An aerodynamically improved bullet mounted atop a bullet and fired from a discharge chamber of a gun includes a bullet having a rear portion and a front portion that, together, defines an interior area. A rod having a linear and elongate configuration is movable between a retracted configuration completely inside the interior area and an extended configuration partially extending forwardly of the bullet the rod being pushed downstream by the gas pressures of the discharged bullet itself.

An attitude control system includes one or more control moment gyro pairs, with gyros of individual of the pairs being counter-rotated to rotate the rotation axes of flywheels of the gyros of a gyro pair in opposite direction. The flywheels of a gyro pair may be in paddle configuration, with the rotation axes of the flywheels rotating in the counter-rotation through separate planes as the gyros are rotated. The rotation of the gyros of a gyro pair may be accomplished by coupling both of the gyros to a servo motor with suitable coupling gears, or by using independent servos for each gyro. The counter-rotation of gyros of an individual pair produces a resultant torque about a fixed global axis, such as the axis of a flight vehicle of which the attitude control system is a part. Further control may be accomplished for example by varying rotation speeds of the flywheels.

An aerodynamically improved bullet mounted atop a bullet and fired from a discharge chamber of a gun includes a bullet having a rear portion and a front portion that, together, defines an interior area. A rod having a linear and elongate configuration is movable between a retracted configuration completely inside the interior area and an extended configuration partially extending forwardly of the bullet the rod being pushed downstream by the gas pressures of the discharged bullet itself.

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.

An attitude control system includes one or more control moment gyro pairs, with gyros of individual of the pairs being counter-rotated to rotate the rotation axes of flywheels of the gyros of a gyro pair in opposite direction. The flywheels of a gyro pair may be in paddle configuration, with the rotation axes of the flywheels rotating in the counter-rotation through separate planes as the gyros are rotated. The rotation of the gyros of a gyro pair may be accomplished by coupling both of the gyros to a servo motor with suitable coupling gears, or by using independent servos for each gyro. The counter-rotation of gyros of an individual pair produces a resultant torque about a fixed global axis, such as the axis of a flight vehicle of which the attitude control system is a part. Further control may be accomplished for example by varying rotation speeds of the flywheels.

A method of controlling a gyroscopically-stabilized projectile, comprising a control system producing a control signal, a rotating aerodynamic shell, and a reaction mass system responsive to the control signal, the method comprising: imparting rotational and translational kinetic energy to induce gyroscopic stabilization of the projectile about a gyroscopic axis and a movement of the projectile along a flight path; interacting the shell with surrounding air while moving, to induce aerodynamic forces; generating the control signal from the control system; and altering a state of the reaction wheel system selectively in dependence on the control signal, to alter the flight path.

A projectile apparatus is provided that includes a projectile, a propellant, and optional components such as a wading, a sabot, and an intermediary device. The projectile can be fired through a barrel having a smooth bore. A sabot is provided that can include molded features, for example, a base portion and a plurality of petal portions defining, in-part, a volume for accommodating a projectile. The sabot and wadding can include molded features that control and direct gases produced by the propellant. The apparatus can convert gas pressure or gas velocity into a high rate of projectile spin. The projectile has long-range accuracy due to a high or sustainable velocity and high rate of spin.

Launching an aeronautical system can comprise applying force or energy to the system in connection with accelerating the system. Responsive to the force or energy, an element of the system can move along a defined path within the system. The system can comprise a drive that converts motion along the defined path into rotational motion. The drive can rotate a mass within the system, which can be supported by a gas bearing. The rotating mass can comprise the moving element, a different system element, or the entire system. The rotating mass can produce angular momentum and can support gyroscopic stabilization of the aeronautical system. Rotational energy can be selectively imparted to and transferred between system elements in connection with stabilization management. System elements can moderate the system's response to impulsive stimuli associated with rotation and acceleration. A gas bearing can support an external surface of the system during launch.

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.

A method of making a projectile apparatus is provided that includes making one or components of the apparatus using an additive manufacture technique such as 3-D printing or laser-aided additive manufacture. The projectile apparatus can have a projectile, a propellant, and one or more optional components such as a wading, a sabot, and an intermediary device. The projectile can be fired through a barrel having a smooth bore. Additive manufacture methods can be used that involve forming components from superalloys having nanoparticles incorporated therein. The projectile apparatus can convert gas pressure or gas velocity into a high rate of projectile spin. The projectile has long-range accuracy due to a high or sustainable velocity and high rate of spin.