KENNETH ROY LORELL
Pilots at Rinconada Ct, Los Altos, CA

5359520, Oct 25, 1994

Jun 8, 1992

7/895313

Jean-Noel Aubrun - Mountain View CA
Kenneth R. Lorell - Los Altos CA
Paul J. Reshatoff - Menlo Park CA

Lockheed Missiles & Space Company, Inc. - Sunnyvale CA

G05B 1302, G05B 1918, G05B 510

364148

An adaptive control includes a digital error correction system (DECS) to reduce control system error to near zero by anticipating a problem and feeding forward in time a correction to deal with the problem before it happens. The adaptive control is used in a controlled system of the kind which is cyclical in operation and which operates in response to repetitive cycle commands so that the operation of the system is substantially predictable for a significant number of cycles of operation. The adaptive control is incorporated in a spatial chopping or scanning telescope system of the kind in which a telescope mirror is moved in repetitive cycle motions and in a rigidly prescribed pattern between varied orientations and wherein the mirror is held for a prescribed, relatively long period of time in each orientation and is moved rapidly in a relatively short period of time from one orientation to another. The adaptive control permits accurate control of the command waveform frequency and shape, enables the telescope system to keep position error near zero by using, in combination with the feedback loop, a feed forward loop directly driving the actuators during the transition period and actively holding the mirror in position during the dwell periods. The adaptive control provides the ability to eliminate overshoot and ringing, because the force command provides the precise amount of braking required to exactly stop the mirror motion.

6896441, May 24, 2005

Mar 4, 2003

10/379982

Patrick Joseph Champagne - Portola Valley CA, US
Kenneth Roy Lorell - Los Altos CA, US

Lockheed Martin Corporation - Bethesda MD

B64G001/64

403326, 244161

Embodiments of the present invention are directed to a compact and lightweight, automated latching device which includes a passive catch configured to be engaged with a motor-powered latch to form a mechanical connection between two structure in a precise and repeatable manner. An active damping mechanism is used to dissipate any vibrational energy that may be present in the latched structure. The apparatus may be used to precisely orient and attach a deployable element, usually of a space vehicle, to the main body of the vehicle. In one embodiment, a latching apparatus comprises a catch having a catch body and a probe connected to the catch body. A latch has a main housing and a grip mechanism movable relative to the main housing. The grip mechanism is configured to grip the probe and to be actuatable to pull the probe toward the latch. A damping member is coupled with the main housing of the latch, and is movable relative to the main housing of the latch toward the catch.

5245830, Sep 21, 1993

Jun 3, 1992

7/892855

Jean-Noel Aubrun - Mountain View CA
Kenneth R. Lorell - Los Altos CA
Paul J. Reshatoff - Menlo Park CA
Robert R. Clappier - Los Altos CA

Lockheed Missiles & Space Company, Inc. - Sunnyvale CA

F25B 900

62 6

An adaptive control includes a digital error correction system (DECS) to reduce control system error to near zero by anticipating a problem and feeding forward in time a correction to deal with the problem before it happens. The adaptive control is used in a controlled system of the kind which is cyclical in operation and which operates in response to repetitive cycle commands so that the operation of the system is substantially predictable for a significant number of cycles of operation. The adaptive control is incorporated in a refrigerator system in which two Stirling cycle refrigerators are mounted in opposition to one another. The adaptive control permits accurate control of the command waveform frequency and shape, enables the refrigerator system to be more thermodynamically efficient, and enables the two refrigerators to exactly cancel each other's vibration.

7009752, Mar 7, 2006

Jan 21, 2004

10/763021

Kenneth Roy Lorell - Los Altos CA, US
Jean-Noël Aubrun - Mountain View CA, US

Lockheed Martin Corporation - Bethesda MD

G02B 26/00

359290, 359291, 359292, 359198, 359203

A steerable mirror assembly, the assembly comprising a mounting plate and a mirror with a mounting surface and a reflective surface. The assembly further comprising at least one flexible connector coupled between the mounting plate and a peripheral portion of the mirror. The flexible connector is adapted to allow the mirror to move within a predetermined range along an axis perpendicular to the surface of the mirror and adapted to allow tilting of the mirror. The assembly also comprising at least one moveable support member coupled between the mounting plate and the mounting surface of the mirror. The moveable support member provides mechanical support to the mirror and is adapted to move the mirror within a predetermined range along an axis perpendicular to the surface of the mirror and adapted to allow tilting of the mirror. The assembly additionally comprising at least one position sensor.

7086300, Aug 8, 2006

Apr 11, 2003

10/412565

Donald F. Zacharie - Sunnyvale CA, US
Kenneth R. Lorell - Los Altos CA, US
Jean-Noel Auburn - Mountain View CA, US

Lockheed Martin Corporation - Bethesda MD

F16H 61/06

74 175, 74 178

Embodiments of the present invention are directed to a linear motion flexural apparatus to provide friction-free linear travel for large stroke motion. In one embodiment, a linear motion flexural apparatus comprises a first member having a first surface, and a second member having a second surface which is spaced from the first surface of the first member. One of the first member and the second member is movable relative to another one of the first member and the second member in a linear direction. At least one sheet is disposed between the first surface of the first member and the second surface of the second member. Each sheet has a first edge portion and a second edge portion generally opposite from the first edge portion. The first edge portion is attached to the first surface of the first member. The second edge portion is attached to the second surface of the second member.

