Method and apparatus for borehole surveying

• US 6,453,239 B1
• Filed: 06/08/1999
• Issued: 09/17/2002
• Est. Priority Date: 06/08/1999
• Status: Expired due to Term

• Current Assignee: Schlumberger Technology Corporation (Schlumberger NV)
• Original Assignee: Schlumberger Technology Corporation (Schlumberger NV)
• Inventors: Schrader, Kirby G., Hache, Jean-Michel, Shirasaka, Ichiro
• Primary Examiner(s): Cuchlinksi, Jr., William A.
• Assistant Examiner(s): Donnelly, Arthur D.
• Application Number:
  US09/327,873
• Time in Patent Office: 1,197 Days
• Field of Search: 701/220, 702/6, 731/525.4, 731/51, 333/04, 333/24, 333/13, 175/45, 175/26
• US Class Current: 701/220
• CPC Class Codes: E21B 47/022 of the borehole, e.g. using geomagnetism
• CPC Class Codes: G01C 21/188 for accumulated errors, e.g. by coupling inertial systems with absolute positioning systems

Abstract

The invention is, in its various aspects, a method and apparatus useful for strapdown inertial navigation and surveying in a borehole. The method comprises maneuvering a probe including three vibrating mass, Coriolis effect gyroscopes in a borehole and initializing the probe'"'"'s attitude in the borehole within the probe'"'"'s frame of reference. Three orthogonal, incremental rotation angles and three orthogonal, incremental velocities are determined for the probe within the probe'"'"'s frame of reference. The incremental rotation angles are determined from the gyroscopes. The method then translates the three incremental velocities from the probe'"'"'s frame of reference into the inertial frame of reference using the three incremental rotation angles. Next, a velocity vector in a local-vertical, wander-azimuth frame of reference is determined from the translated incremental velocities. A velocity error observation is then obtained. A system error is then estimated from the velocity vector and the velocity error observation. The system error is then fed back into the inertial navigation system for use in refining the method. In as second aspect, the invention is a strapdown, inertial measurement unit. The inertial measurement unit includes a housing, three accelerometers, and three vibrating mass, Coriolis effect gyroscopes. The three accelerometers are mounted within the housing. The three vibrating mass, Coriolis effect are rigidly mounted within the housing.

Claims

1. A strapdown inertial navigation method comprising:

maneuvering a probe including at least three vibrating mass, Coriolis effect gyroscopes in a borehole;

initializing the probe'"'"'s attitude in the borehole within the probe'"'"'s frame of reference;

determining, from the gyroscopes, three orthogonal, incremental rotation angles for the probe within the probe'"'"'s frame of reference;

determining three orthogonal, incremental velocities for the probe within the probe'"'"'s frame of reference;

translating the three incremental velocities from the probe'"'"'s frame of reference into the inertial frame of reference using the three incremental rotation angles;

determining from the translated incremental velocities a velocity vector in a local-vertical, wander-azimuth frame of reference;

obtaining a velocity error observation;

estimating a system error from the velocity vector and a velocity error observation; and

feeding the system error back into the inertial navigation method.

2. The method of claim 1, wherein maneuvering the probe within the borehole includes maneuvering the probe within the borehole during measurement-while-drilling operations.

3. The method of claim 2, wherein the measurement-while-drilling operations include one of multi-shot gyrocompassing, measurement-while-drilling operations and zero-velocity update inertial navigation in measurement-while-drilling operations.

4. The method of claim 1, wherein maneuvering the probe within the borehole includes maneuvering the probe within the borehole during wireline logging operations.

5. The method of claim 4, wherein the wireline logging operations include one of multi-shot, gyrocompassing wireline operations;

continuous, cable-aided inertial navigation in wireline logging operations; and

zero-velocity update inertial navigation in wireline operations.

6. The method of claim 1, wherein initializing the probe'"'"'s attitude within the probe'"'"'s frame of reference includes at least one of a coarse alignment and a fine alignment.

