Inertial reference system

• US 4,675,820 A
• Filed: 06/14/1984
• Issued: 06/23/1987
• Est. Priority Date: 06/14/1984
• Status: Expired due to Fees

• Current Assignee: Alliedsignal Inc. (Honeywell International Inc.)
• Original Assignee: Sundstrand Data Control, Inc. (Rtx Corporation)
• Inventors: Smith, Jeffrey T., Frazier, David E., Leonardson, Ronald B.
• Primary Examiner(s): Chin, Gary
• Application Number:
  US06/620,519
• Time in Patent Office: 1,104 Days
• Field of Search: 364/443, 364/450, 364/453, 364/454, 364/571, 364/434, 33/318, 33/320, 33/324, 33/326, 73/178 R, 73/510
• 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

An inertial sensor assembly (ISA) includes a cluster of three ring laser gyros, each gyro producing an output signal having a pulse repetition rate representative of the rate of angular deviation of the ISA about one of three coordinate axes X, Y, and Z. The ring laser gyros are synchronously dithered at a relatively constant rate. The ISA also includes a triad of three accelerometers, with each accelerometer producing an output signal representative of the rate of velocity deviation of the ISA along one of the X, Y, and Z coordinate axes. A first processor, P1, accumulates the pulses produced by each ring laser gyro over its dither period. The resultant counts are stored in registers for subsequent sampling by the P1 processor at a periodic sampling rate which is greater than the dither rate. The P1 processor then synchronizes each sampled pulse count to a common sampling interval, thereby eliminating errors otherwise caused by using positional data values taken at different times. The P1 processor also compensates the ring laser gyro and accelerometer-produced signals at the sensor and the system level for effects such as temperature, bias offsets, scale factor and misalignment by the use of compensating coefficients stored in electrically erasable, programmable read-only memory. The processed data from the P1 processor are passed to a P2 processor which performs navigational computations to thereby produce computed positional information.

Claims

1. An inertial reference system comprising:

an inertial sensor assembly including;

(a) first, second and third ring laser gyros respectfully mounted for sensing angular deviation of said inertial sensor assembly about the X, Y and Z axes of an orthogonal coordinate system, said first ring laser gyro including means for producing first and second signals +Δ

θ

_x and -Δ

θ

_x, having pulse repetition rates that are respectively proportional to the rate of clockwise and counterclockwise rotation of said first ring laser gyro about said X axis, said second ring laser gyro including means for producing third and fourth signals, +Δ

θ

_y and -Δ

θ

_y, having pulse repetition rates that are respectively proportional to the rate of clockwise and counterclockwise angular displacement of said second ring laser gyro about said Y axis, said third ring laser gyro including means for producing fifth and sixth signals, +Δ

θ

_z and -Δ

θ

_z, having pulse repetition rates that are respectively proportional to the rate of clockwise and counterclockwise angular displacement of said third ring laser gyro about said Z axis;

(b) accelerometer means for producing output signals Δ

V_x, Δ

V_y and Δ

V_z representative of the change in velocity of the inertial sensor assembly in said coordinate axes X, Y and Z, respectively;

dither means for cyclically and asynchronously dithering each of said first, second and third ring laser gyros;

a first processor, P1, for predeterminedly accessing and processing said first, second, third, fourth, fifth and sixth signals supplied by said first, second and third ring laser gyros and said Δ

V_x, Δ

V_y and Δ

V_z signals supplied by said accelerometer means, said P1 processor including;

(a) gyro counter means for accumulating over each dither cycle of said cyclically, asynchronous, dithering of said first, second and third ring laser gyros, said first, third and fifth signals +Δ

θ

_x, +Δ

θ

_y and +Δ

θ

_z supplied by said first, second and third ring laser gyros and for accumulating over each said dither cycle of said cyclically, asynchronous dithering of said first, second and third ring laser gyros, said second, fourth and sixth signals -Δ

θ

_x, -Δ

θ

_y and -Δ

θ

_z supplied by said first, second and third ring laser gyros;

(b) gyro storage means for storing said accumulated pulse counts for each of said signals +Δ

θ

_x, +Δ

θ

_y, +Δ

θ

_z, -Δ

θ

_x, -Δ

θ

_y and -Δ

θ

_z ;

(c) logic means for periodically sampling said gyro storage means and predeterminedly processing said stored pulse counts for producing a seventh signal, Δ

θ

_x, representative of the angular rate of said first ring laser gyro, an eighth signal, Δ

θ

_y, representative of the angular rate of said second ring laser gyro, and a ninth signal, Δ

θ

_z, representative of the angular rate of said third ring laser gyro, each said signal Δ

