermittent blowdown type with an exchangeable nozzle block. In this study, the proper sized and low priced commercial parts are used to reduce the total cost of supersonic wind tunnel. A nozzle design and small supersonic wind tunnel design process has been established, and it is confirmed that a given supersonic flow field has been obtained and proved by experiment.