Interorbital Systems

The two-stage NEPTUNE rocket uses high-performance liquid oxygen and densified propane propellants.[5][1] The first stage is powered by four stationary throttleable ablatively-cooled liquid rocket engines, each generating 10,000-lbf of thrust.Throttling of the engines generates the pitch, yaw, and roll control moments required for steering. By using throttleable stationary engines instead of gimballed engines, the heavy and complex gimbals, gimbal actuators, and the gimbal actuator drive hardware are eliminated, substantially reducing the weight and complexity of the propulsion system.[1] The second stage is powered by a single stationary ablatively-cooled liquid rocket engine generating 3,000-lbf of thrust. Cold-gas thrusters provide pitch, yaw, and roll control during the second-stage engine burn and on orbit. All of Interorbital's ablatively-cooled rocket engines are rapidly manufactured using a filament-winding process. These state-of-the-art composite engines are manufactured with the most advanced high-temperature resistant composite materials allowing the engines to be safely operated for up to forty minutes. They are more reliable and much lighter than the typical regenerative-cooled engines that use primitive nineteenth-century steam-engine technology for cooling and they simplify the engine plumbing and the multiple engine start process while on orbit.[6]

The propellants are fed into the NEPTUNE liquid rocket engines by a proprietary pressurant system that does not require dangerous and heavy high-pressure pressurant tanks. This system design results in a propellant tank/pressurant system that weighs the same as an equivalent propellant tank/pressurant system/pump-fed system. By eliminating the propellant pump and its heavy electric or gas-generator pump-drive system, we have substantially reduced both the overall rocket development cost and the manufacturing cost and manufacturing time.[7]

All IOS rockets are launched from an ocean-going barge with motion compensation. Equivalent to a private spaceport, barge-launch eliminates the enormous cost of liability insurance when launching from the existing land-based spaceports and allows IOS to schedule launches based only on the weather and sea conditions. Initially our orbital flights will take place from the Pacific Ocean southwest of Los Angeles.

In 2006, IOS had an active Office of Commercial Space Transportation launch license for Tachyon,[8] a sounding rocket designed for a 120-mile apogee suborbital flight.

Milestones

Test flight of the single CPM on March 29th, 2014 with four payloads on board.

• The CPM's main engine underwent its first successful static engine firing on October 28, 2012. The all composite-chambered engine performed with 7,500lbs of thrust, using nitric acid and turpentine.
• The Common Propulsion Module Test Vehicle (CPM TV) performed its first successful test flight on March 29, 2014.[9] The payloads included two CubeSats, a Synergy Moon payload and a music CD by "ENCLOSURE" by former Red Hot Chili Peppers guitarist, John Frusciante.[10] The rocket reached an altitude of 10,000 feet and will be reused for the next test flight. All payloads were recovered intact.[9]

Interorbital Systems was engaged in June 2016 as a member of and launch provider for Team Synergy Moon in the Google Lunar X Prize competition.[12][2] The team's lunar rover was to have been lifted to the Moon's surface by a modified, 36-module version of the NEPTUNE rocket.[13]

• Private spaceflight
• Orbital spaceflight
• Sub-orbital spaceflight
• OTRAG, which used a similar modular rocket design
• Mojave Air and Space Port
• Team Synergy Moon
• FreeFly Astronaut Project

• Interorbital Systems Official Site
• Trans Lunar Research
• Team SYNERGY MOON