Method and apparatus for maintaining the integrity of spacecraft based time and position using GPS

• US 6,134,484 A
• Filed: 01/28/2000
• Issued: 10/17/2000
• Est. Priority Date: 01/28/2000
• Status: Expired due to Term

• Current Assignee: General Dynamics Mission Systems Inc. (General Dynamics Corporation)
• Original Assignee: Motorola, Inc. (Motorola Solutions, Inc.)
• Inventors: Brenchley, Gaylin David, Geier, George Jeffrey, Hart, Roger Charles
• Primary Examiner(s): Cuchlinski, Jr., William A
• Assistant Examiner(s): Beaulieu, Yonel
• Application Number:
  US09/493,482
• Time in Patent Office: 263 Days
• Field of Search: 701/13, 701/3, 701/200, 701/213, 701/214, 701/215, 342/357.06, 342/357.12, 342/357.15, 73/178 R, 455/8, 455/9, 455/12.1
• US Class Current: 701/13
• CPC Class Codes: G01S 19/20 Integrity monitoring, fault detection or fault isolation of space segment
• CPC Class Codes: H04B 7/18519 Operations control, administration or maintenance

Abstract

A method and apparatus for maintaining the integrity of spacecraft based time and position using GPS (11) is disclosed. A GPS receiver is provided with a Receiver Autonomous Integrity Monitor (RAIM) processor (12) and a Kalman filter (14). GPS signals are received from at least four GPS satellites and processed in the GPS receiver to provide time and position information. Periodically, an extended fault vector is formed in the Kalman filter with propagated open-loop position and velocity measurements. The extended fault vector is used to isolate and remove failing GPS satellites.

Claims

1. A method for maintaining the integrity of spacecraft based time and position using the Global Positioning System (GPS) comprising the steps of:

providing a GPS receiver coupled to a Receiver Autonomous Integrity Monitor (RAIM) processor and a Kalman filter;

receiving GPS signals from GPS satellites and processing the GPS signals in the GPS receiver to provide time and position information;

periodically forming an extended fault vector in the Kalman filter with propagated open-loop position and velocity measurements;

the step of periodically forming the extended fault vector includes inputting a spacecraft acceleration model into the Kalman filter; and

using the extended fault vector to isolate and remove failing GPS satellites.

2. A method for maintaining the integrity of spacecraft based time and position using the Global Positioning System (GPS) as claimed in claim 1 wherein the step of periodically forming the extended fault vector includes forming the extended fault vector at intervals which are long relative to Selective Availability (SA).

3. A method for maintaining the integrity of spacecraft based time and position using the Global Positioning System (GPS) as claimed in claim 1 wherein the step of periodically forming the extended fault vector includes forming the extended fault vector at intervals of approximately 300 seconds.

4. A method for maintaining the integrity of spacecraft based time and position using the Global Positioning System (GPS) comprising the steps of:

providing a GPS receiver coupled to a Receiver Autonomous Integrity Monitor (RAIM) processor and a Kalman filter;

receiving GPS signals from GPS satellites and processing the GPS signals in the GPS receiver to provide time and position information;

computing unit variance in the RAIM processor and using the unit variance to desensitize the Kalman filter to off-nominal conditions;

periodically forming an extended fault vector in the Kalman filter with propagated open-loop position and velocity measurements;

the step of periodically forming the extended fault vector includes inputting a spacecraft acceleration model into the Kalman filter; and

using the extended fault vector to isolate failures of GPS satellites and failing GPS satellites.

5. A method for maintaining the integrity of spacecraft based time and position using the Global Positioning System (GPS) as claimed in claim 4 wherein the step of periodically forming the extended fault vector includes forming the extended fault vector at intervals which are long relative to Selective Availability (SA).

6. A method for maintaining the integrity of spacecraft based time and position using the Global Positioning System (GPS) as claimed in claim 4, wherein the step of periodically forming the extended fault vector includes forming the extended fault vector at intervals of approximately 300 seconds.

7. A method for maintaining the integrity of spacecraft based time and position using the Global Positioning System (GPS) as claimed in claim 4 wherein the step of computing unit variance includes computing pseudo ranges from the received time and position information.

8. A method for maintaining the integrity of spacecraft based time and position using the Global Positioning System (GPS) as claimed in claim 4 wherein the step of receiving GPS signals includes receiving carrier phase data and the step of computing unit variance includes computing delta ranges from differenced carrier phase data.

9. An apparatus for maintaining the integrity of spacecraft based time and position using the Global Positioning System (GPS) comprising:

a GPS receiver;

a Receiver Autonomous Integrity Monitor (RAIM) processor coupled to receive signals from the GPS receiver;

a Kalman filter coupled to receive signals from the RAIM processor;

a spacecraft acceleration model coupled to provide information to the Kalman filter to generate an extended fault vector;

an open loop propagator coupled to receive extended fault vector information from the Kalman filter and supplying open-loop position and velocity measurements to the RAIM processor; and

the RAIM processor, Kalman filter, spacecraft acceleration model, and open loop propagator are all functions performed in a single processor embedded in the GPS receiver.

10. An apparatus for maintaining the integrity of spacecraft based time and position using the Global Positioning System (GPS) as claimed in claim 9 wherein the GPS receiver includes at least four channels for tracking GPS satellites.