Abstract: A projectile may include a body and a base fixed to a rear end of the body. The base may include a gas cavity and an opening extending from a rear end of the base to the gas cavity. A retention plug may be disposed in the opening wherein a fit between the retention plug and the opening is such that propellant gas pressure in the gas cavity forces the retention plug out of the opening. The retention plug may include at least one gas conduit between an outer surface of the retention plug and the gas cavity. A plurality of fins may be rotatably fixed to the base. The fins may have a folded position and a deployed position.

Abstract: An aerodynamic projectile is provided having a shell with an aerodynamic structure and a controlled center of gravity, and which exhibits improved aerodynamics and resulting accuracy, and which is suitable for less lethal uses. The projectile shell has a closed front cavity housing a payload, such as a marking agent, therein. The projectile shell also has an open rear portion to provide access to the open rear cavity, and to decrease the weight of the projectile and appropriately locate the center of gravity. The projectile shell also includes a plurality of fins on a sidewall member to enhance the accuracy of the projectile.

Abstract: A projectile, air vehicle or submersible craft with a spinning or rolling fuselage, rotating on its axis, has a collar which can be positioned relative to a longitudinal axis of the projectile using aerodynamic forces. Aerodynamic surfaces, such as lift-producing surfaces, for example tails or canards, are coupled to the collar, and rotate with the collar. An actuator system or mechanism controls orienting of the lift-producing surfaces, such as tilting of the lift producing surfaces, to direct the collar into a desired position relative to a longitudinal axis of the projectile, and to maintain the collar in that position. With such a control the projectile is able to be steered using bank-to-turn maneuvering. The actuator system may use any of a variety of mechanisms to move the lift-producing surfaces, thereby positioning the collar.

Abstract: A projectile, air vehicle or submersible craft with a spinning or rolling fuselage, rotating on its axis, has a collar which can be positioned relative to a longitudinal axis of the projectile using aerodynamic forces. Aerodynamic surfaces, such as lift-producing surfaces, for example tails or canards, are coupled to the collar, and rotate with the collar. An actuator system or mechanism controls orienting of the lift-producing surfaces, such as tilting of the lift producing surfaces, to direct the collar into a desired position relative to a longitudinal axis of the projectile, and to maintain the collar in that position. With such a control the projectile is able to be steered using bank-to-turn maneuvering. The actuator system may use any of a variety of mechanisms to move the lift-producing surfaces, thereby positioning the collar.

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 fuze guidance system is configurable by an end user, allowing the end user to select between different configurations of canards of the system. The different configurations of canards may include canards with different surface areas, optimized for providing appropriate control with different sizes of munitions. The different configurations may be accomplished by having canards with separable portions which may be broken off or otherwise removed by the end user, to reduce canard surface area and/or span. Alternatively the fuze guidance system may come in a kit with multiple sets of canards having different sizes or otherwise having different configurations for providing different aerodynamic characteristics. The end user may select a canard set based on the munition size or type that the fuze guidance system is to be used with.

Abstract: A weapon and weapon system, and methods of manufacturing and operating the same. In one embodiment, the weapon includes a warhead including destructive elements and a guidance section with a target sensor configured to guide the weapon to a target. The target sensor includes a front lens configured to provide a cover to protect the target sensor from an environment and a fast fresnel lens behind the front lens to provide a multi-lens focusing system for the target sensor. In a related embodiment, the weapon includes an aft section including a tail fin having a modifiable control surface area thereby changing an aspect ratio thereof.

Abstract: A solid-fuel pellet thrust and control actuation system (PT-CAS) provides command authority for maneuvering flight vehicles over subsonic and supersonic speeds and within the atmosphere and exo-atmosphere. The PT-CAS includes a chamber or solid-fuel pellets that are ignited to expel gas through a throat. The expelled gas is directed at supersonic vehicle speeds in atmosphere to a cavity between an aero control surface and the airframe to pressurize the cavity and deploy the surface or at subsonic speeds in atmosphere or any speed in exo-atmosphere allowed to flow out a through-hole in the surface where the throat and through-hole provide a virtual converging/diverging nozzle to produce a supersonic divert thrust. A pellet and control actuation system (P-CAS) without the through-hole provides command authority at supersonic speeds in atmosphere.

