A rocket propelled bullet assembly for increasing the effective range of a gun includes a shell casing that is positioned in a chamber of a gun and the shell casing has an open end. A first propellant is contained in the shell casing and the first propellant is ignited when the gun is fired. A bullet is positioned in the open end of the shell casing. The bullet is fired from the shell casing when the first propellant is ignited and the bullet is projected from the gun. A rocket unit is integrated into the bullet and the rocket unit fires when the bullet is fired from the shell casing. The rocket unit increases a velocity of the bullet when the bullet is traveling thereby increasing a range of the bullet.

The present invention relates to a bullet with an increased effective range. The bullet includes a front end portion (10) having a hemispherical shape, a recess portion (20) connected to a rear end of the front end portion (10) and having a curved surface that is recessed inward, an inclined portion (30) connected to a rear end of the recess portion (20) and inclined at a predetermined angle (A) with respect to a horizontal line, a stepped portion (40) connected to a rear end of the inclined portion (30) and inclined at a predetermined angle (A) with respect to the horizontal line, and fluid inducing grooves formed from the rear to a rear end surface of the bullet (1). Thus, when the bullet passes through underwater, super cavitation may be more effectively generated and maintained for even longer to significantly increase the effective range of the bullet.

A shutter mechanism for covering a wing's spreading opening formed in an airborne body and a method for covering such opening while implementing the shutter mechanism, wherein the shutter comprises at least one flap assembly, and wherein from the instant that a deployed wing of the airborne body passed and moved over it, it is biased by traction of at least one springy element to an angular motion around an axis, unto a condition where the flap component of the assembly is positioned so that it is substantially conformal to the outline of the outer surface of the fuselage of the airborne body and while it covers the opening through which the wing passed in its motion; and from an instant that the wing returned and connected to the flap component of the assembly, the flap is biased to an angular motion counter the spring, to the state that the wing returns and is relocated on its top surface.

A shutter mechanism for covering a wing's spreading opening formed in an airborne body and a method for covering such opening while implementing the shutter mechanism, wherein the shutter comprises at least one flap assembly, and wherein from the instant that a deployed wing of the airborne body passed and moved over it, it is biased by traction of at least one springy element to an angular motion around an axis, unto a condition where the flap component of the assembly is positioned so that it is substantially conformal to the outline of the outer surface of the fuselage of the airborne body and while it covers the opening through which the wing passed in its motion; and from an instant that the wing returned and connected to the flap component of the assembly, the flap is biased to an angular motion counter the spring, to the state that the wing returns and is relocated on its top surface.

Various embodiments of optimized subsonic projectiles are provided along with related methods. For example, one exemplary subsonic projectile can include an elliptical nose cone, a cylindrical body and a boattail with various design features that can be used in a subsonic ammunition cartridge where the subsonic projectile is stabile throughout at least a segment of a flight allowing for better accuracy, maintaining low drag, maximizing range and achieving desired performance while ensuring the projectile stays below the speed of sound and lowering a noise profile of projectile and a launcher firing the projectile.

Various embodiments of optimized subsonic projectiles are provided along with related methods. For example, one exemplary subsonic projectile can include an elliptical nose cone, a cylindrical body and a boattail with various design features that can be used in a subsonic ammunition cartridge where the subsonic projectile is stabile throughout at least a segment of a flight allowing for better accuracy, maintaining low drag, maximizing range and achieving desired performance while ensuring the projectile stays below the speed of sound and lowering a noise profile of projectile and a launcher firing the projectile.

A flight vehicle engine includes an isolator with a swept-back wedge to improve flow mixing. The wedge includes forward shock-anchoring locations, such as edges or rapidly-curved portions, that anchor oblique shocks in situations where the isolator has sufficient back pressure. The swept-back wedge may also create swept oblique shocks along its length. Boundary layer flow streamlines are diverted running parallel to or parallel but moving outward conically to the swept-wedge leading edge moving outboard and upward. The non-viscous flow outside the boundary layer is processed through the swept-back ramp shock and diverted outboard and upward as well. The outboard aft portion of the wedge at the sidewall intersection may also induce shocks and divert flow near the walls closer toward the walls and upward, and/or improve flow mixing.

Firearm projectiles with turbulence-inducing surfaces, firearm cartridges including the same, and associated methods. A firearm projectile comprises a projectile body and a turbulence-inducing surface at least substantially enclosing the projectile body. The firearm projectile is at least substantially spherical. The turbulence-inducing surface is configured to induce a drag crisis in a drag coefficient of the firearm projectile when the firearm projectile travels through air with a Reynolds number that is less than 300,000.

Firearm projectiles with turbulence-inducing surfaces, firearm cartridges including the same, and associated methods. A firearm projectile comprises a projectile body and a turbulence-inducing surface at least substantially enclosing the projectile body. The firearm projectile is at least substantially spherical. The turbulence-inducing surface is configured to induce a drag crisis in a drag coefficient of the firearm projectile when the firearm projectile travels through air with a Reynolds number that is less than 300,000.

A projectile has a front portion and a cylindrical portion. 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.