Inexpensive monitoring technique for achieving high level integrity monitoring for differential GPS

• US 5,969,670 A
• Filed: 01/22/1998
• Issued: 10/19/1999
• Est. Priority Date: 01/22/1998
• Status: Expired due to Term

• Current Assignee: Trimble Navigation Limited (Trimble Inc.)
• Original Assignee: Trimble Navigation Limited (Trimble Inc.)
• Inventors: Eschenbach, Ralph F., Kalafus, Rudolph M.
• Primary Examiner(s): Issing, Gregory C.
• Assistant Examiner(s): DRUMMOND, DEVIN E
• Application Number:
  US09/010,812
• Time in Patent Office: 635 Days
• Field of Search: 342/357, 244/183
• US Class Current: 342/357.31
• CPC Class Codes: G01S 19/20 Integrity monitoring, fault detection or fault isolation of space segment
• CPC Class Codes: G01S 19/41 Differential correction, e.g. DGPS [differential GPS]

Abstract

A dual global positioning system (GPS) receiver navigation system. The system of the present invention includes a primary GPS receiver adapted to determine a first position. The primary GPS receiver is certified to a first integrity level and is further adapted to provide GPS navigation data to an external device. The system of the present invention also includes a secondary GPS receiver coupled to the primary GPS receiver. The secondary GPS receiver is certified to a second integrity level having less stringent requirements than the first integrity level. The secondary GPS receiver is adapted to determine a second position and monitor the primary GPS receiver to detect a fault condition by comparing the first position and the second position, such that the GPS navigation data is provided in accordance with the first certification level regardless of the second integrity level of the secondary GPS receiver.

Claims

1. An integrity monitor global positioning system (GPS) navigation system, comprising:

a primary GPS receiver adapted to determine a first position, said primary GPS receiver certified to a first certification level, said primary GPS receiver further adapted to provide GPS navigation data; and

a secondary GPS receiver coupled to said primary GPS receiver, said secondary GPS receiver certified to a second certification level having less stringent requirements than said first certification level, said secondary GPS receiver adapted to determine a second position and monitor said primary GPS receiver to detect a fault condition by comparing said first position and said second position, such that said secondary GPS, receiver ensures the integrity of said primary GPS receiver and ensures said GPS navigation data is provided in accordance with said first certification level.

2. The system of claim 1, wherein said first certification level corresponds to RTCA DO178 Level B.

3. The system of claim 1, wherein said second certification level corresponds to RTCA DO178 Level C.

4. The system of claim 1, wherein said primary GPS receiver provides said navigation data directly to a plurality of primary flight instruments of an aircraft.

5. The system of claim 4, wherein said primary GPS receiver is further adapted to determine a first deviation of said aircraft from an intended flight path and said secondary GPS receiver is further adapted to determine a second deviation of said aircraft from said intended flight path, and wherein said first deviation and said second deviation are compared to detect a fault.

6. The system of claim 4, wherein said primary GPS receiver is adapted to provide said navigation data in a digital format to said plurality of primary flight instruments, and wherein said primary GPS receiver comprises at least one digital to analog converter certified in accordance with said first certification level, said at least one digital to analog converter coupled to provide said navigation data in an analog format to said plurality of primary flight instruments.

7. The system of claim 6, wherein said secondary GPS receiver is adapted to test said navigation data in said digital format to detect a fault in a communications port of said primary GPS receiver.

8. The system of claim 6, wherein said secondary GPS receiver includes at least one analog to digital converter adapted to receive said navigation data in said analog format and detect a fault in said at least one digital to analog converter.

9. An integrity monitor differential global positioning system (GPS) navigation system, comprising:

a radio receiver adapted to receive a GPS differential correction message from a broadcast;

a GPS sensor coupled to receive said differential correction message from said radio receiver, said GPS sensor adapted to determine a first position using said differential correction message, said GPS sensor further adapted to provide navigation data directly to a plurality of primary flight instruments of an aircraft, said GPS sensor certified to a first certification level; and

a GPS monitor coupled to said GPS sensor, said GPS monitor coupled to receive said differential correction message from said radio receiver, said GPS monitor certified to a second certification level below said first certification level, said GPS monitor adapted to determine a second position using said differential correction message and monitor said GPS sensor to detect a fault condition by comparing said first position and said second position, such that said GPS monitor ensures the integrity of said GPS sensor and ensures said navigation data is provided in accordance with said first certification level.

10. The system of claim 9, wherein said first certification level corresponds to RTCA DO178 Level B.

11. The system of claim 9, wherein said second certification level corresponds to RTCA DO178 Level C.

12. The system of claim 9, wherein said GPS sensor is further adapted to determine a first deviation of said aircraft from an intended flight path and said GPS monitor is further adapted to determine a second deviation of said aircraft from said. intended flight path, said system further adapted to compare said first deviation and said second deviation to detect a fault.

13. The system of claim 9, wherein said GPS sensor is further adapted to provide said navigation data in a digital format to said plurality of primary flight instruments, and wherein said GPS sensor comprises at least one digital to analog converter certified in accordance with said first certification level adapted to provide said navigation data in an analog format to said plurality of primary flight instruments.

14. The system of claim 13, wherein said GPS monitor tests said navigation data in said digital format to detect a fault in a communications port of said GPS sensor.

15. The system of claim 13, wherein said GPS monitor includes at least one analog to digital converter adapted to receive said navigation data in said analog format and detect a fault in said at least one digital to analog converter.

16. The system of claim 13, wherein said GPS sensor and said GPS monitor are each adapted to detect a respective internal fault and flag said internal fault to said plurality of primary aircraft instruments.

17. In an integrity monitor differential global positioning system (GPS) navigation system, a method for providing high integrity navigation data for aircraft navigation, the method comprising the steps of:

a) receiving a GPS (global positioning system) signal;

b) receiving a GPS differential correction message from a broadcast by using a radio receiver;

c) determining a first position from said differential correction message and said GPS signal using a GPS sensor certified to a first certification level;

d) providing navigation data directly to a plurality of primary flight instruments of an aircraft by using said GPS sensor;

e) determining a second position from said differential correction message and said GPS signal using a GPS monitor certified to a second certification level having less stringent requirements than said first certification level;

f) ensuring said navigation data complies with the requirements of said first certification level by comparing said first position and said second position to detect a fault condition; and

g) ensuring the integrity of said GPS sensor by comparing said first position and said second position.

18. The method of claim 17, further including the steps of:

h) determining a first deviation of said aircraft from an intended flight path using said GPS sensor;

i) determining a second deviation of said aircraft from said intended flight path using said GPS monitor; and

j) detecting said fault condition by comparing said first deviation and said second deviation.

19. The method of claim 17, further including the steps of:

h) providing said navigation data in a digital format to said plurality of flight instruments by using said GPS sensor; and

i) providing said navigation data in an analog format to said plurality of flight instruments by using at least one digital to analog converter certified to said first certification level included in said GPS sensor.

20. The method of claim 19, further including the step of:

j) testing said navigation data in said digital format to detect a fault condition in a communications port of said GPS sensor using said GPS monitor.

21. The method of claim 20, further including the step of:

k) using at least one analog to digital converter included in said GPS monitor to receive said navigation data in said analog format and detect a fault in said at least one digital to analog converter.

22. The method of claim 19, further including the steps of:

h) determining said first position using said GPS sensor certified to an RTCA DO178 Level B; and

i) determining said second position using said GPS monitor certified to an RTCA DO178 Level C.