Steerable rotating projectile
OwnerSteven M. Hoffberginventor
Life of this patent
Estimating the term…
Abstract
A method for controlling a flying projectile which rotates during flight, comprising: determining an angle of rotation of an inertial mass spinning about an axis during flight; and controlling at least one actuator for altering at least a portion of an aerodynamic structure, selectively in dependence on the determined angle of rotation and a control input, to control aerodynamic forces during flight. An aerodynamic surface may rotate and interact with surrounding air during flight, to produce aerodynamic forces. A sensor determines an angular rotation of the spin during flight. A control system, responsive to the sensor, produces a control signal in dependence on the determined angular rotation. An actuator selectively alters an aerodynamic characteristic of the aerodynamic surface in response to the control signal.
Claims20
A projectile guidance system, comprising:
- an angular rotation sensor, configured to determine a phase of rotation about an inertial mass rotational axis of a rotating inertial mass of a gyroscopically-stabilized projectile;
- a radio frequency receiver, configured to receive a wireless radio frequency control signal during flight of the gyroscopically-stabilized projectile;
- and
- an automated controller, configured to generate a rotational actuator control signal output, to synchronize a phase of rotation of a rotatable actuator, which rotates about a rotatable actuator axis having an orthogonal component with respect to the inertial mass rotational axis, with respect to the phase of rotation of the rotating inertial mass of the gyroscopically-stabilized projectile about the rotational axis, and dependent on the wireless radio frequency control signal.
A projectile guidance method, comprising:
- determining a phase of rotation about an inertial mass rotational axis of a rotating inertial mass of a gyroscopically-stabilized projectile;
- receiving a wireless radio frequency control signal during flight of the gyroscopically-stabilized projectile;
- and
- generating a rotational actuator control signal output of an automated control system, to synchronize a phase of rotation of a rotatable actuator about a rotatable actuator axis, with respect to the determined phase of rotation of the gyroscopically-stabilized projectile about the inertial mass rotational axis, perturbed dependent on the wireless radio frequency control signal, wherein the rotatable actuator axis is not parallel to the inertial mass rotational axis.
A guidance system for a rotating projectile, comprising:
- a sensor, configured to generate a sensor signal representing a phase of a rotation about a rotational axis of a rotating projectile;
- a control signal input, configured to define a control signal during rotating flight of the rotating projectile;
- and
- an automated control, configured to generate a rotational actuator control signal output, adapted to synchronize a phase of rotation of a rotatable actuator with respect to a phase of rotation of the rotating projectile, selectively dependent on the control signal input and a feedback signal, wherein the rotational actuator rotates about an axis non-parallel to the rotational axis of a rotating projectile.
Dependencies are inferred from the claim text.