at ChungNam National University
Hwanil Huh[1]
Department of Aerospace Engineering
Chungnam National University, Daejeon, Korea
(Tel : +82-42-821-6687; E-mail: hwanil@cnu.ac.kr)
We, at Chungnam National University, are interested in three main research topics: micropropulsion, high speed airbreathing propulsion such as ramjet and scramjet, and liquid/ hybrid rocket.
Recently, spacecraft technology trends can be expressed in three words, i.e. "faster, cheaper and smaller." In light of this, subsystems of spacecraft are getting higher density. Among these subsystems, micro propulsion device is an essential component. And micro nozzle is the most important part in the micro propulsion device. We conduct experiments for the micro nozzles with throat diameter of 1.0, 0.5 and 0.25 mm, respectively. We measure the thrust using strain gage based thrust measurement system. Also we estimate the micro-nozzle performance.
Conventional method to determine the thrust of an aerospace engine is to use a thrust stand or a force measurement system. However, these conventional methods are not applicable to the case where thrust stands are impractical, such as free jet testing of engines, and model combustor. For this reason, the thrust determination method from measured pitot pressure is considered and applied to the 2-D supersonic wind tunnel in Chungnam National University.
As part of Korean Space Launch Vehicle (KSLV) program, we focus on a study of regenerative cooling in a liquid rocket combustor. Analytic study of combustion instability using linear model has been studied.
a) Micro nozzle & chamber b) Nozzle throat: 0.25mm
Figure 1 Micro nozzle Figure 2 Mach 2.5 Supersonic Wind Tunnel