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 liquid 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. Below are some of the basic equations that are pertinent to this project scope.

Speed of Sound:


 * $$ a=\sqrt{\gamma R T_{abs}} \qquad \mbox{(1)} $$

where a = Speed of Sound, $$\gamma$$ = Specific Heat Ratio, R = Ideal Gas Constant, and $$T_{abs}$$ = Absolute Temperature.

Mach Number:
 * $$ M=V/a \qquad \mbox{(2)} $$

where M = Mach Number and V = Velocity.

Below is the equation of thrust for an air breathing engine.


 * $$ T=(\dot{m}+\dot{m}_{fuel})V_{out}-\dot{m}V_{in} \qquad \mbox{(3)} $$

where T = Thrust, $$\dot{m}$$ = Mass Flow Rate, and V = Velocity.

Project Learning
Computational Fluid Dynamics

Research Literature
Johns Hopkins Integrated Rocket Ramjet History

Combined Cycle Engines Thesis

Unified Rocket Ramjet Engine I

Unified Rocket Ramjet Engine II

Other Resources
AeroMech Compressible Flow for Students

NPTEL E-Learning Courses