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According to one embodiment of the invention, a system for altering a fluid flow includes a nozzle having a fluid flow and including a converging portion, a diverging portion downstream of the converging portion, and a throat coupling the converging portion to the diverging portion, at least one por

According to one embodiment of the invention, a system for altering a fluid flow includes a nozzle having a fluid flow and including a converging portion, a diverging portion downstream of the converging portion, and a throat coupling the converging portion to the diverging portion, at least one port located in a wall of the nozzle and angled with respect to the fluid flow, and at least one pulse detonation device operable to inject a plurality of detonation waves in a pulsed manner through the port and into the fluid flow. The pulsed detonation waves operate to alter the fluid flow.

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1. A system for altering a fluid flow, comprising:a nozzle having a fluid flow and comprising a converging portion, a diverging portion downstream of the converging portion, and a throat coupling the converging portion to the diverging portion;at least one port located in a wall of the nozzle and an

1. A system for altering a fluid flow, comprising:a nozzle having a fluid flow and comprising a converging portion, a diverging portion downstream of the converging portion, and a throat coupling the converging portion to the diverging portion;at least one port located in a wall of the nozzle and angled with respect to the fluid flow; andat least one pulse detonation device operable to inject a plurality of detonation waves in a pulsed manner through the port and into the fluid flow, the pulsed detonation waves operable to alter the fluid flow. 2. The system of claim 1, wherein the at least one port comprises a plurality of ports, the ports positioned proximate the throat such that the detonation waves operate to vary the effective cross-sectional area of the throat within the nozzle. 3. The system of claim 1, wherein the at least one port is adapted to provide an asymmetric cross flow field in order to vector the fluid flow through the nozzle. 4. The system of claim 1, wherein the at least one port comprises a plurality of ports, the ports individually positioned such that the pulsed detonation waves simultaneously throttle and vector the fluid flow. 5. The system of claim 1, wherein the at least one pulse detonation device pulses the detonation waves at a predetermined frequency. 6. The system of claim 5, wherein the predetermined frequency is within a range of approximately 100 hertz to approximately 1000 hertz. 7. The system of claim 1, wherein the detonation waves travel inside the port at a speed approaching the theoretical Chapman-Jouguet wave speed. 8. The system of claim 1, wherein the at least one pulse detonation device is operable to inject the plurality of detonation waves in a pulsed manner through the port and into the fluid flow to throttle the fluid flow by decreasing the effective cross-sectional area of the throat to control a temperature of the fluid flow. 9. The system of claim 1, wherein the at least one pulse detonation device is operable to inject the plurality of detonation waves in a pulsed manner through the port and into the fluid flow to throttle the fluid flow by decreasing the effective cross-sectional area of the throat to control a pressure of the fluid flow. 10. The system of claim 1, wherein the at least one pulse detonation device is operable to inject the plurality of detonation waves in a pulsed manner through the port and into the fluid flow to throttle the fluid flow by decreasing the effective cross-sectional area of the throat to control a mass flow of the fluid flow. 11. The system of claim 1, wherein the nozzle is selected from the group consisting of a fixed geometry nozzle and a variable geometry nozzle. 12. The system of claim 1, wherein the nozzle is integral to a jet engine onboard an aircraft. 13. The system of claim 1, wherein the pulsed detonation wave is followed into the nozzle by a plurality of products of combustion that are fuel rich. 14. The system of claim 1, wherein the pulse detonation device further comprises a processor operable to execute software instructions to control the effective cross-sectional area of the throat of the nozzle over a range of operating conditions. 15. A system for altering a fluid flow, comprising:a nozzle integral to a jet engine onboard an aircraft, the nozzle having a fluid flow and comprising a converging portion, a diverging portion downstream of the converging portion, and a throat coupling the converging portion to the diverging portion;a plurality of ports located in a wall of the nozzle; anda plurality of pulse detonation devices operatively coupled to a respective port, each pulse detonation device operable to inject a plurality of detonation waves in a pulsed manner through its respective port and into the fluid flow in a direction that is non-parallel to the fluid flow. 16. The system of claim 15, wherein the ports are individually positioned to provide a symmetric cross flow field in order to vary the effective cross-sectional area of the throat within the nozzle. 17. The system of claim 15, wherein at least one port is adapted to provide an asymmetric cross flow field in order to vector the fluid flow through the nozzle. 18. The system of claim 15, wherein the ports are individually positioned such that the pulsed detonation waves simultaneously throttle and vector the fluid flow. 19. The system of claim 15, wherein the detonation waves are pulsed within a frequency range of approximately 100 hertz to approximately 1000 hertz. 20. The system of claim 15, wherein the detonation waves are pulsed at variable frequencies. 21. The system of claim 15, wherein the detonation waves travel inside the ports at a speed approaching the theoretical Chapman-Jouguet wave speed. 22. The system of claim 15, wherein the nozzle is selected from the group consisting of a fixed geometry nozzle and a variable geometry nozzle. 23. The system of claim 15, wherein the pulsed detonation waves are followed into the nozzle by a plurality of products of combustion that are fuel rich. 24. The system of claim 15, wherein the pulse detonation devices are coupled to at least one processor operable to execute software instructions to control the effective cross-sectional area of the throat of the nozzle over a range of operating conditions.