Abstract
The microwave rocket is a candidate for use as a future low cost launch system. Plasma generated by a millimeter-wave beam drives a detonation wave in a thruster tube, and the vehicle acquires impulsive thrust by exhausting the gas, similarly to a pulse detonation engine. The air breathing rate is important for thrust performance in multi-pulse propulsion. Therefore, an air-breathing mechanism using reed valves is under development. In this study, the air flow rate through the reed valves was computed and its performance was evaluated in terms of the partial filling rate: PFR. Results show that, when using reed valves, a 10–15-fold increase in thrust is obtainable over conventional performance.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
