JOHN PAUL HARRELL
Pilots at Ibeza Rd, San Juan Capistrano, CA

5751460, May 12, 1998

Oct 11, 1995

8/540731

John P. Harrell - Mission Viejo CA
Bryce A. Wheeler - Mammoth Lakes CA

Hughes Aircraft Company - Los Angeles CA

G02B 2608, G02B 7182

359198

An articulated optical system has a pair of actuators (42, 44) each of which pivot a head mirror (34) about respective parallel axes (E. sub. 1, E. sub. 2) to direct the line-of-sight of an optical beam through a window (36) of a vehicle (30) to an optical sensor (38). Of the actuators, a coarse actuator (42) pivots the mirror (34) through substantially the entire desired field of regard of the optical system, and a fine actuator (44) pivots the mirror (34) for fine adjustment, e. g. , less than five degrees. The coarse actuator (42) is positioned so that the axis thereof (E. sub. 1) is located as close as possible to an edge of the mirror (34), so that the radial distance therebetween is small; therefore, the size of the window (36) is minimized with respect to the diameter (d. sub. b) of the optical beam. The fine actuator (44) is attached to approximately the geometric center of the mirror (34), so that the mirror (34) is statically balanced about the elevation axis (E. sub.

5820079, Oct 13, 1998

Apr 24, 1997

8/843115

John P. Harrell - Mission Viejo CA

Hughes Electronics - Los Angeles CA

F16F 1512, B64D 2700, B64G 138

244165

An apparatus for mounting a momentum wheel assembly (10) to a spacecraft (54). The momentum wheel assembly (10) includes a momentum wheel which has a primary spin axis coinciding with the primary spin axis of the spacecraft and spins in a direction opposite that of the spacecraft (54). Suspension isolation struts (20) attach the momentum wheel assembly (10) to the spacecraft (54) and provide substantial vibration isolation between the spacecraft (54) and the momentum wheel assembly (10). Voice coil actuators (40) attach to an adaptor ring (14) which in turn attaches to the spacecraft (54). The voice coil actuators (40) magnetically interact with a magnetically conductive element (42) attached to the momentum wheel assembly case (12). Interaction between the voice coil actuators (40) and the magnetic element (42) provides forces which displace the momentum wheel assembly case (12) in two axes orthogonal to the primary spin axis.

2012012, May 17, 2012

Nov 12, 2010

12/945701

John P. HARRELL - Mission Viejo CA, US
Geoffrey A. LONG - Torrance CA, US
Michael L. MENENDEZ - Corona CA, US

RAYTHEON COMPANY - Waltham MA

G02B 7/00, H02K 49/10

359896, 310103

Various embodiments provide a system for moving optical elements. The system includes a first rotor and a second rotor configured to rotate in opposite directions. The system further includes a first plurality of paddles coupled to the first rotor, each of the plurality of paddles having an aperture configured to receive a first optical element, and a second plurality of paddles coupled to the second rotor, each of the plurality of paddles having an aperture configured to receive a second optical element. The first rotor and the second rotor are configured to move the first optical element between a retracted position and a desired position and to move the second optical element between the desired position and a retracted position substantially simultaneously such that a reaction torque of the first rotor cancels a reaction torque of the second rotor.

5790049, Aug 4, 1998

Feb 20, 1996

8/602560

John P. Harrell - Mission Viejo CA

Raytheon Company - Los Angeles CA

G08C 1700

34087028

A suspension system permits fine angular adjustment of a gimbal-mounted platform and, in combination with a wireless power and communications transfer system, eliminates the unwanted forces associated with systems which rely upon cables to transfer power and signals between a gimbal platform and its support structure.

5820078, Oct 13, 1998

Sep 27, 1996

8/721882

John P. Harrell - Mission Viejo CA

Hughes Electronics Corporation - El Segundo CA

B64G 128

244165

A control moment gyro having a housing enclosing a spinning momentum wheel. A rocking plate circumscribes the housing and is compliantly connected thereto by a set of isolator struts and non-contacting actuators which isolate the rocking plate from the inherent vibrations and oscillations of the momentum wheel. The rocking plate is pivotably connected to a gimbal ring about a first pivot axis normal to the spin axis of the momentum wheel. The gimbal ring is pivotably connected to the structure of the spacecraft about a second axis orthogonal to the spin axis and the first pivot axis. Actuators are provided to control the attitude of the housing relative to the rocking plate, the rocking plate relative to the gimbal ring, and the gimbal ring relative to the spacecraft.

6113033, Sep 5, 2000

Feb 4, 1999

9/244695

Thomas R. Parks - Hermosa Beach CA
John W. Smay - Redondo Beach CA
John P. Harrell - Mission Viejo CA

Hughes Electronics Corporation - El Segundo CA

B64G 128

244165

An apparatus for storing energy and actuating the attitude of a spacecraft includes a first gimbaled flywheel assembly having a first rotor rotating in a first direction, and a second gimbaled flywheel assembly having a second rotor rotating in a second direction opposing the first direction. The first and second gimbaled flywheel assemblies are adapted to store and release energy and to actuate the attitude of the spacecraft. The apparatus includes one or more non-gimbaled counter-rotating flywheel pairs that are adapted to store and release energy.