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Apparatus and methods provide a guidance kit that can be attached to a projectile, such as screwed into a fuze well of an artillery round or a mortar round. A portion of the guidance kit is configured to spin constantly during flight. In the context of an artillery round that is shot from a rifled b

Apparatus and methods provide a guidance kit that can be attached to a projectile, such as screwed into a fuze well of an artillery round or a mortar round. A portion of the guidance kit is configured to spin constantly during flight. In the context of an artillery round that is shot from a rifled barrel, the direction of the spin torque is counter to the direction of the spin induced by the rifled barrel. Control surfaces are present in the portion of the guidance kit that spins constantly during flight. While the portion spins, the control surfaces are actuated to steer the projectile towards an intended target via, for example, GPS.

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1. An apparatus comprising: a threaded housing configured to fasten into a fuze well of a projectile for attachment;a nose assembly configured to mate with the threaded housing such that at least a first portion of the nose assembly is within an interior of the threaded housing and a second portion

1. An apparatus comprising: a threaded housing configured to fasten into a fuze well of a projectile for attachment;a nose assembly configured to mate with the threaded housing such that at least a first portion of the nose assembly is within an interior of the threaded housing and a second portion of the nose assembly is outside of the threaded housing, wherein the nose assembly is configured to revolve without despinning with respect to the threaded housing;one or more fixed spin fins coupled to the nose assembly, wherein the one or more fixed spin fins are configured to generate a torque during flight in angular direction opposite to an angular direction of a spin of the projectile;one or more antennas configured to receive Global Positioning System (GPS) satellite navigation signals, wherein the one or more antennas are attached to the nose assembly such that the one or more antennas revolve with the nose assembly and not with the projectile;a GPS receiver configured to determine spatial position and rotational position, wherein the GPS receiver is coupled to the one or more antennas;a voice coil actuator;movable fins coupled to the nose assembly, wherein the movable fins are configured to move based on actuation by the voice coil actuator for steering of the projectile;a guidance and control system configured to control the voice coil actuator based at least partly on a pre-programmed trajectory, spatial position, and rotational position;a fuze for triggering of the artillery round, wherein the fuze is disposed within the first portion of the nose assembly;an alternator configured generate electrical power during flight of the artillery round and is not configured to controllably brake the nose assembly relative to the threaded housing, wherein at least a portion of the alternator is disposed in the threaded housing and another portion is disposed in the nose assembly; andat least one of a battery or a capacitor configured to provide power prior to operation of the alternator. 2. The apparatus of claim 1, wherein a rate of revolution for the nose assembly during flight after initial spin up is between about 2 hertz to 30 hertz. 3. The apparatus of claim 1, further comprising a fuze disposed in the nose assembly for triggering of an explosive of the projectile. 4. The apparatus of claim 1, further comprising a configurable arming mechanism for the fuze. 5. An apparatus comprising: a housing configured to mount in a fuze well of a projectile for attachment;a nose assembly configured to mate with the housing such that at least a first portion of the nose assembly is within an interior of the housing and a second portion of the nose assembly is outside of the housing;one or more spin fins coupled to the nose assembly, wherein the one or more spin fins are configured to generate a torque during flight in an opposing direction to a direction of spin, if any, of the projectile, wherein the nose assembly is configured to revolve even during flight control;an actuator;one or more control surfaces coupled to the nose assembly, wherein the one or more control surfaces are configured to steer the projectile based on actuation by the actuator; anda guidance and control system configured to control the actuator based at least partly on a pre-programmed trajectory, spatial position, and rotational position. 6. The apparatus of claim 5, wherein the actuator comprises a voice coil actuator. 7. The apparatus of claim 6, wherein actuation of the voice coil actuator varies at least partly based on an angle of the nose assembly relative to a reference angle external to the projectile. 8. The apparatus of claim 5, wherein the nose assembly revolves during flight at a spin rate less than 30 Hz. 9. The apparatus of claim 5, wherein the one or more control surfaces are deflected in a first direction relative to the nose assembly when the nose assembly is at a first rotational position external to the projectile, and are deflected in a second direction opposite to the first direction when the nose assembly is at a second rotational position 180 degrees opposite to the first rotational position. 10. The apparatus of claim 5, further comprising a height of burst sensor for triggering of the fuze. 11. The apparatus of claim 5, further comprising: one or more antennas configured to receive satellite positioning system signals, wherein the one or more antennas are attached to the nose assembly such that the one or more antennas revolve with the nose assembly and not with the projectile; anda satellite positioning system receiver configured to determine spatial position and rotational position, wherein the satellite positioning system receiver is coupled to the one or more antennas, wherein the satellite positioning system receiver is configured to determine spatial position. 12. A method of controlling flight of a projectile, the method comprising: spinning a nose assembly via torque generated by one or more spin fins coupled to the nose assembly, wherein after launch and initial spin up, the nose assembly is spun continuously during flight, wherein the nose assembly comprises the one or more spin fins, a satellite positioning system receiver, one or more antennas for the satellite positioning system receiver, one or more control surfaces, and an actuator for the one or more control surfaces;actuating the one or more control surfaces to steer the projectile, wherein actuating is performed while the nose assembly is revolving without despinning the nose assembly to control the flight of the projectile; andsteering the projectile along a pre-programmed trajectory. 13. The method of claim 12, wherein the actuator comprises a voice coil actuator. 14. The method of claim 13, further comprising actuating the voice coil actuator at least partly based on an angle of the nose assembly relative to a reference angle external to the projectile. 15. The method of claim 12, further comprising: deflecting the one or more control surfaces in a first direction relative to the nose assembly when the nose assembly is at a first rotational position external to the projectile; anddeflecting the one or more control surfaces in a second direction opposite to the first direction when the nose assembly is at a second rotational position 180 degrees opposite to the first rotational position for steering of the projectile. 16. An apparatus for controlling flight of a projectile, the apparatus comprising: means for spinning a nose assembly via torque generated by one or more spin fins coupled to the nose assembly, wherein after launch and initial spin up, the nose assembly is spun continuously during flight, wherein the nose assembly comprises the one or more spin fins, a satellite positioning system receiver, one or more antennas for the satellite positioning system receiver, one or more control surfaces, and an actuator for the one or more control surfaces;means for actuating the one or more control surfaces to steer the projectile, wherein actuating is performed while the nose assembly is revolving without despinning the nose assembly to control the flight of the projectile; andmeans for steering the projectile along a pre-programmed trajectory.