Automatic correction of key error sources in an inertial navigator

• US 6,032,099 A
• Filed: 11/02/1996
• Issued: 02/29/2000
• Est. Priority Date: 11/02/1996
• Status: Expired due to Fees

• Current Assignee: Manuel Fernandez
• Original Assignee: Manuel Fernandez
• Inventors: Fernandez, Manuel
• Primary Examiner(s): Chin, Gary
• Application Number:
  US08/747,008
• Time in Patent Office: 1,214 Days
• Field of Search: 701/200, 701/207, 701/220, 701/221, 73/178 R, 73/180
• US Class Current: 701/220
• CPC Class Codes: G01C 21/188 for accumulated errors, e.g. by coupling inertial systems with absolute positioning systems

Abstract

Processes and algorithms to determine and correct key error sources in an inertial navigator. These key error sources are azimuth misalignment error and all gyro drift rate errors ("North", "East" and "Down"). Thus the invention provides improved directional accuracy and improved navigation performance. The processes and algorithms can be implemented within the system computer to determine and correct for the system error sources thus determined automatically.

Claims

1. An inertial navigator, comprising:

a plurality of gyros, said gyros providing a north gyro input signal, an east gyro input signal, and a down gyro input signal;

a plurality of accelerometers;

means for converting measurements from said accelerometers to a system east velocity and a system north velocity; and

a control system comprising a first control loop and a second control loop;

wherein said first control loop comprises a first rate damping control block responsive to said system east velocity and an external east velocity measurement, said first control loop generating an observable signal proportional to a north gyro drift rate when said accelerometers and said gyros are at rest and the first control loop is in a steady state;

wherein said second control loop comprises a second rate damping control block responsive to said system north velocity and an external north velocity measurement, said second control loop generating an adjusted system north velocity using an output of said second rate damping control block; and

wherein said second control loop is connected to an integral control block responsive to a difference between said adjusted system north velocity and said external north velocity measurement, said integral control block outputting an observable signal proportional to a down gyro drift rate when the second control loop is in a steady state.

2. The inertial navigator of claim 1, further comprising a computer system programmed to correct the control system for said north gyro drift rate and said down gyro drift rate after a period of time of sufficient duration to place the first control loop and second control loop in a steady state.

3. An inertial navigator, comprising:

a plurality of gyros, said gyros providing a north gyro input signal, an east gyro input signal, and a down gyro input signal;

a plurality of accelerometers from which velocity measurements can be derived; and

a control system comprising a plurality of control loops, said control loops including an east velocity control loop and a north velocity control loop receiving as inputs said velocity measurements from said accelerometers, said control system generating an observable signal proportional to a north gyro drift rate when said accelerometers and said gyros are at rest and said east velocity control loop is in a steady state, and generating an observable signal proportional to a down gyro drift rate when said accelerometers and said gyros are at rest and said north velocity control loop is in a steady state.

4. The inertial navigator of claim 3, wherein said control system further comprises means for correcting the inertial navigator for said north gyro drift rate and said down gyro drift rate after a period of time of sufficient duration to place the east velocity control loop and north velocity control loop in a steady state.

5. The inertial navigator of claim 3, wherein said east velocity control loop comprises a rate damping control block responsive to a system east velocity and an external east velocity measurement, said east velocity control loop generating said observable signal proportional to said north gyro drift rate when said accelerometers and said gyros are at rest and said east velocity control loop is in a steady state.

6. The inertial navigator of claim 5, wherein said north velocity control loop comprises a second rate damping control block responsive to a system north velocity and an external north velocity measurement, said north velocity control loop generating an adjusted system north velocity using an output of said second rate damping control block;

and

wherein said control system further comprises an integral control block responsive to a difference between said adjusted system north velocity and said external north velocity measurement, said integral control block outputting said observable signal proportional to said down gyro drift rate when said north velocity control loop is in a steady state.

7. The inertial navigator of claim 3, wherein said control system further comprises means for determining initial azimuth misalignment error and east gyro drift rate after a period of flight using cross-axis position or velocity errors, and correcting the inertial navigator for said initial azimuth misalignment error and said east gyro drift rate.

8. The inertial navigator of claim 7, wherein said control system corrects the inertial navigator for said initial azimuth misalignment error and said east gyro drift rate by subtracting from an input to the north gyro a quantity corresponding to (V_N /R_E0)ψ

₀, where V_N represents a true north velocity as obtained from an external navigation aid, R_E0 represents the distance from the center of the Earth to the inertial navigator, and ψ

₀ represents the initial azimuth misalignment error.

