Bernard J Lamberty

US Patent:

48621854, Aug 29, 1989

Filed:

Apr 5, 1988

Appl. No.:

7/177966

Inventors:

George S. Andrews - Kent WA
Bernard J. Lamberty - Kent WA
Daniel J. Tracy - Maple Valley WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

H01Q 320

US Classification:

343761

Abstract:

Disclosed is a variable angle conical scanning antenna that employs an offset paraboloidal reflector which is rotated about an axis that extends through the focus of the paraboloid of revolution that defines the reflector. Electromagnetic energy is supplied to the reflector by an antenna feed that is mounted at the focus of the paraboloid of revolution and directed along the axis of rotation. In this arrangement the electromagnetic energy that is reflected from the offset paraboloidal reflector forms an angle between the axis of rotation and the beam of reflected electromagnetic energy that is equal to the angle between the axis of rotation and the focal axis of the paraboloid of revolution that defines the reflector. Thus, conical scanning at a cone angle that is equal to twice the angle between the axis of rotation and the reflected beam of electromagnetic energy is achieved as the offset paraboloidal reflector is rotated. Variable angle scanning (i. e.

US Patent:

46085726, Aug 26, 1986

Filed:

Dec 10, 1982

Appl. No.:

6/448511

Inventors:

Thomas L. Blakney - Bellevue WA
Douglas D. Connell - Seattle WA
Bernard J. Lamberty - Kent WA
James R. Lee - Seattle WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

H01Q 148
H01Q 136

US Classification:

3437925

Abstract:

To optimize antenna bandwidth and efficiency in broad-band antenna elements of the planar, multiarm spiral and log periodic types, a conically shaped ground plane characterized by progressively sized circumferential chokes, is arranged on a common axis with the axial center of the spiral or log periodic elements so that the electrical spacing between the excited regions of the log periodic of spiral elements and the ground plane maintains a constant one-quarter wavelength relationship. The progressively sized circumferential chokes on the ground plane cut off the flow of excessive radial currents along the ground plane surface to achieve an improved mix of excitation and reexcitation modes. In one embodiment, the circumferential chokes on the conical ground plane are partially shunted by shunting strips that electrically or capacitively bridge the choke walls to reestablish limited radial currents along the ground plane for sustaining certain desirable antenna modes. In another disclosed embodiment, the equivalent one-quarter wavelength relationship between the driven spiral or log elements and the reflecting ground plane is maintained in an antenna structure in which the driven elements are disposed on the surface of a dielectrically shaped cone and the ground plane and progressively sized circumferential chokes are arranged in a generally planar array.

US Patent:

52931722, Mar 8, 1994

Filed:

Sep 28, 1992

Appl. No.:

7/953528

Inventors:

Bernard J. Lamberty - Kent WA
George S. Andrews - Kent WA
James L. Freeman - Renton WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

H01Q 126
H01Q 1930

US Classification:

343701

Abstract:

Disclosed is an array antenna (10) that may be reconfigured to point in multiple directions. The array antenna includes a driven element (12) coupled to a transmission line (14) and a pair of passive elements (22) and (24). The passive elements (22) and (24) each include three antenna segments that are coupled together by a pair of optoelectronic switches (26) and (28), respectively. When the optoelectronic switches coupled to a particular passive element are closed the element functions as a reflector; when the switches are open, the element functions as a director. Other reconfigurable antennas are also disclosed, including antennas with reconfigurable gain and field pattern characteristics.

US Patent:

48704261, Sep 26, 1989

Filed:

Aug 22, 1988

Appl. No.:

7/234636

Inventors:

Bernard J. Lamberty - Kent WA
Luis L. Oh - Seattle WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

H01Q 500
H01Q 1300

US Classification:

343727

Abstract:

A radar antenna element comprises a lower band waveguide and an array of parallel, dual-polarized, higher band waveguides and dipoles mounted within or directly adjacent an aperture of the lower band waveguide. The lower band waveguide and each higher band waveguide have one cross-sectional dimension less than 0. 5 wavelength. A choke section, tuned dielectric or absorber isolates signals of the higher band waveguides from signals of the lower band waveguide. An array of such radar antenna elements locates a radar target with lower band signals and tracks that target with higher band signals, for instance.

