Battery - Propellant Hybrid Systems
Abstract
stored in rechargeable batteries is normally retrieved through reversible electrochemical reactions. Under extreme conditions, however, the chemical energy could be released via violent exothermic reactions accompanied with gas generation known as thermal runaway. While such a phenomenon poses severe safety threats to battery operation, this proposed research seeks to explore whether the known phenomenon could be exploited to generate propulsion thrust in a controllable way. By merging battery and thruster systems into one device, the weight of a spacecraft could be significantly reduced to benefit future space exploration. To this end, we propose integrated modeling and experimental efforts to acquire fundamental knowledge essential to the realization of such hybrid systems. Two promising battery chemistries, in which alkali metal anode serve as the fuel and an oxide cathode or a novel perchlorate-based catholyte as the oxidizer, will be investigated to determine the combustion reaction pathways, energy output and initiation conditions. Meanwhile, the solid-liquid interfacial behavior of alkali metal will be elucidated and leveraged to suppress dendritic growth and reduce the risk of unintended thermal runaway. As a key enabler of the hybrid systems, a reliable mechanism for in-situ propellant preparation will be uncovered based on controlled melting and mixing of the alkali metal anode with cathode-catholyte. Results from this project will also contribute to the scientific understanding of thermal runaway in alkali metal based batteries and its mitigation.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Mar 06, 2024
- Source ID
- FA95502310444
Entities
People
- Ming Tang
Organizations
- Air Force Office of Scientific Research
- Rice University
- United States Air Force