Projectile with inertial sensors oriented for enhanced failure detection

• US 8,558,153 B2
• Filed: 01/23/2009
• Issued: 10/15/2013
• Est. Priority Date: 01/23/2009
• Status: Active Grant

• Current Assignee: Raytheon Company (Rtx Corporation)
• Original Assignee: Raytheon Company (Rtx Corporation)
• Inventors: Geswender, Chris E.
• Primary Examiner(s): GREGORY, BERNARR E
• Application Number:
  US12/359,156
• Publication Number:
  US 20120025007A1
• Time in Patent Office: 1,726 Days
• Field of Search: 244 31- 33, 89/11, 89/11.1, 701 3- 18, 701/200, 701/207, 701/220, 701/221, 701/400, 701/408, 701/468, 701500-512, 701534-536, 102/382, 102/384, 102/473, 102/501
• US Class Current: 244/3.24
• CPC Class Codes: F42B 10/62 Steering by movement of flight surfaces
• CPC Class Codes: F42B 15/01 Arrangements thereon for guidance or control steering arrangements F42B10/60; aircraft flight control B64C; guidance systems other than those installed aboard F41G7/00, F41G9/00; locating by use of radio or other waves G01S; flight control in general G05D1/00; computer aspects G06]

Abstract

A guided projectile may include a projectile body, an inertial measurement unit disposed within the projectile body, one or more control surfaces extendable from the projectile body, and a controller which controls the one or more control surfaces in response, at least in part, to measurement data received from the inertial measurement unit. The inertial measurement unit may include sensors to measure motion parameters relative to first, second, and third mutually orthogonal axes, wherein each of the first, second and third mutually orthogonal axes is oblique to a longitudinal axis of the projectile body.

Claims

1. A guided projectile, comprising:

a projectile body

an inertial measurement unit disposed within the projectile body, the inertial measurement unit including sensors to measure motion parameters relative to first, second, and third mutually orthogonal axes, wherein each of the first, second and third mutually orthogonal axes is oblique to a longitudinal axis of the projectile body

one or more control surfaces extendable from the projectile body, the one or more control surfaces stowed within the projectile body before and during launch

a controller which controls the one or more control surfaces in response, at least in part, to measurement data received from the inertial measurement unit, wherein

the control unit is adapted to compare measurement data relative to the first, second, and third mutually orthogonal axes to determine if the inertial measurement unit is functioning within predetermined tolerances after launch and before extension of the one or more control surfaces, and

the control unit is further adapted to inhibit extension of the one or more control surfaces if a determination is made that the inertial measurement unit is not functioning within predetermined tolerances.

2. The projectile of claim 1, wherein

the angles formed by each of the first, second, and third mutually orthogonal axes and the longitudinal axis of the projectile body are essentially equal.

3. The projectile of claim 1, wherein

the inertial measurement unit comprises first, second, and third accelerometers disposed to measures acceleration along each of the first, second, and third mutually orthogonal axes, respectively

after launch and before extension of the one or more control surfaces, the control unit compares measurement data indicating the acceleration along the first, second, and third mutually orthogonal axes to determine if the first, second, and third accelerometers are functioning within predetermined tolerances.

4. The projectile of claim 1, wherein

the inertial measurement unit comprises respective first, second, and third gyroscopes disposed to measure rotation rate about each of the first, second, and third mutually orthogonal axes, respectively

after launch and before extension of the one or more control surfaces, the control unit compares measurement data indicating the rotation rate about the first, second, and third mutually orthogonal axes to determine if the first, second, and third gyroscopes are functioning within predetermined tolerances.

5. The projectile of claim 1, wherein

the projectile may be programmed to operate in one of a test mode and a tactical mode

wherein the predetermined tolerances for the test mode are different from the predetermined tolerances for the tactical mode.

6. The projectile of claim 1, further comprising:

a GPS receiver

wherein the control unit controls the one or more control surfaces in response, at least in part, to positional data provided by the GPS receiver.

7. A method for operating a projectile, comprising:

launching the projectile with one or more control surfaces extendable from a body of the projectile

after launch, measuring motion parameters relative to first, second, and third mutually orthogonal axes with an inertial measurement unit, wherein each of the first, second and third mutually orthogonal axes is oblique to a longitudinal axis of the body of the projectile

after launch and before extension of the one or more control surfaces, determining if the inertial measurement unit is functioning within predetermined tolerances based on the measured motion parameters relative to the first, second, and third, mutually orthogonal axes

when a determination is made that the inertial measurement unit is not functioning within predetermined tolerances, inhibiting extension of the one or more control surfaces whereby the projectile continues on a ballistic flight path

when a determination is made that the inertial measurement unit is functioning within predetermined tolerances, extending the one or more control surfaces from the projectile body and controlling the control surfaces, at least in part, in response to measured motion parameters.

8. The method for operating a projectile of claim 7, further comprising

prior to launching the projectile, programming the projectile to operate in one of a test mode and a tactical mode

wherein the predetermined tolerances for the test mode are different from the predetermined tolerances for the tactical mode.

9. The method for operating a projectile of claim 7, wherein

measuring motion parameters comprises measuring first, second, and third acceleration values indicating acceleration along the first, second, and third mutually orthogonal axes, respectively

determining if the inertial measurement unit is functioning within predetermined tolerances comprises comparing the first, second, and third measured acceleration values

wherein a determination is made that the inertial measurement unit is functioning within predetermined tolerances if the first, second, and third measured acceleration values are equal within a predetermined tolerance.

10. The method for operating a projectile of claim 9, wherein the first, second, and third measured acceleration values are multiplied by respective scale factors prior to the comparing.

11. The method for operating a projectile of claim 7, wherein

measuring motion parameters comprises measuring first, second, and third rotation rate values indicating rotation rate about the first, second, and third mutually orthogonal axes, respectively

determining if the inertial measurement unit is functioning within predetermined tolerances comprises comparing the first, second, and third measured rotation rate values

wherein a determination is made that the inertial measurement unit is functioning within predetermined tolerances if the first, second, and third measured rotation rate values are equal within a predetermined tolerance.

12. The method for operating a projectile of claim 11, wherein the first, second, and third measured rotation rate values are multiplied by respective scale factors prior to the comparing.