Brian K Hershberger

US Patent:

6679048, Jan 20, 2004

Filed:

Dec 18, 2002

Appl. No.:

10/323484

Inventors:

Douglas Lee - Valencia CA
J. Thomas Anderson - Santa Clarita CA
Brian K. Hershberger - Granada Hills CA

Assignee:

Lockheed Martin Corporation - Bethesda MD

International Classification:

F02K 128

US Classification:

60204, 60231, 23926523

Abstract:

A device for controlling the direction of flow of a primary fluid includes one or more injectors oriented to inject a secondary fluid against the direction of flow of the primary fluid. The injector is formed by drilling or otherwise forming a hole at an angle to the surface of one or more sidewalls of an engine nozzle or other device. A feedback controller regulates the amount and duration of the secondary fluid injection to achieve the commanded attitude or attitude rate. The controller is coupled to one or more plenums attached to the sidewall(s). The plenums can be arranged to deliver secondary fluid to one or more of the injectors. Secondary fluid delivery to each plenum can be controlled independently to control the flow of the primary fluid in one or more directions. The device can be used to provide thrust vectoring in an aircraft or other type of vehicle, as well as other applications where it is desired to control the direction of a primary fluid.

US Patent:

7621481, Nov 24, 2009

Filed:

Sep 3, 2004

Appl. No.:

10/933962

Inventors:

Brian Keith Hershberger - Granada Hills CA, US
David J. Devine - Thousand Oaks CA, US
Axel Sehic - Canyon County CA, US

Assignee:

Lockheed-Martin Corporation - Bethesda MD

International Classification:

B64C 25/10
B64C 25/20

US Classification:

244102A, 244102 SS

Abstract:

A landing gear assembly comprises a landing gear strut assembly further comprising a landing gear strut having a longitudinal axis and extending from an inboard end to an outboard end capable of attaching to a wheel, and a landing gear housing. The landing gear housing has a longitudinal axis coincident with the landing gear strut longitudinal axis and having an interior chamber capable of accepting a portion of the landing gear strut. The landing gear housing is capable of pivotably coupling to an aircraft. The landing gear assembly further comprises a retraction linkage having an inboard end capable of coupling to the aircraft and an outboard end coupled to the landing gear housing. The retraction linkage is moveable to retract the landing gear strut assembly into an aircraft landing gear compartment about the landing gear housing pivotable aircraft coupling. The landing gear assembly further comprises a steering linkage capable of coupling and decoupling to the landing gear strut and, when coupled, capable of steerably rotating the landing gear strut with respect to the landing gear housing about the coincident longitudinal axis. The landing gear assembly further comprises a planing linkage that can gradually rotate the landing gear strut into a planar position as the landing gear strut assembly is retracted and decoupled from the steering linkage.

US Patent:

6460445, Oct 8, 2002

Filed:

Jan 7, 2002

Appl. No.:

10/038424

Inventors:

Eric P. Young - Pasadena CA 91106
John Reynolds - Stevenson Ranch CA 91381
Brian Hershberger - Granada Hills CA 91344

International Classification:

B64D 104

US Classification:

89 151, 89 154, 89 159, 2441374, 294 8226

Abstract:

A payload dispensing system for an aircraft is disclosed that includes a housing mounted to the aircraft. A hollow shaft is mounted to the housing having an open first end and a closed off second end with a hole therethrough. The payload includes an aperture having a first end on an external surface thereof and a second end in the interior therein. A wire cable releasably secures the payload to the housing such that the hollow shaft extends into the aperture of the payload. A compression spring is mounted at least partially within the hollow shaft, having a first end in contact with the second end of the hollow shaft and a second end in contact with the second end of the aperture within the payload, the spring having a compressed position when the hollow shaft is within the aperture in the payload and asserts a force tending to separate the payload from the aircraft. A cable cutter is used to cut the cable to release the payload from the housing, such that the spring forces the payload away from the aircraft and the hollow shaft guides the payload during separation.