초록 ▼

Concepts and technologies described herein provide for the creation of a high speed actuating fluid flow utilizing one or more pulse detonation actuators. According to one aspect of the disclosure provided herein, an actuating flow trigger is detected with respect to a high speed airflow over an aer

Concepts and technologies described herein provide for the creation of a high speed actuating fluid flow utilizing one or more pulse detonation actuators. According to one aspect of the disclosure provided herein, an actuating flow trigger is detected with respect to a high speed airflow over an aerodynamic surface. In response, a pulse detonation actuator is activated and a resulting high speed actuating flow is directed into the high speed airflow to alter at least one attribute of the high speed airflow.

대표청구항 ▼

1. An active flow control system, comprising: an ignition source;a first pulse detonation tube coupled to the ignition source and comprising a fuel inlet, the first pulse detonation tube configured to create a detonation wave from a deflagration wave after ignition of fuel within the first pulse det

1. An active flow control system, comprising: an ignition source;a first pulse detonation tube coupled to the ignition source and comprising a fuel inlet, the first pulse detonation tube configured to create a detonation wave from a deflagration wave after ignition of fuel within the first pulse detonation tube via the ignition source; anda first outlet coupled to an aerodynamic surface and configured to direct the detonation wave into an ambient airflow over the aerodynamic surface;a second pulse detonation tube having a second outlet coupled to the aerodynamic surface and configured to direct a detonation wave from the second pulse detonation tube into the ambient airflow over the aerodynamic surface; anda pulse detonation controller configured to determine a presence of a shock wave, and in response to determining the presence of the shock wave, coordinating the ignition of the first pulse detonation tube and the second pulse detonation tube such that the shock wave is eliminated or moved forward or aft. 2. The active flow control system of claim 1, further comprising a plenum coupled to each pulse detonation tube, each plenum having an entrance connected to an end of the pulse detonation tube opposite the ignition source and further connected to the outlet coupled to the aerodynamic surface, the plenum configured to alter a velocity of the detonation wave received from the pulse detonation tube before expelling the detonation wave through the outlet. 3. The active flow control system of claim 1, wherein coordinating the ignition of the first pulse detonation tube and the second pulse detonation tube comprises coordinating ignition of the first pulse detonation tube and the second pulse detonation tube according to a pre-determined time delay. 4. The active flow control system of claim 1, wherein each outlet comprises a plurality of outlets such that the detonation wave is directed into the ambient airflow at a plurality of locations associated with the aerodynamic surface. 5. An active flow control system, comprising: an aerodynamic surface exposed to a high speed airflow and having a first outlet and a second outlet downstream of the first outlet, each outlet providing for fluid flow through the aerodynamic surface and into the high speed airflow;at least one sensor associated with the aerodynamic surface, the at least one sensor configured to measure an attribute of the high speed airflow;a first pulse detonation actuator coupled to the first outlet of the aerodynamic surface and configured to direct an actuating flow through the first outlet and into the high speed airflow;a second pulse detonation actuator coupled to the second outlet and configured to direct an actuating flow through the second outlet and into the high speed airflow; anda pulse detonation controller communicatively linked to the at least one sensor, to the first pulse detonation actuator, and to the second pulse detonation actuator, and configured to receive a measurement of the attribute of the high speed airflow from the at least one sensor,determine an indication of a shock wave from the measurement, the shock wave positioned at a location between the first outlet and the second outlet, andresponsive to the indication of the shock wave, coordinate activation of the first pulse detonation actuator with activation of the second pulse detonation actuator to create the actuating flow.