Richard Eugene Annati

US Patent:

6622489, Sep 23, 2003

Filed:

Oct 25, 2000

Appl. No.:

09/696649

Inventors:

Lorenzo Najera - Rio Rancho NM
Brian Finstad - Albuquerque NM
Richard Annati - Albuquerque NM

Assignee:

Hybrid Power Generation Systems, LLC - Los Angeles CA

International Classification:

F02C 322

US Classification:

60773, 60 39281, 417295

Abstract:

A method of controlling a gas booster comprises computing in an engine control unit a reference discharge pressure for the gas booster. In the engine control unit, an actual discharge pressure of the gas booster and the reference discharge pressure are compared. The engine control unit generates a correcting signal derived from the step of comparing. The engine control unit sends the correcting signal to an inlet valve in flow communication with the gas booster. The inlet valve is adjusted in response to the correcting signal. It is emphasized that this abstract is provided to comply with the rules requiring an abstract that will allow a searcher or other reader to ascertain quickly the subject matter of the technical disclosure. The abstract is submitted with the understanding that it will not be used to interpret or limit the scope or meaning of the claims.

US Patent:

7469725, Dec 30, 2008

Filed:

Feb 22, 2006

Appl. No.:

11/359733

Inventors:

Richard E. Annati - Albuquerque NM, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

B65B 3/04
B65B 39/02
B67C 3/02
B67C 11/02
F16K 31/18
B64D 37/16

US Classification:

141 1, 141 95, 141205, 141337, 141344, 137426, 137448, 244135 A

Abstract:

A system for accurately measuring and delivering a predetermined amount of fuel to a vehicle for a specified mission. This system rapidly refuels vehicles to a specific wet vehicle weight. The fuel loading value is determined based upon an algorithm, which accounts for interactions of mission duration, and/or mission payload weight, and/or mission environmental effects. The fuel loading is accomplished by using one or more measuring tubes with a floating valve, which precludes the continued flow of fuel into the tank when the predetermined amount of fuel is delivered. The measuring tubes can be of specific lengths each corresponding to an output of the algorithm or a single telescoping tube that enables varying the length of the tube. Each unique tube length corresponding to a unique output of the algorithm. An alternative system comprises different sized fuel bladders.

US Patent:

7999698, Aug 16, 2011

Filed:

Jun 4, 2008

Appl. No.:

12/133040

Inventors:

Richard E. Annati - Albuquerque NM, US
David E. Ekhaguere - Albuquerque NM, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

G08B 21/00

US Classification:

340945, 340981, 340982, 701 9, 362470, 244 24

Abstract:

Systems and methods for anti-collision lights on a UAV. A method for passive anti-collision lights on a Micro-Aerial Vehicle (“MAV”) including determining a location of the MAV using a flight management computer configured to fly the MAV on a programmed path using data from a global positioning system and an inertial navigation system. The flight management system transmits light activation data and selectively activates at least one navigation light located on a visible surface of the MAV using the light activation data from the flight management computer.

US Patent:

8128019, Mar 6, 2012

Filed:

Dec 12, 2008

Appl. No.:

12/334098

Inventors:

Richard E. Annati - Albuquerque NM, US
Patrick L. O'Brien - Albuquerque NM, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

B64C 29/00

US Classification:

244 23A, 244 123

Abstract:

A propulsion system for a vertical take-off and landing ducted fan aerial vehicle is provided, the propulsion system comprising an internal combustion engine, an electric motor that comprises a motor generator, a motor drive and a battery. The motor drive and battery are integrated into the aerial vehicle and provide power to the ducted fan aerial vehicle. The electric motor may comprise a ring motor generator. In operation, this dual propulsion system serves as a weight-efficient option to allow for two sources of power on a ducted fan unmanned aerial vehicle.

US Patent:

20100286860, Nov 11, 2010

Filed:

Nov 11, 2008

Appl. No.:

12/268696

Inventors:

Eric Rowe - Albuquerque NM, US
James Nickerson - Albuquerque NM, US
David E. Ekhaguere - Albuquerque NM, US
Richard E. Annati - Albuquerque NM, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

G06F 7/00

US Classification:

701 29

Abstract:

Propulsion prognostics apparatus and systems for an unmanned aerial vehicle (UAV) are provided. One propulsion prognostics apparatus comprises a prognostics module configured to generate prognostics data and a power output sensor configured to be coupled to the engine system and configured to generate power output data representing an actual power output of the engine system. The propulsion prognostics apparatus further comprises a processor coupled to the prognostics module and the power output sensor. The processor is configured to receive the prognostics data and the power output data, compare the prognostics data and the power output data, and determine the airworthiness of the UAV based on the comparison. A propulsion prognostics system includes a UAV having an engine system and the above propulsion prognostics apparatus coupled to the UAV.

US Patent:

55670512, Oct 22, 1996

Filed:

Aug 8, 1994

Appl. No.:

8/287396

Inventors:

Richard E. Annati - Phoenix AZ
Allan J. Rodrigue - Chandler AZ
James T. Sublett - Mesa AZ
Craig W. Irwin - Tempe AZ

Assignee:

AlliedSignal Inc. - Morris Township NJ

International Classification:

G01N 360
G01N 2500

US Classification:

374 57

Abstract:

Non-destructive evaluation of a ceramic nozzle is accomplished by generating a thermal gradient across the nozzle while it is mounted in a test rig. The thermal gradient is then measured and compared to a preselected gradient that is representative of the harshest condition to which the nozzle will be exposed during its operating life. The thermal gradient is adjusted until it approximates the preselected gradient. The nozzle is then observed for any cracks which reveal a weakness in the ceramic.