Charles Calvin Morris

US Patent:

7322545, Jan 29, 2008

Filed:

Dec 29, 2005

Appl. No.:

11/320886

Inventors:

Charles E. Morris - Des Peres MO, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64C 3/56
B64C 13/00

US Classification:

244 49, 244 992

Abstract:

A structural mechanism for an aircraft includes a support, a hinged surface, and a hinge assembly joining the hinged surface to the support. An actuation system includes an actuator shaft engaged to the hinges and lying coincident with a hinged-surface hinge axis and extending through the aligned center passagways of the hinges of the hinge assembly. A lock is selectively operable to lock the hinged surface to the support when the actuator shaft engages the lock. An actuator structure is controllably operable to move the actuator shaft longitudinally along the hinge-surface hinge axis between a first shaft axial position wherein the actuator shaft engages the lock and the hinges, and a second shaft axial position wherein the actuator shaft does not engage the lock but does engage the hinges, and is controllably operable to rotate the actuator shaft about the hinged-surface hinge axis.

US Patent:

7665690, Feb 23, 2010

Filed:

Dec 4, 2007

Appl. No.:

11/949980

Inventors:

Charles E. Morris - Des Peres MO, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64C 3/56
B64C 13/00
F16D 11/04

US Classification:

244 49, 244 992, 192 6991

Abstract:

A structural mechanism for an aircraft includes a support, a hinged surface, and a hinge assembly joining the hinged surface to the support. An actuation system includes an actuator shaft engaged to the hinges and lying coincident with a hinged-surface hinge axis and extending through the aligned center passageways of the hinges of the hinge assembly. A lock is selectively operable to lock the hinged surface to the support when the actuator shaft engages the lock. An actuator structure is controllably operable to move the actuator shaft longitudinally along the hinge-surface hinge axis between a first shaft axial position wherein the actuator shaft engages the lock and the hinges, and a second shaft axial position wherein the actuator shaft does not engage the lock but does engage the hinges, and is controllably operable to rotate the actuator shaft about the hinged-surface hinge axis.

US Patent:

7898120, Mar 1, 2011

Filed:

May 31, 2007

Appl. No.:

11/756462

Inventors:

Charles E. Morris - Des Peres MO, US
Paul Kersens - CreveCoeur MO, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

H02K 41/02

US Classification:

310 1214, 310112, 310114

Abstract:

In an embodiment, an actuator includes a plurality of stator windings adapted to produce a first stator magnetic field that translates along a stator axis, and to produce a second stator magnetic field that rotates around the stator axis. In addition, the actuator includes a rotor, coupled to a shaft, and positioned within a central stator channel. The rotor is adapted to produce a first rotor magnetic field that translates along a shaft axis and to produce a second rotor magnetic field that rotates around the shaft axis. An actuator system includes an actuator and an actuator controller unit, which is adapted to produce actuator inputs. An embodiment of a method for controlling the actuator includes providing actuator inputs to produce a translating magnetic field in the stator, a translating magnetic field in the rotor, a rotating magnetic field in the stator, and a rotating magnetic field in the rotor.

US Patent:

8023794, Sep 20, 2011

Filed:

Aug 10, 2009

Appl. No.:

12/538579

Inventors:

Charles Eugene Morris - Saint Louis MO, US
Thomas L. Weaver - Webster Groves MO, US
Kirby J. Keller - Chesterfield MO, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

G02B 6/00
G02B 6/38

US Classification:

385137, 385 25, 385 26, 385 56, 385 62, 385 66, 385 99

Abstract:

An apparatus for establishing an optical circuit path spanning a discontinuity in an optical channel supported by a first cable oriented about a first axis on a first side of the discontinuity and supported by a second cable section oriented about a second axis on a second side of the discontinuity includes: (a) a first coupling member coupled with the optical channel on the first side; (b) a first supporting member fixed with the first coupling member in an installed orientation in a clamping relation with the first cable section; (c) a second coupling member coupled with the optical channel on the second side; (d) a second supporting member fixed with the second coupling member in an installed orientation clamped with the second cable section; and (e) a connecting member optically coupling the first coupling member with the second coupling member to establish the optical circuit path.

