Advancing Propulsion for Hypersonic and Space Rockets
#JetFuel
Advancing Propulsion for Hypersonic and Space Rockets
#JetFuel
Research Terms
The University of Central Florida invention comprises a standing normal detonation wave jet engine (STANDJET), systems, and methods for generating a standing normal detonation wave. The technology offers configuration and flow conditions that have the potential to revolutionize supersonic to hypersonic propulsion for atmospheric and space flights (Mach 4 to 6 flights). In one example application, a supersonic to hypersonic flow fuel injection with a double ramp or wedge generates a normal, stabilized detonation—the most powerful form of combustion—relative to the incoming supersonic to hypersonic flow generating the reaction power. This is game-changing and allows for a possible pathway to develop and integrate supersonic to hypersonic detonation technology that enables hypersonic propulsion and advanced power systems.
Partnering Opportunity: The research team is seeking partners for licensing, research collaboration, or both.
Stage of Development: Prototype available.
Stabilized detonation for hypersonic propulsion, Proc Natl Acad Sci USA. 2021 May 18;118(20):e2102244118. doi: 10.1073/pnas.2102244118. PMID: 33972449; PMCID: PMC8157988.
The University of Central Florida invention is a design methodology for rotating injectors in engines that use hydrogen and oxygen detonations. The invention is unique in that the injection scheme is universal for rotating detonation rocket engine (RDRE) technologies, rather than for just a specific hardware architecture. As such, this injector assembly is not just applicable to the hydrogen and oxygen propellant injectors for this specific RDRE but for all future RDREs.
Stage of Development
Prototype available.
Experimental evidence of H2/O2 propellants powered rotating detonation waves, Combustion and Flame, Vol. 214, 2020, p136-138, ISSN 0010-2180, https://doi.org/10.1016/j.combustflame.2019.12.031.
The University of Central Florida invention is a supersonic oblique rotating detonation wave engine (SORDE) and methods for generating supersonic to hypersonic propulsion. The innovation provides a pathway for developing hypersonic propulsion technology for atmospheric and space flights (Mach 1.2 to 6) as well as advanced power systems. As an example, the invention could be used to develop technologies that enable high-speed flight through Earth’s atmosphere and for entering/leaving other planetary atmospheres.
Technical Details: The invention comprises a supersonic oblique rotating detonation wave engine (SORDE), along with systems and methods for generating a SORDE wave. To produce and sustain a SORDE wave, the engine configuration enables the injection of fuel at supersonic speeds into an inlet air flow between Mach 1 and Mach 7. The technology also includes injecting fuel into the inlet air to establish a fuel-air equivalence ratio of 0.2 to 2.5. Some embodiments can include the following:
Partnering Opportunity: The research team is seeking partners for licensing, research collaboration, or both.
Stage of Development: Prototype available.
Stabilized detonation for hypersonic propulsion, Proceedings of the National Academy of Sciences (PNAS), Vol. 118 | No. 20, May 18, 2021, doi: 10.1073/pnas.2102244118, PubMed: 33972449.
