Redundant inertial measurement system

• US 4,125,017 A
• Filed: 07/29/1977
• Issued: 11/14/1978
• Est. Priority Date: 07/29/1977
• Status: Expired due to Term

• Current Assignee: Mcdonnell Douglas Corporation (The Boeing Co.)
• Original Assignee: Mcdonnell Douglas Corporation (The Boeing Co.)
• Inventors: Engelder, Paul D., Dhuyvetter, Henry J., Simmons, Joseph C.
• Primary Examiner(s): Gill, James J.
• Application Number:
  US05/820,249
• Time in Patent Office: 473 Days
• Field of Search: 73/178 R, 73/504, 364/434, 364/443, 364/453, 74/5.34
• US Class Current: 73/178.00R
• CPC Class Codes: G01C 21/166 Mechanical, construction or arrangement details of inertial navigation systems
• CPC Class Codes: G01C 21/183 Compensation of inertial measurements, e.g. for temperature effects
• CPC Class Codes: Y10T 74/1221 Multiple gyroscopes

Abstract

A system providing economical redundant strap-down inertial measurement capability in a space navigation system. By appropriate orientation of two-degree-of-freedom dry tuned rotor gyros, the system is able to achieve complete redundancy utilizing only three gyro units. With this orientation, both orthogonal and skewed rate data are available. Not only are the necessary computations materially simplified, but this system also provides the necessary conditions for failure detection and isolation.

Claims

1. A redundant inertial measurement system for use in space navigation comprising:

three gyros, each having at least two degrees of freedom and including first and second mutually orthogonal axes;

means for mounting said gyros in three distinct attitudes with the respective first axes orthogonally directed with respect to each other so as to develop a first orthogonal triad including the first axis of each gyro and the respective second axes directed at 45°

with respect to corresponding pairs of said first axes so as to develop a second triad skewed at 45°

to the first triad, the second triad including the second axis of each gyro;

means for deriving rate information relative to the first and second triads; and

means for processing said information.

2. The system of claim 1 wherein the gyros are respectively X, Y and Z gyros and wherein the gyros are mounted with the first axes aligned respectively with different ones of three orthogonal, arbitrarily designated X, Y and Z axes, the X gyro having its second axis at 45°

to the Y and z axes in the Y-Z plane, the Y gyro having its second axis at 45°

to the X and Z axes in the X-Z plane, and the Z gyro having its second axis at 45°

to the X and Y axes in the X-Y plane.

3. The system of claim 2 wherein the mounting means comprises a sensor block having X, Y and Z orthogonal axes and an upper face parallel to a Y-Z plane defined by the Y and Z axes;

three 45°

-angled mounting surfaces, one for each of the X, Y and Z gyros, the orientation of the mounting surfaces being defined by reference to first, second and third planes at right angles to said Y-Z plane, the first and second planes being at right angles to each other and the second and third planes being at right angles to each other, the mounting surface for the Z gyro being angled at 45°

with respect to the first plane and the Y-Z plane, the mounting surface for the Y gyro being angled at 45°

with respect to the second plane and the Y-Z plane, and the mounting surface for the X gyro being angled at 45°

with respect to the second and third planes and at 90°

to the Y-Z plane.

4. THe system of claim 3 wherein said gyros are mounted on the mounting surfaces with orientation such that the first axes of the X and Y gyros are directed parallel to the Y-Z plane of the sensor block and the second axis of the Z gyro is directed parallel to said Y-Z plane.

5. The system of claim 1 wherein the three gyros are connected respectively in three distinct gyro channels with associated driving and signal processing means for providing gyro channel redundancy in said system.

6. The system of claim 5 wherein the signal processing means includes separate means in each gyro channel for separately processing signal from the first and second axes of the gyro in that channel.

7. The system of claim 5 wherein each distinct gyro channel includes a capture loop coupled to the gyro of that channel for caging the gyro, a pair of analog-to-digital converters for converting analog signal information from the two axes of the gyro to digital signals corresponding thereto, and means for combining the digital signals with other digital signals in multiplexed form for transmission on a single output data line.

8. The system of claim 7 wherein each channel further includes an individual power supply for powering the gyro and other components of that channel.

9. The system of claim 8 wherein each channel further includes at least one accelerometer for providing acceleration information relative to an axis corresponding to the gyro of that channel and an analog-to-digital converter coupled to the accelerometer for converting analog signals to digital signals for application to the signal combining means.

10. The system of claim 9 wherein one of said gyro channels further includes a second accelerometer in addition to a first accelerometer along the same axis thereof for providing redundant acceleration information relative to that axis, and an additional analog-to-digital converter coupled to the second accelerometer for converting analog signals therefrom to digital signals for application to the signalcombining means.

11. The system of claim 10 further including timing means for generating timing control signals to each of the three gyro channels respectively, and means for providing power to the timing means, said last-mentioned means comprising means for combining outputs from the respective power supplies of the three channels by pairs to develop redundant power supplies coupled to the timing means.

12. The system of claim 1 wherein each of said gyros is a two-degree-of-freedom dry tuned rotor gyro.