Graduation Semester and Year
2011
Language
English
Document Type
Thesis
Degree Name
Master of Science in Aerospace Engineering
Department
Mechanical and Aerospace Engineering
First Advisor
Donald R Wilson
Abstract
An analytical parametric cycle analysis model for the continuous rotating detonation wave ejector-augmented rocket was developed to estimate and evaluate the maximum potential performance that the continuous rotating detonation wave rocket (CRDWR) itself can provide in an ejector ramjet as well as the two-stage rocket for low earth orbit (LEO). This was done by integrating Bykovskii's model for CRDWR with Heiser & Pratt's modified ejector ramjet and their transatmospheric performance model. The performance results of this unique engine in comparison to a regular rocket counterpart were evaluated primarily in terms of specific thrust and specific impulse with respect to flight Mach number in a constant dynamic pressure trajectory as well as in terms of initial payload mass ratio for a transatmospheric trajectory to LEO.
Disciplines
Aerospace Engineering | Engineering | Mechanical Engineering
License
This work is licensed under a Creative Commons Attribution-NonCommercial-Share Alike 4.0 International License.
Recommended Citation
Cao, Huan V., "Analytical Parametric Cycle Analysis Of Continuous Rotating Detonation Ejector-augmented Rocket Engine" (2011). Mechanical and Aerospace Engineering Theses. 250.
https://mavmatrix.uta.edu/mechaerospace_theses/250
Comments
Degree granted by The University of Texas at Arlington