US Patent:

46300643, Dec 16, 1986

Filed:

Sep 30, 1983

Appl. No.:

6/537485

Inventors:

George S. Andrews - Kent WA
Thomas L. Blakney - Bellevue WA
Douglas D. Connell - Seattle WA
Bernard J. Lamberty - Kent WA
James R. Lee - Seattle WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

H01Q 136

US Classification:

343895

Abstract:

A monopulse spiral antenna system of the type having a minimum of three, interwound spiral arms for multimode, direction of arrival sensing, is disclosed in which the antenna arms are shaped and arranged in an overlapping configuration that allows the interarm impedance of the antenna to be adjusted, substantially independently of other electrical properties of the antenna, for matching of the antenna impedance of a mode forming network while preserving the broadband, directional capabilities of the antenna. Several different embodiments of the impedance adaptive antenna are disclosed including a preferred, eight-arm exponential spiral in which the arms are conductive strips transversely inclined relative to a plane formed by the spiral so that opposed and parallel surfaces of adjacent arm strips create a dominant interarm capacitance that in turn determines the overall input impedance of the antenna. Furthermore, the opposed, proximate surfaces of the strip-shaped arms are dimensioned, spaced and inclined at an angle that adapts the input impedance of the antenna to a value matching that of the mode forming network.

US Patent:

51362953, Aug 4, 1992

Filed:

May 14, 1991

Appl. No.:

7/699748

Inventors:

James G. Bull - Issaquah WA
Michael de la Chapelle - Bellevue WA
Bernard J. Lamberty - Kent WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

G01S 738

US Classification:

342 15

Abstract:

One or more decoys (22) are towed by an aircraft (18) to confuse hostile radar. The tow lines (20) to the decoys (22) include fiber optic components which optically transmit to the decoys (22) both radio frequency signals for retransmission to hostile radar (24), and direct current power. The fiber optic components absorb strain forces imposed by towing the decoys (22). Multiple decoys (22) are deployed at varying distances from the aircraft (18) to increase the overall range of frequencies covered by the system, simulate a plurality of false targets, or accomplish angle gate deception. The deception may be accomplished by transmitting signals from the decoys in sequence and can be enhanced by dynamically varying the power levels of the decoy transmitting antennas. The fiber optic components may be separate optical fibers deployed separately or joined together for simultaneous deployment. The preferred configuration is a single optical fiber with coaxial inner and outer cores.

US Patent:

52608204, Nov 9, 1993

Filed:

Dec 16, 1991

Appl. No.:

7/808439

Inventors:

James G. Bull - Issaquah WA
Michael de La Chapelle - Bellevue WA
Bernard J. Lamberty - Kent WA

International Classification:

H04B 1000
H01Q 1500

US Classification:

359145

Abstract:

One or more decoys (22) are towed by an aircraft (18) to confuse hostile radar. The tow lines (20) to the decoys (22) include fiber optic components which optically transmit to the decoys (22) both radio frequency signals for retransmission to hostile radar (24), and direct current power. The fiber optic components absorb strain forces imposed by towing the decoys (22). Multiple decoys (22) are deployed at varying distances from the aircraft (18) to increase the overall range of frequencies covered by the system, simulate a plurality of false targets, or accomplish angle gate deception. The deception may be accomplished by transmitting signals from the decoys in sequence and can be enhanced by dynamically varying the power levels of the decoy transmitting antennas. The fiber optic components may be separate optical fibers deployed separately or joined together for simultaneous deployment. The preferred configuration is a single optical fiber with coaxial inner and outer cores.

US Patent:

50363310, Jul 30, 1991

Filed:

Sep 18, 1989

Appl. No.:

7/408777

Inventors:

Kyle A. Dallabetta - Seattle WA
Bernard J. Lamberty - Kent WA
Kenneth G. Voyce - Bellevue WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

H01Q 2106
H04B 152

US Classification:

342361

Abstract:

A polarization diversity system (10) including an adaptive polarization combiner (14) is disclosed. The combiner receives input signals V. sub. i1 and V. sub. i2 of arbitrary relative phase and amplitude, produced in response to orthogonally polarized components of an incident electromagnetic field. The combiner includes a hybrid network (18) that performs the combination of the input V. sub. i1 and V. sub. i2 based on phase adjustments initiated by a feedback circuit (20). The feedback circuit includes a limit set and sensing circuit (26) that allows feedback signals V. sub. c1, V. sub. c2, V. sub. c3, and V. sub. c4 to be swept through a range suitable to phase shifters (28, 32, 36, and 38) included in the hybrid network, thus allowing different components to be more easily used in the hybrid network. Further, the combiner is constructed to function properly in the absence of one of the signals input to the combiner. More particularly, a sensing circuit (22) is employed to disable the sweep function in response to the occurrence of conditions representative of the absence of one of the input signals.