Abstract: A method for stepping a first member relative to a second member. The method including: providing one of the first and second members with one of a plurality of pockets and movable pins offset from each other with a first spacing; providing the other of the first and second members with the other of the plurality of pockets and movable pins offset from each other with a second spacing, where the first spacing is different from the second spacing; and engaging at least one of the movable pins into a corresponding pocket to step one of the first and second members a predetermined linear and/or rotary displacement.

Abstract: The present invention relates to a missile or aircraft with a hierarchical, modular, closed-loop flow control system and more particularly to aircraft or missile with a flow control system for enhanced aerodynamic control, maneuverability and stabilization. The present invention further relates to a method of operating the flow control system. Various embodiments of the flow control system of the present invention involve different elements including flow sensors, active flow control device or activatable flow effectors and logic devices with closed loop control architecture. The sensors of these various embodiments are used to estimate or determine flow conditions on the various surfaces of a missile or aircraft.

Abstract: Provided is a rotational lock for a control surface, the rotational lock having an output gear including one or more locking members alignable with corresponding locking members on a lock plate in an unlocked position of the rotational lock, the locking members being engageable upon the axial movement of the lock plate to couple the lock plate and lock gear for common rotation. In this way, a rotational lock can be provided that is lightweight, utilizes minimal components, and utilizes an existing motor that actuates the control surface and unlocks the mechanism.

Abstract: In a co-boresighted SAL/IR seeker, the optical system and particularly the secondary lens and position of the SAL detector are configured to produce a well-corrected spot of laser energy at the SAL detector. A spreader is positioned between the secondary mirror/lens and the SAL detector, possibly on the secondary mirror, away from the aperture stop and not in the optical path to the IR detector. The spreader is configured to spatially homogenize the laser energy to increase the size of the spot of focused laser energy at the SAL detector to set the system transfer function to meet slope requirements. Spatial homogenization serves to reduce both boresight shift and slope non-linearities. This approach greatly simplifies the time and labor intensive calibration of the SAL detector's system transfer function.

Abstract: One embodiment is directed to a locking mechanism. The locking mechanism has a housing and a rotary actuator carried by the housing. The rotary actuator includes a shaft and armature disposed around at least a portion of the shaft. The armature is configured to rotate the shaft about a longitudinal axis of the shaft. The locking mechanism also has a cam carried by the shaft and a set of locking balls disposed between the cam and the housing. The locking mechanism has a locking assembly carried by the housing, the locking assembly being axially positionable between a locked position relative to the housing and a released position relative to the housing.

Abstract: An apparatus and method for guiding a cannon shell accurately are disclosed. The apparatus includes two main parts adapted to be installed on the leading end of the cannon shell. The front main part of the apparatus is equipped with at least one pair of fins and is rotatable with respect to the rear main part. The pair of fins is controlled to hold the front main part substantially stable with respect to an external reference frame when the cannon shell rotates as it flies towards its target. Control system is comprised within the apparatus that receives location signals and is adapted to provide guiding control commands to the cannon shell via the fins so as to guide the shell accurately to its preprogrammed target. The control system is adapted to activate the detonation chain of the shell according to preprogrammed mode.

Abstract: A system and method for guiding a projectile is presented. A nozzle system includes a boom assembly body that can be attached to a rear end of a projectile. A gas tank in the boom assembly contains pressurized gas. Fins are attached to the boom assembly body to guide the projectile. A valve lets a pulse of gas out of the gas tank. A nozzle expels the pulse of gas to control an angle of attack and lift of the projectile to guide the projectile to a target.