θ

_x, Δ

θ

_y and Δ

θ

_z being synchronized to a common interval, said logic means including means for resynchronizing each stored pulse count to each logic means sampling time;

(d) means for coning correction for said Δ

θ

_x, Δ

θ

_y and Δ

θ

_z signals;

(e) means for sculling correction for said Δ

V_x, Δ

V_y and Δ

V_z signals;

(f) means for temperature compensating said Δ

θ

_x, Δ

θ

_y, Δ

θ

_z, Δ

V_x, Δ

V_y and Δ

V_z signals; and

means for supplying signals that are representative of said temperature, sculling and coning compensated signals; and

,

a second processor, P2, for performing navigational computations with the temperature, sculling and coning compensated signals supplied by said P1 processor.

2. The inertial reference system of claim 1, wherein the period of each dither cycle is larger than the sampling period of said logic means and wherein said P1 processor further comprises:

a clock for producing a periodic signal having a significantly higher frequency than the frequency of said logic means sampling period;

resync timer means for accumulating a count of said clock signal during the interval between the end of each dither cycle for each ring laser gyro and each subsequent logic sampling time; and

wherein said logic means predeterminedly processes said stored pulse counts and said resync timer means stored count for synchronizing each ring laser gyro-produced signal to said logic means sampling interval.

3. The inertial reference system of claim 2, wherein said logic means includes means for identifying a first condition wherein the sampled pulse count was updated from the previous sampling interval and a second condition wherein, due to the dither period being longer than the logic means sampling period, the sampled pulse count remained the same as the previous sampled pulse count and, in response to said first condition, interpolating a value for said resynchronized pulse count between the sampled pulse counts for the preceding two dither cycles and, in response to said second condition, extrapolating a value for said resynchronized pulse count from the sampled pulse counts for the preceding two dither cycles.

4. The inertial reference system of claim 1, wherein said accelerometer means comprises a triad of three accelerometers, each accelerometer being mounted to sense acceleration of said inertial sensor assembly in one of said X, Y, and Z coordinate axes, each accelerometer producing a first output signal +Δ

V_x, +Δ

V_y, +Δ

V_z having a pulse repetition rate proportional to the acceleration of said accelerometer in a reference positive direction and a second output signal -Δ

V_x, -Δ

V_y, -Δ

V_z having a pulse repetition rate proportional to acceleration in a reference negative direction of said accelerometer.

5. The inertial reference system of claim 4, wherein said P1 processor includes:

accelerometer counter means for accumulating the pulse count of each accelerometer-produced first output signal +Δ

V_x, +Δ

V_y and +Δ

V_z and each accelerometer-produced second output signal -Δ

V_x, -Δ

V_y and -Δ

V_z over a predetermined periodic interval;

accelerometer storage means for storing said accumulated pulse counts for each of said output signals +Δ

V_x, +Δ

V_y, +Δ

V_z, -Δ

V_x, -Δ

V_y and -Δ

V_z over each of said predetermined periodic intervals; and

means for periodically sampling said acclerometer storage means and predeterminedly processing said stored pulse counts.

6. The inertial system of claim 1, wherein said means included in said P1 processor means for temperature compensating said Δ

θ

_x, Δ

θ

_y, Δ

θ

_z, Δ

V_x, Δ

V_y and Δ

V_z signals includes means for;

(i) monitoring the temperature of said first, second and third ring laser gyros,

(ii) monitoring the temperature of said accelerometer means,

(iii) storing predetermined coefficients for said first, second and third ring laser gyros and for said accelerometer means, said coefficients providing correction factors for the output signals produced by said first, second and third ring laser gyros and for said accelerometer means as a function of temperature; and

(iv) means for producing temperature compensated Δ

θ

_x, Δ

θ

_y, Δ

θ

_z, Δ

V_x, Δ

V_y, and Δ

V_z signals responsive to said monitored temperatures and said stored coefficients.

7. The inertial reference system of claim 6, wherein said means for storing predetermined coefficients includes electrically erasable, programmable read-only memory (EEPROM) such that said coefficients can be changed by erasing previous coefficients and writing in new coefficients.

8. The inertial reference system of claim 1, wherein said P1 processor further includes means for:

(e) providing bias-related correction for said Δ

θ

_x, Δ

θ

_y, Δ

θ

_z, Δ

V_x, Δ

V_y, and Δ

V_z signals;

(f) providing misalignment-related correction for said Δ

V_x, Δ

V_y, and Δ

V_z signals; and

(g) providing scale factor-related correction for said Δ

θ

_x, Δ

θ

_y, Δ

θ

_z, Δ

V_x, Δ

V_y, and Δ

V_z signals.