7. The method of claim 6, wherein at least one of the coarse alignment and the fine alignment includes filtering.

8. The method of claim 1, wherein initializing the probe'"'"'s attitude within the probe'"'"'s frame of reference includes at least one of accelerometer error compensation and gyroscopic error compensation.

9. The method of claim 8, wherein at least one of the accelerometer error compensation and gyroscopic error compensation includes compensating for major deterministic errors.

10. The method of claim 9, wherein the major deterministic errors include a major deterministic error selected from the group comprising bias, scale factor error, and misalignment.

11. The method of claim 10, wherein translating the three incremental velocities from the probe'"'"'s frame of reference into the inertial frame of reference includes determining the probe'"'"'s velocity-attitude.

12. The method of claim 10, wherein determining the probe'"'"'s velocity attitude includes updating a body-to-inertial direction cosine matrix and updating a body-to-inertial quaternion.

13. The method of claim 1, wherein at least one of translating the three incremental velocity signals into the inertial frame of reference and determining the position of the probe is aided by a linear estimator.

14. The method of claim 13, wherein the linear estimator includes one of a linear Kalman filter, an extended Kalman filter, a backward Kalman smoother, and a minimum model error estimator.

15. The method of claim 1, wherein at least one of translating the three incremental velocity signals into the inertial frame of reference and determining the position of the probe is aided by a non-linear estimator.

16. The method of claim 15, wherein the non-linear estimator includes one of a linear Kalman filter, an extended Kalman filter, a backward Kalman smoother, and a minimum model error estimator.

17. The method of claim 1, further comprising determining the position of the probe from the translated incremental velocities.

18. The method of claim 17, wherein determining the position of the probe from the translated incremental velocities includes determining the true vertical depth.

19. The method of claim 1, wherein determining from the translated incremental velocities a velocity vector in a local-vertical, wander-azimuth frame of reference includes applying an earth gravity model.

20. The method of claim 19, wherein feeding the system error back into the inertial navigation method includes feeding the system error into the earth gravity model.

21. The method of claim 1, wherein obtaining the velocity error observation includes obtaining a zero-velocity update.

22. The method of claim 1, wherein obtaining the velocity error observation includes:

obtaining a cable velocity; and

translating the cable velocity into the local-vertical frame of reference.

23. The method of claim 1, wherein estimating a system error from the velocity vector and the velocity error observation includes

summing the velocity vector and the velocity error observation;

and

filtering the sum.

24. The method of claim 23, wherein filtering the sum comprises filtering the sum through a Kalman filter.

25. The method of claim 1, further comprising buffering the incremental rotation angles and the incremental velocities before translating the three incremental velocities from the probe'"'"'s frame of reference into the inertial frame of reference.

26. The method of claim 1, wherein feeding the system error back into the inertial navigation method includes feeding the system error back into at least one of the initialization of the probe'"'"'s attitude, the translation of the three incremental velocities from the probe'"'"'s frame of reference into the inertial frame of reference, and the determination of the updated velocity vector.

27. The method of claim 1, wherein at least one of determining the rotation angles and determining the velocities includes at least one of accelerometer error compensation and gyroscopic error compensation.

28. The method of claim 27, wherein at least one of accelerometer error compensation and gyroscopic error compensation includes compensating for major deterministic errors.

29. The method of claim 28, wherein the major deterministic errors include a major deterministic error selected from the group comprising bias, scale factor error, and misalignment.

30. A strapdown, inertial measurement unit, comprising:

a housing;

three accelerometers mounted within the housing; and

three vibrating mass, Coriolis effect gyroscopes rigidly mounted within the housing.

31. The strapdown inertial measurement unit of claim 30, wherein the three accelerometers are oriented orthogonally respective to each other.

32. The strapdown inertial measurement unit of claim 30, wherein the three gyroscopes are oriented orthogonally respective to each other.

33. The strapdown inertial measurement unit of claim 30, wherein at least one of the three gyroscopes includes a hemispherical resonator gyroscope.

