Class / Patent application number | Description | Number of patent applications / Date published |
244300240 | Externally mounted stabilizing appendage (e.g., fin) | 73 |
20090101752 | LOCKING ASSEMBLY FOR ROTARY SHAFTS - A locking assembly has a base and a rotary shaft which is capable of rotating relative to the base. The rotary shaft has a shaft body and a set of capture portions supported by the shaft body. The locking assembly further includes a set of detention mechanisms supported by the base. The set of detention mechanisms is arranged to (i) initially apply retention force to the set of capture portions to provide resistance against rotation of the rotary shaft from an initial angular position, and (ii) remove application of the retention force from the set of capture portions in response to an amount of rotational torque on the rotary shaft. The amount of rotational torque on the rotary shaft exceeds a predetermined threshold and is sufficient to substantially rotate the rotary shaft from the initial angular position. | 04-23-2009 |
20090114763 | MODULAR, HARNESSLESS ELECTROMECHANICAL ACTUATION SYSTEM ASSEMBLY - 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. | 05-07-2009 |
20100327107 | BIDIRECTIONAL CONTROL SURFACES FOR USE WITH HIGH SPEED VEHICLES, AND ASSOCIATED SYSTEMS AND METHODS - 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. | 12-30-2010 |
20100327108 | SPACECRAFT AFTERBODY DEVICE - 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. | 12-30-2010 |
20110073705 | DRIVE DEVICE FOR PROJECTILE FINS - 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. | 03-31-2011 |
20110240793 | APPARATUS AND METHOD FOR CONTROLLING A VEHICLE, AND VEHICLE CONTROLLED THEREBY - 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. | 10-06-2011 |
20120043411 | UNMANNED AERIAL VEHICLE SYSTEM - 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. | 02-23-2012 |
20120111993 | ROTATIONAL LOCK MECHANISM FOR ACTUATOR - 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. | 05-10-2012 |
20120175458 | GUIDANCE CONTROL FOR SPINNING OR ROLLING PROJECTILE - 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. | 07-12-2012 |
20120175459 | GUIDANCE CONTROL FOR SPINNING OR ROLLING VEHICLE - 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. | 07-12-2012 |
20120234967 | LOW-HEAT-TRANSFER INTERFACE BETWEEN METAL PARTS - A low-heat-transfer coupling or assembly is configured to mechanically couple together a pair of mating parts, one of which may be in a heat-producing environment. By roughening at least part of the surface of one of the parts, the contact area between the mating parts can be reduced, while still maintaining the structural integrity of the connection. The roughening can be a knurling process of all or part of the mating surface on one of the parts. This can produce a series of recesses on the surface that are in contact with the other part. The recesses can be small enough, interspersed with non-etched areas of the contact surface, that structural integrity of the coupling between the parts is still maintained. The coupling may be between a leading edge of an aircraft control surface, such as a missile fin, and a body of the control surface. | 09-20-2012 |
20120241551 | METHOD FOR STEPPING A FIRST MEMBER RELATIVE TO A SECOND MEMBER ASSOCIATED WITH A PROJECTILE - A method for stepping a first member relative to a second member associated with a projectile. 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. | 09-27-2012 |
20130032659 | RING GEAR CONTROL ACTUATION SYSTEM FOR AIR-BREATHING ROCKET MOTORS - A control actuation system for an air-breathing rocket motor propelled guided missile positions the drive motors and input gears in an inlet fairing extending aft of the air inlet towards the tail of the missile. The output gears are positioned coincident with and mechanically coupled to their respective tail fins spaced around the circumference of the missile. At least one of the tail fins is offset in a circumferential direction of the missile from its corresponding input gear and the inlet fairing. At least one ring gear is positioned around the exhaust tube to rotate in the circumferential direction of the missile. The ring gear comprises input and output teeth that engage the input and output gears, respectively, to actuate the tail fin. | 02-07-2013 |
