The successful ignition test of the semi-cryo pre-burner is a major achievement in the development of semi-cryogenic propulsion systems. According to ISRO, semi-cryogenic engine ignition start was done using fuel ampule. A combination of triethyl aluminide and triethyl boron was used in this. It has been used for the first time in 2000 Kilonewton Semi-Cryogenic in ISRO. The ignition process is important in the development of liquid rocket engine systems.
ISRO is developing semi-cryogenic engine. Its purpose is to increase the payload capacity of Launch Vehicle Mark-3 (LVM3). It will be an engine of 2,000 kilonewton thrust working on liquid oxygen (LOX) kerosene propellant combination. The Indian Space Research Organization (ISRO) on Monday said the first ignition test of the semi-cryo pre-burner under development of the engine was successfully conducted on May 2 at the Semi Cryo Integrated Engine Test Center (SIET) at ISRO Propulsion Complex, Mahendragiri.
The successful ignition test of the semi-cryo pre-burner is a major achievement in the development of semi-cryogenic propulsion systems. According to ISRO, the semi-cryogenic engine ignition start was done using fuel ampule. A combination of triethyl aluminide and triethyl boron was used in this.
It has been used for the first time in 2000 Kilonewton Semi-Cryogenic in ISRO. The ignition process is important in the development of liquid rocket engine systems. This will be followed by tests of the engine powerhead test article and the fully integrated engine
