Lockheed Martin Corporation

Other

Lockhead Martin Corp.

Lockheed Martin Corroration

Daniel N Miller

Neal David Domel

Dan J Baruzzini

Patrick J Yagle

Philip P Truax

Eric Frederick Charlton

Kerry B Ginn

Jeffrey W Hamstra

Brian Taylor Rosenberger

Brent N McCallum

Paul Douglas McClure

Robert R Boyd

Charles J Chase

David M Wells

Stewart A Jenkins

Edward C Ma

Jeffrey Alan Catt

Brian T Rosenberger

Louis G Hunter

Brian R Smith

Paul E Hagseth

Kent W Benner

Jeffrey G Hakes

Richard Scott Ely, Ii

Perry Wooden

Cole W Schemm

Ruble E Moor

Rob S Burgun

Jeff G Hakes

Edwin L Blosch

David D Young

Jeffrey J Azevedo

Erich E Bender

Neal D Domel

Construction bucket having a sloped interior bottom surface

A wing includes a low pressure side, a high pressure side opposite the low pressure side, and a drag reducing apparatus coupled to the low pressure using an adhesive. The drag reducing apparatus includes a first side coupled to the low pressure side of the wing, and a second side opposite the first side. The second side includes a plurality of vortex generators arranged in an array configuration. The vortex generators generate one or more vane vortices near an end of the low pressure side of the wing, thereby weakening a wingtip vortex generated by the wing.

Adhesive panels of microvane arrays for reducing effects of wingtip vortices

An exhaust plume cooling device for cooling an exhaust gas plume to reduce deleterious heat effects on impinged and surrounding surfaces. The device is supportable in a position downstream of an exhaust nozzle of an exhaust gas plume-producing engine and configured to periodically interrupt the flow of exhaust gases by injecting fluid into the exhaust plume zone.

Exhaust plume cooling using periodic interruption of exhaust gas flow to form ambient air entraining vortices

In one embodiment, an airfoil includes a first end and a second end opposite the first end. The airfoil also includes a first side and a second side opposite the first side. The airfoil includes a continuous panel coupled to the first side of the airfoil. The continuous panel includes a first edge having a first uneven edge pattern. The first edge has at least four vertices disposed thereon. The continuous panel extends from the first end of the airfoil to a second end of the airfoil.

Panels comprising uneven edge patterns for reducing boundary layer separation

An apparatus for suppressing shock-induced separation of high speed airflow from a relatively low-energy boundary layer. The apparatus may include an actuator or array of actuators configured to alternately inhale and exhale fluid and positioned to alternately inhale fluid from and exhale fluid into a boundary layer of a fluid mass flowing along the wall. The actuator may be positioned to inhale fluid from a boundary layer separation bubble induced by a supersonic shock wave propagated in the fluid mass.

Suprression of shock-induced airflow separation

An exhaust impingement cooling device for reducing heating effects of an exhaust plume on an impinged surface. An exhaust nozzle exit screen is positioned across an exhaust plume flow path, and includes a plurality of flowpath diverging apertures that spread at least a portion of an exhaust plume that is being emitted along the exhaust plume flow path from an exhaust plume source. Flow control jets are arrayed within the exhaust plume flow path in respective positions where their operation will augment the flow of exhaust plume gases through the screen, thereby increasing the momentum and mixing of the exhaust plume with cooler ambient air.

Exhaust impingement cooling

An airfoil tip vortex mitigation arrangement comprising one or more flow directors configured and positioned to re-direct freestream air over a low pressure surface of an airfoil in such a way as to displace and weaken a main tip vortex generated at a tip of the airfoil.

Minimally intrusive wingtip vortex wake mitigation using microvane arrays

In one embodiment, a wing includes a low pressure side, a high pressure side opposite the low pressure side, and a drag reducing apparatus coupled to the low pressure using an adhesive. The drag reducing apparatus includes a first side coupled to the low pressure side of the wing, and a second side opposite the first side, the second side comprising a plurality of vortex generators arranged in an array configuration, the array configuration of vortex generators operable to weaken a wingtip vortex generated by the wing by generating one or more vane vortices near an end of the low pressure side of the wing.

Reducing jet noise by weakening Mach cones in a jet exhaust gas streamtube. The Mach cones are weakened by modifying exhaust gas flow in a longitudinal axial core of the exhaust gas streamtube.

Jet exhaust noise reduction

An exhaust plume cooling device for cooling an exhaust gas plume to reduce deleterious heat effects on impinged and surrounding surfaces. The device is supportable in a position downstream of an exhaust nozzle of an exhaust gas plume-producing engine and configured to periodically interrupt the flow of exhaust gases.

An airfoil active bleed system and related method. A housing includes an induction wall, an exhaust wall having one or more exhaust ports, and a chamber between the induction and exhaust walls. Zero-net-mass-flux actuators are located in the chamber and configured and positioned to collectively induct fluid through the induction wall and selectively exhaust fluid through the exhaust port(s).

Active bleed for airfoils

An airfoil tip vortex mitigation device comprising an intake port disposed in a first surface of an airfoil and an exit port in fluid communication with the intake port and disposed in a second surface of the airfoil where air pressure is less than at the first surface when the airfoil is producing lift. The channel and exit port are positioned and configured to direct diverted air in such a way as to weaken an airfoil tip vortex that's produced by the airfoil when the airfoil is producing lift.

Minimally intrusive wingtip vortex wake mitigation using inside-mold-line surface modifications

A pulsed-jet active flowfield control actuation system enhances the rate of heat transfer and heat removal in a heat exchanger for better management of thermal loads. The pulsed jet actuators impart an unsteady component of velocity to the working fluid of the heat exchanger. This design increases the convective heat transfer, and avoids increases in heat exchanger volume and weight for a given performance value.

System, method, and apparatus for pulsed-jet-enhanced heat exchanger

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Bainbridge Island, WA, United States of America

Daniel N Miller