Self-contained supplemental guidance module for projectile weapons

• US 4,899,956 A
• Filed: 07/20/1988
• Issued: 02/13/1990
• Est. Priority Date: 07/20/1988
• Status: Expired due to Fees

• Current Assignee: Teleflex Incorporated
• Original Assignee: Teleflex Incorporated
• Inventors: Katucki, Gregory M., King, Maurice E.
• Primary Examiner(s): Jordan, Charles T.
• Application Number:
  US07/221,933
• Time in Patent Office: 573 Days
• Field of Search: 244/3.21, 244/3.22, 102/293
• US Class Current: 244/3.21
• CPC Class Codes: F42B 10/661 using several transversally acting rocket motors, each motor containing an individual propellant charge, e.g. solid charge
• CPC Class Codes: G05D 1/12 Target-seeking control

Abstract

A self-contained supplemental guidance module for use with projectile weapons having a connected body and payload in attachable to the weapon between the body and payload, and includes self-contained power supply, inertial sensors and a plurality of incremental charges angularly spaced around an outer periphery of the module. A control processor in the module is operable responsive to the position of the module as detected by the sensors to calculate deviation of the projectile from a nominal flight path, taking gravity into account, and to detonate individual incremental charges when deviation exceeds a threshold and the incremental charge is in position to reduce the deviation. The supplemental guidance module is particularly applicable to barrage rockets, and includes a multi-level safe-and-arm apparatus initiating operation with sufficient axial thrust and disabling operation in the event of loss of sensor signals.

Claims

1. A self-contained supplemental guidance apparatus for use with a projectile weapon having a body, at least one payload attachable to the body and means for propelling the body and payload towards a target, the apparatus comprising:

a supplemental guidance module to be fitted to at least one of the body and the payload, the supplemental guidance module being self-contained and having on-board a power supply, whereby the guidance apparatus is operable apart from electrical connection to the body and the payload;

sensing means in the module, including position sensing means operative to sense at least one of a starting orientation of the projectile weapon and an instantaneous orientation of the projectile weapon;

actuation means including a plurality of individually controllable incremental charges angularly spaced around a periphery of the module; and

,

a control processor in the module, operable to monitor an output of said sensing means, to calculate deviation from a nominal flight path, and to actuate at least one of the incremental charges when said deviation exceeds a threshold and said at least one of the incremental charges is in a position to reduce said deviation.

2. The apparatus of claim 1, further comprising launch-sensing means in the module, operable to detect launch, the control processor being connected to the launch-sensing means, the control processor being operable to initiate operation of the supplemental guidance apparatus.

3. The apparatus of claim 2, wherein the launch-sensing means includes a power switch sensitive to axial acceleration, said switch connecting power to at least one of said processor, sensing means and actuation means.

4. The apparatus of claim 1, wherein the body of the projectile weapon includes a propulsion motor and further comprising means on the module for physically engaging the payload and the body, respectively, whereby the module is fittable optionally to the projectile weapon by first separating the payload from the body and then attaching said apparatus between the payload and the body, whereby the supplemental guidance apparatus can be used preferentially with accuracy-sensitive forms of payload.

5. The apparatus of claim 1, wherein the incremental charges are explosive charges disposed in at least one band around the module.

6. The apparatus of claim 1, wherein the position sensing means includes at least one of a tilt sensor, an accelerometer and a rotational velocity sensor, the tilt sensor being operative to sense position of the module relative to vertical, the accelerometer being operative to sense acceleration of the module and the rotational velocity sensor sensing angular velocity around at least one of three mutually perpendicular axes.

7. The apparatus of claim 6, wherein the axes are yaw, pitch and roll axes.

8. The apparatus of claim 6, wherein the module includes said accelerometer, and further comprising means for twice integrating at least one output of the accelerometer, the control processor being connected to at least one of the accelerometer and said means for integrating.

9. The apparatus of claim 6, wherein the module includes the rotational velocity sensor, and further compromising means for integrating an output of the rotational velocity sensor to determine attitude of the module.

10. The apparatus of claim 8, wherein the accelerometer includes a two axis gyro operable to detect pitch and yaw acceleration, and further comprising means connected to the control processor for twice integrating said pitch and yaw acceleration, whereby said apparatus monitors attitude of the module.

11. The apparatus of claim 1, wherein the position sensing means includes at least one sensor operable at intervals during a flight of the projectile weapon to determine orientation of the module relative to vertical.

12. The apparatus of claim 8, wherein the accelerometer detects rotational acceleration around at least one axis of the projectile, and further comprising means connected to the control processor for integrating said rotational acceleration, whereby the apparatus monitors a rotational position of the module.

13. The apparatus of claim 12, wherein the accelerometer detects rotational acceleration around three mutually-perpendicular axes of said module.

14. The apparatus of claim 1, wherein the position sensing means includes at least one sensor operable to determine instantaneous orientation of the module at least at one time during a flight of the projectile weapon, and further comprising at least one of an accelerometer and a rotational rate sensor, operative to sense at least one of rotational acceleration and rotational rate after said one time, and means integrating at least one of said rotational acceleration and said rotational rate to determine changes in orientation from said instantaneous orientation, the control processor being operable to distinguish and ignore such changes in orientation from a straight flight which are due to gravitational acceleration, whereby the supplemental module acts to maintain proper attitude of the projectile weapon regardless of range to the target.

15. The apparatus of claim 14, wherein the position sensing means includes a track sensor having a plurality of segments defining a circular track and a movable element freely disposed in the track and influenced by gravity, and further comprising means at each said segment for detecting presence of the movable element when in proximity with said segment, whereby the track sensor detects orientation of the module relative to vertical.

16. The apparatus of claim 14, wherein the position sensing means includes a pendulum and means spaced around the module for detecting passage of the pendulum.

17. The apparatus of claim 14, wherein the position sensing means includes a side-looking apparatus having means sensitive to a physical parameter varying with orientation relative to the earth.

18. The apparatus of claim 17, wherein the physical parameter is infrared emission.

19. The apparatus of claim 1, comprising a two axis gyroscopic sensor and means sensing orientation of the module relative to vertical, said gyroscopic sensor and said means sensing orientation being connected to the control processor and the control processor monitoring pitch, yaw and rotational position periodically during at least one phase of a flight of the projectile weapon.

20. The apparatus of claim 1, wherein the position sensing means includes at least one rotational rate sensor having a resiliently bendable element subject to bending with inertial forces produced by rotation.

21. The apparatus of claim 14, wherein the position sensing means includes a pendulum on a pivot axis coincident with a longitudinal axis of the module, the pendulum having a mass defining a movable element disposed in a circular track having a plurality of segments, and further comprising means at each segment for sensing one of the position and rate of movement of the mass of pendulum, providing a track sensor for detecting at least one of instantaneous orientation of the module and instantaneous rate of roll.

22. The apparatus of claim 14, wherein the position sensing means includes an apparatus sensitive to a physical parameter varying with orientation relative to the earth.