Survivable redundant vector sensors for systems with differing maximum output requirements

• US 4,280,188 A
• Filed: 06/28/1979
• Issued: 07/21/1981
• Est. Priority Date: 10/11/1978
• Status: Expired due to Term

• Current Assignee: Grumman Aerospace Corporation (Northrop Grumman Corporation)
• Original Assignee: Grumman Aerospace Corporation (Northrop Grumman Corporation)
• Inventors: Boudreau, Jean A., Gertz, Donald, Weinstein, Warren D.
• Primary Examiner(s): Ruggiero, Joseph F.
• Application Number:
  US06/052,804
• Time in Patent Office: 754 Days
• Field of Search: 364/424, 364/434, 364/443, 364/453, 364/454, 364/566, 364/559, 33/318, 33/321, 33/322, 73/1 R, 73/1 E, 73/1 D, 73/178 R, 73/504, 244/3.2, 244/79, 244/191, 244/194, 244/165, 74/5.34, 74/5.37, 74/5.4, 318/648, 318/649
• US Class Current: 702/141
• CPC Class Codes: G01C 21/166 Mechanical, construction or arrangement details of inertial navigation systems
• CPC Class Codes: G01C 21/188 for accumulated errors, e.g. by coupling inertial systems with absolute positioning systems
• CPC Class Codes: Y10T 74/1221 Multiple gyroscopes

Abstract

Six sensors are oriented to position their input axes on the surface of a cone. The cone angle is optimized to permit the use of sensors with identical range capacity despite the fact that the maximum input along each of the orthogonal axes differs.

The optimization of cone angle minimizes the average total error amplification due to skewing and change of sensor maximum rate capability to provide data closely approximating that derived from a non skewed, orthogonal, sensor array. The sensors may be gyroscope or accelerometer which are packaged in assemblies of two identical sensors each.

Claims

1. A vector sensing system for measuring triad rates or accelerations of an aircraft comprising six identical vector sensors, each sensor having a predetermined input axis;

means for mounting said sensors in said aircraft with their input axes arranged in a non-orthogonal relationship relative to one another and with their input axes defining the surface of a cone having its axis coincident with the axis of maximum input to the aircraft, said cone having a central half angle such that an average total amplification factor is minimum; and

a data management means responsive to the output signals of said sensors to resolve said outputs into aircraft axes rates or accelerations.

2. A system of claim 1, wherein said means for mounting includes means for mounting the six sensors in three packages each containing two sensors.

3. A system of claim 2, wherein each package is identical.

4. A system of claim 2, wherein said packages are mounted on a common bulkhead of said aircraft to minimize the effect of bending of the aircraft.

5. A system of claim 1, wherein said sensors are each oriented with their input axes symmetrically spaced on the surface of said cone.

6. A system of claim 5, wherein two of said sensors input axes are coplanar with the plane defined by the yaw and roll axes.

7. A system of claim 6, wherein said vector sensors are rate sensors whose input axes are arranged to define a cone having a half angle of 77°

.

8. A system of claim 6, wherein said vector sensors are accelerometers;

and the half angle of the cone is about 63°

26'"'"'.

9. A system of claim 5, wherein one of said sensor axis lies in a plane displaced 30°

from the yaw-roll plane.

10. A method of measuring triad rates or accelerations in an aircraft in which the maximum rate requirements about the axes of the aircraft differ which comprises the steps of:

providing six vector sensors having identical maximum rate capacities;

positioning the sensors with their input axes defining a cone having its axes coincident with the axis of maximum input to the aircraft, said cone having a central half angle selected to minimize the average total amplification factor; and

utilizing the output of said sensors to resolve the rates or accelerations along the roll, pitch and yaw axes.

11. A method of claim 10 including the steps of arranging the six rate sensors in three packages containing two sensors each.

12. A method of claim 10, wherein said sensors are each symmetrically spaced on the surface of said cone.

13. A method of claim 12, wherein said sensors are gyroscopes and said cone axis is coincident with the roll axis.

14. A method of claim 13, wherein the central half angle is 77°

.

15. A method of claim 13, including the steps of mounting said sensors on a common bulkhead located aft of the anti node of the first mode of vibration of the aircraft.

16. A method of claim 12, wherein said sensors are accelerometers and said cone axis is coincident with the yaw axis.

17. A method of claim 16, wherein the central half angle is about 63°

26'"'"'.

18. A vector sensing system for measuring triad rates or accelerations of an aircraft comprising six identical vector sensors, each sensor having a pre-determined input axis;

means for mounting said sensors in said aircraft with their input axes arranged in a non-orthogonal relationship relative to one another and with their input axes defining the surface of a cone having its axis coincident with the axis of maximum input to the aircraft, said cone having a central half angle such that an average total amplification factor is minimum.

19. A system of claim 18, wherein said means for mounting includes means for mounting the six sensors in three packages each containing two sensors.

20. A system of claim 19, wherein each package is identical.

21. A system of claim 19, wherein said packages are mounted on a common bulkhead of said aircraft to minimize the effect of bending of the aircraft.

22. A system of claim 18, wherein said sensors are each oriented with their input axes symmetrically spaced on the surface of said cone.

23. A system of claim 22, wherein two of said sensor input axes are coplanar with the plane defined by the yaw and roll axes.

24. A system of claim 23, wherein said vector sensors are rate sensors whose input axes are arranged to define a cone having a half angle of 77°

.

25. A system of claim 23, wherein said vector sensors are accelerometers;

and the half angle of the cone is about 63°

26'"'"'.

26. A system of claim 22, wherein one of said sensor axis lies in a plane displaced 30°

from the yaw-roll plane.

27. A system of claim 22, wherein said sensors are gyroscopes and said cone axis is coincident with the roll axis.

28. A system of claim 26, wherein said sensors are mounted on a common bulkhead located aft of the antinode of the first mode of vibration of the aircraft.

29. A system of claim 22, wherein said sensors are accelerometers and said cone axis is coincident with the yaw axis.