• International Journal of Aeronautical and Space Sciences
• /
• 제18권3호
• /
• pp.512-521
• /
• 2017

This paper reports development process of a university-based sounding rocket using simplified hybrid rocket propulsion system for low-altitude flight application. A hybrid propulsion system was tried to be designed with as few components as possible for more economical, simpler and safer propulsion system, which is essential for the small scale sounding rocket operation as a CanSat carrier. Using blow-down feeding system and catalytic ignition as combustion starter, 250 N class hybrid rocket system was composed of three components: a composite tank, valves, and a thruster. With a composite tank filled with both hydrogen peroxide($H_2O_2$) as an oxidizer and nitrogen gas($N_2$) as a pressurant, the feeding pressure was operated in blowdown mode during thruster operation. The $MnO_2/Al_2O_3$ catalyst was fabricated for propellant decomposition, and ground test of propulsion system showed the almost theoretical temperature of decomposed $H_2O_2$ at the catalyst reactor, indicating sufficient catalyst efficiency for propellant decomposition. Auto-ignition of the high density polyethylene(HDPE) fuel grain successfully occurred by the decomposed $H_2O_2$ product without additional installation of any ignition devices. Performance test result was well matched with numerical internal ballistics conducted prior to the experimental propulsion system ground test. A sounding rocket using the developed hybrid rocket was designed, fabricated, flight simulated and launch tested. Six degree-of-freedom trajectory estimation code was developed and the comparison result between expected and experimental trajectory validated the accuracy of the developed trajectory estimation code. The fabricated sounding rocket was successfully launched showing the effectiveness of the simplified hybrid rocket propulsion system.

• Journal of Platform Technology
• /
• 제10권4호
• /
• pp.3-10
• /
• 2022

본 연구에서는 수소차에 사용되는 수소압력용기 비파괴 안전성 평가 플랫폼 개발을 위해 유한요소해석을 사용하여 안전성 평가 기준 개발에 대한 연구를 수행하였다. Type 4 수소 압력 용기의 안전성을 평가하기 위해 복합 재료의 특성에 따른 매개변수를 바탕으로 재료의 물성을 유한요소 해석을 통해 도출하였다. 이를 통해 수소압력용기에 사용되는 CFRP 복합소재의 기계적 특성을 바탕으로, 내부 결함을 모델링하고 수소압력용기에 대한 평가기준을 사용하여 내부결함에 대한 파손가능성 여부를 도출하는 프로세스를 연구하였다. 결함은 박리, 이물질, 표면 수직균열을 모델링하고 파손 기준에 따른 손상을 분석하여 비파괴검사를 통해 검출된 결함의 안전성 여부를 판단할 수 있는 방법을 연구하였다. 연구 결과 박리 결함은 수소 압력용기의 내부에 근접할수록 파손가능성이 높아졌으며, 수직 균열을 경우 균열의 깊이가 깊어질수록 손상가능성이 높게 나타났다. 또한, 이물질 결함의 경우 압력용기의 외부 방향에 비해 내부 방향에 위치한 경우 손상가능성이 높게 나타났다. 본 연구를 통해 결함의 종류, 형상 및 크기에 따른 수소압력용기의 안전성을 평가할 수 있는 방법을 제시하였으며, 향후 본 연구결과를 바탕으로 수소차량 압력용기의 비파괴시험 안전검사 플랫폼 개발 연구를 수행하고자 한다.

• 소성∙가공
• /
• 제28권4호
• /
• pp.203-211
• /
• 2019

In this study, the weight of type IV pressure vessel is optimized through the burst pressure condition using the finite element analysis (FEA) based on the genetic algorithm (GA). The optimization design variables include the thickness of composite layers and the winding angles. The optimized design variables are validated using the numerical simulations for the pressure vessel. Consequently, the weight is decreased by about 6.5% as compared to the previously reported results for Type III pressure vessel. Additionally, a method which reduces the entire optimization time is proposed. In the original method, the population size is constant across all generations. However, the proposed method could reduce the workload through the reduction of the population size by half for every 25 generations. Thus, the proposed method is observed to increase the weight by about 0.1%, however, the working time for the optimization could be decreased by about 46.5%.