• Current Industrial and Technological Trends in Aerospace
• /
• v.4 no.1
• /
• pp.44-54
• /
• 2006

초음속 또는 극초음속 비행체용 추진기관은 산화재 공급방식에 따라 공기흡입형과 로켓 그리고 이들을 혼합한 형태인 복합사이클 추진기관으로 구분할 수 있다. 그러나 재사용이 가능하다는 측면에서 미래의 추진기관들은 공기흡입형과 복합사이클 추진기관들이 주류를 이룰 것으로 예상된다. 본 논문에서는 차세대 초고속 추진기관으로 유력시 되고 있는 공기흡입형 추진기관들 중에서 램/스크램 제트 추진기관들을 중심으로 세계적인 개발동향과 기술개념을 기술하였으며 이 두 가지 추진기관들을 바탕으로 구성된 복합사이클 추진기관들에 대한 개념들을 소개하였다. 항공우주선진국들을 중심으로 차세대 고속비행체 및 고속추진기관의 실용화 개발 움직임들이 구체화 되고 있는 가운데 최근 들어 비록 미약하지만 한국항공우주연구원을 비롯한 몇 개의 기관 및 대학에서 램제트/스크램제트 추진기관에 대한 핵심 요소기술 연구들이 진행되고 있는 것은 그나마 다행이라 할 수 있으며 본 논문이 차세대 초고속 추진기관에 대한 이해를 돕는데 도움이 되기를 기대한다.

• Journal of the Society of Disaster Information
• /
• v.19 no.3
• /
• pp.608-623
• /
• 2023

Purpose: Recently, the number of logistics warehouses has been on the rise. In addition, as the number of such logistics warehouses increases, number of fire accidents also increases every year, increasing the importance of preventing fires in large logistics warehouses. Method: investigated aspirating smoke detectors that are emerging as adaptive fire detectors in logistics warehouses. Then, through fire simulation (FDS), logistics warehouse modeling was conducted to compare and analyze the detection speed of general smoke detectors and aspirating smoke detectors according to four stages of fire growth and three locations of fire in the logistics warehouse. Result: Growth speed in Slow-class fires and Mediumclass fires, the detection speed of aspirating smoke detectors was faster regardless of the location of the fire. However, in Fast-class fires and Ultra-Fast-class fires, it was confirmed that the detection speed of general smoke detectors was faster depending on the location of the fire. Conclusion: It was confirmed that the detection performance of the aspirating smoke detector decreased as the fire growth speed increased and the location of the fire occurred further than the receiver of the aspirating smoke detector. Therefore, even if an aspirating smoke detector is installed in a warehouse that stores combustibles with high fire growth rates, it is judged that an additional smoke detector is attached far away from the receiver of the general smoke detector to increase fire safety.

• Fire Science and Engineering
• /
• v.17 no.4
• /
• pp.86-91
• /
• 2003

Since the air stream in the room controlled by HVAC system affects on he expected response of conventional detectors which are designed in accordance with normal characteristics of air stream in the fire incident, unexpected operation time delay may occur in fire. In order to solve this problem and to improve sensitivity so that to initiate fire in its early stages for minimizing damage and protecting people, we studied and developed Air Sampling Smoke Detector. The Air Sampling Smoke Detector is a kind of active-type fire detection system. it draws air continuously from the protected area through an air sampling pipe network to the smoke density analyzer. This study presents smoke density analysing technique and air intake balancing technique through an air sampling pipe network. As a result of evaluating, Air Sampling Smoke Detector was much more sensitive than conventional smoke detectors that passively wait for smoke to reach them and was not affected by ambient airflow in the room by means of balanced air intake through the sampling holes.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.11a
• /
• pp.992-995
• /
• 2011

A study on the performance design schemes of the supersonic air intakes applied to the supersonic air-breathing propulsion system(Ramjet/Scramjet) was conducted and for two kinds of air intakes, the preliminary configuration designs and the performance analysis models were established. For axisymmetric conical air intake and two dimensional rectangular air intake, the performance effects were assessed according to compression angles and shock wave numbers.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2012.05a
• /
• pp.424-428
• /
• 2012

Air-breathing Propulsion System is one of the promising propulsion systems because of low cost, easy storage, compactness and simplicity. A study of gas generator propellant for air-breathing propulsion system was performed in this paper. Amorphous Boron Powder was applied in propellant with various kinds of additives to determine combustion characteristics. And boron beads were made to apply them to the propellant. Combustion characteristics of propellant using amorphous boron powder and boron beads was compared.