20130206897 | VERY LOW-POWER ACTUATION DEVICES - An actuator including: a housing; a piston movably disposed in the housing, the piston being movable between an extended and retracted position; a plurality of gas generation charges generating a gas in fluid communication with the housing; and an exhaust port for exhausting gas from the cylinder generated by the plurality of gas generation charges; wherein activation of each of the plurality of gas generation charges results in an increase in pressure in the housing causing the piston to move in the housing from the refracted to the extended position. The actuator can further include a return spring for biasing the piston in the retracted position and the plurality of gas generation charges can be disposed in the housing. | 08-15-2013 |
20130277494 | Very Low Power Actuation Devices - A method of actuating a control surface in a munition. The method including: coupling a pair of fins to an actuation device; generating pressurized gas to selectively actuate the actuation device; and converting the actuation of the actuation device to rotation of the pair of fins. The converting can convert a linear output of the actuation device to the rotation of the pair of fins or a rotary output of the actuation device to the rotation of the pair of fins. The generated gas can be directly provided to the actuation device or the generated gas can be stored in a storage device before being provided to the actuation device. The method can further include repeating the coupling, generating and converting for a second pair of fins. | 10-24-2013 |
20130334358 | Apparatus and method for trajectory correction - A system and method of trajectory correction includes a voice coil coupled to the projectile and providing a linear force; a linkage assembly coupled to the voice coil and comprising: a linkage shaft; a slot coupled to the linkage shaft; and a pin loosely coupled to the slot to form a first pivot point, wherein the linkage assembly converts the linear force to a torque force through the first pivot point; and a canard assembly coupled to the linkage assembly and including a canard shaft coupled to the linkage shaft to form a second pivot point; and at least one canard coupled to the canard shaft, wherein the torque force is transmitted to canard shaft by the linkage shaft, and wherein the canard shaft transmits the torque force to the canard to correct the trajectory of the projectile. | 12-19-2013 |
20140021289 | RESETTABLE MISSILE CONTROL FIN LOCK ASSEMBLY - A fin lock assembly | 01-23-2014 |
20140027563 | GROUND-PROJECTILE GUIDANCE SYSTEM - A guidance unit system is configured to be used for a ground-launched projectile. The system includes a housing configured to be attached to a ground-launched projectile. The housing is coupled to an attachment region that attaches to the projectile, wherein the housing is configure to rotate relative to the attachment region. A motor is contained within the housing and a bearing surrounding the motor. The bearing is rigidly attached to the housing such that the motor rotates with the housing and shields the motor from inertial loads experienced by the housing. | 01-30-2014 |
20140042266 | FIN BUZZ SYSTEM AND METHOD FOR ASSISTING IN UNLOCKING A MISSILE FIN LOCK MECHANISM - By removing the aerodynamic fin forces from the fin lock mechanism, achieved by actuating the fin control system to apply a controlled force that counters the aerodynamic forces acting on the control fins, the system can reduce the transmission of aerodynamic forces onto the fin lock mechanism, which makes the fin lock mechanism easier to unlock with less force. Accordingly, a method for unlocking a fin lock mechanism that releasably holds one or more missile control fins in a locked position, where the control fins are prevented from rotating, includes the steps of (i) applying an alternating positive and negative rotational force to a control fin; (ii) monitoring the position of the control fin during the applying step; and (iii) while the position of the control fin does not exceed a predetermined value, repeating the applying step for a predetermined number of times or for a predetermined period. | 02-13-2014 |
20140042267 | BIDIRECTIONAL CONTROL SURFACES FOR USE WITH HIGH SPEED VEHICLES, AND ASSOCIATED SYSTEMS AND METHODS - 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. | 02-13-2014 |
