Fault-tolerant inertial navigation system

• US 5,184,304 A
• Filed: 04/26/1991
• Issued: 02/02/1993
• Est. Priority Date: 04/26/1991
• Status: Expired due to Term

• Current Assignee: Northrop Grumman Systems Corporation (Northrop Grumman Corporation)
• Original Assignee: Litton Systems Incorporated
• Inventors: Huddle, James R.
• Primary Examiner(s): Lall, Parshotam S.
• Assistant Examiner(s): ZANELLI, MICHAEL J
• Application Number:
  US07/692,348
• Time in Patent Office: 648 Days
• Field of Search: 364/453, 364/560, 364/131, 364/184, 33/318, 33/321, 318/564
• US Class Current: 701/220
• CPC Class Codes: G01C 21/188 for accumulated errors, e.g. by coupling inertial systems with absolute positioning systems
• CPC Class Codes: G01C 25/005 initial alignment, calibration or starting-up of inertial devices

Abstract

Disclosed herein is a Fault-Tolerant Inertial Navigation System comprising, in a preferred embodiment, a Redundant Set of at least two Inertial Navigation Systems, from which one may identify and isolate at least one instrument within an Inertial Navigation Unit which shows substantial performance degradation. The two inertial navigation units are fully capable of performing navigational functions. Each of these inertial navigation units has a plurality of navigational instruments, including at least three linear sensors (such as accelerometers) and three angular change sensors (such as gyroscopes or ring laser gyroscopes). No two linear sensors nor any two angular change sensors of either unit are aligned colinearly. Each of the inertial navigation units produces a set of independent navigational solutions at each of their respective outputs. The independent navigational solutions of each of the navigation units are compared and any significantly degraded performance of any one linear sensor or any one angular change sensor is detected.

Claims

1. A fault-tolerant inertial navigation system, comprising:

only two independent inertial navigation units, each of said inertial navigation units performing navigational functions, and each of said inertial navigation units comprising a plurality of single degree of freedom navigational instruments, none of which produce redundant measurements, including at least three linear force sensors and three angular change sensors, any two of said linear sensors and any two of said angular change sensors of either unit aligned other than co-linear; and

, all three of said linear sensors, and all three of said angular change sensors positioned in different planes;

each of said inertial navigation units producing a set of independently derived navigational solutions at each of their respective outputs, said independently derived navigational solutions providing estimates of error parameters indicative of the performance of each sensor in each of said navigation units;

means for comparing said independent navigational solutions of each of said navigation units and detecting any significantly degraded performance of either of said navigation units, by contrasting said estimates of error parameters of each instrument in one navigation unit with the estimates of error parameters in the other navigation unit;

whereby, one of said navigation units indicating such degraded performance, is isolated and identified as to being faulty.

2. The fault-tolerant inertial navigation system of claim 1, wherein:

said means for comparing said independent navigational solutions includes an optimal estimation Kalman filter, operating according to a Kalman algorithm which processes differences in the compared navigational solutions, and said algorithm includes in its error state vector the errors in navigation variables, such as position, velocity, and orientation; and

said Kalman algorithm further includes error states for the inertial instrument errors.

3. The fault-tolerant inertial navigation system of claim 2, wherein:

said Kalman filter algorithm of said comparing means includes performance factors such as individual angular change sensors and linear force sensor biases, scale factor errors, mounting misalignments of said angular change and linear force sensors within each of said navigation units, with respect to one other, and mechanical misalignments between the two navigation units.

4. The fault-tolerant inertial navigation system of claim 2, wherein:

said means for comparing said independent navigational solutions further includes;

means for computing a set of error state estimate values, said error state estimate values being computed navigation variables, such as position, velocity, and orientation, said error state estimate values forming sub-vectors, e_s1 and e_s2 of the error estimate vectors e₁ and e₂ ;

means for combining said set of said independent navigational solutions, which solutions are provided at each of the respective outputs of said inertial navigation units, with said computed error state estimate values;

means for determining changes in said error estimate state values as a function of the error in the estimated values of the independent navigational solutions from both of said inertial navigation units;

means for updating said error estimate state values with said changes in said error state estimate values;

whereby, estimated navigational solutions approach the true navigational solutions for each navigational unit so that fault detection of navigational instruments is achieved.

5. The fault-tolerant inertial navigation system of claim 2, wherein:

said means for comparing said independent navigational solutions further includes;

means for computing a plurality of sets of error state estimates, each set comprising estimates associated with error state variables such as errors in position, velocity, and orientation, for each of said navigational units;

means for determining changes in said error state estimate values, wherein a function of the error state vector estimates for each of said inertial navigation units is obtained independent of any effect of one of said navigation units on the other;

means for updating said error state estimate values with said changes in said error state estimate values;

whereby, estimated navigational solutions approach the true navigational solutions for each navigational unit so that fault detection of navigational instruments may be achieved.

6. The fault-tolerant inertial navigation system of claim 1, wherein:

said means for comparing said independent navigational solutions includes a least square estimation algorithm which processes differences in said compared navigational solutions, and said algorithm includes in its error states the errors in navigation variables, such as position, velocity, and orientation; and

said algorithm further includes error states for the inertial instrument errors.

7. The fault-tolerant inertial navigation system of claim 1, wherein:

said means for comparing said independent navigational solutions of each of said navigation units and detecting any significant degraded performance detects significantly degraded performance of any one sensor of a first type of instrument and significantly degraded performance of any one sensor of a second type of instrument;

means for identifying the type of a first of such sensors exhibiting such significantly degraded performance and, said identifying means further identifying the type of a second of such sensors exhibiting such significantly degraded performance, provided such second sensor is a different type than said first sensor;

whereby, a first of such sensors indicating such degraded performance is isolated and identified as to being faulty, and a second of such sensors, of a different type than the first of such sensors so identified, is also identified.

8. A fault-tolerant inertial navigation system, comprising:

only two independent inertial navigation units, each of said inertial navigation units measuring at least one of a plurality of navigational variables, such variables including position, velocity, and orientation, and each of said inertial navigation units comprising a plurality of single degree of freedom navigational instruments including at least three linear force sensors and three angular change sensors, any two of said linear sensors and any two of said angular change sensors of either unit aligned other than co-linear; and

, all three of said linear sensors, and all three of said angular change sensors positioned in different planes;

each of said inertial navigation units producing a set of independently derived navigational solutions at each of their respective outputs, said independently derived navigational solutions providing estimates of error parameters indicative of the performance of each sensor in each of said navigation units;

means for comparing said independent navigational solutions of each of said navigation units and detecting any significantly degraded performance of either of said navigation units, by contrasting said estimates of error parameters of each instrument in one navigation unit with the estimates of error parameters in the other navigation unit;

whereby, one of said navigation units, indicating such degraded measurement performance, is isolated and identified as to being faulty.