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US 8,552,349 B1Granted
Projectile guidance kit
AssigneeInterstate Electronics Corporation
InventorSteven B. Alexander
Life of this patent
Estimating the term…
Abstract
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.
Claims16
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;
- and
- at least one of a battery or a capacitor configured to provide power prior to operation of the alternator.
9 more elements
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;
- and
- a guidance and control system configured to control the actuator based at least partly on a pre-programmed trajectory, spatial position, and rotational position.
4 more elements
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;
- and
- steering the projectile along a pre-programmed trajectory.
1 more element
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;
- and
- means for steering the projectile along a pre-programmed trajectory.
1 more element
Dependencies are inferred from the claim text.