Robert Joseph Freeman

US Patent:

20100100260, Apr 22, 2010

Filed:

Oct 21, 2008

Appl. No.:

12/255233

Inventors:

Melville Duncan Walter McIntyre - Bellevue WA, US
Andrew William Houck - Woodinville WA, US
Russell Tanner Bridgewater - Monroe WA, US
Robert E. Freeman - Seattle WA, US
Paul Salo - Lynnwood WA, US
Douglas L. Wilson - Mercer Island WA, US
Jonathan K. Moore - Kirkland WA, US

International Classification:

G06F 19/00
G01S 19/14

US Classification:

701 6, 34235709

Abstract:

A method, apparatus, and computer program product for identifying air data for an aircraft. The lift for the aircraft is identified. The number of surface positions for the aircraft is identified. The angle of attack during flight of the aircraft is identified. A synthetic dynamic pressure is computed from the lift, the number of surface positions, and the angle of attack.

US Patent:

20130253859, Sep 26, 2013

Filed:

Mar 23, 2012

Appl. No.:

13/428713

Inventors:

Robert Erik Freeman - Seattle WA, US

International Classification:

G01R 31/00

US Classification:

702 58

Abstract:

A signal selection and fault detection system is provided. The system includes four input equalization circuits each configured to receive an input signal from an associated sensor, wherein the input signal is indicative of a parameter measured by the associated sensor, and output an equalized signal based on the received input signal. The system further includes a five-input output selection circuit coupled to the four input equalization circuits, the five-input output selection circuit configured to receive an equalized signal from each of the four input equalization circuits, receive a previous frame output signal, and select an output signal from the four equalized signals and the previous frame output signal.

US Patent:

57107769, Jan 20, 1998

Filed:

May 15, 1995

Appl. No.:

8/441680

Inventors:

Lloyd R. Tomlinson - Renton WA
Robert E. Freeman - Kent WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

G06F 1100

US Classification:

371 51

Abstract:

A signal selection and fault detection system receives multiple redundant sensor input signals that are processed through an equalizing and selecting network which outputs the midvalue signal. The system provides a variable fault monitoring threshold that provides the ability to detect for oscillatory faults among input signals that are less than 10% of static tracking tolerances for the inputs, while also assuring that nuisance fault detections are very improbable. The system provides a variable equalization rate that assures satisfactory blocking of oscillatory faults under dynamic conditions when signal disagreements are increased by gain tolerances between the input signals, and maintains high signal resolution of the output under such dynamic conditions. The system also provides cross-channel equalization of the selected midvalue signal in all operating channels to assure that all channels provide the same steady state output for only two input operation, while also maximizing fault blocking capability.

US Patent:

39466914, Mar 30, 1976

Filed:

Jun 23, 1975

Appl. No.:

5/589269

Inventors:

Robert M. Freeman - Tacoma WA

Assignee:

Metal Marine Pilot, Inc. - Tacoma WA

International Classification:

B63H 2502

US Classification:

114144E

Abstract:

An improved marine compass employs a Hall-effect device which provides an output signal related to the relative rotation of the compass card therein. When the Hall-effect device is mounted on a course dial whose position with respect to the compass' lubber line indicates a desired course, the output signal may be used as an input to an autopilot system. The system includes a DC constant current supply for the Hall-effect device, and an integrated circuit operational amplifier for amplifying said output signal to provide an angle signal having a usable level. A differentiator including a second IC operational amplifier provides a rate signal from the angle signal. A rudder signal is provided by a rudder position sensor employing a second Hall-effect device and a third IC operational amplifier. The angle and rate signals are combined and supplied with the rudder signal to a variable-threshold differential amplifier which in turn provides a control signal to a steering servomotor to modify the rudder position so as to return the vessel to its desired course. To allow high rates of rudder positioning without overshoot, a null damper circuit varies the threshold of the differential amplifier to pulse modulate the control signal at small values thereof.

US Patent:

42531497, Feb 24, 1981

Filed:

Feb 14, 1979

Appl. No.:

6/012040

Inventors:

Peter M. Cunningham - Tacoma WA
Robert M. Freeman - Tacoma WA

Assignee:

Metal Marine Pilot, Inc. - Tacoma WA

International Classification:

G05B 1142
B63H 2504

US Classification:

364444

Abstract:

A system for controlling the course of a vessel. A digital computer 22 receives information signals from a geographic position locator 20, such as a Loran-C receiver, a depth sounder, or a water temperature sensor, and is also capable of interactive communcations with a remote terminal 24 which is accessible by an operator of the vessel. The digital computer 22 continuously monitors the information signals and develops therefrom a digital output signal representing the sign and magnitude of vessel cross-track error. To obtain information required to determine cross-track error, and to obtain certain other information relating to the identity and type of the geographic position locator 20, the digital computer 22 transmits questions to the remote terminal 24 for display therby and evaluates responses made by the operator through remote terminal 24. The digital computer 22 may be enabled or disabled in response to instructions from the operator using remote terminal 24. The digital computer 22 may also be disabled during the existence of an alarm condition resulting from instability in the information signals, or upon detection of information in the information signals representing loss of tracking by the geographic position locator 20.

US Patent:

20220258877, Aug 18, 2022

Filed:

Jan 18, 2022

Appl. No.:

17/578100

Inventors:

- Chicago IL, US
Leonard John Inderhees - Bothell WA, US
Russell T. Bridgewater - Monroe WA, US
Robert Erik Freeman - Seattle WA, US
William Tyler Piersol - Everett WA, US

International Classification:

B64D 43/02
B64C 13/50
G01P 13/02

Abstract:

Example apparatus, systems, and methods for managing common mode pneumatic events are disclosed herein. An example system includes a common mode pneumatic event detector to detect a common mode pneumatic event at pitot tubes of an aircraft, a latch, a relay switch in communication with the latch, and a latch controller to set the latch in a first state to cause the latch to output a first latch signal, the relay switch to output a first pressure signal in response to the first latch signal, the first pressure signal based on pressure data from the pitot tubes, and set the latch in a second state to cause the latch to output a second latch signal based on the detection of the common mode pneumatic event. The relay switch is to output a second pressure signal in response to the second latch signal. The second pressure signal includes estimated pressure data.

US Patent:

20180364716, Dec 20, 2018

Filed:

Nov 1, 2016

Appl. No.:

15/340318

Inventors:

- Chicago IL, US
Robert Erik Freeman - Seattle WA, US

International Classification:

G05D 1/02
G08G 5/02

Abstract:

A flight control module for computing localizer deviation during landing of an aircraft is provided. The flight control module includes a communication interface and a processor. The communication interface is configured to receive inertial data for the aircraft. The processor is coupled to the communication interface and is configured to compute an inertial localizer deviation based on the inertial data.

US Patent:

20180120850, May 3, 2018

Filed:

Nov 1, 2016

Appl. No.:

15/340349

Inventors:

- Chicago IL, US
Robert Erik Freeman - Seattle WA, US

International Classification:

G05D 1/02
G08G 5/02

Abstract:

A flight control module for computing glideslope deviation during landing of an aircraft is provided. The flight control module includes a communication interface and a processor. The communication interface is configured to receive inertial data for the aircraft. The processor is coupled to the communication interface and configured to compute an inertial glideslope deviation based on the inertial data.