Airflow Controller and Isolator for Pulse Detonation Engines

The development of a revolutionary airflow controller and isolator for application with a high-speed inlet and a pulse detonation engine (PDE) is proposed. This innovation has the potential of providing a solution to the unique airflow-matching problemimposed by the integration of a PDE with a high-speed inlet. The cyclic (on/off) characteristic in the PDE airflow demand imposes a difficult airflow-matching problem for the inlet. The proposed concept will serve to control the airflow to the detonationchambers, provide sealing, and function to isolate the inlet from the severe airflow disturbances that could be imposed by the PDE operation. The inlet, when coupled with the airflow controller, will function in a normal conventional mode by providing aconstant airflow supply to the engine. The SBIR Phase I study has identified aerodynamic designs of the airflow controller. The objective of the proposed Phase II SBIR work effort is to demonstrate the feasibility of the rotary airflow controller for aPDE propulsion system through evaluation in a research test rig. This will include aerodynamic testing followed by integration with a operating PDE. Successful design and validation of the concept will provide breakthrough inlet technology for a PDEairbreathing propulsion system.