• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.11a
• /
• pp.317-320
• /
• 2011

Hydrogen peroxide turbopump was designed for bi-propellant liquid rocket engine using hydrogen peroxide and kerosene as propellants. Turbopump operation was verified through water tests. Design conditions of hydrogen peroxide turbopump were determined, and impeller was designed. Turbine which drives pump was selected from commercial turbocharger. Gas generator was designed by reference from turbine map. Pump, turbine, gas generator were integrated, and turbopump system was constructed. Turbopump supplied water by 1.47 bar of pressure and as well as 3.4 kg/s of mass flow rate.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2003.10a
• /
• pp.253-256
• /
• 2003

The engine core of a 65hp-turboshaft engine for UAV is developed and modified into a 55lbf-turbojet engine. Since the core engine is installed with a propelling nozzle, which has the same mass flow characteristics as the power generator of the turboshaft engine its mechanical and aerodynamic characteristics are basically the same as those of the complete engine. Engine output is not shaft power but thrust force that is easier to measure. The core engine is very useful for core test purpose. Besides, the core engine itself can be directly used for propulsion of small air vehicles.

• The Journal of Korean Institute of Communications and Information Sciences
• /
• v.28 no.9C
• /
• pp.843-850
• /
• 2003

Turbo coding and turbo processing have been known as methods close to Shannon limit in the aspect of wireless MIMO communications similarly to wireless single antenna communication. The iterative processing can maximize the mutual effect of coding and interference cancellation, but turbo coding has not been used for turbo processing because of the inherent decoding process delay. This paper proposes a turbo coded MIMO system with adaptive turbo parallel space-time (Turbo-PAST) processing for high-speed wireless communications and a enhanced cyclic redundancy check (E-CRC) scheme as an efficient and simple priori stopping criterion. Simulation results show that the Turbo-PAST outperforms conventional system with 1.3dB and the proposed E-CRC scheme effectively reduces the amount of turbo processing iterations from the point of average number of iterations.

• The Journal of Korean Institute of Communications and Information Sciences
• /
• v.38A no.10
• /
• pp.850-857
• /
• 2013

Turbo equalizer system is a method which can improve performance through a combination of the equalizer and decoder. The turbo equalizer has been mainly used a MAP equalizer. However, this turbo equalizer has a disadvantage that has a high computational complexity. To overcome the disadvantage and to improve efficiency of bandwidth, blind turbo equalization system is proposed. blind turbo equalization system has low equalization performance than conventional turbo equalization system. To circumvent this problem, we adapt the beamforming method based on the MUSIC algorithm. we confirmed that the proposed method improves the equalization performance.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2008.11a
• /
• pp.129-132
• /
• 2008

For the development of the 30tonf level LOx/kerosene liquid rocket engine, turbopump-gas generator closed-loop coupled tests are performed. To simulate engine operation conditions, combustion chamber was substituted by flow control orifices. In simulated engine system operation environment, chill-down procedure, startup characteristics, nominal operability of turbopump+gas generator coupled Test Plant are confirmed. Turbopump and gas generator are confirmed to operate well in simulated engine environment. The control system for regulating power and mixture ratio of Test Plant are also successfully confirmed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2012.05a
• /
• pp.11-15
• /
• 2012

A rotordynamic analysis is performed for a 7 ton class turbopump applied to the third stage LRE(Liquid Rocket Engine) of the KSLV(Korea Space Launch Vehicle). Based on the heritage of the developed experimental 30 ton class turbopump and developing 75 ton class turbopump for the KSLV first and second stage LRE, the 7 ton class turbopump is designed as an one-axis rotor turbopump. Two rotor systems comprised of one oxidizer pump assembly and the other fuel pump-turbine assembly are connected each other using a spline shaft and operating at a design speed. Through the rotordynamic analysis, it is investigated that the turbopump acquires sufficient separate margin of critical speed as a sub-critical rotor.

• The Journal of Korean Institute of Communications and Information Sciences
• /
• v.36 no.9C
• /
• pp.537-545
• /
• 2011

This paper analyzed performance of three dimensional turbo code and turbo ${\Phi}$ codes proposed in the next generation DVB-RCS systems. In the view of turbo ${\Phi}$ codes, we proposed the optimal permutation and puncturing patterns for triple binary input data. We also proposed optimal post-encoder types and interleaving algorithm for three dimensional turbo codes. Based on optimal parameters, we simulated both turbo codes, and we confirmed that the performance of turbo ${\Phi}$ codes are better than that of three dimensional turbo codes. However, the complexity of turbo ${\Phi}$ is more complex than that of three dimensional turbo codes by 18%.

• The Journal of Korean Institute of Communications and Information Sciences
• /
• v.26 no.8A
• /
• pp.1441-1449
• /
• 2001

차세대 멀티미디어 이동통신인 IMT-2000의 규격에서는 3GPP와 3GPP2에서 모두 터보 코드를 채널 코덱으로 채택하고 있다. 그 중 3GPP 에서는 용도에 따라 길쌈부호와, 제한길이 4인 1/3 터보코드를 선택적으로 사용하도록 정의되어 있다. 터보코드는 복호기의 출력으로 경판정 복호 비트에 대한 신뢰도 값을 동시에 생성하여, 이를 이용한 반복복호로 우수한 BER 특성을 얻을 수 있어야 한다. 본 논문에서는 먼저 3GPP 규격의 터보 복호기에 적용할 수 있는 내부 복호기로서 SOVA 복호기를 설계하였다. 또한 터보 복호기에서의 연판정 출력값의 중요성을 감안하여, 누적메트릭 정규화에 있어서 신뢰도 값에 영향을 주지않는 구조를 제안하여 적용하였다. 본 연구에서는 효율적인 구조의 3GPP SOVA 복호기를 설계하기 위하여 C++를 이용하여 알고리즘에 대한 성능을 검증하였으며, 이를 기반으로 VHDL을 이용하여 복호기를 설계하였다. 마지막으로 Altera사의 EPF10K100GC503 FPGA를 이용하여 복호기를 하드웨어로 구현하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2007.11a
• /
• pp.155-158
• /
• 2007

As a secondary stage of the liquid rocket engine development test, turbopump-gas generator powerpack tests are being performed. The schematics of the test hardware and the test facility for the TP+GG coupled test are presented. The results of a preliminary test results for the verification of the propellant supply system of the test facility are also presented. Based on the preliminary tests results, the verification of the propellants supply systems of the facility system was performed.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.12 no.5
• /
• pp.73-78
• /
• 2008

The development of turbopump in Korea has been practically started from 1999. Recently, the turbopump for a LRE with 30-ton level thrust has been successfully developed, which is able to work for all the required LRE regimes. This success is considered as a breakthrough in development of LRE because the turbopump, a core component of LREs, has been considered as a critical barrier in domestic technology point of view. In this paper, status of the turbopump development in Korea is provided and some suggestions are made for the prospective future.