1. 제 목 : Developing a Liquid Valve System for a Micro Rocket Propulsion Using 2-Stage Valves





2. 연 사 : 이 진욱, Ph.D.


(Ph. D candidate & research assistant Gas Turbine Lab., MIT)





3. 일 시 : 2002년 8월 8일 (목) 16:00





4. 장 소 : 301동 1512호





5. 요 약 :





This seminar presents development of a high pressure and high mass flow liquid valve system for micro spacecraft propulsion. A MEMS rocket engine developed at MIT requires a flow control capability that can allow 0.5g/s of liquid fuel at inlet pressure of 10atm. The valve system must also be operated in a temperature range of –120C to 200C. None of existing MEMS valves from the literatures can meet these specifications.


In order to overcome intrinsic power limitation of MEMS actuators, 2-stage valve, so called, pilot/servo valve concept was adopted. This seminar will focus on this novel concept for a MEMS fluid control system and development of individual valves. The servo valve is operated by hydraulic pressure force without actuator. On the other hand, an electrostatic actuator operates the pilot valve for its valve functions and ultimately controls the servo valve.

















6. 약 력 :





B.S, Mechanical design & production engineering, Yonsei univ., 1998





M.S, Aeronautics & astronautics, MIT, 2000








7. 문 의 : 기계항공공학부 송성진 교수 (880-1667)