20140061365 | PROJECTILE WITH STEERABLE FINS AND CONTROL METHOD OF THE FINS OF SUCH A PROJECTILE - The invention relates to a steering method of a projectile and to the associated projectile with incidence steerable fins, comprising at least three fins, each being pivotable with respect to the projectile around a pivot axis perpendicular to the longitudinal axis X of the projectile, wherein the projectile comprises a fin orientation ring, the ring comprising as many arms as there are fins, wherein the ring can translate in a plan P perpendicular to the longitudinal axis X of the projectile and following at least two directions of this plan P, wherein the orientation ring can rotate on itself around its centre parallel to the longitudinal axis X of the projectile, each arm comprising means cooperating with an orientation lever fixed to a fin to be able to pivot the fin around its pivot axis during translation of the ring by positioning means. | 03-06-2014 |
20140231577 | PROJECTILE WITH STEERABLE CONTROL SURFACES AND CONTROL METHOD OF THE CONTROL SURFACES OF SUCH A PROJECTILE - The subject-matter of the invention is a method for controlling the control surfaces of a projectile and the associated projectile comprising incidence steerable control surfaces and comprising at least two control surfaces, each one being rotatable with respect to the projectile around a pivot axis perpendicular to the longitudinal axis X of the projectile, wherein the projectile comprises central means for controlling the control surfaces having at least a spherical shape, a control arm secured to the spherical shape and adapted to rotate the spherical shape, for each control surface a transmission member cooperating with the spherical shape and adapted to transmit to the control surface the rotation movements of the spherical shape, and means for positioning the arm. | 08-21-2014 |
20140312163 | BIDIRECTIONAL CONTROL SURFACES FOR USE WITH HIGH SPEED VEHICLES, AND ASSOCIATED SYSTEMS AND METHODS - 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. | 10-23-2014 |
20150034759 | BIDIRECTIONAL CONTROL SURFACES FOR USE WITH HIGH SPEED VEHICLES, AND ASSOCIATED SYSTEMS AND METHODS - 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. | 02-05-2015 |
20150362301 | PASSIVE STABILITY SYSTEM FOR A VEHICLE MOVING THROUGH A FLUID - A stability system for a vehicle moving through a fluid includes stabilizers each having a drive surface that follows the position of the fluid stream perceived by the vehicle. The movement of the drive surface positions control surfaces of the stabilizers, which are coupled to the drive surfaces by mechanical linkages. Lift forces on the drive surfaces provide the force that is used in positioning the control surfaces. The deflection of the control surfaces provides a force on the vehicle that affects stability of the vehicle, for instance in making an inherently unstable vehicle more stable. The stability system may work completely passively, without any active control, and without the need for power to operate it. | 12-17-2015 |
20160040967 | AIR VEHICLE WITH CONTROL SYSTEM MECHANICAL COUPLER - An air vehicle, such as a munition like a guided bomb or missile, has a control system that allows control surfaces to be mechanically uncoupled from one or more actuators to allow the control surfaces to freely move (rotate) relative to a fuselage of the vehicle, for example allowing the control surfaces to “weather vane” by assuming an orientation corresponding to the direction of airflow past the air vehicle (direction of airflow relative to the air vehicle). When active positioning of the control surfaces is desired, the control surfaces may be mechanically coupled to one or more actuators that are used to position the control surfaces. The selective coupling of the actuator(s) and the control surfaces may be accomplished by selectively coupling together a sleeve that is mechanically coupled to the control surfaces, and a nut that moves along a shaft of an actuator, for example using a resilient device. | 02-11-2016 |
20160084623 | ADAPTIVE ELECTRONICALLY STEERABLE ARRAY (AESA) SYSTEM FOR INTERCEPTOR RF TARGET ENGAGEMENT AND COMMUNICATIONS - An AESA system comprises a plurality of arrays, each comprising a plurality of radiating elements, each array configured for placement on a forward-facing surface of a different one of a plurality of aerodynamic control surfaces on an interceptor. A plurality of RF transmissive radome elements, each having an aerodynamic shape complementary to the aerodynamic control surface, are placed over one of the arrays. Control circuitry configures the arrays, independently or in concert, for RF target engagement and communication. Additional arrays may be positioned on side or aft-facing surfaces of the aerodynamic control surfaces for RF communication. The AESA system may be paired with an ER system for dual-mode operation. | 03-24-2016 |
