Rocket Engines
Our rocket engines are built to customer specifications.  Below is a selection of engines that illustrate some of our capabilities.  Click on any engine class to learn more.

• XR-2P1 15 lbf N2O-Ethane
  R&D and educational, variable propellants and third fluid injections
   
• XR-3E17 56 lbf N2O-Ethane
  Stationkeeping - storable
   
• XR-3B4 50 lbf N2O-Isopropyl
  Stationkeeping - storable
  
  
• XR-3M9 50 lbf LOX-Methane
  Stationkeeping - storable
   
• XR-4A3 400 lbf LOX-Alcohol
  Auxilliary or primary propulsion
   
• XR-4K14 1,500 lbf LOX-Kerosene
  Primary propulsion, 'Rocket Racer' engine
   
• XR-4K5 1,800 lbf LOX-Kerosene
  Primary propulsion
   
• XR-5M15 7,500 lbf LOX-Methane
  Primary propulsion, space storable

The 3M9 is shown here with a 6-inch rule

In 2005 we built and tested the XR-3M9, a 50 lb thrust, self-pressurized LOX/methane engine with regenerative cooling and specially designed injector. The design, fabrication, and testing of this engine was initially funded entirely through private investment capital. Recent engine tests were conducted as part of a Phase I SBIR contract under the Air Force Research Lab’s (AFRL’s) Propulsion Directorate at Edwards Air Force Base, and as part of development for an advanced regeneratively cooled LOX/methane engine for space applications.

XCOR built the 3M9 to be the reaction control system for its next generation vehicle, and the AFRL SBIR Phase 1 contract allowed us to validate the design models and test the engine for performance characteristics. In turn, this work enabled us to predict performance of larger engines with safer, environmentally friendly propellants and reliable, responsive operations for low cost launch vehicles, satellite maneuvering stages, and commercial sounding rockets.

This engine has four distinct advantages: 

• It uses non-toxic LOX/methane propellants with inherently high specific impulse.

• It has a new injector design that is inherently low cost to manufacture.

• It is optimized to operate with self pressurizing propellants, which eliminate the need for either pumps or a propellant tank pressurization system. Additionally, the engine can operate with subcooled propellants.

• Use of LOX/methane means that the main engines, orbital maneuvering system (OMS), and reaction control system (RCS) can all use the same propellants, which will simplify the overall system and reduce weight.

LOX/methane rocket engines show promise to provide higher performance necessary for manned moon missions. NASA, in its Exploration Systems Architecture Study (ESAS) of how to return to the Moon, recognized the importance of LOX/methane:

"...limited ground test has shown the combustion performance to be suitable for use as a propellant. LOX/LCH4 is a clean-burning propellant combination. LOX does have an extensive history as a fluid on spacecraft and as propellant on propulsion stages; however, the on-orbit operational experience for LOX systems is limited. The safe handling and safe system design aspect of LOX are well understood. LOX/methane does offer higher Isp performance compared to state-of-the-art storables (i.e.,hypergols), without the volume increase that is common with LOX/liquid hydrogen systems, which results in an overall lower vehicle mass as compared to [hypergolic] propulsion systems. A LOX/liquid methane system uses less power, on the order of 1,000 watts less power, than comparable [hypergolic] propulsion systems, thereby significantly reducing the mass of the spacecraft power system(s)." ESAS, Section 4, p. 115.

In addition to higher performance, LOX/methane engines have long term storability necessary for manned Moon or Mars missions; LOX and methane can be obtained from the Martian soil and atmosphere, and LOX can come from the lunar soil. Also, it's non-toxic nature significantly lowers operations costs, enhances crew safety, and is safer for the environment.