Abstract: A guided projectile may include a projectile body, an inertial measurement unit disposed within the projectile body, one or more control surfaces extendible from the projectile body, and a controller which controls the one or more control surfaces in response, at least in part, to measurement data received from the inertial measurement unit.

Abstract: A guided projectile may include a projectile body. An inertial measurement unit may be disposed within the projectile body, the inertial measurement unit including sensors to measure motion parameters relative to first, second, and third mutually orthogonal axes. Each of the first, second, and third mutually orthogonal axes may form an oblique angle with a longitudinal axis of the projectile body. A controller may be configured to control a trajectory of the guided projectile in response, at least in part, to measurement data received from the inertial measurement unit.

Abstract: A guidance system according to various aspects of the present invention operates in conjunction with a suite of different ordnance delivery devices. In one embodiment, the guidance system comprises an interface configured to attach to the ordnance delivery devices in the suite, such as via the fuze well. The guidance system may further include a control system adapted to attempt to establish communications with a subsystem of the ordnance delivery device and operate the guidance system as a standalone guidance system if the attempt fails. The guidance system may further include a control surface interchangeably attachable, for example via an interchangeable control surface module.

Abstract: A method of modifying a projectile includes removing material from an aft end of the projectile, and coupling a device to the aft end. The method may be used to convert a spin-stabilized projectile into a fin stabilized projectile, by modifying the aft end of a spin-stabilized projectile to accept a fin kit. The modifying may involve removing material with lathe, and may include forming external threads on the aft end that may engage corresponding internal threads on the device, to effect the coupling of the device to the aft end. The modification method allows versatility in employing projectiles, including existing stocks of projectiles. In particular the method allows spin-stabilized projectiles to be converted to more accurate fin-stabilized projectiles.

Abstract: A gun fired projectile includes a rocket motor housing including a pressure chamber and an exhaust nozzle. A plurality of propellant cells are positioned within the pressure chamber. The rocket motor propellant is mechanically supported during the severe gun fire event. This support may take several forms, each of which is discussed herein. The projectile further includes a support structure including one or more supports: wherein each of the one or more supports is engaged with the rocket motor housing. Each of the one or more supports is engaged with one propellant cell of the plurality of propellant cells, and each of the one or more supports suspends an individual propellant cell from the remainder of the plurality of propellant cells. All of these approaches provide the opportunity to tailor the performance of the rocket motor by combining a combination of propellant formulations and geometries to optimize the projectile performance.

Abstract: Methods and apparatus for delivering a missile may operate in conjunction with a missile comprising an outer skin. The missile may be configured in a closed position and an open position. In the open position, an aperture is opened in the outer skin, for example to supply air to an air-breathing engine. In the closed position, the aperture is closed.

Abstract: A projectile has filler material placed between an outer surface of its fuselage, and fins that are hingedly coupled to the fuselage. The filler material fills space that otherwise would be occupied by pressurized gases. Such pressurized gases could cause undesired outward force against the projectile fins during launch of the projectile from a launch tube or gun, such as when pressure outside the fins is suddenly removed, as in when the projectile passes a muzzle brake in the launch tube. The filler material may be any of a variety of lightweight solid materials, such as suitable plastics or closed cell foams. The filler material prevents pressurized gases from entering at least some of the space between the fins and the outer fuselage surface. When the fins deploy after the projectile emerges from the launch tube the filler material pieces fall away harmlessly.

Abstract: A deployment system is provided for utilization onboard an airborne object including a deployable element. In one embodiment, the deployment system includes a circumferential restraint and a release mechanism mounted to the airborne object. The circumferential restraint is disposed at least partially around the airborne object in a constraining position wherein the circumferential restraint prevents deployment of the deployable element. The release mechanism normally resides in a first position in which the release mechanism maintains the circumferential restraint in the constraining position. The release mechanism is movable to a second position to release the circumferential restraint from the constraining position and permit deployment of the deployable element.

Abstract: Methods and apparatus for an air brake system for a projectile according to various aspects of the present invention comprises a pivot and a protrusion mounted on the pivot. The protrusion is adapted to selectively translate outward from the projectile around a translation axis that is parallel to the longitudinal axis of the projectile. The methods and apparatus may further operate in conjunction with an actuation system engaging the protrusion, wherein the actuation system is configured to selectively facilitate the translation of the protrusion.

Abstract: A projectile has fins that are hingedly coupled to a fuselage. The fins are configured to wrap around the fuselage, assuming a location as close as possible to the fuselage, when the projectile is in a gun or launch tube. The fins have spiracles, one or more openings in each of the fins that allow pressurized gases to pass therethrough. The spiracles may be always open, or may open only when there is a sufficient pressure differential between the sides (major surfaces) of the fins. The spiracles allow release of pressurized gases that are trapped between the fins and the fuselage during the launch process. This prevents undesired outward movement or bending of the fins when the projectile reaches a muzzle brake during launch, a structure which causes a sudden release of pressure at radially outer locations of the launch tube.

Abstract: A projectile fuze sends a signal having encoded telemetry data. The telemetry data may be encoded by modulating an aspect or characteristic of the signal, such as frequency modulation of the signal. The fuze may receive and interpret reflections in order to determine proximity to a target or other object, such as by functioning as a height of burst sensor. The signal may include a series of random or seemingly random pulses (a keyed pattern of pulses), such as pulses in amplitude of the signal. The fuze includes a pair of transceivers for sending signals of different frequencies through an antenna, and for receiving signals through the antenna. The transceivers are configured such that one or the other is used at any one time when telemetry data is sent, with telemetry being encoded by changes in frequencies.

