ORAL DELIVERY OF ENCAPSULATED MULTIMERIC AIDS VACCINES

Not Available This Phase I SBIR proposal is aimed at developing a design capability and comprehensive set of simulation tools for exploring the feasibility and making a realistic assessment of the potential for advanced rocket propulsion based on the Pulsed Detonation Engine (PDE) cycle. The PDE is a new engine concept that provides higher specific impulse than conventional rockets because of its constant-volume, nonsteady operating cycle. It also has several advantages because of its simple design. In PDEs a detonation wave initiated in a fuel-oxidizer mixture propagates exially in the detonation chamber, producing thrust when it loads the thrust wall. In Phase I we will identify the codes needed for modeling PDE operation and benchmark them against a previously developed prototype engine. In Phase II we will calibrate and test them in connection with all the key PDE processes: injection, mixing, detonation initiation, evolution, and propagation, venting of exhaust products, and the acoustic signature and structural response of a multiple-chamber PDE, thus enabling realistic end-to-end PDE performance simulation. Using these tools we will design and build a flight-capable full-scale propulsion system.