The atmosphere of Mars is predominantly carbon dioxide (95.5 percent), with nitrogen, argon, and trace gases comprising the remaining portion. KSC and GRC are developing a cryofreezer and a temperature swing absorption pump, respectively, for CO2 collection. The cryofreezer freezes CO2 selectively out of the Mars atmosphere onto a cold head which is then heated to vaporize the CO2 resulting in a chamber of high pressure CO2 that can be provided to downstream oxygen or fuel processing. In the temperature swing adsorption pump, Mars atmosphere is pushed through a sorbent material that preferentially adsorbs carbon dioxide at low temperatures. Once the adsorbent material is saturated, the material is heated to release the carbon dioxide at higher pressure. Thermal and fluid analyses are being applied to investigate the best combination of cycle time, number of stages, adsorption/desorption temperatures, sorption material, and stage size.
To prevent dust ingested from the Mars atmosphere from degrading the performance of the CO2 collection system, a scroll media filter and an electrostatic precipitator are also being developed. A scroll filter system is based on a design of a filter system developed for life support systems to clean particulates out of spacecraft cabin air. This filter will be tested and characterized in the Mars Flow Loop facility at Glenn Research Center (GRC). Electrostatic precipitators use a high voltage corona discharge to charge aerosolized particles which are deposited on collector electrodes as a result of electrostatic forces. Tests are being conducted at Kennedy Space Center (KSC) to determine the effects of length, diameter, inlet velocity, and applied voltage on dust removal efficiency.
Carbon Dioxide Collection, Separation, and Pressurization is part of the AES In-Situ Resource Utilization (ISRU) Technology Project which is developing the component, subsystem, and system technology to enable production of mission consumables from regolith and atmospheric resources at a variety of destinations for future human exploration missions.
The overall goals of the ISRU Technology project are to achieve system-level TRL 6 to support future flight demonstration missions and provide exploration architecture teams with validated, high-fidelity answers for mass, power, and volume of ISRU systems.
The project's initial focus is on critical technology gap closure and component development in a relevant environment (TRL 5) for Resource Acquisition (excavation, drilling, atmosphere collection, and preparation/beneficiation before processing) and Resource Processing & Consumable Production (extraction and processing of resources into products with immediate use as propellants, life support gases, fuel cell reactants, and feedstock for construction and manufacturing). The interim project goal is to complete ISRU subsystem tests in a relevant environment to advance the subsystem to TRL 6. The project end goals are to perform end-to-end ISRU system tests in a relevant environment (system TRL 6) and integrated ISRU-exploration elements demonstrations in a relevant environment.
ISRU is a disruptive capability that enables more affordable exploration than today’s paradigm where all supplies are brought from Earth, and allows more sustainable architectures to be developed. The availability of ISRU technologies can radically change the mission architecture and be the sizing design driver for other complex systems already in development. For example, the current Mars architecture assumes ISRU production of up to 30 metric tons of propellant on the Mars surface in order to reduce the ascent vehicle landed mass by 75 percent and reduce Earth launch needs by at least 300 metric tons. If a decision was made to use storable propellants for the Mars ascent vehicle instead of ISRU-producible oxygen and methane, many other drastic changes to the architecture could be required, such as lander and ascent vehicle size, number of landers needed, surface operations for ascent vehicle fueling, and Mars rendezvous orbit. Other surface systems might become more complex or heavier if they are not designed to take full advantage of ISRU technologies. Examples include a more complex closed-loop life support system if resupply with ISRU water cannot be assumed, or a heavy, built-in habitat radiation shield if a water- or regolith-based shield cannot be added after habitat delivery to the surface.
Other system designers may also make decisions that reduce the benefit of incorporating ISRU into the mission, resulting in a larger or more inefficient ISRU system. For example, a non-continuous power source such as solar power would increase the required production rate and peak power of an ISRU plant, thus increasing its size and complexity due to hundreds of start-stop cycles. However, a continuous power source, such as nuclear or solar power with storage, would allow an ISRU plant to operate continuously, thus minimizing its size, complexity, and power draw. These are only a few examples of how the inclusion of ISRU has ripple effects across many other exploration elements.
ISRU is also a new capability that has never before been demonstrated in space or on another extraterrestrial body. Every other exploration system or element, such as power, propulsion, habitats, landers, life support, rovers, etc., have some form of flight heritage, although almost all still need technology development to achieve the objectives of future missions. This is another critical reason why ISRU technology development, leading to a flight demonstration mission, needs to be started now, so that flight demonstration results can be obtained early enough to ensure that lessons learned can be incorporated into the final design.More »
This technology is categorized as a prototype hardware system for manned spaceflight.
The ISRU Carbon Dioxide Collection, Separation, and Pressurization technology captures carbon dioxide from the Martian atmosphere and prepares it for use by downstream ISRU processes that can produce resources for life support, propellant, and construction applications. This capability can significantly reduce mission launch mass, lander size and/or number needed, reduce ascent vehicle size and/or increase rendezvous orbit, and enable or enhance mission capabilities.More »
|Organizations Performing Work||Role||Type||Location|
|Glenn Research Center (GRC)||Lead Organization||NASA Center||Cleveland, OH|
|Johnson Space Center (JSC)||Supporting Organization||NASA Center||Houston, TX|
|Kennedy Space Center (KSC)||Supporting Organization||NASA Center||Kennedy Space Center, FL|