34. The strapdown inertial measurement unit of claim 30, wherein the longitudinal axis of the gyroscopes is skewed relative to the longitudinal axis of the inertial measurement unit.

35. The strapdown inertial measurement unit of claim 33, wherein the longitudinal axis of the gyroscopes is skewed relative to the longitudinal axis of the inertial measurement unit at an angle of 60°

.

36. The strapdown inertial measurement unit of claim 30, wherein at least one of the gyroscopes comprises:

an axisymmetric resonator;

a forcer joined to the resonator;

a pickoff bonded to the forcer

a vacuum housing into which the resonator, forcer, and pickoff are placed.

37. The strapdown inertial measurement unit of claim 34, wherein the longitudinal axis of the gyroscopes is skewed relative to the longitudinal axis of the inertial measurement unit.

38. The strapdown inertial measurement unit of claim 30, further comprising three magnetometers mounted within the housing.

39. An inertial navigation probe, comprising:

a strapdown inertial measurement unit, including;

three accelerometers oriented orthogonally respective to each other and mounted within the housing; and

three vibrating mass, Coriolis effect gyroscopes oriented orthogonally respective to each other and rigidly mounted within the housing; and

acquisition electronics for the accelerometers and the gyroscopes; and

an external bus;

an electronics subassembly capable of communicating with the inertial measurement unit over the external bus, the electronics subassembly including;

a plurality of magnetometers;

a controller; and

an internal bus over which the magnetometers and the controller communicate;

a power supply for powering at least one of the accelerometers, gyroscopes, magnetometers, acquisition electronics, controllers.

40. The inertial navigation probe of claim 39, wherein the longitudinal axis of the gyroscopes is skewed relative to the longitudinal axis of the inertial measurement unit.

41. The inertial navigation probe of claim 40, wherein the longitudinal axis of the gyroscopes is skewed relative to the longitudinal axis of the inertial measurement unit at an angle 60°

.

42. The inertial navigation probe of claim 39, wherein at least one of the gyroscopes comprises:

an axisymmetric resonator;

a forcer joined to the resonator;

a pickoff bonded to the forcer

a vacuum housing into which the resonator, forcer, and pickoff are placed.

43. The inertial navigation probe of claim 41, wherein the longitudinal axis of the gyroscopes is skewed relative to the longitudinal axis of the inertial measurement unit.

44. The inertial navigation probe of claim 39, wherein the strapdown inertial measurement unit further includes three magnetometers.

45. The inertial navigation probe of claim 39, further comprising a program storage device encoded with instructions that, when executed by the controller, perform a method comprising:

initializing the probe'"'"'s attitude in the borehole within the probe'"'"'s frame of reference;

determining three orthogonal, incremental rotation angles for the probe within the probe'"'"'s frame of reference;

determining three orthogonal, incremental velocities for the probe within the probe'"'"'s frame of reference;

translating the three incremental velocities from the probe'"'"'s frame of reference into the inertial frame of reference using the three incremental rotation angles;

determining from the translated incremental velocities a velocity vector in a local-vertical, wander-azimuth frame of reference;

obtaining a velocity error observation;

estimating a system error from the velocity vector and a velocity error observation; and

feeding the system error back into the inertial navigation method.

46. A strapdown inertial navigation method for use in measurement-while-drilling operations, the method comprising:

maneuvering a probe in a borehole during drilling operations;

initializing the probe'"'"'s attitude in the borehole within the probe'"'"'s frame of reference;

determining three orthogonal, incremental rotation angles for the probe within the probe'"'"'s frame of reference;

determining three orthogonal, incremental velocities for the probe within the probe'"'"'s frame of reference;

translating the three incremental velocities from the probe'"'"'s frame of reference into the inertial frame of reference using the three incremental rotation angles;

determining from the translated incremental velocities a velocity vector in a local-vertical, wander-azimuth frame of reference;

obtaining a velocity error observation;

estimating a system error from the velocity vector and a velocity error observation; and

feeding the system error back into at least one of initializing the probe'"'"'s attitude, translating the three incremental velocities, and determining the velocity vector.

