초록 ▼

The disclosed system, device and method for guiding a hypersonic kinetic penetrator projectile (300) generally includes a kinetic penetrator body (110, 230) and a slip-over electronic guidance unit (120, 220), where the kinetic penetrator body slidably mounts through the slip-over electronic guidanc

The disclosed system, device and method for guiding a hypersonic kinetic penetrator projectile (300) generally includes a kinetic penetrator body (110, 230) and a slip-over electronic guidance unit (120, 220), where the kinetic penetrator body slidably mounts through the slip-over electronic guidance unit. Disclosed features and specifications may be variously controlled, adapted or otherwise optionally modified to improve accuracy and control of a hypersonic projectile. Exemplary embodiments of the present invention generally provide multi-use slip-over electronic guidance units for hypersonic kinetic penetrator projectiles in 105 mm and 120 mm munition rounds, surface-to-surface missiles, and air-to-surface missiles.

대표청구항 ▼

I claim: 1. A projectile guidance system, comprising: a detachable launch system defining an inner volume; a kinetic penetrator body at least partially enclosed within the inner volume of the detachable launch system; and a controllable slip-over guidance unit approximately forming a cylinder open

I claim: 1. A projectile guidance system, comprising: a detachable launch system defining an inner volume; a kinetic penetrator body at least partially enclosed within the inner volume of the detachable launch system; and a controllable slip-over guidance unit approximately forming a cylinder open on both ends, wherein: the slip-over guidance unit is enclosed within the inner volume of the detachable launch system, and the kinetic energy penetrator body longitudinally slidably mounts to the slip-over guidance unit through the cylinder, wherein exterior surface portion of the kinetic energy penetrator body engages an inner surface of the cylinder before the projectile is launched. 2. The projectile guidance system of claim 1, wherein the controllable slip-over guidance unit engages with the kinetic penetrator body via at least one of a taper and a flare. 3. The projectile guidance system of claim 1, wherein: the controllable slip-over guidance unit is stored in a forward portion of a rocket motor assembly; and the kinetic penetrator body is stored within an aft portion of the rocket motor assembly and is adapted to be slidably repositioned from the aft portion of the rocket motor assembly to the forward portion of the rocket motor assembly to engage the controllable slip-over guidance unit before launch. 4. The projectile guidance system of claim 1, wherein the controllable slip-over guidance unit comprises a transmit system, the transmit system comprising a linearly polarized transmit antenna system, a first transmitter coupled to the transmit antenna system for transmitting a first transmit signal at a first frequency, a second transmitter coupled to the transmit antenna system for transmitting a second transmit signal at a second frequency, wherein the first frequency is different from the second frequency, and the first transmit signal and the second transmit signal are in phase coherence. 5. The projectile guidance system of claim 1, wherein the system includes at least one of a divert charge mounted on the controllable slip-over guidance unit and a substantially moveable nose mounted on the kinetic penetrator body, wherein the movable nose is configured to pivot relative to the kinetic penetrator body. 6. The projectile guidance system of claim 5, wherein at least one of the moveable nose and the divert charge is actuated via at least one of a wireless and a wired communication. 7. The projectile guidance system of claim 6, wherein control signals are at least one of communicated from and processed by the controllable slip-over guidance unit. 8. The projectile guidance system of claim 1, wherein a millimeter wavelength wave emitter is carried in a rear portion of kinetic penetrator body. 9. The projectile guidance system of claim 1, wherein the kinetic penetrator body comprises at least one of tungsten, carbide steel, and depleted uranium. 10. The projectile guidance system of claim 1, wherein the kinetic penetrator body and the controllable slip-over electronic guidance unit are adapted for interchangeable placement inside of detachable launch systems of varying diameters. 11. The projectile guidance system of claim 10, wherein the varying diameters comprise a munition round of a first diameter and a rocket motor assembly of a second diameter. 12. A kinetic energy projectile device, comprising: a detachable exterior shell; a controllable slip-over electronic guidance unit forming a cylinder open on both ends with an inner surface, wherein the controllable slip-over electronic guidance unit is enclosed within the detachable exterior shell; a kinetic penetrator body disposed at least partially within the detachable exterior shell, wherein: the kinetic penetrator body longitudinally slidably mounts to the controllable slip-over electronic guidance unit through the cylinder of the controllable slip-over electronic guidance unit prior to the kinetic energy projectile device launching; and the controllable slip-over electronic guidance unit engages with the kinetic penetrator body via at least one of a locking taper and a flare; and at least one of a divert charge disposed on the controllable slip-over electronic guidance unit and a substantially moveable nose disposed on the kinetic penetrator body, wherein the moveable nose is configured to pivot relative to the kinetic penetrator body. 13. The kinetic energy projectile device of claim 12, wherein controllable slip-over electronic guidance unit comprises a transmit system, the transmit system comprising a linearly polarized transmit antenna system, a first transmitter coupled to the transmit antenna system for transmitting a first transmit signal at a first frequency, a second transmitter coupled to the transmit antenna system for transmitting a second transmit signal at a second frequency, wherein the first frequency is different from the second frequency, and the first transmit signal and the second transmit signal are in phase coherency. 14. The kinetic energy projectile device of claim 12, wherein the controllable slip-over electronic guidance unit further comprises a millimeter wavelength wave emitter. 15. The kinetic energy projectile device of claim 12, wherein the kinetic penetrator body and the controllable slip-over electronic guidance unit are adapted for interchangeable placement inside of detachable exterior shells of varying diameters. 16. The kinetic energy projectile device of claim 15, wherein the varying diameters comprise a munition round of a first diameter and a rocket motor assembly of a second diameter.