Interorbital completes static fire test of upper-stage engine
Capitalism in space: The smallsat rocket company Interorbital (IOS) today released a short video showing a successfully static fire test of the upper-stage engine for its Neptune rocket.
The IOS rocket team successfully completed the first test of Interorbital’s NEPTUNE series launch vehicle’s liquid upper-stage rocket engine (GPRE 0.75KNTA). Engine performance was well within its design parameters, generating a sea-level thrust of 750 pounds and a sea-level specific impulse of 245 seconds. This translates to a thrust of 1,000 pounds and a specific impulse of 300 seconds in a vacuum (with expansion nozzle). The ablatively-cooled rocket engine is powered by the hypergolic combination of White Fuming Nitric Acid (WFNA) and Turpentine/Furfuryl Alcohol. These high-density storable auto-igniting propellants power all IOS liquid rocket engines. Interorbital’s N1 launch vehicle utilizes two GPRE 0.75KNTA engines for its second stage and a single GPRE 0.75KNTA engine for its third stage.
I have embedded the video below the fold. This is the first real news update from Interorbital in months. In April 2017 they looked like they were close to a launch, but until today there were no further updates. Part of the issue appears that they changed their approach for manufacturing their rocket in order to save cost, and this might have thrown a wrench in their schedule.
Capitalism in space: The smallsat rocket company Interorbital (IOS) today released a short video showing a successfully static fire test of the upper-stage engine for its Neptune rocket.
The IOS rocket team successfully completed the first test of Interorbital’s NEPTUNE series launch vehicle’s liquid upper-stage rocket engine (GPRE 0.75KNTA). Engine performance was well within its design parameters, generating a sea-level thrust of 750 pounds and a sea-level specific impulse of 245 seconds. This translates to a thrust of 1,000 pounds and a specific impulse of 300 seconds in a vacuum (with expansion nozzle). The ablatively-cooled rocket engine is powered by the hypergolic combination of White Fuming Nitric Acid (WFNA) and Turpentine/Furfuryl Alcohol. These high-density storable auto-igniting propellants power all IOS liquid rocket engines. Interorbital’s N1 launch vehicle utilizes two GPRE 0.75KNTA engines for its second stage and a single GPRE 0.75KNTA engine for its third stage.
I have embedded the video below the fold. This is the first real news update from Interorbital in months. In April 2017 they looked like they were close to a launch, but until today there were no further updates. Part of the issue appears that they changed their approach for manufacturing their rocket in order to save cost, and this might have thrown a wrench in their schedule.