US Patent:

8217331, Jul 10, 2012

Filed:

Jan 19, 2010

Appl. No.:

12/689490

Inventors:

Thomas L. Weaver - Webster Groves MO, US
Charles E. Morris - Des Peres MO, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

H03K 17/78
H03K 17/687

US Classification:

250214SW, 977742

Abstract:

An EMI-resistant control device for providing a control signal may include an optical glass fiber connector housing adapted to be connectable to an apparatus for providing the control signal to the apparatus for controlling operation thereof. The EMI-resistant control device may also include a carbon nanotube optical switch mounted in the optical glass fiber connector housing. The carbon nanotube optical switch may include a plurality of light sensitive carbon nanotubes adapted to connect a voltage source to an output of the EMI-resistant control device in response to an optical signal being received by the optical glass fiber connector housing. The optical glass fiber connector housing directs the optical signal onto the plurality of light sensitive carbon nanotubes. The voltage source provides the control signal to the apparatus.

US Patent:

8362719, Jan 29, 2013

Filed:

Dec 15, 2010

Appl. No.:

12/968751

Inventors:

Charles E. Morris - Des Peres MO, US
Paul Kersens - CreveCoeur MO, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

H02K 7/06
H02K 41/02

US Classification:

318115, 310 1214, 310114

Abstract:

In an embodiment, an actuator includes a plurality of stator windings adapted to produce a first stator magnetic field that translates along a stator axis, and to produce a second stator magnetic field that rotates around the stator axis. In addition, the actuator includes a rotor, coupled to a shaft, and positioned within a central stator channel. The rotor is adapted to produce a first rotor magnetic field that translates along a shaft axis and to produce a second rotor magnetic field that rotates around the shaft axis. An actuator system includes an actuator and an actuator controller unit, which is adapted to produce actuator inputs. An embodiment of a method for controlling the actuator includes providing actuator inputs to produce a translating magnetic field in the stator, a translating magnetic field in the rotor, a rotating magnetic field in the stator, and a rotating magnetic field in the rotor.

US Patent:

8567714, Oct 29, 2013

Filed:

Dec 7, 2007

Appl. No.:

11/952317

Inventors:

Charles E. Morris - Des Peres MO, US
Jeffrey M. Roach - St. Charles MO, US
Howard Carter - Chesterfield MO, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64C 5/10

US Classification:

244 90R, 244 9914, 244213

Abstract:

Systems and techniques are described for actuating a control surface about a pivot point using variable moments. A bracket having a moment arm is coupled to the pivot point such that the bracket is rotatable about the pivot point to actuate the surface. A power actuator has a shaft coupled to the bracket at a coupling point on the moment arm such that actuation force applied to the shaft results in a moment produced about the pivot point. A linear actuator is configured to adjust the location of the coupling point with respect to the pivot point to thereby changing the moment arm and the moment produced about the pivot point as the bracket rotates. By adjusting the distance between the pivot point and the coupling point, the moments produced about the pivot point can be increased while conserving actuator power.

US Patent:

20090146003, Jun 11, 2009

Filed:

Dec 10, 2007

Appl. No.:

11/953567

Inventors:

Charles E. Morris - Des Peres MO, US
Jeffrey M. Roach - St. Charles MO, US

International Classification:

B64C 9/10

US Classification:

244 9914

Abstract:

A flight control system for an aircraft directs a primary surface that is pivotable with respect to the aircraft with a moveable tab located at the end of the primary surface. A primary surface actuator maintains a position of the primary surface. A tab actuator moves the tab with respect to the primary flight control surface. A controller configured to coordinate the movement of the primary flight control surface with the movement of the tab by deflecting the tab with respect to the primary flight control surface, thereby allowing aerodynamic forces acting upon the deflected tab to position the primary flight control surface at a desired position. The primary flight control surface can then be maintained at the desired position by the primary surface actuator.