Development of a Main Oxidizer Shut-off Valve for Liquid Rocket Engines

Paper number

IAC-09.C4.P.3

Author

Mr. HOYOUL PARK, Hanwha Corporation, Korea, Republic of

Coauthor

Dr. Moongeun Hong, Korea Aerospace Research Institute, Korea, Republic of

Coauthor

Mr. KI WON JANG, Hanwha Corporation, Korea, Republic of

Coauthor

Mr. JOON WON LEE, Hanwha Corporation, Korea, Republic of

Year

2009

Abstract

In space launch vehicle propulsion systems, a Main Oxidizer shut-off Valve (MOV) controls the supply of liquid oxygen into a combustion chamber by opening and shutting operations. Moreover, in steady-state operational state, the MOV should secure a constant flow rate of liquid oxygen for combustion stability in the combustion chamber.

   A poppet type shutoff valve under pneumatic control has been taken into account and finally adapted for the MOV for a Korea space launch vehicle. For the development of the MOV, experimental tests have been performed to understand some important design parameters such as force balance of moving components and external leakages at cryogenic condition. This paper presents the experimental results concerning these important design parameters of the MOV.

Abstract document

IAC-09.C4.P.3.pdf

Manuscript document

IAC-09.C4.P.3.pdf (🔒 authorized access only).

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