A method of improving optical characteristics of an optical window operating in a flow of fluid and having first and second panes of optically transmissive material—each having an edge adjacent to, parallel with, and at least partially coextensive with each other—is described herein. The method includes inserting a thermally conductive blade between two adjacent edges of the first and second panes of optically transmissive material; and lifting an adverse flow stagnation zone forward of the optical window by protruding the thermally conductive blade into the flow of fluid from an outer surface of the panes of the optical window.

A method of improving optical characteristics of an optical window operating in a flow of fluid and having first and second panes of optically transmissive material—each having an edge adjacent to, parallel with, and at least partially coextensive with each other—is described herein. The method includes inserting a thermally conductive blade between two adjacent edges of the first and second panes of optically transmissive material; and lifting an adverse flow stagnation zone forward of the optical window by protruding the thermally conductive blade into the flow of fluid from an outer surface of the panes of the optical window.

A bullet having a front unit and a rear unit, the front unit adapted to house the rear unit is provided. The front unit has a fragmented section, a cavity wall section, and a separation ring. The separation ring being angled forward or rearward with respect to the center of the bullet or with respect to the outermost edge of the bullet and being disposed on the front unit between the fragmented section and the cavity wall section.

A device is disclosed for deflating a gas cavity about a projectile formed upon entry of the projectile into a liquid. The device can include a wall coupleable with a body operable as a projectile and defining an exterior and an interior space. The wall can be oriented toward a trailing end relative to a leading end defined by the body. The device can also include at least one inlet to facilitate gas flow from the exterior to the interior space. An outlet can facilitate gas flow from the interior space to the exterior and can be oriented toward the trailing end relative to the at least one inlet. Upon entry of the body and the wall into a liquid and formation of a gas cavity about a portion of the body and the wall, the at least one inlet can be located within the gas cavity and the outlet can be located outside the gas cavity, such that gas flows from the exterior through the at least one inlet to the interior space, and from the interior space through the outlet to the exterior to deflate the gas cavity.

A device is disclosed for deflating a gas cavity about a projectile formed upon entry of the projectile into a liquid. The device can include a wall coupleable with a body operable as a projectile and defining an exterior and an interior space. The wall can be oriented toward a trailing end relative to a leading end defined by the body. The device can also include at least one inlet to facilitate gas flow from the exterior to the interior space. An outlet can facilitate gas flow from the interior space to the exterior and can be oriented toward the trailing end relative to the at least one inlet. Upon entry of the body and the wall into a liquid and formation of a gas cavity about a portion of the body and the wall, the at least one inlet can be located within the gas cavity and the outlet can be located outside the gas cavity, such that gas flows from the exterior through the at least one inlet to the interior space, and from the interior space through the outlet to the exterior to deflate the gas cavity.

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 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 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.

A ball joint gimbal (BJG) seeker assembly is provided and includes a back shell, a retaining system disposed to urge the seeker ball toward the back shell and a piezoelectric ultrasonic motor and sensor system arrayed between the seeker ball and the back shell. The piezoelectric ultrasonic motor and sensor system is pre-loaded by the retaining system and configured to controllably drive an angular orientation of the seeker ball.

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.