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 UAV includes: a rocket body, having a rocket motor and a payload section; a parachute coupled with the payload section; an image capture device; a magnetometer to provide a compass reference for images taken from the image capture device; and a transmitter to communicate image and compass data to a remote receiver. Compass bearings are overlaid on image data from the image capture device. A handheld launch unit includes an ignition system, having an activation mechanism and an igniter to activate the rocket motor. A safety pin prevents electrical current from flowing to the igniter until the pin is removed. An accelerometer and/or magnetometer determines an angular orientation of the UAV. Software verifies that the angle is within a user-defined safety limit before activating the igniter.

Abstract: A Hybrid Projectile is provided for delivering an explosive payload to a target wherein the Hybrid Projectile may be steered in flight using relatively inexpensive means. The Hybrid Projectile is exteriorly configured in the same physical exterior configuration of conventional ammunition of various standard types so it can be launched in conventional manner from the same weapon systems. However, internal features allow the Hybrid Projectile to be transformed in flight from a command signal to deploy wings and fins, and in some projectiles to telescope open to deploy such wings and fins. An inexpensive televisual means is activated in the fore region of the round which through RF uplink command can be used to select a path, while motors on the wings can then be used to more precisely glide the projectile to a target, or otherwise to abort the target run.

Abstract: A projectile including: a body having an internal space; and a mechanical stepper motor disposed in the body. The mechanical stepper motor including: a shuttle having one of a plurality of pockets and movable pins offset from each other with a first spacing; a body portion having the other of the plurality of pockets and movable pins offset from each other with a second spacing, where the first spacing is different from the first spacing; and actuation means for engaging at least one of the movable pins into a corresponding pocket to step one of the shuttle and body portion a predetermined linear and/or rotary displacement.

Abstract: The invention relates to a method for increasing the range of shells (1, 8, 13) charged with an explosive substance and other types of shell, which function as carriers of the one or other type of active payload. The method according to the invention thus provides an opportunity for increasing the range of fire of most types of artillery piece by increasing the muzzle velocity and the gliding flight capability of shells or projectiles fired from them, but without the need to increase the energy content in the propellant charges utilized for firing the shells or the projectiles concerned. The novelty proposed in accordance with the invention instead represents a radical modification to the design of the shell (1, 8, 13) utilized in conjunction therewith. The invention also relates to a shell charged with an explosive substance or provided with some other active payload which has been given a long range.

Abstract: A modular electromechanical actuation system assembly is provided that includes an electronic control unit housing having a plurality of motor receptacles and a plurality of battery receptacles formed in an outer surface thereof. Each of the motor receptacles has an associated motor electrical interface, and each of the battery receptacles has an associated battery electrical interface. An electronic control unit is disposed within the electronic control unit housing and is electrically coupled to each of the motor electrical interfaces and each of the battery electrical interfaces. A plurality of motors are supported, one each, within one of the motor receptacles, and a plurality of batteries are supported, one each, within one of the battery receptacles.

Abstract: A surface ship, deck-launched anti-torpedo projectile is disclosed. The projectile has a blunt-end nose to create a cavitating running mode. The nose has a gradual, stepped, right-circular cylindrical or conic geometry. In some embodiments, the projectile includes a plurality of tail fins that are dimensioned and arranged to be within the generalized elliptical cavity that shrouds the projectile in the cavitating running mode.

Abstract: Rolling airframe projectile guidance and stability systems are disclosed. Flight control surfaces, such as canards and/or tail fins are attached to a projectile airframe that is designed to roll during flight. Stepper motors are attached to the flight control surfaces and move the flight control surfaces in discrete increments. A control system generates signals that control the flight control surfaces. The control system may include a neural network that is trained to generate control signals in response to received inputs.

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: Apparatus and method are provided for controlling a vehicle in motion through a fluid medium. A manipulable flare assembly is mounted to a load bearing structure, the structure being configured for mounting to the vehicle. An actuating mechanism has a rotational member operably associated with the flare assembly, the actuating mechanism being configured for selectively providing relative rotation between the rotational member and the load bearing structure. The actuating mechanism is configured for manipulating the flare assembly responsive to selective relative rotation between the rotational member and the load bearing structure. A vehicle is also provided incorporating the apparatus.

