Christopher J Heiberg from Sunset Beach, CA, age 62

License #:

70108734 - Active

Category:

EMS Licensing

Issued Date:

Sep 20, 2016

Expiration Date:

Jun 30, 2018

Type:

EMT-Basic

Address:

PO Box 1415, Sunset Beach, CA

License #:

30035 - Active

Category:

Professional

Issued Date:

Feb 6, 1996

Expiration Date:

Mar 31, 2020

Mitigating Gimbal Induced Disturbances In Cmg Arrays
view source
US Patent:

6354163, Mar 12, 2002
Filed:

May 17, 2000
Appl. No.:

09/572468
Inventors:

Christopher J. Heiberg - Peoria AZ
Assignee:

Honeywell International Inc. - Morristown NJ
International Classification:

G01C 1940
US Classification:

74 547, 74 54, 74 57
Abstract:

In a CMG array used to change the attitude of a satellite, noise in the motion of the inner gimbal as it is moved is detected and the speed of the CMG rotors is changed to reduce the noise.

Gear Transmission Damping Apparatus And Method
view source
US Patent:

6415674, Jul 9, 2002
Filed:

Apr 28, 2000
Appl. No.:

09/561335
Inventors:

L. Porter Davis - Phoenix AZ
Christopher J. Heiberg - Peoria AZ
Jack H. Jacobs - Glendale AZ
Assignee:

Honeywell International Inc. - Morristown NJ
International Classification:

F16H 5518
US Classification:

74409, 74411
Abstract:

A gear drive having a third order damper operating with the antibacklash gear so as to lower the impact of the antibacklash gear at high torques to reduce gear wear while maintaining good contact with the antibacklash gear at lower torques to maintain high accuracy and bandwidth.

Dynamic Unbalance Compensation System And Method
view source
US Patent:

6772978, Aug 10, 2004
Filed:

Feb 22, 2002
Appl. No.:

10/081639
Inventors:

David A. Osterberg - Glendale AZ
Christopher J. Heiberg - Peoria AZ
Assignee:

Honeywell International Inc. - Morristown NJ
International Classification:

B64G 128
US Classification:

244165, 74 522, 74 534
Abstract:

A dynamic unbalance compensation system that compensates for dynamic unbalance of a rotating assembly on a vehicle, such as a spacecraft, to compensate for the presence of a dynamic unbalance moment. The system includes a vehicle, such as a spacecraft, a rotational assembly mounted on the vehicle and rotatable about an axis of rotation relative to the vehicle, and one or more momentum devices mounted on the rotational assembly and generating a momentum vector component perpendicular to the axis of rotation. The one or more momentum devices generate a compensation torque during spinning of the rotational assembly so as to compensate for dynamic unbalance of the rotational assembly.

Singularity Escape And Avoidance Using A Virtual Array Rotation
view source
US Patent:

7627404, Dec 1, 2009
Filed:

Apr 13, 2007
Appl. No.:

11/735145
Inventors:

Christopher J. Heiberg - Sunset Beach CA, US
Assignee:

The Boeing Company - Chicago IL
International Classification:

B64G 1/28
US Classification:

701 13, 244165
Abstract:

Techniques for providing singularity escape and avoidance are disclosed. In one embodiment, a method for providing control moment gyroscope (CMG) attitude control singularity escape includes calculating a Jacobian A of a set of control equations, calculating a measure of closeness to a singularity, and comparing the calculated closeness to a threshold value, when the calculated closeness is less than or equal to the threshold value, recalculating the Jacobian A. Recalculating may include determining a new direction of virtual misalignment of β and γ, recalculating the Jacobian inputting the new direction of the virtual misalignment, recalculating the measure of closeness to a singularity, and comparing the measure of closeness to the threshold value. Further, the method may include calculating a gimbal rate command if the of closeness is greater than the threshold value and generating a torque from the gimbal rate command to control the attitude of a satellite.

Singularity Escape And Avoidance Using A Virtual Array Rotation
view source
US Patent:

7904214, Mar 8, 2011
Filed:

Oct 5, 2009
Appl. No.:

12/573765
Inventors:

Christopher J. Heiberg - Sunset Beach CA, US
Assignee:

The Boeing Company - Chicago IL
International Classification:

G05D 1/00
US Classification:

701 13, 701 4, 701 33, 244165, 74 52
Abstract:

Techniques for providing singularity escape and avoidance are disclosed. In one embodiment, a method for providing control moment gyroscope (CMG) attitude control singularity escape includes calculating a Jacobian A of a set of control equations, calculating a measure of closeness to a singularity, and comparing the calculated closeness to a threshold value, when the calculated closeness is less than or equal to the threshold value, recalculating the Jacobian A. Recalculating may include determining a new direction of virtual misalignment of β and γ, recalculating the Jacobian inputting the new direction of the virtual misalignment, recalculating the measure of closeness to a singularity, and comparing the measure of closeness to the threshold value. Further, the method may include calculating a gimbal rate command if the of closeness is greater than the threshold value and generating a torque from the gimbal rate command to control the attitude of a satellite.

Singularity Escape And Avoidance Using A Virtual Array Rotation
view source
US Patent:

7974746, Jul 5, 2011
Filed:

Oct 5, 2009
Appl. No.:

12/573743
Inventors:

Christopher J. Heiberg - Sunset Beach CA, US
Assignee:

The Boeing Company - Chicago IL
International Classification:

B64G 1/28
US Classification:

701 13, 244165
Abstract:

Techniques for providing singularity escape and avoidance are disclosed. In one embodiment, a method for providing control moment gyroscope (CMG) attitude control singularity escape includes calculating a Jacobian A of a set of control equations, calculating a measure of closeness to a singularity, and comparing the calculated closeness to a threshold value, when the calculated closeness is less than or equal to the threshold value, recalculating the Jacobian A. Recalculating may include determining a new direction of virtual misalignment of β and γ, recalculating the Jacobian inputting the new direction of the virtual misalignment, recalculating the measure of closeness to a singularity, and comparing the measure of closeness to the threshold value. Further, the method may include calculating a gimbal rate command if the of closeness is greater than the threshold value and generating a torque from the gimbal rate command to control the attitude of a satellite.

Control Moment Gyroscope Desaturation In Aircraft
view source
US Patent:

20130133445, May 30, 2013
Filed:

Nov 29, 2011
Appl. No.:

13/305922
Inventors:

Christopher Jan Heiberg - Sunset Beach CA, US
International Classification:

G01C 19/52
G01C 19/02
US Classification:

74 534, 74 543
Abstract:

A method for adjusting a control moment gyroscope array includes receiving a stream and directing the stream to adjust momentum in the control moment gyroscope.

Variable Periodic Disturbance Rejection Filter
view source
US Patent:

59447613, Aug 31, 1999
Filed:

Jun 6, 1997
Appl. No.:

8/870743
Inventors:

Christopher J. Heiberg - Peoria AZ
Assignee:

Honeywell Inc. - Minneapolis MN
International Classification:

B64G 128
G06F16500
US Classification:

701 13
Abstract:

A filter for use in an attitude control system which may be subjected to vibrations from disturbances which have frequency contents that vary with time. Sensors on the system produce signals that contain the disturbance frequencies and a calculator connected to the source of disturbance produces a signal which varies as a function of the disturbance. The filter receives these signals and augments the control loop gain at the disturbance frequencies thereby enabling the attitude control devices to null the disturbance effects on the attitude of the system.