Advanced Combustion - Hypersonics

Project Scope

In collaboration with the University of North Carolina at Charlotte, the Institute of Digital Engineering USA has been selected as a partner for new research involving combustion and hypersonic vehicles.

An area of interest for hypersonic development is advanced control systems. This project will specifically focus on divert attitude control systems (DACS). Currently, there is limited simulation data that exists on DACS, leaving a need for modeling of combustion reactions and products.

In this project, we will adopt a multiscale strategy in which insights from simulations will inform particle model development. A simulation IMPACT code, developed by University of North Carolina at Charlotte’s Dr. Ramaprabhu, will be used to generate the in-depth physics that will be needed. At the microscale level, IMPACT code will be used to run single droplet fuel particle simulations that will provide insight into fuel burning and vapor conversion. At the mesoscale level, the interaction of multiphase jets with boundary layer flow will be modeled. These simulations will provide information for mathematical models for turbulence used in fluid dynamics called Large Eddy simulations. These mesoscale models will be used for the reignitions of unburned fuel in the flow field. Reignition effects are critical to assess the survivability and maneuverability of hypersonic interceptors utilizing DACS system.

This research would directly benefit ongoing and future work involving the analysis of supersonic and hypersonic weapon systems. Improved modeling and simulation strategies for combustion will also impact work focused on more ‘green’ power systems such as rotating detonation engines (RDEs).

Rotating Detonation Engines (RDEs)

Rotating Detonation Engines are a promising new type of propulsion system that has potential to be more efficient than traditional engines. RDEs have the potential to operate at higher pressures and temperatures than traditional engines, resulting in higher efficiency and lower emissions. RDEs are of considerable, recent interest for agencies supporting hypersonic missions such as the Department of Defense and NASA.

Experimental studies on aircraft propulsions systems have been largely limited and the operating mechanisms of these engines remain poorly understood. This project aims to develop a liquid fuel model for RDEs by producing simulations of liquid fuel injection, breakup, and combustion using the IMPACT code. Additionally, this research will implement single-phase combustion models allowingfor comparison of the mechanism of detonation in gas-phase and liquid-fuel RDEs. This research will also begin to investigate which methodologies will be best for future multiphase strategies.

The broader impact of this research is enabling efficient and high speed flight propulsion technologies which will inform the design of hypersonic propulsion systems and strengthen our national defense.