A system, apparatus and method for mitigating the shock front of a rocket or aerospace plane flying at hypersonic speeds while simultaneously distilling liquid chemical elements regeneratively from the ambient air by means of vortex inversion splines. The splines may additionally be tuned by geometry to function as both centripetal and/or isentropic thrust augmentation attribute and/or double-decker Joule-Thomson refrigeration means. Because of the stochastic stagnation flux that reaches into the absolute zero zone by means of precooling, a splined stochastically switched hypersonic nosecone may be constructively tuned into a complex Carnot refrigeration engine commanding both personal and enterprise liquid Helium distilling means with orders of magnitude efficacy gains over existing methods.

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.

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.

A projectile has a front portion, a divider and a cylindrical portion. The front portion has a wall defining an interior cavity, which is closed by the divider. The cylindrical portion comprises a cylindrical sidewall having an outer surface and an inner surface. The projectile also has a plurality of depressions in the cylindrical sidewall. The depressions have an outlet adjacent the second end, an inlet toward the first end and a neck area between the inlet and the outlet. A width of the inlet is smaller than a width of the outlet. The depressions at the neck area have a curved sidewall, but a generally straight sidewall between the neck area and the outlet. The surface of the depression extends at a ramp angle from the outer surface of the sidewall at the inlet of the depression toward the inner surface of the sidewall at the outlet.

A projectile has a front portion, a divider and a cylindrical portion. The front portion has a wall defining an interior cavity, which is closed by the divider. The cylindrical portion comprises a cylindrical sidewall having an outer surface and an inner surface. The projectile also has a plurality of depressions in the cylindrical sidewall. The depressions have an outlet adjacent the second end, an inlet toward the first end and a neck area between the inlet and the outlet. A width of the inlet is smaller than a width of the outlet. The depressions at the neck area have a curved sidewall, but a generally straight sidewall between the neck area and the outlet. The surface of the depression extends at a ramp angle from the outer surface of the sidewall at the inlet of the depression toward the inner surface of the sidewall at the outlet.

A projectile launching system can include a projectile launcher and a projectile. The projectile launcher can include at least one barrel, a projectile, a firing pin mechanism, an activator, and a power system. The barrel can extend along a longitudinal axis between first and second ends, with an exit port at the second end. The projectile can be positioned in the barrel and include primer, propellant, and a sub-projectile. The firing pin mechanism can be selectively project into the barrel to engage the primer, whereby the propellant is ignited and the projectile is launched out of the barrel. The activator can be engaged with the firing pin mechanism and engageable by a user to control the firing pin mechanism. The power system can rotate the barrel or the projectile as the firing pin mechanism is projecting into the barrel and engaging the primer of the projectile.

A range extension unit extends the range of a guided mortar bomb. The range extension unit includes a housing interface defining an internal cup that receives a rear portion of a guided mortar bomb, wherein the housing interface covers a rear portion of the mortar bomb. The housing interface, when coupled to the mortar bomb, collectively forms an aerodynamically shaped body with the mortar bomb. At least two deployable wings are attached to the housing interface, wherein the wings transition between a retracted state and a deployed state.

A range extension unit extends the range of a guided mortar bomb. The range extension unit includes a housing interface defining an internal cup that receives a rear portion of a guided mortar bomb, wherein the housing interface covers a rear portion of the mortar bomb. The housing interface, when coupled to the mortar bomb, collectively forms an aerodynamically shaped body with the mortar bomb. At least two deployable wings are attached to the housing interface, wherein the wings transition between a retracted state and a deployed state.

An ordnance for air-borne delivery to a target under remotely controlled in-flight navigation. In one embodiment, self-powered aerial ordnance includes upper and lower cases. A plurality of co-axial, deployable blades is powered by a motor positioned in the upper case. When deployed, the blades are rotatable about the upper case to impart thrust and bring the vehicle to a first altitude above a target position. An explosive material and a camera are positioned in a lower case which is attached to the upper case. The camera generates a view along the ground plane and above the target when the ordinance is in flight. When the vehicle is deployed it is remotely controllable to deliver the vehicle to the target to detonate the explosive at the target. The ordnance may drop directly on a target as a bomb does.

An ordnance for air-borne delivery to a target under remotely controlled in-flight navigation. In one embodiment, self-powered aerial ordnance includes upper and lower cases. A plurality of co-axial, deployable blades is powered by a motor positioned in the upper case. When deployed, the blades are rotatable about the upper case to impart thrust and bring the vehicle to a first altitude above a target position. An explosive material and a camera are positioned in a lower case which is attached to the upper case. The camera generates a view along the ground plane and above the target when the ordinance is in flight. When the vehicle is deployed it is remotely controllable to deliver the vehicle to the target to detonate the explosive at the target. The ordnance may drop directly on a target as a bomb does.