Stephen M Peck

US Patent:

20130050020, Feb 28, 2013

Filed:

Aug 23, 2011

Appl. No.:

13/216130

Inventors:

Stephen R. Peck - West Hills CA, US
Shuwu Wu - Yorba Linda CA, US
Robert M. Fries - Irvine CA, US

Assignee:

RAYTHEON COMPANY - Waltham MA

International Classification:

G01S 19/44

US Classification:

34235727

Abstract:

A method and system to handle single failure GPS faults in high integrity relative positioning systems is provided. The system is configured to receive a number of reference measurements in carrier-phase real time kinetic positioning systems and identify if a single fault exists. The system identifies the type of fault and mitigates the effects of the single fault to provide a positioning system with a high integrity that is suitable for applications involving risk to human lives.

US Patent:

20140070988, Mar 13, 2014

Filed:

Sep 12, 2012

Appl. No.:

13/612499

Inventors:

Stephen R. Peck - West Hills CA, US
Shuwu Wu - Yorba Linda CA, US

International Classification:

G01S 19/41

US Classification:

34235724

Abstract:

Technology for generating a H1 protection level from an N−1 position in a global positioning system (GPS) receiver is disclosed. One approach can include an H1 monitor configured to generate an H1 protection level from an N number of N−1 positions. The N−1 position can be derived by a differential global positioning system (GPS) satellite measurement removed from a plurality of N differential GPS satellites measurements.

US Patent:

20180045833, Feb 15, 2018

Filed:

Aug 10, 2016

Appl. No.:

15/233270

Inventors:

- Waltham MA, US
Stephen R. Peck - West Hills CA, US
Jason M. Burke - Placentia CA, US
Tyler Thomas - Brea CA, US
Joseph Chang - Orange CA, US

Assignee:

Raytheon Company - Waltham MA

International Classification:

G01S 19/40
G01S 19/54

Abstract:

The concepts, systems and methods described herein are directed towards real time carrier phase monitoring and platform attitude solutions on a moving platform. In an embodiment, highly accurate platform attitude and monitored carrier phases can be determined in a single step and use data screening, error bounds inflation and statistical tests to ensure both inputs and outputs of an attitude solution are self-consistent. The method includes determining a carrier phase error level for each of the satellite-receiver tracks, identifying the satellite-receiver tracks having the carrier phase error level greater than or equal to a carrier phase error threshold, generating an attitude correction using the received data from the one or more satellite-receiver tracks having the carrier phase error level less than the carrier phase error threshold and determining a convergence state of the attitude correction. The carrier phase monitoring may be activated or dis-activated based on the convergence level.