ISRU Challenge Production of O2 and Fuel from CO2

PDF Publication Title:

ISRU Challenge Production of O2 and Fuel from CO2 ( isru-challenge-production-o2-and-fuel-from-co2 )

Previous Page View | Next Page View | Return to Search List

Text from PDF Page: 011

11 In looking toward the future, there are various roadmaps and architectures that feature the use of O2 production on Mars (Rapp, 2016; Drake et al., 2009; Rucker et al., 2016; Sanders et al., 2015). One of the key uses is to support a Mars Ascent Vehicle (MAV) propellant system. Since approximately 78% of the reactant mass is O2 for a O2/CH4 based chemical propulsion system, this would provide a significant benefit to any mission with respect to launch mass. Preliminary mission models suggest that up to 30,000 kg of oxygen will be required as the oxidant for this ascent vehicle, which would require 2 to 3 heavy lift launches if brought directly from Earth to Mars (Richter, 1981). Current approaches target the production of 25–30 metric tons of oxygen over a 14 to 17 month time frame at a rate of 2–3 kg/hour (Rapp, 2016; Drake et al., 2009; Rucker et al., 2016; Sanders et al., 2015). It should be noted here that CO as an ascent vehicle fuel is impractical relative to the high energy content of CH4, though as a byproduct of an EC or PEC reduction of CO2, CO may serve as a lower-energy-content fuel for other energy conversion applications on Mars. A concern regarding SOXE-based approaches is the significant power required to support the electrolysis current, as well as to provide make-up heating to maintain sufficient stack temperatures. According to the latest calculations, the MOXIE demonstration payload is projected to require up to 300 W of power to support what is anticipated to be about a 0.45% demonstration (i.e., 􏰖10g O2/hr); this suggests that the power required to scale up to requisite production levels is on the order of 􏰖66 kW, although this likely overestimates the power level due to non-linear scaling of heat leakage, electronics and other system factors (Hecht et al., 2015). A detailed system design would be required to establish a high fidelity value. Other analyses suggest that baseline SOXE designs will require 30–45 kW of power for a 3 kg/14 month (420 sol) scenario, with approximately 20 kW required for the SOXE unit alone (Rapp, 2016). Design Reference Architecture-5 (DRA-5) notes power levels on the order of 26 kW (operating continuously) when using a fission power source (FPS) and 96 kW (operating eight hours/day) for a solar array approach (Drake et al., 2009). A summary of the mass and power levels from these various studies is noted in Table 2.1. Table 2.1: Estimated Mass and Power Required for SOXE-Based ISRU Architectures. aDrake et al. (2009) bSanders et al. (2015) Taking a value of 25 kW as a starting point, there are two options to supply these levels of power: solar arrays and FPS. To date, the United States has flown one fission reactor in space O2 Power Source Production (kW) Rate (kg/h) SOXE Plant Mass (kg) Solar Array Mass (kg) FPS Mass (kg) Total Mass (PV+plant) (kg) DRA-5a 2.2 26 (FPS) 900 14,595 7,800 15,495 96 (SA) COMPASSb 2.2 26 671 17,815 9,154 18,486

PDF Image | ISRU Challenge Production of O2 and Fuel from CO2

isru-challenge-production-o2-and-fuel-from-co2-011

PDF Search Title:

ISRU Challenge Production of O2 and Fuel from CO2

Original File Name Searched:

ISRU_final_report.pdf

DIY PDF Search: Google It | Yahoo | Bing

Salgenx Redox Flow Battery Technology: Power up your energy storage game with Salgenx Salt Water Battery. With its advanced technology, the flow battery provides reliable, scalable, and sustainable energy storage for utility-scale projects. Upgrade to a Salgenx flow battery today and take control of your energy future.

CONTACT TEL: 608-238-6001 Email: greg@salgenx.com (Standard Web Page)