Abstract: Methods and apparatus for delivering a missile may operate in conjunction with a missile comprising an outer skin. The missile may be configured in a closed position and an open position. In the open position, an aperture is opened in the outer skin, for example to supply air to an air-breathing engine. In the closed position, the aperture is closed.

Abstract: An electronics module is provided for utilization onboard an airborne object. In one embodiment, the electronics module includes a housing having a cavity therein, a first printed circuit board (PCB) disposed in the cavity, a second PCB disposed in the cavity above the first PCB, and a supportive interconnect structure. The supportive interconnect structure includes a substantially annular insulative body and a plurality of vias. The substantially annular insulative body extends around an inner circumferential portion of the housing between the first PCB and the second PCB to support the second PCB and to axially space the second PCB from the first PCB. The plurality of vias is formed through the substantially annular insulative body and electrically couples the first PCB to the second PCB.

Abstract: A projectile has a fuze kit that includes deployable canards. The canards are ends of a strip of material. The strip of material is initially in an angled recess of a collar of the fuze kit, with the angled recess angled relative to a longitudinal axis of the projectile, defining a plane that is not perpendicular to the longitudinal axis. At some point in flight of the projectile, for example during mid-course of the projectile flight after a ballistic phase of the projectile flight, the canards are deployed by releasing the ends of the strip. This causes the ends of the strip to pull away from the longitudinal axis of the projectile, out of the recess, into the airstream around the projectile. Resilient forces in the strip may cause the ends to be moved out of the recess when the ends are released.

Abstract: A deployment system is provided for utilization onboard an airborne object including a deployable element. In one embodiment, the deployment system includes a circumferential restraint and a release mechanism mounted to the airborne object. The circumferential restraint is disposed at least partially around the airborne object in a constraining position wherein the circumferential restraint prevents deployment of the deployable element. The release mechanism normally resides in a first position in which the release mechanism maintains the circumferential restraint in the constraining position. The release mechanism is movable to a second position to release the circumferential restraint from the constraining position and permit deployment of the deployable element.

Abstract: A smart fuze system includes a radome used to hold a replaceable smart fuze module in place. An internally-threaded collar screws onto threads on the main body of the smart fuze system. Pressure from the radome presses the smart fuze module against electrical connections in the main body. The smart fuze module may thereby be held in place without potting material, allowing different types of fuzes to be swapped into place. The different types of fuzes may include a type that communicates height of burst (HOB) information a type that communicates telemetry, and a type that communicates both HOB and telemetry information.

Abstract: A projectile, such as a missile, rolls during at least a portion of its flight, while retaining its roll reference to enable navigation during the rolling period of flight. The roll reference may be retained by using a sensor, such as magnetometer, to periodically check and correct the roll reference. Alternatively or in addition the missile may alternate roll directions, for example varying roll rate in a substantially sinusoidal function. By rolling the missile inaccuracies in an inertial measurement unit (IMU) of the missile may be ameliorated by being to a large extent canceled out by the changes in orientation of the missile as the missile rolls. This enables use of IMUs with lower accuracy than would otherwise be required to obtain accurate flight. Thus accurate flight may be accomplished with less costly IMUs, without sacrificing the ability to navigate.

Abstract: A projectile fuze sends a signal having encoded telemetry data. The telemetry data may be encoded by modulating an aspect or characteristic of the signal, such as frequency modulation of the signal. The fuze may receive and interpret reflections in order to determine proximity to a target or other object, such as by functioning as a height of burst sensor. The signal may include a series of random or seemingly random pulses (a keyed pattern of pulses), such as pulses in amplitude of the signal. The fuze includes a pair of transceivers for sending signals of different frequencies through an antenna, and for receiving signals through the antenna. The transceivers are configured such that one or the other is used at any one time when telemetry data is sent, with telemetry being encoded by changes in frequencies.

Abstract: A projectile has filler material placed between an outer surface of its fuselage, and fins that are hingedly coupled to the fuselage. The filler material fills space that otherwise would be occupied by pressurized gases. Such pressurized gases could cause undesired outward force against the projectile fins during launch of the projectile from a launch tube or gun, such as when pressure outside the fins is suddenly removed, as in when the projectile passes a muzzle brake in the launch tube. The filler material may be any of a variety of lightweight solid materials, such as suitable plastics or closed cell foams. The filler material prevents pressurized gases from entering at least some of the space between the fins and the outer fuselage surface. When the fins deploy after the projectile emerges from the launch tube the filler material pieces fall away harmlessly.

Abstract: A projectile has fins that are hingedly coupled to a fuselage. The fins are configured to wrap around the fuselage, assuming a location as close as possible to the fuselage, when the projectile is in a gun or launch tube. The fins have spiracles, one or more openings in each of the fins that allow pressurized gases to pass therethrough. The spiracles may be always open, or may open only when there is a sufficient pressure differential between the sides (major surfaces) of the fins. The spiracles allow release of pressurized gases that are trapped between the fins and the fuselage during the launch process. This prevents undesired outward movement or bending of the fins when the projectile reaches a muzzle brake during launch, a structure which causes a sudden release of pressure at radially outer locations of the launch tube.