Valve connector system of launching vehicle

The present invention relates to a connector valve system of a launch vehicle and, more specifically, relates to a connector valve system of a launch vehicle which has a valve unit in a connecting unit of a launch vehicle module and a ground side module when supplying a high-pressured fuel to a laun...

Ausführliche Beschreibung

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Bibliographische Detailangaben
1. Verfasser:	KO, JU YONG
Format:	Patent
Sprache:	eng ; kor
Schlagworte:	ACTUATING-FLOATS AIRCRAFT AVIATION BLASTING COCKS COSMONAUTICS DEVICES FOR VENTING OR AERATING ENGINEERING ELEMENTS AND UNITS GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS HEATING JOINTS OR FITTINGS FOR PIPES LIGHTING MEANS FOR THERMAL INSULATION IN GENERAL MECHANICAL ENGINEERING PERFORMING OPERATIONS PIPES SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING TAPS THERMAL INSULATION IN GENERAL TRANSPORTING VALVES VEHICLES OR EQUIPMENT THEREFOR WEAPONS
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Beschreibung
Zusammenfassung:	The present invention relates to a connector valve system of a launch vehicle and, more specifically, relates to a connector valve system of a launch vehicle which has a valve unit in a connecting unit of a launch vehicle module and a ground side module when supplying a high-pressured fuel to a launch vehicle on the ground to open a flow path in which fuel passes through when the launch vehicle module and the ground side module are connected, and to automatically shut the flow path when the launch vehicle module and the ground side module are separated. 본 발명은 발사체 커넥터 밸브 시스템에 관한 것으로, 상세하게는 지상에서 발사체로 고압의 연료를 공급시에 발사체모듈과 지상측모듈이 연결부 내부에 밸브부를 구비함으로써 발사체모듈과 지상측모듈이 연결시에 연료가 통과하는 유로가 개방되며 분리시에 자동으로 유로가 차단되는 효과가 있는 것을 특징으로 하는 발사체 커넥터 밸브 시스템에 관한 것이다.