Abstract: The present invention provides an apparatus and methods directed to a selectively engageable shaft locking device. In one embodiment, a shaft lock device is presented which enables the testing of the shaft and shaft drive device without engaging the drive mechanism into a fully operational state. Another embodiment provides the ability to return the shaft lock device to a storage state after full engagement. The present invention also provides for methods of testing a selective shaft lock device according to the disclosures contained herein.

Abstract: A guided fuse is provided for installation on a projectile at its nose. The fuse includes a conical frustrum housing, a pair of control panels rotatably connected to pivotable knuckles, and a pair of drag panels disposed on hinges. Each of the control panels releases on command from stowage to deployment. Stowage configuration disposes each control and drag panel to conform against the housing, whereas deployment configuration separately splays the control and drag panels radially outward from the housing. In response to maneuver commands, each control panel turns on one of the knuckles along a radial control axis substantially perpendicular to the longitudinal axis. The control panels turn together either the same angular direction or the opposite angular direction. The control and drag panels form a cruciform pattern along the exterior.

Abstract: A forebody flow control system and more particularly to aircraft or missile flow control systems for enhanced maneuverability and stabilization at high angles of attack. The present invention further relates to a method of operating the flow control system. In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one flow effector on the missile or aircraft forebody; at least one sensor having a signal associated therewith, the at least one sensor being positioned to detect flow separation on the missile or aircraft forebody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one flow effector based on at least in part the signal of the at least one sensor.

Abstract: A projectile including: a shell; and a movable exterior surface of the shell, the movable exterior surface having one or more actuators for providing thrust to move the movable exterior surface from a first position to a second position.

Abstract: A position sensing assembly includes a bearing element and a helically shaped rotational member used to drive a portion of a sensor assembly, such as a Digital Rotary Magnetic Encoder. Interaction between the bearing element and a helically shaped rotational member minimizes the presence of backlash in the position sensing assembly. Accordingly, as an actuator assembly drives both a control element, such as a flight control surface, and the position sensing assembly, the sensor assembly generates an output signal that accurately reflects the position of the control element.

Abstract: A laser guided projectile device and method for shooting the device through a percussion actuated non-electric disrupter or dearmer to disable or destroy improvised explosive devices, bombs, or other ordnance. The device can include a cartridge case, a laser housing, a laser module, and a projectile head. An aperture in the projectile head permits a laser beam to be emitted through the head and projected onto a target to facilitate increased shooting accuracy of the disrupter or dearmer. The device can include O-rings positioned around the laser housing and projectile head that assist in aligning the device within the disrupter or dearmer and that also provide a seal for gases that are emitted during detonation, thereby assisting in the propulsion of the device during firing. The projectile head can be interchangeable and can be rounded or cone-shaped or can comprise a shot cup.

Abstract: An attachment system for attaching a tail unit to an attachment surface of an aircraft is disclosed. An attachment surface may be a fuselage, for example. In an arrangement, the attachment system includes a mounting with a first bearing surface that is capable of resting against the tail unit, and a second bearing surface that is capable of resting against the attachment surface. The first bearing surface and the second bearing surface, of which there is at least one, include a common line of contact. In the arrangement, the planes of the first bearing surface and of the second bearing surface are at an angle that differs from 0° and 180°.

Abstract: A device for driving in rotation fins of a projectile, the fins being of the deployable type integral with fin heads which are able to be oriented along an axis of spin (X, Y) substantially orthogonal to a projectile's longitudinal axis (Z), wherein the fin heads are driven in rotation by motors and substantially ring sector-shaped sliders which slide in a circular groove.

Abstract: The invention relates to a locking device for a deployable surface or fin of a projectile characterized in that it incorporates at least one flexible tongue, one end of which protrudes in the groove, a recess to the side of the groove enabling the tongue to bend in a first direction to enable the fin to enter the groove.