20160187112 | SHELL - Provided is a shell including: a shell body; a steering wing including a drive shaft and that mounted on an external surface of the shell body; an auxiliary wing including a shaft connection portion which is connected to the drive shaft and moving in the lengthwise direction of the drive shaft within the drive shaft to be inserted into and be spread outward from within the steering wing; an auxiliary-wing holding unit including a holding protrusion which is fixedly arranged in a direction of intersecting the shaft connection portion to selectively hold the auxiliary wing in place; and an auxiliary-wing spreading unit installed within the drive shaft, and that provides driving force for spreading the auxiliary wing outward from within the steering wing when the holding protrusion is disengaged with the shaft connection portion. | 06-30-2016 |
244300250 | Removable | 3 |
20100032515 | FUZE GUIDANCE SYSTEM WITH MULTIPLE CALIBER CAPABILITY - 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. | 02-11-2010 |
20100219285 | DETACHABLE AERODYNAMIC MISSILE STABILIZING SYSTEM - 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. | 09-02-2010 |
20100237186 | DRAG-STABILIZED WATER-ENTRY PROJECTILE AND CARTRIDGE ASSEMBLY - A drag-stabilized water-entry projectile having a projectile body, one or more drag-stabilizing elements, such as fins, flares or canards, and one or more attachment members adapted to hold the one or more drag-stabilizing elements to the projectile body. The one or more attachment members are coated with a thermally reactive material. A projectile and cartridge assembly has a shear pin, a projectile having a first cutout portion, the cutout portion sized to receive the shear pin. The assembly also includes a sabot configured to house the projectile and having a second cutout portion, the second cutout portion sized to receive the shear pin. The cutout portion is positioned to provide an offset region between an aft end of the projectile and a base of the sabot. | 09-23-2010 |
244300260 | Sliding | 1 |
20160252333 | FIN DEPLOYMENT MECHANISM FOR PROJECTILE AND METHOD FOR FIN DEPLOYMENT | 09-01-2016 |
244300270 | Collapsible | 40 |
20090127378 | METHODS AND APPARATUS FOR DEPLOYING CONTROL SURFACES SEQUENTIALLY - Methods and apparatus for deploying control surfaces generally comprise a fin deployment system for projectiles. The fin deployment system is used to control the timing of the control surface deployment. In one embodiment, the deployment system comprises a clip that is configured to react the biasing force of one control surface against another in order to maintain the control surfaces in a non-deployed state until at least one control surface is able to overcome the retention force of the clip, thus beginning a chain reaction in which all of the control surfaces deploy sequentially. | 05-21-2009 |
20090206192 | METHODS AND APPARATUS FOR ADJUSTABLE SURFACES - Methods and apparatus for systems having deployable elements according to various aspects of the present invention comprise a system including a deployable surface and an adaptive actuator including a polymer foam. In one embodiment, the system comprises a vehicle including a deployable wing comprising an exterior surface. The exterior surface may be adjusted by adjusting the shape, size, position, and/or orientation of the adaptive actuator. | 08-20-2009 |
20100032516 | SOLID-FUEL PELLET THRUST AND CONTROL ACTUATION SYSTEM TO MANEUVER A FLIGHT VEHICLE - 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. A restrictor mechanism controls the bleed of pressurized gas from the cavity to the external environment to achieve a deployment time objective for either the PT-CAS or P-CAS. | 02-11-2010 |
20100102161 | PROJECTILE HAVING FINS WITH SPIRACLES - 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. | 04-29-2010 |
20100102162 | PROJECTILE WITH FILLER MATERIAL BETWEEN FINS AND FUSELAGE - 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. | 04-29-2010 |
20100264254 | TECHNIQUES FOR CONTROLLING ACCESS THROUGH A SLOT ON A PROJECTILE - A slot cover actuation assembly controls access through a slot on a projectile. The slot cover actuation assembly includes a slot cover, a fastener (e.g., a screw), and an actuator (e.g., a squib device). The fastener is arranged to position the slot cover at an installation position on the projectile. The slot cover covers the slot on the projectile when the slot cover resides at the installation position. The actuator is arranged to release the slot cover from the installation position on the projectile. The slot cover uncovers the slot on the projectile when the actuator releases the slot cover from the installation position on the projectile, thus allowing a control surface member (e.g., a fin) to deploy. | 10-21-2010 |
