Projectile control actuation system and method of steering a projectile
A projectile incorporates one or more spoiler-tabbed spinning disks to effect flow around the projectile and thus impart steering forces and/or moments. The spoiler tabs may be deployed only during steering phases of travel thus minimizing the drag penalty associated with steering systems. The disks are driven by motors and informed and controlled by sensors and electronic control systems. The spoiler tabs protrude through the surface of the projectile only for certain angles of spin of the spinning disk. For spin-stabilized projectiles, the disks spin at substantially the same rate as the projectile, but the disks may function in fin-stabilized projectiles as well. Any number of such spinning flow effector disks may be incorporated in a projectile, with the manner of functional coordination differing slightly for even and odd numbers of disks.
1. A guidance system for a projectile comprising:
at least one spinning disk having an axle, the spinning disk comprising or being asymmetrically shaped to comprise at least one flow-effecting spoiler, the axle of the spinning disk being positioned within a projectile such that, by the rotation of the spinning disk, the spoiler is adapted to deploy so as to protrude from an outer surface of the projectile only for some angles of spin of the spinning disk so as to exert a steering force and/or moment on the projectile;
at least one sensor having a signal corresponding to a measurement of spin frequency and/or spin orientation of the projectile; and
a controller adapted to adjust the steering force and/or moment on the projectile based at least in part on the signal of the at least one sensor,
wherein the at least one spinning disk, the at least one sensor and the controller are comprised in a modular fuze kit adapted to be attached to a projectile.
2. The guidance system of claim 1 , wherein projectile comprises an even number of spinning disks each comprising or being asymmetrically shaped to comprise at least one flow-effecting spoiler, and the spoilers are deployed periodically by the spinning of the disks, and the orientation of the periodic deployment of the spoilers is such that each spoiler maximally deploys normal to a desired turning plane and one flow effector disk's phase is shifted positive and an opposite flow effector disk's phase is shifted negative resulting in a net steering force and/or moment on the projectile.
3. The guidance system of claim 1 , wherein the projectile exhibits a circular error probable (CEP) distance of less than 50 meters for projectile ranges greater than 18 kilometers.
4. The guidance system of claim 3 , wherein the controller further comprises a processor adapted to control the spin of the at least one spinning disk based at least in part on the at least one sensor signal by changing the phase and/or frequency of the spin of the at least one spinning disk.
5. The guidance system of claim 4 , further comprising a telemetry system adapted to transmit data between the guided projectile and a ground-based sensor system.
6. A method of guiding a projectile comprising:
spinning up at least one asymmetric spinning disk comprising or shaped to comprise a flow-effecting spoiler to substantially the same rotational speed as the spin of the projectile, the spinning disk being housed within the projectile and oriented normal to the direction of travel;
measuring with at least one sensor spin frequency and/or spin orientation of the projectile; and
adjusting, with a controller, the speed of the spin of the at least one spinning disk such that the flow-effecting spoiler is maximally deployed to protrude outside of the outer surface of the projectile during a desired phase of rotation of the projectile and a steering force or moment is exerted on the projectile based at least in part of the measured sensor spin frequency and/or spin orientation,
wherein the at least one asymmetric spinning disk, the at least one sensor and the controller are comprised in a modular fuze kit adapted to be attached to a projectile.
7. The method of claim 6 , wherein the controller further comprises a processor adapted to calculate the adjustment based at least in part on the measured spin frequency and/or spin orientation of the projectile.
8. The method of claim 6 , wherein the use of the method results in the projectile having a circular error probable (CEP) of less than 50 meters for projectile ranges greater than 18 kilometers.
9. The method of claim 6 , further comprising the step of transmitting data with a telemetry system between the guided projectile and a ground-based sensor system.
10. A guidance system for a projectile comprising;
at least one spinning disk having an axle, the spinning disk comprising or being asymmetrically shaped to comprise at least one flow-effecting spoiler, the axle of the spinning disk being positioned within a projectile such that, by the rotation of the spinning disk, the spoiler is adapted to deploy to protrude from an outer surface of the projectile only for some angles of spin of the spinning disk so as to exert a steering force and/or moment on the guided projectile;
at least one sensor having a signal corresponding to a measurement of spin frequency and/or spin orientation of the projectile;
a controller adapted to adjust the steering force and/or moment on the guided projectile; and
a telemetry system adapted to transmit data between the projectile and a ground-based sensor system.
11. The guidance system of claim 10 , wherein the projectile exhibits a circular error probable (CEP) distance of less than 50 meters for projectile ranges greater than 18 kilometers.
12. The guidance system of claim 10 , wherein the projectile comprises an even number of spinning disks each comprising or being asymmetrically shaped to comprise at least one flow-effecting spoiler, and the spoilers are deployed periodically by the spinning of the disks, and the orientation of the periodic deployment of the spoilers is such that each spoiler maximally deploys normal to a desired turning plane and one flow effector disk's phase is shifted positive and an opposite flow effector disk's phase is shifted negative resulting in a net steering force and/or moment on the guided projectile.
13. The guidance system of claim 10 , wherein the projectile comprises an odd number of spinning disks, three or greater, each comprising or being shaped to comprise at least one flow-effecting spoiler, and the spoilers are deployed periodically by the spinning of the disks, and the orientation of the periodic deployment of the spoilers is such that each spoiler maximally deploys normal to a desired turning plane and one flow effector disk's phase is shifted positive and an opposite flow effector disk's phase is shifted negative resulting in a net steering force and/or moment on the guided projectile.
14. The guidance system of claim 13 , wherein the controller further comprises a processor adapted to control the spin of the at least one spinning disk based at least in part on the measured spin frequency and/or spin orientation by changing the phase and/or frequency of the spin of the at least one spinning disk.
15. The guidance system of claim 14 , wherein the guidance system is adapted to operate to at least begin spinning the at least one spinning disk and perform measurements with the at least one sensor immediately after launch or firing of the projectile, but the at least one spinning disk is locked or braked within the projectile prior to launch or firing.
16. The guidance system of claim 15 , wherein the at least one spinning disk, the at least one sensor and the controller are comprised in a modular fuze kit adapted to be attached to a projectile.