Tetrahedral redundant inertial reference unit

• US 4,179,818 A
• Filed: 10/07/1976
• Issued: 12/25/1979
• Est. Priority Date: 10/07/1976
• Status: Expired due to Term

• Current Assignee: Litton Systems Incorporated
• Original Assignee: Litton Systems Incorporated
• Inventors: Craig, Robert J. G.
• Primary Examiner(s): Martin, Jr., William D.
• Application Number:
  US05/730,419
• Time in Patent Office: 1,174 Days
• Field of Search: 33/321, 33/322, 33/318, 73/1 E, 73/178 R, 74/5.34, 74/5.37
• US Class Current: 33/321
• CPC Class Codes: G01C 21/166 Mechanical, construction or arrangement details of inertial navigation systems
• CPC Class Codes: Y10T 74/1221 Multiple gyroscopes

Abstract

A redundant inertial reference system is provided with four gyroscope units, with the spin axes of the gyroscopes in the units being oriented, respectively, perpendicular to the four faces of an equilateral tetrahedron. Incidentally, a tetrahedron is a four sided body, and an equilateral tetrahedron is a four sided body having equilateral triangles for the four sides. With the four gyroscopes mounted perpendicular to the four sides of an equilateral tetrahedron, each of the gyroscopes is located symmetrically with respect to the others, with an angle of approximately 109.4 degrees between the spin axes of the gyroscopes. The system is particularly applicable to strapdown type inertial guidance systems and can provide three dimensional orientation information even if two of the gyros fail. The system uses four gyro units, a minimum number which can accomplish a foregoing function, with the four gyro units arranged substantially symmetrically with respect to one another.

Claims

1. A symmetrical redundant inertial reference unit comprising:

(a) a plurality of gyroscopes included in said reference unit, the gyroscopes of said reference unit consisting solely of four two-degree-of-freedom gyroscopes, each said gyroscope having its two sensitive axes substantially perpendicular to each other;

(b) means associated with each gyroscope for generating two output signals from each said gyroscope, one output signal being generated for each of said two sensitive axes, each signal representing rate of angular motion about one sensitive axes; and

(c) means for fixedly positioning each said gyroscope with respect to each other in a primary coordinate system with the two sensitive axes of each of said four gyroscopes defining a plane which intersects the planes defined by the two sensitive axes of each of the other three gyroscopes at substantially the same angle, whereby said unit is capable of providing correct coordinate information about three mutually orthogonal axes despite failure of up to two of said four gyroscopes.

2. An inertial reference unit as defined in claim 1 further comprising means for resolving said gyroscope output signals into corresponding information relative to a second coordinate system.

3. The inertial reference unit described in claim 2 further comprising:

(a) means for measuring linear motion along one or more primary coordinate system directions and for generating output signals representative of the magnitude of said motion; and

(b) wherein said resolving means also includes means for resolving output signals from said measuring means into information relative to said second coordinate system.

4. The inertial reference unit described in claim 2 further comprising means for analyzing said gyroscope output signals to identify at least one of said gyroscopes giving erroneous output signals.

5. The inertial reference unit described in claim 4 further comprising means for blocking erroneous data from at least one gyroscope, whereby said unit remains capable of determining correct coordinate location in said second coordinate system during periods when up to two of said gyroscopes are giving erroneous output signals.

6. The inertial reference unit described in claim 2 further comprising:

(a) means for measuring linear motion along one or more primary coordinate system directions and for generating output signals repesentative of the magnitude of said linear motions; and

(b) means for resolving said output signals from said measuring means into corresponding information relative to a second coordinate system.

7. A reference unit as defined in claim 1 further comprising symmetrical data processing means for detecting invalid initial signals from said gyroscopes and for averaging valid inertial signals.

8. A symmetrical redundant inertial reference unit comprising:

(a) a plurality of gyroscopes included in said reference unit, the gyroscope of said reference unit consisting solely of four two-degree-of-freedom gyroscopes, each said gyroscope having its two sensitive axes substantially perpendicular to each other;

(b) means associated with each said gyroscope for generating two output signals, each output signal generated representing the rate of angular motion about one of said sensitive axes;

(c) means for fixedly positioning said gyroscopes in a primary coordinate system with said sensitive axes of each of said four gyroscopes defining a plane parallel to the respective faces an equilateral tetrahedron, whereby said unit is capable of providing correct coordinate information about three mutually orthogonal axes of a second coordinate system despite failure of up to two of said four gyroscopes; and

(d) means for resolving said output signals into corresponding information referenced to said second coordinate system to determine angular position in said second coordinate system.

9. The inertial reference unit described in claim 8 further comprising:

(a) means for analyzing output signals from said gyroscopes to identify at least one of said gyroscopes giving erroneous outputs; and

(b) means for blocking said erroneous output signals in said resolving means whereby said inertial reference unit is capable of resolving correct coordinate location with up to two of said gyroscopes rendering erroneous signals.

10. A symmetrical redundant strapdown inertial reference unit for a vehicle comprising:

(a) a plurality of gyroscopes included in said reference unit, the gyroscopes of said reference unit consisting solely of four two-degree-of-freedom gyroscopes, each gyroscope having two sensitive axes substantially orthogonal to each other and to the spin vector along the spin axis;

(b) means associated with each said gyroscope for generating two output signals from each said gyroscope, each signal being respresentative of the rate of angular motion about one of said sensitive axes;

(c) means for fixedly positioning said gyroscope in a primary coordinate system with said sensitive axes of each of said four gyroscopes defining a plate parallel to the respective faces of an equilateral tetrahedron, and with said spin vectors pointing away from said tetrahedron;

(d) means for measuring linear motion along one or more primary coordinate directions, said measuring means generating output signals representative of the magnitude of motion in said directions;

(e) means for resolving said gyroscope outputs in said motion-measuring-means outputs into corresponding information referenced to a second coordinate system having three mutually orthogonal axes; and

(f) means for isolating erroneous output signals from at least one of said gyroscopes and blocking said erroneous signals in resolving said output signals into said second coordinate system whereby said inertial reference unit is capable of resolving substantially correct three dimensional coordinate information in said second coordinate system with up to two of said gyroscopes said gyroscopes rendering erroneous output signals.