A unitary radome layer assembly is provided and includes a first nanocomposite formulation and a second nanocomposite formulation. The first and second nanocomposite formulations are provided together in a unitary radome layer with respective distribution gradients.

A unitary radome layer assembly is provided and includes a first nanocomposite formulation and a second nanocomposite formulation. The first and second nanocomposite formulations are provided together in a unitary radome layer with respective distribution gradients.

A nosecone apparatus for hypersonic aircraft, rocket or missiles using a method for the mitigation of the created the shock front of a rocket or aerospace plane flying at hypersonic speeds by using nosecone splines to create both centripetal and isentropic airflows in conjunction with regeneratively cooling the nosecone structure.

A nosecone apparatus for hypersonic aircraft, rocket or missiles using a method for the mitigation of the created the shock front of a rocket or aerospace plane flying at hypersonic speeds by using nosecone splines to create both centripetal and isentropic airflows in conjunction with regeneratively cooling the nosecone structure.

A cartridge comprising an elongate rifle bullet with a plurality of circumferential grooves having overmolded polymer therein defining embedded polymer rings. The cartridge further having a case and propellant. The polymer rings have an outer surface that is flush with, that is, conforming to the outer surface of the body. The polymer may have be selected to have a favorable coefficient of friction with respect to the barrel. The bands offering reduction of the metal to metal contact between the bullet and the barrel while not diminishing the ballistic coefficient of the bullet.

There is provided a projectile, a system and a related method of operation of a projectile comprising: a front ogive section; an aft section; and a control module; wherein the front ogive section is rotatably connected to the aft section by a coupling device, the front ogive section further comprising an asymmetric surface such that the asymmetric surface exerts an imbalance upon the projectile, where in use, the angular rotation of the front ogive section can be selectively adjusted relative to the aft section by commands from the control module to the coupling device influencing a helical trajectory of the projectile in flight thereby causing a change in direction thereby steering the projectile towards a target.

There is provided a projectile, a system and a related method of operation of a projectile comprising: a front ogive section; an aft section; and a control module; wherein the front ogive section is rotatably connected to the aft section by a coupling device, the front ogive section further comprising an asymmetric surface such that the asymmetric surface exerts an imbalance upon the projectile, where in use, the angular rotation of the front ogive section can be selectively adjusted relative to the aft section by commands from the control module to the coupling device influencing a helical trajectory of the projectile in flight thereby causing a change in direction thereby steering the projectile towards a target.

A propulsionless munition configured to be launched from a hypersonic aerial includes a munition body that is free of any propulsion system for producing thrust. The munition body includes a forward section including a radome assembly and an aft section including a control system. The radome assembly includes a nose radome and a frangible radome cover disposed over the nose radome for shielding the nose radome from high temperatures resulting from aerodynamic heating at hypersonic speeds. The frangible radome cover is detachable from the nose radome upon detection by the control system of a predetermined threshold comprising at least one of a predetermined speed, a predetermined altitude, and a predetermined temperature.

A propulsionless munition configured to be launched from a hypersonic aerial includes a munition body that is free of any propulsion system for producing thrust. The munition body includes a forward section including a radome assembly and an aft section including a control system. The radome assembly includes a nose radome and a frangible radome cover disposed over the nose radome for shielding the nose radome from high temperatures resulting from aerodynamic heating at hypersonic speeds. The frangible radome cover is detachable from the nose radome upon detection by the control system of a predetermined threshold comprising at least one of a predetermined speed, a predetermined altitude, and a predetermined temperature.

A projectile enables axial assembly and precise angular alignment of cylindrical or ogival sections of the projectile without interfering with internal parts spanning those sections. The projectile includes a turnbuckle design that minimizes Outer Mold Line (OML) transitions and maintains structural integrity. Advantageously, the turnbuckle allows surface mounted antennas and internal electronics to span structural sections of the projectile. The minimal OML produces less turbulence and drag. Finally, the turnbuckle is structurally robust for gun launched applications.