47. The method of claim 46, wherein the measurement-while-drilling operations include one of multi-shot gyrocompassing, measurement-while-drilling operations and zero-velocity update inertial navigation in measurement-while-drilling operations.

48. The method of claim 46, wherein initializing the probe'"'"'s attitude within the probe'"'"'s frame of reference includes at least one of a coarse alignment and a fine alignment.

49. The method of claim 48, wherein at least one of the coarse alignment and the fine alignment includes filtering.

50. The method of claim 46, wherein initializing the probe'"'"'s attitude within the probe'"'"'s frame of reference includes at least one of accelerometer error compensation and gyroscopic error compensation.

51. The method of claim 50, wherein at least one of the accelerometer error compensation and gyroscopic error compensation includes compensating for major deterministic errors.

52. The method of claim 51, wherein the major deterministic errors include a major deterministic error selected from the group comprising bias, scale factor error, and misalignment.

53. The method of claim 52, wherein translating the three incremental velocities from the probe'"'"'s frame of reference into the inertial frame of reference includes determining the probe'"'"'s velocity-attitude.

54. The method of claim 52, wherein determining the probe'"'"'s velocity attitude includes updating a body-to-inertial direction cosine matrix and updating a body-to-inertial quaternion.

55. The method of claim 46, wherein at least one of translating the three incremental velocity signals into the inertial frame of reference and determining the position of the probe is aided by a linear estimator.

56. The method of claim 55, wherein the linear estimator includes one of a linear Kalman filter, an extended Kalman filter, a backward Kalman smoother, and a minimum model error estimator.

57. The method of claim 46, wherein at least one of translating the three incremental velocity signals into the inertial frame of reference and determining the position of the probe is aided by a non-linear estimator.

58. The method of claim 57, wherein the non-linear estimator includes one of a linear Kalman filter, an extended Kalman filter, a backward Kalman smoother, and a minimum model error estimator.

59. The method of claim 46, further comprising determining the position of the probe from the translated incremental velocities.

60. The method of claim 59, wherein determining the position of the probe from the translated incremental velocities includes determining the true vertical depth.

61. The method of claim 46, wherein determining from the translated incremental velocities a velocity vector in a local-vertical, wander-azimuth frame of reference includes applying an earth gravity model.

62. The method of claim 61, wherein feeding the system error back into the inertial navigation method includes feeding the system error into the earth gravity model.

63. The method of claim 46, wherein obtaining the velocity error observation includes obtaining a zero-velocity update.

64. The method of claim 46, wherein obtaining the velocity error observation includes:

obtaining a cable velocity; and

translating the cable velocity into the local-vertical frame of reference.

65. The method of claim 46, wherein estimating a system error from the velocity vector and the velocity error observation includes

summing the velocity vector and the velocity error observation;

and

filtering the sum.

66. The method of claim 65, wherein filtering the sum comprises filtering the sum through a Kalman filter.

67. The method of claim 46, further comprising buffering the incremental rotation angles and the incremental velocities before translating the three incremental velocities from the probe'"'"'s frame of reference into the inertial frame of reference.

68. The method of claim 46, wherein feeding the system error back into the inertial navigation method includes feeding the system error back into at least one of the initialization of the probe'"'"'s attitude, the translation of the three incremental velocities from the probe'"'"'s frame of reference into the inertial frame of reference, and the determination of the updated velocity vector.

69. The method of claim 46, wherein at least one of determining the rotation angles and determining the velocities includes at least one of accelerometer error compensation and gyroscopic error compensation.

70. The method of claim 69, wherein at least one of accelerometer error compensation and gyroscopic error compensation includes compensating for major deterministic errors.

71. The method of claim 70, wherein the major deterministic errors include a major deterministic error selected from the group comprising bias, scale factor error, and misalignment.