The present disclosure provides a projectile with a self-contained internal chamber. Reaction of propellant inside the internal chamber can generate high pressure and the resultant exhaust gases can be used for projectile linear acceleration, rotational acceleration or other purposes. Torque can be produced by exhausting the pressure via radially placed, tangential nozzles or other outlets and can be configured to induce sufficient projectile spin to stabilize the projectile without the need for barrel rifling. The internal chamber may be separate or integral to the projectile itself. The projectile may include two or more chambers or compartments internal to the chambers. The disclosed projectile allows for higher pressures in the internal chamber than in the barrel and greater flexibility on pressure manipulation in the barrel and the projectile, allowing for a more efficient propellant combustion and manipulation of projectile characteristics such as muzzle and rotational speeds.

An aeromechanically stable sabot system that includes a center of gravity that is placed forward of an aerodynamic center of the aeromechanically stable sabot system when in steady-state flight. By placing the center of gravity forwards of the aerodynamic center, the sabot system exhibits positive longitudinal and directional stability. To illustrate, the sabot system and/or portions thereof will return to stable flight after being disturbed in pitch (vertically or about a transverse horizontal axis) or yaw (side to side or about a vertical axis) when traveling horizontally.

An aeromechanically stable sabot system that includes a center of gravity that is placed forward of an aerodynamic center of the aeromechanically stable sabot system when in steady-state flight. By placing the center of gravity forwards of the aerodynamic center, the sabot system exhibits positive longitudinal and directional stability. To illustrate, the sabot system and/or portions thereof will return to stable flight after being disturbed in pitch (vertically or about a transverse horizontal axis) or yaw (side to side or about a vertical axis) when traveling horizontally.

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.

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.

An aeromechanically stable sabot system that includes a center of gravity that is placed forward of an aerodynamic center of the aeromechanically stable sabot system when in steady-state flight. By placing the center of gravity forwards of the aerodynamic center, the sabot system exhibits positive longitudinal and directional stability. To illustrate, the sabot system and/or portions thereof will return to stable flight after being disturbed in pitch (vertically or about a transverse horizontal axis) or yaw (side to side or about a vertical axis) when traveling horizontally.

An aeromechanically stable sabot system that includes a center of gravity that is placed forward of an aerodynamic center of the aeromechanically stable sabot system when in steady-state flight. By placing the center of gravity forwards of the aerodynamic center, the sabot system exhibits positive longitudinal and directional stability. To illustrate, the sabot system and/or portions thereof will return to stable flight after being disturbed in pitch (vertically or about a transverse horizontal axis) or yaw (side to side or about a vertical axis) when traveling horizontally.

The present invention provides a thrust flow powered vehicle comprising a first thrust flow expeller for expelling a first thrust flow in a first direction, a second thrust flow expeller for expelling a second thrust flow in a second direction, the second direction being a different direction to the first direction but sharing a plane with the first direction, a thrust flow deflector surface at an angle to the plane of the first and second directions, and an outlet portion for providing an output thrust flow, such that, in use, the thrust flow deflector surface deflects at least a portion of both the first and second thrust flows to form the output thrust flow such that the output thrust flow has a component in the plane of the first and second directions, and a component out of that plane.

The present invention provides a thrust flow powered vehicle comprising a first thrust flow expeller for expelling a first thrust flow in a first direction, a second thrust flow expeller for expelling a second thrust flow in a second direction, the second direction being a different direction to the first direction but sharing a plane with the first direction, a thrust flow deflector surface at an angle to the plane of the first and second directions, and an outlet portion for providing an output thrust flow, such that, in use, the thrust flow deflector surface deflects at least a portion of both the first and second thrust flows to form the output thrust flow such that the output thrust flow has a component in the plane of the first and second directions, and a component out of that plane.

The present disclosure provides a projectile with a self-contained internal chamber. Reaction of propellant inside the internal chamber can generate high pressure and the resultant exhaust gases can be used for projectile linear acceleration, rotational acceleration or other purposes. Torque can be produced by exhausting the pressure via radially placed, tangential nozzles or other outlets and can be configured to induce sufficient projectile spin to stabilize the projectile without the need for barrel rifling. The internal chamber may be separate or integral to the projectile itself. The projectile may include two or more chambers or compartments internal to the chambers. The disclosed projectile allows for higher pressures in the internal chamber than in the barrel and greater flexibility on pressure manipulation in the barrel and the projectile, allowing for a more efficient propellant combustion and manipulation of projectile characteristics such as muzzle and rotational speeds.