Integrated Rocket Ramjet (IRR): Team Rocket

The goal is to design and model an Integrated Rocket Ramjet (IRR) engine design that will transition from the solid rocket phase to the ramjet phase after reaching the designed speed while utilizing minimal breakaway parts or by means of control surfaces. The control surfaces will also serve as an inlet optimization tool to minimize exergetic losses into the combustion chamber and simultaneously maximize exit conditions for optimal thrust.

Background
This design project requires an understanding of compressible flow (also known as gas dynamics), thermodynamics of fluids including exergy analysis, and current propulsion system designs including ramjets.

For macroscopic systems (above the thermodynamic limit), these statements are both expressions of the second law of thermodynamics if the following expression is used for exergy:


 * $$ B=U +P_RV -T_RS-\sum_i\mu_{i,R}N_i \qquad \mbox{(1)} $$

where the extensive quantities for the system are: U = Internal energy, V = Volume, and Ni = Moles of component i

There are many sources available for reference and understanding of compressible flow dynamics and some links below in the references section.

Project Learning
The nature of this project is primarily based in thermodynamic analysis and optimization of geometries for the control surfaces.

Other Resources
AeroMech Compressible Flow for Students