Skewed axis inertial sensor assembly

• US 5,363,700 A
• Filed: 11/17/1992
• Issued: 11/15/1994
• Est. Priority Date: 11/17/1992
• Status: Expired due to Term

• Current Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Original Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Inventors: Miller, Michelle J., Nitzschke, George O., Joly, Lucien E., Weinberger, Mark T., Knipfer, Michael A.
• Primary Examiner(s): Chapman, John E.
• Assistant Examiner(s): NOT, DEFINED
• Application Number:
  US07/977,319
• Time in Patent Office: 728 Days
• Field of Search: 73/504, 73/510, 73/493, 73/866.5, 73/178 R, 73/431, 74/5.34, 364/453, 356/350
• US Class Current: 73/504.18
• CPC Class Codes: G01C 21/166 Mechanical, construction or arrangement details of inertial navigation systems
• CPC Class Codes: G01P 15/18 in two or more dimensions

Abstract

In the present invention six gyros and six accelerometers are mounted to a support frame generally comprised of a block of a selected material. The relationship of each input axis of each of the gyros and accelerometers is selected to permit all of the sensors to be mounted on the block so as to provide minimal size and weight of the combination of the block and the six gyros and six accelerometers. More specifically, first, second and third pairs of gyros (totaling six gyros) and six accelerometers are mounted to the block such that the input axis of each gyro and accelerometer is in non-colinear alignment with any other input axis, and that the input axes of the first, second, and third pairs of gyros intersect at mutually exclusive first, second, and third intersection points, and such that each input axis of all six of the accelerometers intersect at a common accelerometer intersection point, and wherein the first, second, and third gyro intersection points and the accelerometer intersection point lie in a plane which is substantially a plane of symmetry of the combination of the block, the six gyros, and the six accelerometers.

Claims

1. An inertial sensor assembly comprising:

a support frame for supporting first, second, third, fourth, fifth, and sixth gyros, the peripheral portions of said support frame surrounding a coordinate reference point of a right hand orthogonal XYZ coordinate system including ±

XYZ reference axes passing through said coordinate reference point, and in which said X and Y reference axes define an XY plane, said Y and Z reference axes define a YZ plane, and said X and Z reference axes define an XZ plane;

said first and second gyros being mounted to said support frame and spaced apart from said XY plane in the +Z direction therefrom and spaced apart from said YZ plane in the -X direction therefrom, said first and second gyros having the extension of their respective input axes intersecting at a first intersection point in the XZ plane, and in which said first and second gyro input axes are at a first selected angle relative to said XY plane, and in which the angle value between said +X axis and the perpendicular projection of said first gyro input axis onto said XY plane measure in the counter-clockwise direction is a selected second angle value, and in which the angle between said +X axis and the perpendicular projection of said second gyro input axis on said XY plane measured in the clockwise direction is also said selected second angle value, and wherein said first intersection point is spaced apart from said YZ plane in the +X direction therefrom;

said third gyro being mounted to said support frame and spaced apart from said XY plane in the +Z direction therefrom and spaced apart from said YZ plane in the +X direction therefrom, said third gyro having the extension of its input axis which lies in said XZ plane and is at said first selected angle relative to said XY plane;

said fourth and fifth gyros being mounted to said support frame and spaced apart from said XY plane in the +Z direction therefrom and spaced apart from said YZ plane in the +X direction therefrom, said fourth and fifth gyros having the extension of their respective input axes intersecting at a second intersection point in said XZ plane, and in which said fourth and fifth gyro input axes are at a said first selected angle relative to said XY plane, and in which the angle between said +X axis and the perpendicular projection of said fourth gyro input axis on said XY plane is a third selected angle value measured in the counter-clockwise direction, and in which the angle between said +X axis and the perpendicular projection of said fifth gyro input axis on said XY plane measured in the clockwise direction is also said selected third angle value, and wherein said second intersection point is spaced apart from said YZ plane in the +X direction therefrom; and

said sixth gyro being mounted to said support frame and spaced apart from said XY plane in the +Z direction therefrom and slanted apart from said YZ plane in the -X direction therefrom, said sixth gyro having its input axis in parallel with said Z axis and the extension thereof intersecting the extension of said third gyro input axis at a third intersection point, and wherein said third intersection point lies in said XZ plane and is spaced apart from said YZ plane in the -X direction therefrom and spaced apart from said XY plane in the +Z direction therefrom.

