Abstract: Methods and apparatus for projectile systems according to various aspects of the present invention comprise a projectile attached to an auxiliary control system. The auxiliary control system may include a control system and a transverse propulsion system. The control system controls the trajectory of the projectile system, for example by activating the transverse propulsion system to adjust the trajectory.

Abstract: A projectile reconfigures in flight from a launch configuration, in which the center of gravity is aft of the center of pressure, to a flight configuration, in which the center of gravity is forward of the center of pressure. The projectile includes a forward portion and an aft portion, and the reconfiguration involves movement of at least part of one of the portions relative to the other portion. The projectile may have an overall substantially conical shape when in the launch configuration. The forward portion may include a substantially conical nose, and a cylindrical central body attached to the nose. In the launch configuration, at least part of the central body may be located within a hollow in a base of the aft portion. The base may be slidable relative to the central body.

Abstract: A projectile reconfigures in flight from a launch configuration, in which the center of gravity is aft of the center of pressure, to a flight configuration, in which the center of gravity is forward of the center of pressure. The projectile includes a forward portion and an aft portion, and the reconfiguration involves movement of at least part of one of the portions relative to the other portion. The projectile may have an overall substantially conical shape when in the launch configuration. The forward portion may include a substantially conical nose, and a cylindrical central body attached to the nose. In the launch configuration, at least part of the central body may be located within a hollow in a base of the aft portion. The base may be slidable relative to the central body.

Abstract: A 2-D correction system uses intermittent deployment of aerodynamic surfaces to control a spin or fin stabilized projectile in flight; correcting both crossrange and downrange impact errors. Intermittent surface deployment develops rotational moments, which create body lift that nudge the projectile in two-dimensions to correct the projectile in its ballistic trajectory. In low spin rate projectiles (“fin stabilized”), the rotational moment directly produces the body lift that moves the projectile. In high spin rate projectiles (“spin stabilized”), the rotational moment creates a much larger orthogonal precession that in turn produces the body lift that moves the projectile. The aerodynamic surfaces are suitably deployed over multiple partial roll cycles at precise on (deployed) and off (stowed) positions in the cycle to nudge the projectile up or down range or left or right cross range until the desired ballistic trajectory is restored.

Abstract: The disclosed system, device and method for providing a multi-mode munition generally includes a modular projectile assembly having an aft module suitably configured for mechanical and electrical engagement with a forward module. The aft module generally provides a common assembly for engagement with a variety of forward modules as well as engagement with cartridge casings of various calibers. Disclosed features and specifications may be suitably controlled, adapted or otherwise optionally modified to improve optimization of artillery projectiles for a specific role. Exemplary embodiments of the present invention generally provide munition cartridges that may be augmented in the field with the utilization of specialized forward modules.

Abstract: A projectile, such as a mortar projectile, includes a self-discarding or self-consumable propelling charge holder. A self-discarding propelling charge holder is made up of multiple segments. The propelling charge holder is maintained in place during launch by an igniter holder, and by folding fins of the projectile. The propelling charge increments are consumed during the launch process. After launch, as the folding fins deploy, the segments of the propelling charge holder separate from each other and from the remainder of the projectile, and the igniter holder is forcibly removed from the propelling charge holder segments. Alternatively, the propelling charge holder may be self-consumable, being made of a material that is consumed along with the propelling charge increments.

Abstract: A deployment mechanism (414) in combination with a missile (10), guided projectile (410) or other ordnance that automatically pivots and rotates a fin (412) from a stowed orientation to a deployed orientation. The deployment mechanism (414) includes a tubular cam (434) having a retention mechanism (455) that retains the fin (412) simply and reliably in the stowed orientation. The tubular cam also guides the fin (412) quickly to the deployed orientation.

Abstract: A projectile, such as a mortar projectile, includes a self-discarding or self-consumable propelling charge holder. A self-discarding propelling charge holder is made up of multiple segments. The propelling charge holder is maintained in place during launch by an igniter holder, and by folding fins of the projectile. The propelling charge increments are consumed during the launch process. After launch, as the folding fins deploy, the segments of the propelling charge holder separate from each other and from the remainder of the projectile, and the igniter holder is forcibly removed from the propelling charge holder segments. Alternatively, the propelling charge holder may be self-consumable, being made of a material that is consumed along with the propelling charge increments.

Abstract: A deployment mechanism (414) in combination with a missile (10), guided projectile (410) or other ordnance that automatically pivots and rotates a fin (412) from a stowed orientation to a deployed orientation. The deployment mechanism (414) includes a tubular cam (434) having a retention mechanism (455) that retains the fin (412) simply and reliably in the stowed orientation. The tubular cam also guides the fin (412) quickly to the deployed orientation.

Abstract: A tacital base for a guided projectile includes a base structure, and an adaptor structure for securing the base structure to a forward section of the projectile. The base further includes a plurality of fin slots. A plurality of deployable fins are pivotally mounted to the base structure and supported for movement between a stowed position and a deployed position.

Abstract: A tactical base for a guided projectile includes a base structure, and an adaptor structure for securing the base structure to a forward section of the projectile. The base further includes a plurality of fin slots. A plurality of deployable fins are pivotally mounted to the base structure and supported for movement between a stowed position and a deployed position.

Abstract: A missile or projectile tail section includes an outflow device and a number of deployable fins. The outflow device may be a base bleed device that includes a slow-burning propellant which fills the vacuum created by the projectile's motion through the air. Use of the outflow device may allow the projectile range to be extended by up to 20%. The fins are stowed canted relative to planes that include the axis of the tail section. By canting or tilting the fins relative to the axis of the tail section, increased space is made in the tail section for the outflow device. Although the fins are stowed canted relative to the tail section, they may be configured so as to be deployed such that the axis of the tail section is substantially within the planes of the fins.

Abstract: A tactical base for a guided projectile includes a base structure, and an adaptor structure for securing the base structure to a forward section of the projectile. The base further includes a plurality of fin slots, with a plurality of insert structures fitted into corresponding ones of the fin slots. A plurality of deployable fins are pivotally mounted to the base structure and supported within the insert structures for movement between a stowed position and a deployed position.

Abstract: A tactical base for a guided projectile includes a base structure, and an adaptor structure for securing the base structure to a forward section of the projectile. The base further includes a plurality of fin slots, with a plurality of insert structures fitted into corresponding ones of the fin slots. A plurality of deployable fins are pivotally mounted to the base structure and supported within the insert structures for movement between a stowed position and a deployed position.

Abstract: The present invention 10 discloses a sanitizing toothbrush holder comprising a container 12 having at least a pair of compartments 32 therein for receiving removable platforms 26 upon which the toothbrushes 18 rest. The platforms 26 are connected by downwardly extending rod-like members 44 to a closure means or lid 24 of the container. The closure means 24 is connected to and operates on a central post 40 which slidably operates inside a central aperture 46 of the container. Further, a frame-like member 28 is provided to rest on pin members 30 disposed on the members 44 which has the purpose of maintaining the toothbrush handles 18 on the platforms 26 when the entire mechanism is removed from container 12. Embodiments are shown adapted for use with two to four toothbrushes 18.