• Journal of the Korean Society of Propulsion Engineers
• /
• v.20 no.4
• /
• pp.59-67
• /
• 2016

Numerical simulations have been performed to investigate thrust characteristics of a through-type pintle nozzle with or without flow separation at various operating altitudes. The low Reynolds number $k-{\varepsilon}$ with compressibility correction proposed by Sarkar are applied. The detail flow structures are observed and static pressures along nozzle wall are compared with experimental results. The flow separation in the pintle nozzle disappears and jet plume strongly expands as its operating altitude increases. To evaluate the thrust characteristics, the momentum term and pressure term of thrust are analyzed. Thrust and thrust coefficient at altitude 20 km are about 10% more than them at the ground 0km.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.44 no.2
• /
• pp.116-122
• /
• 2016

The performance characteristics of a TBCC engine considering the transition mode from a turbojet to a ramjet engine has been investigated. The performance of each engine was proposed and a transition mode of the TBCC engine has been evaluated by adjusting the operating rate of the ramjet engine and turbojet engine performance changes continuously. Based on the transition model, it was confirmed that the performance is continuously changed at various flight Mach numbers and altitudes. The performance characteristics including thrust and specific impulse considering various flight conditions and transition mode were analyzed, which testifies characteristics of the engine itself, as well as transition of the combined cycle.

• Aerospace Engineering and Technology
• /
• v.3 no.1
• /
• pp.65-78
• /
• 2004

This research was conducted for an acquisition of the ramjet engine test facility design technique which are concerned about freejet type test facility. In this research, we concentrated on the design technique and the construction technique of the vitiation air heater(VAH), test section, diffuser and ejector. Based on the operating modes of the basic test facility, ten operating modes in coordinates "Altitude-Mach number" was regenerated from Mach 2, Altitude 0km to Mach 5, Altitude 15km. In this operating modes, we calculated a design parameter of the supersonic nozzle, VAH, diffuser and ejector and acquired a technique for the ramjet test facility operating and repairing.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2010.11a
• /
• pp.807-808
• /
• 2010

To insert payload to the orbit over the 200km-altitude using launch vehicle which has 300sec the Isp, multi staging technique for launch is necessary. The range between the sea-level to the transfer orbit about 200~250km is for operation of 1st and 2nd rocket engines and the higher altitude is for propulsion system of the acceleration block and satellite. The upper stage rocket engine should have the high technology for entering the payload into the orbit precisely more than the performance for high thrust level. With this investigation of the upper stage rocket engines which have been used, we want to understand their development trend and prospect which is going to be references for the development of ours.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2012.05a
• /
• pp.167-171
• /
• 2012

A computational analysis of nozzle flow is conducted to investigate effects of the flight altitude on thrust performance. Reynolds-averaged Navier-Stokes equation with k-${\omega}$ SST(Shear Stress Transport) turbulence model is employed to simulate the nozzle flow in various altitude conditions, where continuum mechanics is to be valid. Thrust performance of the nozzle is exceedingly poor upto 10 km of flight altitude because of the irreversible phenomena such as shock and/or flow separation occurring inside the nozzle, whereas it is restored to the nominal value as the altitude is attained higher than 30 km.

• Defense and Technology
• /
• no.9 s.247
• /
• pp.62-73
• /
• 1999

최근 전자기술을 적극적으로 활용하는 제어시스템이나 기기의 증가 추세가 예상외로 빠르게 증가하고 있다. 지금까지 유압이나 공기력으로 작동되었던 시스템 또는 릴레이나 스위치 등의 전기부품으로 구성된 시스템에 마이크로 프로세서를 중심으로 하는 디지털 기술을 도입하여 소형, 경량화가 가능하게 되고 성능이나 기능도 비약적으로 고도화 되고 있다

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2007.11a
• /
• pp.359-364
• /
• 2007

Spray characteristics of the APU gas turbine engine were investigated. In order to understand blow out phenomena of the APU engine, we performed fuel spray test. In the test, four operating conditions such as sea level idle, sea level max power, 20,000 feet idle, 20,000 feet max power were used as spray experimental conditions. PDPA(phase Doppler Particle Analyzer) was used for measuring the particle diameter and velocity. Also spray visualization was performed by using ND-YAG sheet laser beam. From the test result, in the case of 20,000 feet idle condition, SMD is about 100 ${\mu}m$ and maximum particle velocity is about 10 m/s. For the flame stability, spray quality should be improved at 20,000 feet idle condition.

• Journal of the Korean Data and Information Science Society
• /
• v.28 no.5
• /
• pp.1145-1152
• /
• 2017

Environmental tests are used to verify an equipment that can withstand the rigors of harsh environments. In general, military products have lots of experiences with extreme environment compared to commercial products. Therefore, the military products used in mountains require a tailoring process about temperature drop for the environmental test. The International Organization for Standardization publishes that the coefficient of temperature drop is $-6.5^{\circ}C/1000m$ from all around the world. However, there is no the criteria in the South Korea. In this paper, we calculate the coefficient of temperature drop. Also, an equation used as a tailoring process for a low temperature test of the products has been suggested.

• Proceedings of the Optical Society of Korea Conference
• /
• 2003.02a
• /
• pp.280-281
• /
• 2003

본 연구는 전자파, 표류전압, 정전기 등 위험한 환경에서 충분한 안전성과 우수한 성능을 보이며 금속발열선(HBW)에 비해 빠른 작동시간을 가지는 반도체브리지 착화장치를 개발하여 로켓 추진기관 및 자동차 에어백 (Air-Bag)에 적용하는데 그 목적이 있다. 로켓 추진기관 착화장치 및 안전장치에는 고도의 안전성 및 신뢰성이 요구되어 기존의 금속발열선 착화장치보다 전자파, 표류전압, 정전기 등 위험한 환경에서 충분한 안정성과 제품의 신뢰도를 향상시킬 수 있는 신기술 착화장치 설계사양이 요구되며 자동차 에어백용 인플레이터(inflater)는 에어백에 공급하는 가스를 발생시키기 위한 초기 구성품으로 자동차의 특성상 높은 작동신뢰성 유지와 주변 환경으로부터의 안전성이 요구되어 현존하는 금속발열선형 착화장치를 대체하는 반도체브리지 착화장치 개발이 필수적인 상황이다. (중략)

• Aerospace Engineering and Technology
• /
• v.4 no.2
• /
• pp.27-35
• /
• 2005

In this study, a performance analysis code was developed for the off-design performance analysis of air turbo ramjet(ATR) engine, and the analyses were performed for the pre-designed ATR engine at several operating points in the envelope. Variable intake and thrust nozzle were assumed to cover the wide envelope. Mathematical models for each components were developed to calculate their off-design performance. Simple design formulas were introduced for some components to explore the performance variation versus the design parameters. As a result, the pre-defined engine couldn't cover the entire mission profile. And it was also found that the effect of the pre-cooler was not very great, especially in the region of low Mach number.