Inertial navigation system

Patent metadata

Field	Value
Publication number	US-9689684-B2
Application number	US-201515121854-A
Country	US
Kind code	B2
Filing date	Feb 16, 2015
Priority date	Feb 27, 2014
Publication date	Jun 27, 2017
Grant date	Jun 27, 2017

Abstract

An inertial measurement system for a longitudinal projectile comprising: a first, roll gyro to be oriented substantially parallel to the longitudinal axis of the projectile; a second gyro and a third gyro with axes arranged with respect to the roll gyro such that they define a three dimensional coordinate system; a controller, arranged to: compute a current projectile attitude from the outputs of the first, second and third gyros, the computed attitude comprising a roll angle, a pitch angle and a yaw angle; compare the computed pitch and yaw angles with expected values for the pitch and yaw angles; calculate a roll angle error and a roll scale factor error based on the difference between the computed pitch and yaw angles and the expected pitch and yaw angles; and apply the calculated roll angle error and roll scale factor error to the output of the roll gyro.

First claim

The invention claimed is:

1. An inertial measurement system for a longitudinal projectile comprising:
a first, roll gyro to be oriented substantially parallel to the longitudinal axis of the projectile;
a second gyro and a third gyro with axes arranged with respect to the roll gyro such that they define a three dimensional coordinate system;
a controller, arranged to:
compute a current projectile attitude from the outputs of the first, second and third gyros, the computed attitude comprising a roll angle, a pitch angle and a yaw angle;
compare the computed pitch and yaw angles with expected values for the pitch and yaw angles;
calculate a roll angle error and a roll scale factor error based on the difference between the computed pitch and yaw angles and the expected pitch and yaw angles; and
apply the calculated roll angle error and roll scale factor error to the output of the roll gyro.

2. An inertial measurement system as claimed in claim 1 , wherein the roll gyro is a MEMS gyro.

3. An inertial measurement system as claimed in claim 1 , wherein the expected values for pitch and yaw angles as a function of flight time correspond to those expected from planar ballistic flight.

4. An inertial measurement system as claimed in claim 3 , wherein the roll angle error is calculated as the angle whose tangent is the ratio of the rate of change of the calculated yaw angle to the rate of change of the calculated pitch angle.

5. An inertial measurement system as claimed in claim 1 , wherein the expected values for pitch and yaw angles as a function of flight time are taken from a pre-computed flight trajectory which may be non-planar.

6. An inertial measurement system as claimed in claim 1 wherein the roll angle error is multiplied by a roll angle error gain factor before being applied to the output of the roll gyro.

7. An inertial measurement system as claimed in claim 1 , wherein the roll scale factor error is multiplied by a roll scale factor error gain factor before being applied to the output of the roll gyro.

8. An inertial measurement system as claimed in claim 6 , wherein the gain factor is a fixed value.

9. An inertial measurement system as claimed in claim 7 , wherein the roll scale factor error gain is proportional to the reciprocal of the instantaneous roll rate.

10. An inertial measurement system as claimed in claim 1 , wherein the roll angle error and roll scale factor error are only applied prior to any guidance action being initiated.

11. An inertial measurement system as claimed in claim 1 ,
wherein the controller is arranged such that a period of time after launch it performs an attitude reset function, said attitude reset function comprising:
setting the current projectile yaw equal to a corrected yaw value; and
setting the current projectile pitch equal to a corrected pitch value.

12. An inertial measurement system as claimed in claim 11 , further comprising:
body mounted accelerometers for measuring an acceleration vector; and
a velocity calculation unit that calculates a velocity vector from the acceleration vector; and
wherein the corrected yaw value is equal to a current track angle of the velocity vector and the corrected pitch value is equal to a current climb angle of the velocity vector.

13. An inertial measurement system as claimed in claim 11 , wherein the period of time is a time at which the measured roll rate decreases below a threshold roll rate.

14. An inertial measurement system as claimed in claim 11 , wherein the period of time is a set time after launch.

15. A method of correcting roll angle in an inertial measurement system for a longitudinal projectile, comprising:
computing a current projectile attitude comprising a roll angle, a pitch angle and a yaw angle;
comparing the computed pitch angle and computed yaw angle with an expected pitch angle and an expected yaw angle;
calculating a roll angle error and a roll scale factor error based on the difference between the computed pitch and yaw angles and the expected pitch and yaw angles; and
applying the calculated roll angle error and roll scale factor error to the output of a roll gyro.

Assignees

• Atlantic Inertial Systems Ltd
• Atlantic Inertial Systems Ltd

Inventors

• Sheard John Keith
• Faulkner Nicholas Mark

Classifications

• G01C21/185

  for gravity · CPC title

• G01C21/188 Primary

  for accumulated errors, e.g. by coupling inertial systems with absolute positioning systems · CPC title

• G05D2109/28

  Missiles · CPC title

• G05D1/49

  Control of attitude, i.e. control of roll, pitch or yaw · CPC title

• G01C21/16 Primary

  by integrating acceleration or speed, i.e. inertial navigation · CPC title