Jason L Speyer

6580389, Jun 17, 2003

Aug 10, 2001

09/928099

Jason L. Speyer - Los Angeles CA
Laurence H. Mutuel - Los Angeles CA

The Regents of the University of California - Oakland CA

G01S 514

34235711

An apparatus and method for vehicle orientation determination is disclosed. A typical method comprises the steps of receiving position and velocity information data from a global positioning system receiver unit, receiving vehicle dynamics information data from one or more vehicle dynamics sensors and determining a vehicle attitude from the position and velocity information and the vehicle dynamics information data using a Kalman filter.

7487933, Feb 10, 2009

Jul 5, 2006

11/428785

Robert H. Chen - Los Angeles CA, US
Ashitosh Swarup - Los Angeles CA, US
Jason Lee Speyer - Los Angeles CA, US

F42B 15/01
G06F 19/00
F41G 7/00
F42B 15/00

244 315, 244 31, 89 111

A system, processing structure and method for performing vehicle intercept includes target acceleration estimation or blocking via a filter prior to deriving an interceptor acceleration time history via a guidance law. In the processing structure where the unknown target accelerations are blocked from affecting estimates, a guidance law is generated, stored and retrieved accounting for worst case target acceleration. In the processing structure where the target acceleration is presumed constant with a constant bank angle, the guidance law is closed form, exploiting constant heading angular velocity, and thus generated online.

7769543, Aug 3, 2010

Apr 30, 2007

11/742425

Stephen M. Stecko - Fullerton CA, US
Walton Williamson - Burbank CA, US
John F. Takacs - Long Beach CA, US
Jason L. Speyer - Los Angeles CA, US

The Boeing Company - Chicago IL

B64D 39/00
G01C 21/16
G06F 19/00

701214, 701 4, 244135 A

A system for automated control of a refueling boom coupled to a tanker aircraft is provided. The system includes sensors such as electro-optical sensor or GPS sensors that provide measurements used by the system to automatically control the refueling boom so as to mate with a receiver aircraft. The system is configured to monitor the health of the sensors and to reconfigure itself if any of the sensor are faulty.

7894950, Feb 22, 2011

Jul 8, 2010

12/832849

Walton Ross Williamson - Burbank CA, US
Jason Lee Speyer - Los Angeles CA, US

Sysense, Inc. - El Segundo CA

G05D 1/08

701 34, 701 4, 244135 A

Methods and devices for estimating and controlling the orientation of a drogue relative to air mass motion where method and apparatus embodiments incorporate estimation of angle of attack and sideslip and function to correct the direction of a drogue so as to maintain a desired angle of attack and sideslip. Some of the exemplary estimation techniques apply methods of sensor output fusion.

7937190, May 3, 2011

Jun 9, 2009

12/481457

Stephen M. Stecko - Fullerton CA, US
Walton R. Williamson - Burbank CA, US
John F. Takacs - Long Beach CA, US
Jason L. Speyer - Los Angeles CA, US

The Boeing Company - Chicago IL

B64D 39/00
G05D 1/00
G06F 19/00
H04B 7/00

701 3, 244135 A

A system for automated control of a refueling boom coupled to a tanker aircraft is provided. The system includes: a first inertial measurement unit (IMU) providing inertial measurements for the tanker aircraft; a first GPS receiver providing a GPS location for a GPS antenna attached to the tanker aircraft; and a processor adapted to calculate a first inertial navigation state for the tanker aircraft through integration of the inertial measurements, the processor being further adapted to calculate a first inertial navigation state error relative to the GPS location and to filter the first inertial navigation state error and the first inertial navigation state based upon noise characteristics of the first IMU and the first GPS receiver to provide an updated inertial navigation state for the tanker aircraft, the processor being further adapted to control the refueling boom relative to a receiver aircraft based upon the first and updated inertial navigation states.

8447443, May 21, 2013

Feb 7, 2012

13/367990

John J Ryan - Tehachapi CA, US
Jason L Speyer - Los Angeles CA, US

The United States of America as Represented by the Administrator of the National Aeronautics and Space Administration - Washington DC
The Regents of the University of California - Oakland CA

G05B 19/042
G06F 17/00

701 3, 701480, 701510, 340992

A computerized system and method for peak-seeking-control that uses a unique Kalman filter design to optimize a control loop, in real time, to either maximize or minimize a performance function of a physical object (“plant”). The system and method achieves more accurate and efficient peak-seeking-control by using a time-varying Kalman filter to estimate both the performance function gradient (slope) and Hessian (curvature) based on direct position measurements of the plant, and does not rely upon modeling the plant response to persistent excitation. The system and method can be naturally applied in various applications in which plant performance functions have multiple independent parameters, and it does not depend upon frequency separation to distinguish between system dimensions.

20050114023, May 26, 2005

Nov 24, 2004

10/997192

Walton Williamson - Sherman Oaks CA, US
Jason Speyer - Los Angeles CA, US
Dale Cooper - Santa Clarita CA, US

G01C021/00

701214000, 701200000, 342358000

A method, apparatus and system are described having a minimum variance estimator of state estimates typically in navigation embodiments where a sensor and/or effecter fault detecting module is adapted to execute residual testing steps using the Multiple Hypothesis Wald Sequential Probability Ratio test, the Multiple Hypothesis Shiryayev Sequential Probability Ratio test, the Chi-Square test and combinations thereof to determine the likelihood of sensor and/or actuator fault occurrences and thereafter isolate the effects of the one or more identified fault from the state estimates.

20060074558, Apr 6, 2006

Nov 9, 2005

11/272222

Walton Williamson - Sherman Oaks CA, US
Jason Speyer - Los Angeles CA, US

G01C 21/28

701213000

A method, apparatus and system are described having a minimum variance estimator of state estimates typically in navigation embodiments where a sensor and/or effecter fault detecting module is adapted to execute residual testing steps using the Multiple Hypothesis Wald Sequential Probability Ratio test, the Multiple Hypothesis Shiryayev Sequential Probability Ratio test, the Chi-Square test and combinations thereof to determine the likelihood of sensor and/or actuator fault occurrences and thereafter isolate the effects of the one or more identified fault from the state estimates.