Borehole inertial guidance system

• US 4,542,647 A
• Filed: 06/05/1984
• Issued: 09/24/1985
• Est. Priority Date: 02/22/1983
• Status: Expired due to Fees

• Current Assignee: Sundstrand Data Control, Inc.
• Original Assignee: Sundstrand Data Control, Inc.
• Inventors: Molnar, Daniel O.
• Primary Examiner(s): Birmiel, Howard A.
• Application Number:
  US06/617,355
• Time in Patent Office: 476 Days
• Field of Search: 73/151, 33/304, 33/312, 33/313, 175/45
• US Class Current: 73/152.54
• CPC Class Codes: E21B 47/022 of the borehole, e.g. using geomagnetism

Abstract

In order to improve the accuracy of borehole survey systems utilizing probes with inertial components including inclinometers, two ring laser gyro units are included to provide rotation information to the system. When the probe is moving in a borehole, inclinometer iformation is used to produce a synthetic rotation signal to take the piece of a third gyro and the earth'"'"'s rotation is used for a similar purpose in combination with signals from the two ring laser gyros when the probe is stopped. Wire line velocity is used in combination with the inclinometer and gyro information to provide signals representing the probe velocity and position. Coordinate transformations are provided in the probe to transform the inertial signals and wire line velocity signals into earth reference coordinate system. Kalman filtering incorporates noninertial velocity data to reduce the effect of errors inherent in the generation of various input signals to the system.

Claims

1. A borehole survey apparatus comprising:

a borehole probe for insertion in a borehole;

control means for controlling the movement of said probe in the borehole;

means for generating a signal representative of the angular rotation of the earth;

acceleration means secured within said probe for generating three acceleration signals representing the components of acceleration of said probe with respect to three axes;

first angular means secured within said probe for generating two rotation signals representing the angular rotation of said probe with respect to two axes of rotation;

means responsive to said acceleration signals for generating when said probe is moving a first synthetic angular rotation signal representing the angular rotation of said probe about a third axis of rotation different from said two axes of rotation;

means responsive to said signal representative of the angular rotation of the earth for generating when said probe is not moving a second synthetic angular rotation signal representing the angular rotation of said probe about said third axis of rotation;

transform means responsive to said rotation signals and at least one of said first and second synthetic rotation signals, said transform means including means for providing a transformation signal for transforming signals representing probe movement in a probe referenced coordinate system to an earth referenced coordinate system; and

first computation means operatively connected to said transform means and acceleration means for converting said acceleration signals into a first set of velocity signals representing the velocity of said probe.

2. The apparatus of claim 1, further comprising:

means operatively connected to said control means and said probe for generating a signal representative of the movement of said probe; and

second computation means operatively connected to said transform means for converting said movement signal into a second set of velocity signals representing the velocity of said probe and a set of position signals representing the position of the probe in said earth reference coordinate system.

3. The system of claim 2, further comprising means operably connected to said first and second computation means for comparing said first set of velocity signals with said second set of velocity signals and generating an error signal.

4. The system of claim 3, further comprising Kalman filter means operatively connected to said transform means and said means for comparing said first set of velocity signals with said second set of velocity signals for correcting said velocity signals.

5. The apparatus of claim 4, wherein said probe includes memory means for storing Kalman gain coefficients for said Kalman filter means.

6. The apparatus of claim 4, wherein said probe includes means of calculating Kalman gain coefficients for said Kalman filter means.

7. The apparatus of claim 1 wherein said transformation signal is equivalent to a probe body to level coordinate transformation matrix and wherein said means for generating said second synthetic signal includes means for combining said signal representing the angular rotation of the earth with said transformation signal.

8. The apparatus of claim 7 wherein said means for combining said signals representing said rotation of the earth with said transformation signal means is configured and arranged to combine said signals in accordance with the expression ω

_iex^b =C_L11^b Ω

_N +C_L13^b Ω

_D, where ω

_iex^b represents said second synthetic signal, C_L11^b and C_L13^b represent elements in the first row and the first and third column of said probe body to level cooridinate transformation matrix and Ω

_N and Ω

_D represent components of said signal representing the angular rotation of the earth relative to two axes of said earth referenced coordinate system.

9. The apparatus of claim 1 wherein said transform means includes means for combining said signal representing the angular rotation of the earth with a signal representative of said first and second synthetic rotation signals and with said rotation signals to repeatedly update said transform signal.

10. The apparatus of claim 9 further comprising means for summing said first and second synthetic rotation signals to form said signal representative of said first and second signal.

11. The apparatus of claim 10, further comprising:

means operatively connected to said control means and said probe for generating a signal representative of the movement of said probe; and

second computation means operatively connected to said transform means for converting said movement signal into a second set of velocity signals representing the velocity of said probe and a second set of position signals representing the position of the probe in said earth referenced coordinate system.

12. The system of claim 11, further comprising means operably connected to said first and second computation means for comparing said first set of velocity signals with said second set of velocity signals and generating an error signal.

13. The system of claim 12, further comprising Kalman filter means operatively connected to said transform means and said means for comparing said first set of velocity signals with said second set of velocity signals for correcting said velocity signals.

14. The apparatus of claim 13, wherein said probe includes memory means for storing Kalman gain coefficients for said Kalman filter means.