9. The inertial navigator of claim 3, wherein said control system operates generate said observable signal proportional to said north gyro drift rate and said observable signal proportional to said down gyro drift rate when the inertial navigator is at rest.

10. The inertial navigator of claim 3, wherein said control system operates to generate said observable signal proportional to said north gyro drift rate and said observable signal proportional to said down gyro drift rate when the inertial navigator is in flight.

11. A method for determining and correcting error sources in an inertial navigator, said method comprising the steps of:

placing the inertial navigator in an aided navigation mode;

deriving a system cast velocity from an east accelerometer;

generating a north gyro input signal from said system east velocity and from an east velocity measurement provided from an external navigation aid, said step of generating a north gyro input signal comprising the step of applying said system east velocity and said east velocity measurement to a first rate damping block;

deriving a system north velocity from a north accelerometer;

generating an east gyro input signal from said system north velocity and from a north velocity measurement provided from said external navigation aid, said step of generating an east gyro input signal comprising the step of applying said system north velocity and said north velocity measurement to a second rate damping block;

generating a down gyro input signal, said step of generating a down gyro input signal comprising the step of applying an output of said second rate damping control block and said north velocity measurement to an integral control block;

waiting a period of time of sufficient duration after placing the inertial navigator in the aided navigation mode to allow an output of said first rate damping block and the output of said second rate damping block to settle into a steady state;

reading said north gyro input signal when in said steady state, and deriving a north gyro drift rate therefrom;

reading said down gyro input signal when in said steady state, and deriving a down gyro drift rate therefrom; and

correcting said inertial navigator for said north gyro drift rate and said down gyro drift rate.

12. The method of claim 11, wherein said step of reading said north gyro input signal when in said steady state and deriving said north gyro drift rate therefrom comprises the step of reading said north gyro input signal before said inertial navigator has moved from its initial position, and wherein said step of correcting said inertial navigator for said north gyro drift rate and said down gyro drift rate comprises the step of adjusting a north gyro reading by a quantity equal to said north gyro input signal.

13. The method of claim 11, wherein said step of reading said north gyro input signal when in said steady state and deriving said north gyro drift rate therefrom comprises the step of reading said north gyro input signal while said inertial navigator is in flight and subtracting from said north gyro input signal components of east and north velocity, and wherein said step of correcting said inertial navigator for said north gyro drift rate and said down gyro drift rate comprises the steps of adjusting a north gyro reading by a quantity equal to said north gyro input signal with said east and north velocity components subtracted out.

14. The method of claim 11, wherein said step of reading said down gyro input signal when in said steady state and deriving said down gyro drift rate therefrom comprises the step of reading said down gyro input signal, and wherein said step of correcting said inertial navigator for said north gyro drift rate and said down gyro drift rate comprises the step of adjusting a down gyro reading by a quantity equal to said down gyro input signal.

15. The method of claim 11, wherein said first rate damping block and said second rate damping block each have a frequency characteristic given by K.τ

.s/(τ

.s+1), where K represents a gain constant, and τ

represents a time constant.

16. The method of claim 11, further comprising the steps of:

calculating an initial azimuth misalignment error from a cross-axis position or velocity error;

calculating an east gyro drift rate based upon said initial azimuth misalignment error; and

correcting the inertial navigator for said initial azimuth misalignment error and said east gyro drift rate.

17. The method of claim 16, wherein said step of correcting the inertial navigator for said initial azimuth misalignment error and said east gyro drift rate comprises the step of adjusting said north gyro input signal by a quantity corresponding to (V_N /R_E0)ψ

₀, where V_N represents a true north velocity as obtained from said external navigation aid, R_E0 represents a distance from the center of the Earth to the inertial navigator, and ψ

₀ represents the initial azimuth misalignment error.

18. A method for determining and correcting error sources in an inertial navigator, said method comprising the steps of:

placing the inertial navigator in an aided navigation mode;

deriving a system east velocity reading and a system north velocity reading from a plurality of accelerometers;

calculating a north gyro drift rate using an east accelerometer Schuler loop with rate damping, with the east accelerometer Schuler loop in a stead state condition;

calculating a down gyro drift rate using a north accelerometer Schuler loop with rate damping and an azimuth loop with integral control, with the north accelerometer Schuler loop and the azimuth loop in a steady state condition; and

correcting the inertial navigator for said north gyro drift rate and said down gyro drift rate.