Editing Interorbital Systems (section)

==NEPTUNE Launch Vehicle: General==
The NEPTUNE rocket, a two-stage vehicle design from Interorbital Systems, would use high-performance liquid oxygen and densified propane propellants.<ref>{{cite news |title=Interorbital Preps for NEPTUNE Test Launch—and eleven smallsats will go along for the ride |first=Randa |last= Milliron |url=http://satmagazine.com/story.php?number=1600200139 |publisher=SatMagazine |date=October 2017 |url-status=live |archive-url=https://web.archive.org/web/20180124070916/http://satmagazine.com/story.php?number=1600200139 |archive-date=2018-01-24 }}</ref><ref name='Trib 2017'/> The first stage would be equipped with four stationary throttleable ablatively cooled liquid rocket engines, each capable of generating 4,500 pounds of thrust.<ref>{{Cite web |title=Neptune modular rockets for breakthrough low-cost space access |url=https://sbir.nasa.gov/SBIR/abstracts/11/sbir/phase1/SBIR-11-1-O2.01-9812.html |access-date=2023-10-13 |website=sbir.nasa.gov}}</ref> Throttling of these engines allows for precise control of pitch, yaw, and roll during flight. 

The second stage of the NEPTUNE rocket is proposed to be powered by a single stationary ablatively cooled liquid rocket engine that generates 3,000 pounds of thrust. During the second stage engine burn and while in orbit, pitch, yaw, and roll control would be provided by cold-gas thrusters.