20100288870 | PROJECTILE WITH DEPLOYABLE CONTROL SURFACES - 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. | 11-18-2010 |
20100308153 | Device for Opening and Locking a Tail Unit for Ammunition - A device for opening and locking a tail unit is provided. The tail unit includes a body and at least one fin, pivotable relative to the body along a first axis, that has a projection that forms an element. The device comprises a control ring, slidable relative to the body along a second axis, that includes a component, forming an element, that bears against the projection to deploy the fin, the second axis being non-parallel and non-secant to the first axis. A means for shaping one of the elements during translation along the second axis of the control ring towards the projection of the fin is provided on the other element. The body includes a bearing surface to support the fin during shaping, in which the support of the fin on the bearing surface corresponds to the deployed position of the fin. | 12-09-2010 |
20100314488 | FOLDABLE AND DEPLOYABLE PANEL - A foldable deployable panel device ( | 12-16-2010 |
20100314489 | Control Of Projectiles Or The Like - A gun-fired projectile or ballistic missile ( | 12-16-2010 |
20110024550 | DEPLOYABLE BOAT-TAIL DEVICE FOR USE ON PROJECTILES - In accordance with one aspect of the invention, a system, method and apparatus for a boat-tail device is described herein. A body section for a projectile having a deployable portion is provided. Gun gases may pass through an orifice at an aft end of a piston and pressurize a volume in a plenum within the body section. Depressurization at muzzle exit may allow the gas pressurized in the plenum to push the piston aft deploying the deployable portion. A stopping and locking mechanism such as a complementarily tapered piston and opening may engage at the end of the stroke of the piston to stop and lock the piston at a predetermined location. A releasable protective cover may be used to protect the structure of the deployable element and other elements from gun gases and launch loads. | 02-03-2011 |
20110068220 | Unknown - The invention concerns the field of devices for improving the piloting of projectiles More specifically, the object of the invention is a piloting device for a missile or a projectile, for example, of small caliber, especially on the order of 40 mm, which has a lateral main surface with a nose at the level of one of its extremities, whereby said device includes at least one cavity consisting of a combustion chamber and filled, at least partially, by an explosive powder, and means of initiation of this explosive powder, and thereby the explosive powder includes nanothermites or gas-generating nanothermites. | 03-24-2011 |
20110114783 | PROJECTILE BODY EQUIPPED WITH DEPLOYABLE CONTROL SURFACES - A projectile body intended to evolve in a fluid, such body equipped with at least two radially deployable control surfaces, such control surfaces being accommodated prior to their deployment in housings made in the body, body in which the housings communicate at their intersection point, each housing being blocked by sealing means preventing any fluid from the exterior of the projectile body from passing through the housings when the control surfaces are deployed. | 05-19-2011 |
20110186678 | Pyrotechnic fin deployment and retention mechanism - A fin retention and deployment mechanism includes a detent in each of a plurality of fins, a mechanism that engages the detent, and at least one spring clip that maintains each of the fins in a non-deployed position. The mechanism also includes a gas generator, a manifold, coupled to the gas generator and having a plurality of cylinders in fluid communication with gas from the gas generator, and a plurality of pistons disposed in the cylinders. A bottom of each of the pistons is coupled to each of the fins to provide deployment thereof when a corresponding top of each of the pistons is acted upon by gas from the gas generator. In response to the gas generator expelling gas, the pistons may move the fins to a deployed position. | 08-04-2011 |
