Inertial navigation system with automatic redundancy and dynamic compensation of gyroscope drift error

• US 5,194,872 A
• Filed: 11/14/1990
• Issued: 03/16/1993
• Est. Priority Date: 11/14/1990
• Status: Expired due to Term

• Current Assignee: Charles Stark Draper Laboratory Incorporated
• Original Assignee: Charles Stark Draper Laboratory Incorporated
• Inventors: Gilmore, Jerold P., Musoff, Howard
• Primary Examiner(s): Tarcza, Thomas H.
• Assistant Examiner(s): CAIN, DAVID C
• Application Number:
  US07/612,788
• Time in Patent Office: 853 Days
• Field of Search: 364/453, 73/1 E, 342/358
• US Class Current: 342/358
• CPC Class Codes: B64G 1/28 using inertia or gyro effect
• CPC Class Codes: B64G 1/369 using gyroscopes as attitude sensors
• CPC Class Codes: G01C 21/188 for accumulated errors, e.g. by coupling inertial systems with absolute positioning systems

Abstract

An inertial navigation system with automatic redundancy and dynamically calculated gyroscopic drift compensation utilizes three, two-degree of freedom gyroscopes arranged whereby any two of the gyroscopes form an orthogonal triad of measurement sensitive axes. The input axes of the three gyroscopes form three pairs of parallel input axes, each pair of parallel input axes corresponding to one axis of the orthogonal triad of axes. The three gyroscopes are operated in a plurality of preselected combinations of both clockwise and counter clockwise directions, thus changing the direction of the angular momentum vector by 180°. Parity equations are formed from each pair of gyroscope outputs whose measurement sensitive axes are parallel. The parity equations include combinations of gyroscope pairs that have been operated in both the clockwise and counterclockwise directions. Gyroscope drift estimates are then computed using the parity equations to provide individual gyroscope lumped drift corrections (self-calibration) to the inertial guidance and navigation system.

Claims

1. An inertial navigation system, with inherent redundancy comprising:

three, two-input axis wheel-reversable rotor gyroscopes, each of said gyroscopes disposed whereby any two of said gyroscopes provide three orthogonal sense axes, each of said gyroscopes including at least two outputs for providing first and second output signals corresponding to sensed angular rates along said two input axes, and wherein said input axes of said three gyroscopes form three pairs of parallel input axes, each pair of parallel input axes corresponding to one of said orthogonal sense axes;

means for selecting at least three gyroscope output signals, each of said selected gyroscope output signals corresponding to one gyroscope output from one associated gyroscope input axis selected from each of said three pairs of parallel input axes; and

inertial navigation means, responsive to at least said three selected gyroscope output signals, for computing the relative position of a vehicle with reference to a predetermined coordinate system.

2. The system of claim 1 wherein said three gyroscopes include three, two-degree of freedom, wheel-reversable, tuned rotor gyroscopes.

3. The system of claim 2 further including means for powering each of said gyroscopes to operate in one of a forward and a reverse direction.

4. The system of claim 3 further including means for selectively controlling said means for powering, for operating each of said three gyroscopes in a plurality of preselected combinations of forward and reverse directions.

5. The system of claim 4 further including means, responsive to said means for selectively controlling and to said outputs of each of said gyroscopes, for computing an estimate of the gyroscopic drift of each of said gyroscopes.

6. The system of claim 5 wherein said means for computing computes and estimate of the gyroscopic drift utilizing output signals from each gyroscope obtained after each of said gyroscopes has been operated in a reverse direction.

7. The system of claim 5 wherein said means for computing includes parity equations formed from pairs of outputs of said gyroscopes corresponding to said three pairs of parallel input axes, each pair of parallel input axes corresponding to one of said three orthogonal sense axes.

8. The system of claim 5 wherein said means for computing further includes means for indicating one of said gyroscopes is inoperative.

9. The system of claim 2 wherein said inertial navigation means computes the position of said navigation means generally simultaneously with one or more of said gyroscopes operating in a reverse direction.

10. An inertial navigation system, with sense axis redundancy and dynamically calculated gyroscopic drift compensation, comprising:

three, two-input axis, wheel-reversable gyroscopes, each of said gyroscopes disposed whereby any two of said gyroscopes provide three orthogonal sense axes, each of said gyroscopes including at least two outputs for providing first and second output signals corresponding to sensed changes in angular rates along said two gyroscope input axes, and wherein said input axes of said three gyroscopes form three pairs of parallel input axes, each pair of parallel input axes corresponding to one of said three orthogonal axes;

means for powering each of said gyroscope wheels to operate in one of a forward and a reverse direction;

means for selectively controlling said means for powering, for operating said three gyroscopes in a plurality of preselected combinations of forward and reverse directions;

means for selecting at least three gyroscope outputs, each of said selected gyroscope output corresponding to one gyro input axis from each of said three pairs of parallel input axes;

means, responsive to said means for selectively controlling and to said outputs of each of said gyroscopes, for computing an estimate of the gyroscopic drift of each of said gyroscopes; and

inertial navigation means, responsive to at least said three selected gyroscope outputs, for computing the relative position of a vehicle with reference to a predetermined coordinate system.

11. A method of dynamically compensating for gyroscopic drift in an inertial navigation system including at least two gyroscopes, each gyroscope including at least one input sensitive axis disposed parallel to a plurality of reference axes of an inertial navigation system, comprising the steps of:

receiving at least first and a second gyroscope output signals from at least first and second gyroscopes including first and second gyroscope inputs disposed parallel to at least one reference axis of the inertial navigation system, each of said at least first and second gyroscope output signals including a sensed angular rate component and a gyroscopic error component;

forming at least one parity equation such that said angular rate component of one of said first and second gyroscope output signals generally cancels said angular rate component of the other of said first and second gyroscope output signals; and

utilizing the gyroscopic error components of said first and second gyroscope output signals to provide said inertial navigation system with an estimate of gyroscopic error about said reference axis.

12. The method of claim 11 wherein the step of forming at least one parity equation includes forming at least one polynomial parity equation.

13. The method of claim 11 wherein said inertial navigation system includes an orthogonal triad of reference axes and wherein said navigational system further includes at least three, two-degree of freedom gyroscopes, and whereby the gyroscope input axes form three pairs of input axes parallel to the triad of orthogonal axes.

14. The method of claim 13 wherein the step of forming at least one parity equation includes forming three parity equations, one parity equation for each pair of gyroscope output axes disposed parallel to each inertial navigation system reference axis from among the orthogonal triad of reference axes.

15. The method of claim 14 further including prior to the step of forming at least one parity equation the step of sequentially performing gyroscope wheel reversals.

16. The method of claim 15 wherein the step of utilizing the gyroscopic error component of the gyroscope output signals to provide an estimate of lumped gyroscopic error provides an estimate of lumped gyroscopic error after each of said gyroscopes have undergone at least one period of wheel reversal.