7399096, Jul 15, 2008

Jun 28, 2005

11/167393

Kenneth Lorell - Los Altos CA, US
Scott Miller - San Jose CA, US
Jean-Noel Aubrun - Mountain View CA, US
Mark Wolfson - San Francisco CA, US

Lockheed Martin Corporation - Bethesda MD

G02B 7/182

359877, 359202

An enhanced optical delay line device for providing multiple degree of freedom active control, including first and second actively-controlled mirrors, each of the actively-controlled mirrors having two rotational degrees of freedom and one translational degree of freedom. The first actively-controlled mirror is mounted substantially orthogonally to the second actively-controlled mirror. The system also includes a closed-loop control system, the control system providing six mechanical degrees of freedom of active control for the enhanced optical delay line device by controlling the first and second actively-controlled mirrors based upon a command input and mirror position signals. The present invention is smaller than conventional optical delay line devices, has better performance, and eliminates the need for one of the FSMs, bringing the total number of mechanisms down to two from three.

7380950, Jun 3, 2008

Feb 15, 2005

11/057199

Kenneth R. Lorell - Los Altos CA, US
Stephen R. Winzer - San Jose CA, US
Craig L. Horn - Campbell CA, US
Natarajan Shankar - San Jose CA, US
Robert R. Clappier - Discovery Bay CA, US

Lockheed Martin Corporation - Bethesda MD

G02B 5/08

359849, 359224

A high-bandwidth deformable fast steering mirror (“HDFSM”) system, including an electromechanical fast steering mirror (“FSM”) apparatus, and a deformable mirror (“DM”) apparatus mounted on the electromechanical FSM apparatus. The DM apparatus further includes a DM substrate, a backplane assembly, a plurality of electrostrictive actuators in physical communication with and between the DM substrate and the backplane assembly, for deforming the DM substrate, and a plurality of strain gauges, each strain gauge mounted on one of the plurality of electrostrictive actuators, the plurality of strain gauges measuring individual positions of the plurality of electrostrictive actuators and transmitting the positions as actuator position signals. The high-bandwidth deformable FSM also includes a closed-loop control system, the control system controlling the electromechanical FSM apparatus and the DM apparatus based upon a command input and the actuator position signals.

5803979, Sep 8, 1998

Jul 15, 1996

8/680366

Derek Hine - Portola Valley CA
Roger Hine - Portola Valley CA
Eric Selvik - San Francisco CA
Kenneth Lorell - Los Altos CA
Jeffrey Marical - San Mateo CA

Hine Design Inc. - Sunnyvale CA

B25J 1506

134 2

Transport apparatus for semiconductor wafers which have been subject to chemical mechanical polishing (CMP). The risk of malfunction of an articulated arm fitted with a vacuum chuck can be reduced in a number of different ways. The end effector can be constructed so that it can be easily removed from the arm for cleaning and can be easily replaced in the desired position without the need for adjustment. The arm can include one or more catch chambers into which materials drawn into the vacuum chuck will be deposited, but which will not interrupt the vacuum. The near end of the vacuum passage can be coupled to a source of a cleaning fluid, so that the cleaning fluid can be passed outwards through the vacuum passage to flush out materials drawn into the vacuum passage through the chuck.

8179598, May 15, 2012

Aug 13, 2009

12/541110

David Stubbs - Mountain View CA, US
Alan Duncan - Sunnyvale CA, US
Kenneth R. Lorell - Los Altos CA, US
Howard C. Holmes - Boulder Creek CA, US

Lockheed Martin Corporation - Bethesda MD

G02B 23/08, G02B 23/00

359405, 359399, 359408

A telescope comprises a folding reflector comprising a plurality of sections configured to fold at a plurality of substantially parallel hinges, a support structure configured to support at least two of the plurality of sections of the folding reflector and further configured to fold at one of the plurality of substantially parallel hinges, a corrector assembly configured to deploy from a stowed position in which an optical axis of the corrector assembly is substantially parallel to the parallel hinges to a deployed position in which the optical axis is substantially perpendicular to the folding reflector when the folding reflector is deployed. The telescope further comprises a hexapod configured to stow and deploy the corrector assembly.

7275285, Oct 2, 2007

Nov 15, 2004

10/986881

Kenneth R. Lorell - Los Altos CA, US
Patrick J. Champagne - Portola Valley CA, US

Lockheed Martin Corporation - Bethesda MD

E05D 11/10

16321, 16278, 16286

A deployment hinge for deploying an appendage, including a movable portion affixed to the appendage, and a stationary portion affixed to a stationary body. In a non-deployed state, the movable portion is mechanically engaged with the stationary portion and a mechanical load is transferred between the stationary portion and the movable portion. In a deployed state, the movable portion is mechanically disengaged from the stationary portion, and a mechanical load is prevented from being transferred to the movable portion from the stationary portion.