2. The apparatus of claim 1 further comprising:

a first accelerometer being mounted to said support frame and having its input axis parallel to said first gyro input axis and intersecting said Z axis at a fourth intersection point, and in which said fourth intersection point lies in a first reference plane parallel to said XY plane, and in which said first accelerometer is spaced apart from said first reference plane in the +Z direction; and

second, third, fourth, fifth, and sixth accelerometers being mounted to said support frame and having their respective input axes parallel to said second, third, fourth, fifth, and sixth gyro input axis, respectively, and said input axis of each of said second, third, fourth, fifth, and sixth accelerometers intersecting said fourth intersection point, and in which said second, third, fourth, fifth, and sixth accelerometers are spaced apart from said fourth reference plane in the +Z direction.

3. The inertial sensor assembly of claim 1 wherein said first selected angle is substantially 26.565°

.

4. The inertial sensor assembly of claim 1 wherein said second selected angle is 144°

and said third selected angle is 72°

.

5. The inertial sensor assembly of claim 3 wherein said second selected angle is 144°

and said third selected angle is 72°

.

6. The inertial sensor assembly of claim 1 wherein the resultant center of gravity off (i) said support frame, (ii) said first, second, third, fourth, fifth, and sixth accelerometers, and (iii) said first, second, third, fourth, fifth, and sixth gyros mounted thereto lies substantially on said Z axis.

7. The inertial sensor assembly of claim 6 wherein said support frame includes means for mounting four suspension members thereto such that the elastic centers of said suspension members substantially lie in a plane parallel to said YZ plane, and said suspension members are positioned such that the elastic centers thereof are geometrically located as ends of diagonal pairs establishing four corners of a rectangle.

8. The inertial sensor assembly of claim 1 wherein said support frame is constructed in a manner to establish said XZ plane as a substantial plane of symmetry of said support frame with said first, second, third, fourth, fifth, and sixth ones of said gyros and accelerometers mounted thereto.

9. The inertial sensor assembly of claim 1 wherein said support frame comprises a block of a selected material including:

six apertures, each having a mounting means therewith, for mounting said first, second, third, fourth, fifth, and sixth gyros therein, at least in part, and thereby establishing the relationship of each gyro input axis relative to said coordinate system; and

six apertures, each having a mounting means therewith, for mounting said first, second, third, fourth, fifth, and sixth accelerometers therein, at least in part, and thereby establishing the relationship of each accelerometer input axis relative to said coordinate system.

10. The inertial sensor assembly of claim 9 for selecting the moments of inertia about the center of gravity of the mass of said support frame with said first, second, third, fourth, fifth, and sixth ones of said gyros and accelerometers mounted thereto.

11. The inertial sensor assembly of claim 7 wherein said block includes selected apertures therein for causing the elastic center and the center of gravity of the spring mass system, including at least said block and said gyros, to be substantially the same point.

12. An inertial sensor assembly comprising:

a block of material; and

six gyros and six accelerometers mounted to said block such that the input axis of each gyro and accelerometer is in non-colinear alignment with any other input axis, and first, second, and third pairs of gyros of said six gyros intersect at a common gyro intersection point exclusive of one another, and such that each input axis of all six of said accelerometers intersect at a common accelerometer intersection point, and wherein said three gyro intersection points and said accelerometer intersection point lie in a plane which is substantially a plane of symmetry of the combination of said block and said six gyros and said six accelerometers.

13. An inertial sensor assembly comprising:

a block of material; and

six gyros mounted to said block such that the input axis of each gyro is in non-colinear alignment with any other input axis, and the input axes of each of first, second, and third pairs of gyros of said six gyros intersect at first, second, and third gyro intersection points exclusive of one another, and wherein said first, second, and third gyro intersection points lie in a plane.

14. The inertial sensor assembly of claim 13 where said first, second, and third gyro intersection points lie in a plane which is substantially a plane of symmetry of the combination of said block and said six gyros.

15. An inertial sensor assembly comprising:

a block of material; and

six gyros mounted to said block such that the input axis of each gyro is in non-colinear alignment with any other input axis, and first, second, third and fourth ones of said gyros having their respective input axis intersecting a common plane, and in which the input axis of fifth and sixth ones of said gyros lie in said common plane.

16. The inertial sensor assembly of claim 15 where said common plane is substantially a plane of symmetry of the combination of said block and said six gyros.