DANIEL R MILLER, II
Electrician at Comanche Trl, Fort Worth, TX

6371414, Apr 16, 2002

Jul 16, 1999

09/354866

Philip P. Truax - Fort Worth TX
Daniel N. Miller - Fort Worth TX
Jeffrey W. Hamstra - Fort Worth TX
Patrick J. Yagle - Fort Worth TX

Lockheed Martin Corporation - Bethesda MD

B64C 2100

244201, 244204, 244 53 B, 138 38

The present invention provides a system and method for actively manipulating and controlling aerodynamic or hydrodynamic fluid flow over a surface. More specifically, the present invention provides a system and method to control aerodynamic or hydrodynamic fluid flow behavior of a ducted fluid flow using very-small-scale effectors. The system and method for actively manipulating and controlling fluid flow over a surface includes the placement of arrays of very-small-scale effectors on ducted surfaces bounding the ducted fluid flow. These very-small-scale effectors actively manipulated the boundary layer manipulated to control the flow behavior of the ducted fluid flow and suppress or prevent flow separation within the primary fluid flow.

6758032, Jul 6, 2004

Feb 7, 2002

10/072690

Louis G. Hunter - Fort Worth TX
Daniel N. Miller - Fort Worth TX
Paul E. Hagseth - Fort Worth TX

Lockheed Martin Corporation - Bethesda MD

F02K 130

60231, 60242, 23926523

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.

6112512, Sep 5, 2000

Aug 5, 1997

8/906731

Daniel Nicholas Miller - Fort Worth TX
Jeffrey Alan Catt - Benbrook TX

Lockheed Martin Corporation - Fort Worth TX

F02K 130, F02K 128

60204

An apparatus and method for varying the effective cross sectional area of an opening through a nozzle provides a controller 78 that pulses a fluidic cross flow through an injector associated with the nozzle 68 proximate to the opening of the nozzle. The controller 78 directs the injector 76 to provide a pulsed cross flow having a predetermined frequency, amplitude, or wave form. The pulsed cross flow interacts with a primary flow 14 through the nozzle 68 to partially block the nozzle's opening 72, thereby effectively decreasing the cross sectional area of opening 72 in a jet engine 42. A plurality of pulsed cross flows proximate to a nozzle's throat 70 permits effective afterburner 64 operations even with a fixed geometry nozzle by allowing throttling of the primary flow 14. Further, variations in the cross flow's orientation pulse frequency, amplitude or wave form, or the cross flow's mass flow characteristics can allow vectoring of the primary flow 14.

6112513, Sep 5, 2000

Aug 5, 1997

8/906768

Jeffrey Alan Catt - Benbrook TX
Daniel Nicholas Miller - Fort Worth TX

Lockheed Martin Corporation - Fort Worth TX

F02K 130, F02K 128

60204

An apparatus and method for varying the effective cross sectional area of an opening through a fixed geometry nozzle provides a fluidic cross flow with an injector incorporated in the throat of the nozzle 68 proximate to the subsonic portion of the flow through the nozzle. One or more injectors 76 are directed at an injector angle opposed to the subsonic portion of the flow. The opposed cross flow from injector 76 interacts with a primary flow 14 through the nozzle 68 to partially block the nozzle's opening 72, thereby effectively decreasing the cross sectional area of opening 72 in a jet engine 42. A plurality of cross flows proximate to a nozzle's throat 70 permits effective afterburner 64 operations even with a fixed geometry nozzle by allowing throttling of the primary flow 14. Further, variations in the cross flow's mass flow characteristics or injection angle can allow vectoring of the primary flow 14.

6308740, Oct 30, 2001

Aug 15, 2000

9/639187

Brian R. Smith - Colleyville TX
Daniel N. Miller - Fort Worth TX
Patrick J. Yagle - Fort Worth TX
Erich E. Bender - Arlington TX
Kerry B. Ginn - Weatherford TX

Lockheed Martin Corporation - Bethesda MD

E03B 500

137892

The present invention reveals a method and apparatus for more efficiently injecting a primary fluid flow in a fluid ejector used to pump lower velocity fluid from a secondary source. In one embodiment, the primary fluid flow is a pulsed or unsteady fluid flow contained within an inner nozzle situated within a secondary flow field. This secondary fluid flow is bounded within the walls of an ejector or shroud. The secondary and primary fluid flows meet within the ejector shroud section wherein the secondary fluid flow is entrained by the primary fluid flow. The geometry of the ejector shroud section where the primary and secondary fluids mix is such as to allow the beginning of primary injector pulse to be synchronized with an acoustic wave moving upstream through the ejector initiated by the exiting of the previous pulse from the ejector shroud. The ejector's geometric properties are determined by the acoustic properties, frequency, duty cycle, and amplitude, of the pulsed primary fluid flow. Furthermore, the frequency, duty cycle and amplitude of the primary fluid flow may be varied in order to vary the efficiency of the injector.