15. The apparatus of claim 13, wherein said probe includes means of calculating Kalman gain coefficients for said Kalman filter means.

16. The apparatus of claim 1 further comprising means for supplying signals representative of the angular velocity of said probe relative to the earth and means for supplying said signals to said transform means, said transform means including means for combining said signals representative of the angular velocity of said probe relative to the earth with a signal representative of said first and second synthetic signals and with said rotation signals to supply said transform signal.

17. The apparatus of claim 16 wherein said transform means includes means for combining said signals representing the angular rotation of the earth with said signal representing said first and second synthetic rotation signals, said rotation signals and said signals representative of the angular velocity of said probe relative to the earth to provide said transform signal.

18. The apparatus of claim 17 wherein said transform means includes signal integrating means and said transform signal is substantially equivalent to the integral of C_b^L {ω

_i^b }-{ρ

+Ω

}C_b^L, where C_b^L is a probe body to earth coordinate transformation matrix, ω

_i^b is a matrix representing the angular rotation of the probe body about said first second and third axis of rotation, ρ

is a matrix representing the angular velocity of the coordinate system consisting of said first second and third axis of rotation relative to said earth referenced coordinate system, and Ω

is a matrix representing the angular rotation of the earth in said earth referenced system.

19. The apparatus of claim 18 further comprising means for summing said first and second synthetic rotation signals to form said signal representive of said first and second signal.

20. The apparatus of claim 19, further comprising:

means operatively connected to said control means and said probe for generating a signal representative of the movement of said probe; and

second computation means operatively connected to said transform means for converting said movement signal into a second set of velocity signals representing the velocity of said probe and a second set of position signals representing the position of the probe in said earth referenced coordinate system.

21. The system of claim 20, further comprising means operably connected to said first and second computation means for comparing said first set of velocity signals with said second set of velocity signals and generating an error signal.

22. The system of claim 21, further comprising Kalman filter means operatively connected to said transform means and said means for comparing said first set of velocity signals with said second set of velocity signals for correcting said velocity signals.

23. The apparatus of claim 22, wherein said probe includes memory means for storing Kalman gain coefficients for said Kalman filter means.

24. The apparatus of claim 22, wherein said probe includes means of calculating Kalman gain coefficients for said Kalman filter means.

25. The apparatus of claim 1 further comprising:

time delay means responsive to first and second ones of said three acceleration signals that are associated with axes corresponding to said two axes represented by said two rotation signals, said time delay means for delaying each applied acceleration signal; and

means for supplying time delayed acceleration signals supplied by said time delay means to said means for generating said first synthetic angular rotation signal;

said means for supplying said first synthetic angular rotation signal including means for supplying a signal representative of Δ

θ

_x^b =(-a_y(2) a_z(1) +a_y(1) a_z(2))/(a_y(2) a_y(2) +a_z(1) a_z(2)), where a_y(1), a_z(1) represent said two acceleration signals and a_y(2) and a_z(2) represent time delayed representations of said two acceleration signals;

said means for generating said first synthetic angular rotation signal further including means for supplying a signal representative of Δ

θ

_x^b /Δ

t as said first synthetic angular rotation signal, where Δ

t denotes the time delay effected by said time delay means.

26. The apparatus of claim 25 wherein said transformation signal is equivalent to a probe body to level coordinate transformation matrix and wherein said means for generating said second synthetic signal includes means for combining said signal representing the angular rotation of the earth with said transformation signal.

27. The apparatus of claim 26 wherein said means for combining said signals representing said rotation of the earth with said transformation signal means is configured and arranged to combine said signals in accordance with the expression ω

_iex^b =C_L11^b Ω

_N +C_L13^b Ω

_D, where ω

_iex^b represents said second synthetic signal, C_L11^b and C_L13^b represent elements in the first row and the first and third column of said probe body to level coordinate transformation matrix and Ω

_N and Ω

_D represent components of said signal representing the angular rotation of the earth relative to two axes of said earth referenced coordinate system.

28. The apparatus of claim 27 further comprising means for supplying signals representative of the angular velocity of said probe relative to the earth and means for supplying said signals to said transform means, said transform means including means for combining said signals representative of the angular velocity of said probe relative to the earth with a signal representative of said first and second synthetic signals and with said rotation signals to supply said signal for transforming probe movement in said probe referenced coordinate system to probe movement in said earth referenced coordinate system.

29. The apparatus of claim 28 wherein said transform means includes means for combining said signals representing the angular rotation of the earth with said signal representing said first and second synthetic rotation signals, said rotation signals and said signals representative of the angular velocity of said probe relative to the earth to provide said transform signal.

30. The apparatus of claim 29 wherein said transform means includes signal integrating means and said transform signal is substantially equivalent to the integral of C_b^L {ω

_i^b }-{ρ

+Ω

}C_b^L, where C_b^L is a probe body to earth coordinate transformation matrix, w_i^b is a matrix representing the angular rotation of the probe body about said first second and third axis of rotation, ρ

is a matrix representing the angular velocity of the coordinate system consisting of said first second and third axis of rotation relative to said earth referenced coordinate system, and Ω

is a matrix representing the angular rotation of the earth in said earth referenced system.