Apparatus and method for navigation of an aircraft

• US 6,654,685 B2
• Filed: 01/04/2002
• Issued: 11/25/2003
• Est. Priority Date: 01/04/2002
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: McIntyre, Melville Duncan W.
• Primary Examiner(s): Black, Thomas G.
• Assistant Examiner(s): TO, TUAN C
• Application Number:
  US10/037,401
• Publication Number:
  US 20030130791A1
• Time in Patent Office: 690 Days
• Field of Search: 701/213, 701/214, 701/207, 701/220, 701/216, 342/357.14, 342/357.12, 342/358, 342/357.01, 342/357.05, 342/357.06, 342/450, 342/451, 342/352, 340/990, 340/994, 340/995, 340/961, 340/545.5, 340/436, 340/945, 340/947, 244/3.2, 244/79, 79/76, 73/78
• US Class Current: 701/213
• CPC Class Codes: G01C 21/165 combined with non-inertial navigation instruments
• CPC Class Codes: G05D 1/0077 using redundant signals or controls

Abstract

In accordance with this invention, an apparatus and method for aircraft navigation are provided that utilize a blended architecture consisting of a global positioning system (GPS) and micro-electromechanical sensors (MEMS) for the primary navigation system and a laser gyroscope system for the secondary navigation system. The blended architecture of the present invention provides a navigation system that is at least as accurate, redundant and fault-tolerant as conventional navigation systems. In addition, the navigation system components may be distributed throughout the aircraft and may share computing resources with other avionics systems to process signals and provide data to the avionics systems. Overall, the navigation system of the present invention is significantly less expensive and easier to maintain, but equally or more precise and redundant, relative to conventional navigation systems.

Claims

1. An apparatus for navigation of an aircraft, the apparatus comprising:

a primary navigation system having a global positioning system capable of providing signals indicative of a position of the aircraft and a plurality of micro-electromechanical sensors capable of performing inertial referencing of the aircraft, said plurality of micro-electromechanical sensors comprising a micro-electromechanical rate sensor and a micro-electromechanical accelerometer; and

a secondary navigation system having a laser gyroscope system capable of performing inertial referencing of the aircraft and producing navigation signals utilized in the event the primary navigation system malfunctions.

2. The apparatus of claim 1, further comprising a general-purpose computer system for supporting the primary navigation system and a plurality of other avionics systems.

3. The apparatus of claim 2, wherein the general-purpose computer system has redundant processors.

4. The apparatus of claim 1, wherein said plurality of micro-electromechanical sensors comprise a plurality of micro-electromechanical rate sensors and a plurality of micro-electromechanical accelerometers distributed throughout the aircraft.

5. The apparatus of claim 4, wherein the plurality of micro-electromechanical rate sensors and the plurality of micro-electromechanical accelerometers are distributed in a plurality of clusters of three rate sensors and three accelerometers wherein each micro-electromechanical rate sensor provides an output based upon motion of the aircraft in a respective direction, wherein the three rate sensors of a cluster are mounted such that the directions in which the respective rate sensors sense motion of the aircraft are mutually orthogonal, wherein each micro-electromechanical accelerometer provides an output based upon motion of the aircraft in a respective direction, and wherein the three accelerometers of a cluster are mounted such that the directions in which the respective accelerometers sense motion of the aircraft are mutually orthogonal.

6. The apparatus of claim 5, wherein the aircraft has three, mutually orthogonal principle axes, wherein the three rate sensors of a cluster are mounted such that each rate sensor senses motion of the aircraft along a respective axis of the aircraft, and wherein the three accelerometers of a cluster are mounted such that each accelerometer senses motion of the aircraft along a respective axis of the aircraft.

7. The apparatus of claim 1, wherein said global positioning system is capable of determining heading of the aircraft.

8. The apparatus of claim 1, wherein said laser gyroscope system of said secondary navigation system has no more than three ring laser gyroscopes.

9. A method for navigating an aircraft, the method comprising:

providing a primary navigation system having a global positioning system and a plurality of micro-electromechanical sensors;

providing a secondary navigation system having a laser gyroscope system;

providing signals from the global positioning system indicative of a position of the aircraft;

providing signals from the micro-electromechanical sensors indicative of inertial motion of the aircraft;

navigating the aircraft based upon the signals provided by the global positioning system and the micro-electromechanical sensors; and

navigating the aircraft based upon signals from the laser gyroscope system indicative of the inertial motion of the aircraft in the event the primary navigation system malfunctions.

10. The method of claim 9, further comprising processing the signals provided by the primary navigation system with a general-purpose computer system that also supports a plurality of other avionics system.

11. The method of claim 9, wherein providing signals from the micro-electromechanical sensors comprises providing signals from a plurality of micro-electromechanical rate sensors and a plurality of micro-electromechanical accelerometers distributed throughout the aircraft.

12. The method of claim 11, wherein providing signals from the micro-electromechanical sensors further comprises providing signals from a cluster of micro-electromechanical sensors arranged in a mutually orthogonal configuration.

13. The method of claim 12, wherein the aircraft has three, mutually orthogonal principle axes, wherein providing signals from the micro-electromechanical sensors further comprises providing signals from the cluster of micro-electromechanical sensors arranged to sense motion along the principle axes of the aircraft.

14. The method of claim 9, wherein providing signals from the global positioning system comprises providing a signal indicative of a heading of the aircraft.

15. The method of claim 9, wherein navigating the aircraft based upon the signals provided by the global positioning system and the micro-electromechanical sensors comprises blending the signals provided by the global positioning system and the micro-electromechanical sensors to derive inertial data for use in avionics systems.

16. An apparatus for navigation of an aircraft, the apparatus comprising:

a primary navigation system having a global positioning system capable of providing signals indicative of a position of the aircraft and a plurality of micro-electromechanical sensors capable of performing inertial referencing of the aircraft, said plurality of micro-electromechanical sensors comprising a plurality of micro-electromechanical rate sensors and a plurality of micro-electromechanical accelerometers distributed throughout the aircraft in a plurality of clusters of three rate sensors and three accelerometers; and

a secondary navigation system having no more than three ring laser gyroscopes capable of performing inertial referencing of the aircraft and producing navigation signals utilized in the event the primary navigation system malfunctions.

17. The apparatus of claim 16, further comprising a general-purpose computer system for supporting the primary navigation system and a plurality of other avionics systems.

18. The apparatus of claim 17, wherein the general-purpose computer system has redundant processors.

19. The apparatus of claim 16, wherein each micro-electromechanical rate sensor of said plurality of micro-electromechanical sensors provides an output based upon motion of the aircraft in a respective direction, wherein the three rate sensors of a cluster are mounted such that the directions in which the respective rate sensors sense motion of the aircraft are mutually orthogonal, and wherein each micro-electromechanical accelerometer of said plurality of micro-electromechanical sensors provides an output based upon motion of the aircraft in a respective direction, wherein the three accelerometers of a cluster are mounted such that the directions in which the respective accelerometers sense motion of the aircraft are mutually orthogonal.

20. The apparatus of claim 19, wherein the aircraft has three, mutually orthogonal principle axes, wherein the three rate sensors of a cluster are mounted such that each rate sensor senses motion of the aircraft along a respective axis of the aircraft, and wherein the three accelerometers of a cluster are mounted such that each accelerometer senses motion of the aircraft along a respective axis of the aircraft.

21. The apparatus of claim 16, wherein said global positioning system is capable of determining heading of the aircraft.