In the future, the Planetary Science Division of NASA’s Science Mission Directorate hopes to use better-performing and lower-cost propulsion systems to send rovers, probes, and observers to places like Mars, Jupiter, and Saturn. For such purposes, a new propulsion technology called the Advanced Materials Bipropellant Rocket (AMBR) was developed under NASA’s In-Space Propulsion Technology (ISPT) project, located at Glenn Research Center. As an advanced chemical propulsion system, AMBR uses nitrogen tetroxide oxidizer and hydrazine fuel to propel a spacecraft. Based on current research and development efforts, the technology shows great promise for increasing engine operation and engine lifespan, as well as lowering manufacturing costs.
In developing AMBR, ISPT has several goals: to decrease the time it takes for a spacecraft to travel to its destination, reduce the cost of making the propulsion system, and lessen the weight of the propulsion system. If goals like these are met, it could result in greater capabilities for in-space science investigations. For example, if the amount (and weight) of propellant required on a spacecraft is reduced, more scientific instruments (and weight) could be added to the spacecraft.
To achieve AMBR’s maximum potential performance, the engine needed to be capable of operating at extremely high temperatures and pressure. To this end, ISPT required engine chambers made of iridium-coated rhenium (strong, high-temperature metallic elements) that allowed operation at temperatures close to 4,000 °F. In addition, ISPT needed an advanced manufacturing technique for better coating methods to increase the strength of the engine chamber without increasing the costs of fabricating the chamber.
In 2006, NASA’s ISTP project partnered with NASA’s Marshall Space Flight Center and Aerojet through a NASA Research Announcement (NRA) to increase AMBR’s performance efficiency and to lower the fabrication cost for the iridium-coated rhenium combustion chamber. Aerojet subcontracted a company in Huntsville, Alabama, called Plasma Processes Inc. (PPI) to modify a state-of-the-art engine design so the chamber wall materials could operate at very high temperatures.
While Aerojet defined the design details of the chamber configuration and worked with PPI to ensure the processes were in place to fabricate the chamber, the actual fabrication of the chamber was completed by PPI, using a process called EL-Form. Results from performance testing of the technology in 2008 and 2009 showed the propellant efficiency was higher than ever achieved for the hydrazine and nitrogen tetroxide oxidizer propellant combination. The iridium-coated rhenium chamber produced under the NRA set a hydrazine record for performance efficiency, which will mean a reduction in the propellant required to perform spacecraft maneuvers. It also had a 30-percent improvement on production costs.
“EL-Form allows us to deposit a thicker iridium layer for improved oxidation protection. It also allows us to produce the rhenium layer with better consistency and properties than what they had been doing in the past. The iridium rhenium chambers were in use already, but the El-Form process allows us to be able to improve those materials—affecting the quality and the cost,” says Anatoliy Shchetkovskiy, EL-Form director for PPI.
The iridium-coated rhenium combustion chamber fabricated using the EL-Form process addressed the needs of the ISTP project, as well as validated PPI’s process for making high-temperature materials for other applications.