Abstract: An apparatus for wing unfolding is particularly suited for an airborne vehicle. The apparatus has a base body with a longitudinal axis, a number of moveable flaps, and a number of lateral recesses. Attachment devices are configured for fitting the base body to an end face of a wing, with the one or more moveable flap being formed to influence a drag of the wing. Each lateral recess is designed for self-detachable attachment of the base body to the wing. Furthermore, a folding wing is specified, in particular for an airborne vehicle, having a wing, having a swiveling mechanism for extension of the wing to a limit position, having a wing pocket for holding the wing on the longitudinal side in the retracted state, and having an apparatus, which is arranged at the end, for wing unfolding of the type already known. A flying object, such as a guided missile, has a number of such folding wing assemblies.

Abstract: A device for driving in rotation fins of a projectile, the fins being of the deployable type integral with fin heads which are able to be oriented along an axis of spin (X, Y) substantially orthogonal to a projectile's longitudinal axis (Z), wherein the fin heads are driven in rotation by motors and substantially ring sector-shaped sliders which slide in a circular groove.

Abstract: A mechanical deployment and actuation system may comprise a rotation module, a pinion module, a rack module, and a bevel module. The rotation module may be configured to couple to a housing and rotate about the principal axis of the rotation module relative to the housing. The pinion module may be configured to couple to the rotation module and selectively rotate about the principal axis of the pinion module relative to the rotation module. The rack module may be configured to dynamically couple to the pinion module and translate along the principal axis of the rack module in response to rotation of the pinion module. The bevel module may be configured to couple to the rotation module and selectively rotate the rotation module, wherein rotation of the rotation module rotates about the principal axis of the rotation module, the rack module, and the pinion module.

Abstract: A control actuator system. The novel system includes a control surface mounted on a body and adapted to move in a first direction relative to the body, and a first mechanism for storing energy as the control surface moves in the first direction and releasing the stored energy to move the control surface in a second direction opposite the first direction. In an illustrative embodiment, the system is adapted to rotate an aerodynamic control surface of a rolling missile, and the first mechanism is a torsional spring arranged such that rotating the control surface in the first direction winds up the spring and releasing the spring causes the control surface to oscillate back and forth, alternating between the first and second directions. In a preferred embodiment, the spring has a spring constant such that the control surface oscillates at a natural frequency matching a roll rate of the missile.

Abstract: A weapon and weapon system, and methods of manufacturing and operating the same. In one embodiment, the weapon includes a warhead including destructive elements and a guidance section with a target sensor configured to guide the weapon to a target. The target sensor includes a front lens configured to provide a cover to protect the target sensor from an environment and a fast fresnel lens behind the front lens to provide a multi-lens focusing system for the target sensor. In a related embodiment, the weapon includes an aft section including a tail fin having a modifiable control surface area thereby changing an aspect ratio thereof.

Abstract: Vehicles with bidirectional control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to control the orientation and/or flight path of the rocket during both ascent, in a nose-first orientation, and descent, in a tail-first orientation for, e.g., a tail-down landing.

Abstract: An afterbody device for a spacecraft fitted with at least one rocket engine at the rear of the craft includes at least one movable cover element designed to take a first position, masking and reducing the vehicle's rear drag, where it prolongs the vehicle's fuselage around at least one part of a rocket engine nozzle of the vehicle and extends beyond the rear of the vehicle's fuselage, and to take a second position fully deployed, increasing the vehicle's aerodynamic drag.

Abstract: An acceleration activated fin release apparatus comprising a fin holder that when in latched state holds fins in a retracted position and a latching mechanism maintaining the fin holder in latched state until released by an acceleration event.

Abstract: A hybrid spin/fin stabilized projectile. The novel projectile includes a body, a first mechanism for spin stabilizing the body during a first mode, and a second mechanism for fin stabilizing the body during a second mode. In an illustrative embodiment, the projectile includes a rifling band adapted to engage with rifling in a gun during gun launch to impart a spin rate compatible with spin stabilization to the projectile, and a plurality of folding fins attached to an aft end of the body. A fin locking mechanism locks the fins in an undeployed position during the first mode and unlocks to deploy the fins at a predetermined time to switch the projectile to fin stabilization during the second mode. The projectile also includes a mechanism for reducing the spin of the projectile to a rate compatible with guided flight during the second mode.