• Proceedings of the Korean Institute of IIIuminating and Electrical Installation Engineers Conference
• /
• 2007.11a
• /
• pp.267-270
• /
• 2007

오존무 분사장치는 흡입구와 내에 소정의 공간이 형성된 케이스와 자동 손잡이와 $360^{\circ}$회전이 가능해 운반 및 이동이 간편한 케이스, 상기 케이스의 내부 소정 부위에 공기 흡입구로 흡입되는 공기 중에 포함된 먼지 및 습기를 제거하는 제습 장치와, 원료가스인 공기를 일정하게 제공하는 송풍기, 강력한 살균 소독기능을 지닌 오존발생기, 오존을 발생시키기 위한 고주파 펄스 전원장치, 입자경이 $3{\sim}40{\mu}m$이하의 이류체 미세 분사형 노즐, 살수통(물을 담는 용기) 및 기능 조절부(펄스전원제어, 타이머 조절, 송풍기 제어, 이류체 미세 분사형 노즐스위치 제어)로 성되어 작동하는 것으로 일반적인 가습기와는 다르다. 그리고 강력한 살균, 소독, 탈취 및 대기의 정화 기능이 있는 오존을 이용하는 동시에 기존의 방식보다 간단한 구조의 분무발생 수단을 구비함으로써 전체적으로 구성을 간단하게 하면서 대기 정화 효율을 향상시키는 장점이 있다.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.14 no.6
• /
• pp.9-16
• /
• 2010

The SFRJ(Solid Fuel Ram-Jet) propulsion is attractive for projectiles because of the combination of high propulsive performance and low system complexity more than conventional projectiles. The Objective of this research was to characterize the inlet aerodynamic characteristics (center-body & pitot type) in SFRJ. Diffuser static pressure & combustion chamber pressure was tested and the AoA was changed $0^{\circ}$ and $4^{\circ}$ at Mach number of 3.0 for performance estimate. The performance study of inlet was carried out with the Schlieren system and Supersonic cold-flow system. Under mach 3.0, the center-body showed twice higher total pressure recovering ratio than the pitot type. A Computational fluid dynamic solution is applied internal flow of inlet and the solutions are compared with experimental results.

• Proceedings of the Korean Society of Disaster Information Conference
• /
• 2023.11a
• /
• pp.81-82
• /
• 2023

디지털 트윈 플랫폼을 적용하여 가동원전의 화재 안전성을 강화시키고자 한다. 원전에 특화된 화재 감지, 진압 설비를 개발하면서 디지털 트윈에 적용하기 위하여 수집해야 할 데이터에 대한 연구를 수행하고 있다. 본 연구에 대해서 원전에 특화된 공기흡입형 감지모듈과 미분무 소화설비를 개발하고 있으며 제품에 대한 DB를 구축하여 디지털 트윈에 적용시키고자 유니티(Unity) 툴을 이용하여 파일럿 규모의 전기실 화재에 대한 모델링을 수행하였다. 추후 실규모의 소방 시스템을 제작하고 적용 가능한 센서를 통해 데이터를 수집할 것이며, 이를 통해 디지털 트윈 플랫폼을 구축하여 CDF 저감에 기여할 것으로 기대된다.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.50 no.5
• /
• pp.297-308
• /
• 2022

Most air-breathing aircraft operated in the hypersonic region are equipped with a scramjet engine. In a scramjet engine, a shock wave generated at an inlet acts as a compressor for a general gas turbine engine instead, so total pressure loss caused by the shock wave is considered very important. In this study, to minimize total pressure loss, a method of designing an external compression inlet using isentropic compression surface was proposed, and an external compression inlet with 3-deflection angles and Busemann inlet were designed under the same conditions. After that, through computational analysis, the performance characteristics at off-design conditions were compared. Each inlet shape was truncated according to the length of the 3-ramp external compression inlet, and the boundary layer correction was performed. The isentropic external compression inlet showed superior performance at the design point, but under the off-design conditions, its performance was degraded compared to the 3-ramp external compression inlet.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.45 no.12
• /
• pp.1031-1038
• /
• 2017

In order to improve the performance of the air breathing engines, it is important to maximize the total pressure recovery through air intake. In this study, we investigated whether the Oswatitsch method, which guarantees the maximum pressure recovery for supersonic intake, is effective at hypersonic speed by compressing the intake air with the same intensity at each ramp. The non-linearity of the shock wave normal Mach number at each ramp stage was analyzed by comparing the compression ramp angle and the number of ramp to the inflow Mach number in terms of compressible thermodynamics and the operation limits of the inlet. Based on this analysis, the Oswaitisch technique yields valid conditions not only in supersonic but also hypersonic flight regime.