A tail portion for a fin-stabilized projectile includes at least two deployable fins, which are inclined. The fins are arranged in at least two sections, which are arranged adjacent to another in the axial direction.

The invention relates to a test and/or practice ammunition having at least one projectile with a projectile head and a fin which can be found at the end of the projectile for example or a projectile with a projectile base and a projectile ogive. A cartridge shell is used to receive a drive and has a shell base, wherein an interface is attached in or on the shell base. The test and/or practice ammunition is characterized by a programmable fuze which is arranged in the projectile head or the projectile ogive. The projectile head/projectile ogive is equipped with at least one fuze amplifier and an electronic fuze system and optionally a separating charge.

The invention relates to a test and/or practice ammunition having at least one projectile with a projectile head and a fin which can be found at the end of the projectile for example or a projectile with a projectile base and a projectile ogive. A cartridge shell is used to receive a drive and has a shell base, wherein an interface is attached in or on the shell base. The test and/or practice ammunition is characterized by a programmable fuze which is arranged in the projectile head or the projectile ogive. The projectile head/projectile ogive is equipped with at least one fuze amplifier and an electronic fuze system and optionally a separating charge.

A concatenated annular swing-wing tandem lift enhancer (CASTLE) is provided for augmenting aeronautical lift to a canister-launched missile. The CASTLE includes fore and aft housing sections and pluralities of mainstays, airfoils, wing grapples and tension supports. The fore and aft housing sections are disposed circumferentially around the missile along a longitudinal axis of symmetry. The front and rear mainstays are disposed angularly along each housing section. The airfoils stowed circumferentially around each the housing section. Each airfoil has an outer camber surface and an inner arc surface that provides leading and trailing edges ending at port and starboard tips. The wing grapples disposed on the inner arc surface. The supports connect the mainstays with corresponding the grapples such that the airfoils deploy radially outward and swing such that each leading edge faces forward in relation to the longitudinal axis. The supports can be flexible lanyards or else rigid struts.

A concatenated annular swing-wing tandem lift enhancer (CASTLE) is provided for augmenting aeronautical lift to a canister-launched missile. The CASTLE includes fore and aft housing sections and pluralities of mainstays, airfoils, wing grapples and tension supports. The fore and aft housing sections are disposed circumferentially around the missile along a longitudinal axis of symmetry. The front and rear mainstays are disposed angularly along each housing section. The airfoils stowed circumferentially around each the housing section. Each airfoil has an outer camber surface and an inner arc surface that provides leading and trailing edges ending at port and starboard tips. The wing grapples disposed on the inner arc surface. The supports connect the mainstays with corresponding the grapples such that the airfoils deploy radially outward and swing such that each leading edge faces forward in relation to the longitudinal axis. The supports can be flexible lanyards or else rigid struts.

A frangible detent pin comprising a base a pin head and an elastic member. The base is configured to be secured within a bore. The pin head and the base are interconnected through a frangible connection. The elastic member is configured to bias the pin head away from the base. The frangible detent pin has a rigid stage in which the pin head is rigidly positioned relative to the base and a spring-loaded stage in which the pin head is moveable relative to the base under a compression load between pin head and the base. The frangible detent pin is configured to transition from the rigid stage to the spring-loaded stage in response to the compression load exceeding a predetermined threshold sufficient to cause the frangible connection to fail.

The present disclosure relates to a bi-directional wing unfolding mechanism for unfolding and locking wings of air vehicle during deployment. The mechanism comprises one or more flexible member to enable lift and rotational movements of the wings of air vehicle about one or more axis. The mechanism also comprises one or more pairs of lock pins to lock undesired lift and rotational movement of the wings after the desired movements, thereby enabling minimum roll disturbance and near synchronous locking of all wings. Further, the mechanism also enables folding and unfolding of the wings having higher aspect ratio by folding and unfolding at mutually perpendicular axes. The mechanism also enables lower drag and results in high aerodynamic performance, low roll rate and better flight trajectory.

The present disclosure relates to a bi-directional wing unfolding mechanism for unfolding and locking wings of air vehicle during deployment. The mechanism comprises one or more flexible member to enable lift and rotational movements of the wings of air vehicle about one or more axis. The mechanism also comprises one or more pairs of lock pins to lock undesired lift and rotational movement of the wings after the desired movements, thereby enabling minimum roll disturbance and near synchronous locking of all wings. Further, the mechanism also enables folding and unfolding of the wings having higher aspect ratio by folding and unfolding at mutually perpendicular axes. The mechanism also enables lower drag and results in high aerodynamic performance, low roll rate and better flight trajectory.

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 optical seeker assembly having an optical detector located within the wing or canards of a precision guided munition. The optical seeker provides on-wing processing that generates low bandwidth detection data that can be easily transferred to a primary CPU located within the main body or fuselage of the precision guided munition. The on-wing processing reduces or eliminates the need for optical fibers extending between an optical wedge and an optical detector to reduce the likelihood of optical fibers from impeding in the mechanical deployment of the wing and reduces losses. The reduction or elimination of optical fibers between the optical wedge and the optical detector further enables the optical detection assembly to have a higher pixel ratio or transmitting raw data between the wedge and the detector by sending sampled detection data across a low bandwidth link to a CPU in the main body.