Abstract: A grid fin control system for a fluid-borne body includes a nozzle extension, an optional stabilization device, and a plurality of grid fins. The grid fins are stowable folded against the nozzle extension and deployable to extend radially outwardly.

Abstract: A projectile including: a body having an internal space; and a mechanical stepper motor disposed in the body. The mechanical stepper motor including: a shuttle having one of a plurality of pockets and movable pins offset from each other with a first spacing; a body portion having the other of the plurality of pockets and movable pins offset from each other with a second spacing, where the first spacing is different from the first spacing; and actuation means for engaging at least one of the movable pins into a corresponding pocket to step one of the shuttle and body portion a predetermined linear and/or rotary displacement.

Abstract: Provided is a detachable aerodynamic missile stabilizing system for a missile flying at low flight speeds. The system includes a housing adapted to couple to couple to the missile. Extending outward from the housing is at least one grid fin. Specifically the grid fin extends from the housing such that it is transverse to a longitudinal axis of the housing and the missile. The grid fin provides a plurality of apertures. The apertures are parallel to the longitudinal axis of the housing and the missile. A coupler is adapted to detachably couple the housing to the missile. A method of use is also provided.

Abstract: An aircraft in the form of multi-stage missile 1 with a spiral inducing assembly 2 which is capable of inducing the missile to travel in a continuous spiraling motion without the missile rolling. A fin 6a is attached to a tube 3 that is able to rotate around the encircled part of the fuselage. The fin 6a is able to rotate in a pivoting manner on the rotate-able tube 3 with respect to the rotate-able tube 3, thereby changing the pitch relative to the longitudinal axis of the rotate-able tube 3. Fin 6a is rotated to a greater than another fin on the right side of the tube 3. The difference in degree of rotation between the fins makes the fin 6a exert a greater force on the rotate-able tube 3 than the fin on the right side when the fins are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3 to rotate. When rotated, the fins would exert a lateral force on the rotate-able tube 3.

Abstract: The disclosed system, device and method for guiding a hypersonic kinetic penetrator projectile (300) generally includes a kinetic penetrator body (110, 230) and a slip-over electronic guidance unit (120, 220), where the kinetic penetrator body slidably mounts through the slip-over electronic guidance unit. Disclosed features and specifications may be variously controlled, adapted or otherwise optionally modified to improve accuracy and control of a hypersonic projectile. Exemplary embodiments of the present invention generally provide multi-use slip-over electronic guidance units for hypersonic kinetic penetrator projectiles in 105 mm and 120 mm munition rounds, surface-to-surface missiles, and air-to-surface missiles.

Abstract: A guidable projectile has a central shaft, a projectile body, and a surface control assembly. The projectile body is arranged to rotate around at least a portion of the central shaft during flight of the guidable projectile to provide stabilization. The surface control assembly is supported by the central shaft. The surface control assembly includes a movable member arranged to control a trajectory of the guidable projectile during flight of the guidable projectile, and an electromagnetic actuator interconnected between the central shaft and the movable member. The electromagnetic actuator is arranged to control movement of the movable member relative to the central shaft.

Abstract: A non-spinning projectile that is self-guided to a laser designated target and is configured to be fired from a small caliber smooth bore gun barrel has an optical sensor mounted in the nose of the projectile, a counterbalancing mass portion near the fore end of the projectile and a hollow tapered body mounted aft of the counterbalancing mass. Stabilizing strakes are mounted to and extend outward from the tapered body with control fins located at the aft end of the strakes. Guidance and control electronics and electromagnetic actuators for operating the control fins are located within the tapered body section. Output from the optical sensor is processed by the guidance and control electronics to produce command signals for the electromagnetic actuators. A guidance control algorithm incorporating non-proportional, “bang-bang” control is used to steer the projectile to the target.