Various embodiments of optimized subsonic projectiles are provided. 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. 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 cover 10 and method for protecting a missile 15 with stowed wings 20 and connected to a vessel carrying it. The cover 10 includes a spoiler shaped front part 25 for covering a gap between the wings 20 of the missile 15 and the fuselage of the missile 15 for minimizing aerodynamic forces.

A projectile includes a component that is highly reflective and configured to reveal the projectile's trajectory when the projectile is fired from a gun and electromagnetic radiation is directed toward the projectile. With the reflective component, one can more easily limit the visibility of the projectile to areas from where the projectile was fired because the reflective component is passive, not active. As the projectile moves down range, the areas behind the projectile are typically where a shooter and/or spotter for the shooter are located, not where an enemy combatant is located. Thus, the trajectory of the projectile is revealed to the people who can use the information to adjust their fire, and remains hidden from the people who could use the information to locate the shooter.

A hollow spherical projectile is constructed from a plurality of curved structural segments and has a plurality of openings. The projectile can be fired by a conventional paintball marker with a high degree of ballistic accuracy. The projectile is reusable and is fabricated from a flexible and resilient material. The outer surface of the projectile exhibits low friction, achieved by the material itself or by having a low friction coating applied. The projectile possess and transmits less kinetic energy than a conventional paintball and therefore inflicts less pain and damage upon impact. Fabrication can be accomplished by 3D printing, or molding as a single seamless piece, or as a plurality of pieces which are then assembled.

A hollow spherical projectile is constructed from a plurality of curved structural segments and has a plurality of openings. The projectile can be fired by a conventional paintball marker with a high degree of ballistic accuracy. The projectile is reusable and is fabricated from a flexible and resilient material. The outer surface of the projectile exhibits low friction, achieved by the material itself or by having a low friction coating applied. The projectile possess and transmits less kinetic energy than a conventional paintball and therefore inflicts less pain and damage upon impact. Fabrication can be accomplished by 3D printing, or molding as a single seamless piece, or as a plurality of pieces which are then assembled.

The method and apparatus for a remote weapon station or incorporated into manually-aimed weapons. The methodology requires use of a muzzle velocity sensor that refines the aiming of the second and subsequent fires or volleys fired from weapon systems. When firing the first volley a weapon uses an estimated velocity and, at firing, the muzzle velocity of a projectile is measured. When firing the second volley a weapon's fire control calculates an aiming point using the measured velocity of the first volley.

A guided missile with a sleeve-shaped missile body, at least one engine for producing forward thrust, at least one flight direction control device, and at least one aerodynamic extension. The least one flight direction control device is rotatably mounted to a top area and/or a bottom area of the sleeve-shaped missile body for adjusting a flight direction of the guided missile. The least one aerodynamic extension comprises an aerodynamic cross-sectional shape that is arranged on a left-hand side and/or a right-hand side of the sleeve-shaped missile body.

A composite structural component is disclosed. The composite structural component can include a lattice structure, a casing disposed about at least a portion of the lattice structure, and a skin adhered to a surface of the casing. The lattice structure and the casing can be formed of a polymeric material and the skin can be formed of a metallic material. A method of manufacturing a composite structural component is disclosed. The method can include creating a casing of a polymeric material and creating a lattice structure of a polymeric material disposed about at least a portion of the casing. The method can include sealing the porosity of the casing and lattice structure. The method can include adhering a skin of a metallic material to at least a portion of the casing. At least one of creating a lattice structure and creating a casing comprises utilizing an additive manufacturing process.

An effector having an extendible range and a method for extending the range of an effector includes using an axially translatable center body that is movable from a stowed position, in which the center body is stowed in an outer body of the effector, to a deployed position in which the center body extends out of the outer body to extend the axial length of the effector. The effector includes a ramjet assembly and the subsystems of the effector are contained in the center body. The movement of the center body exposes radially positioned ramjet fuel in the outer body, such that the air entering the ramjet inlet may be heated by combusting the air with the fuel for additional fuel and propulsion of the effector.