20120025009 | AIRCRAFT WITH SEGMENTED DEPLOYABLE CONTROL SURFACES - An aircraft, such as a missile, has control surfaces that have segments that are hinged together. The control surfaces deploy from a closed position, for example with the segments folded against a fuselage, so as to allow for launching from a launch tube. Once the aircraft is launched the control surfaces deploy from the closed position to an open position, with the segments opening up farther from the body or fuselage. In the open position or deployed state the segments may be substantially planar. Locks of the control surfaces may be used to lock the segments in place in the open position. The locks may include hollow sleeves that slide over the control surface segments. The sleeves and the segments may include a protrusions and depressions that engage each other to hold the segments in the open configuration. | 02-02-2012 |
20120025010 | AERODYNAMIC FIN LOCK FOR ADJUSTABLE AND DEPLOYABLE FIN - Some embodiments pertain to a projectile that includes a body and a support attached to the body. The projectile further includes at least one partial fin that is rotatably attached to the support such that the partial fin moves between a stowed position and a deployed position. The support moves relative to the partial fin as the partial fin moves between the stowed position and the deployed position such that the partial fin and the support form a complete fin when the partial fin is in the deployed position. The support may form a portion of the front edge of the complete fin when the partial fin is in the deployed position. The support may lock the partial fin in place when the partial fin is in the deployed position. | 02-02-2012 |
20120091255 | SHIFT LOCK ASSEMBLY - A shift lock assembly includes a drive member carried by a drive shaft and configured to rotatably couple to a drive motor and a shift mechanism disposed between the drive member and a ground plate, the shift mechanism configured to move between a first position and a second position relative to the drive member and the ground plate. When disposed in the first position, the shift mechanism is configured to couple the drive shaft to the ground plate and decouple the drive shaft from the drive member to allow rotation of the drive member relative to the drive shaft. When disposed in the second position, the shift mechanism is configured to couple the drive shaft to the drive member and decouple the drive shaft from the ground plate to allow rotation of the drive shaft in response to rotation of the drive member. | 04-19-2012 |
20120181376 | MUNITION AND GUIDANCE NAVIGATION AND CONTROL UNIT - A guidance and control unit assembly for use with a munitions projectile includes a guidance and control unit being roll isolated with respect to the munitions projectile such that roll of the munitions projectile about a projectile longitudinal axis, such roll being imparted to the munitions projectile during the act of launching the munitions projectile, may not be imparted to the guidance and control unit as desired. A munitions projectile is further included. | 07-19-2012 |
20130200208 | CHORD-EXPANDING AIR VEHICLE WINGS - An air vehicle wing includes foldable ribs coupled to a leading-edge spar. The ribs each have multiple rib segments which are foldable (hinged) relative to each other. Extension linkages, each with multiple extension linkage segments, pass through openings in the rib segments, and may be coupled to the rib segments with pin couplings, able to change relative angle between the individual rib segments and the extension linkage segments to which they are coupled. A skin may cover the ribs, to provide an outer surface of the wing that may be unfolded as the wing is expanded from a stowed, small-chord condition, to a deployed, large-chord condition. | 08-08-2013 |
20130214085 | DEPLOYABLE WING AND FIN CONTROL SURFACE ACTUATION - A system for actuating a control surface of a deployable member is provided. The system includes an actuator disposed within a fuselage structure of a missile; a double joint having a distal end for connecting to the actuator and a proximal end for engaging the control surface, wherein the double joint further includes a first and second pivot; and a mechanical brake configured to controllably prevent rotation of the actuator. | 08-22-2013 |
20140131509 | FIN DEPLOYMENT MECHANISM AND PROJECTILE WITH SUCH A MECHANISM - The invention relates to a fin deployment mechanism ( | 05-15-2014 |
20150108268 | SHAPE MEMORY ALLOY MICRO-AERO CONTROL SURFACES - A control system for a missile includes a plurality of control surfaces that can be arrayed across a surface of the missile body, and a controller connected to the control surfaces to selectively move the control surfaces between an aerodynamic stowed position where the control surfaces conform to the surface of the body, and a deployed control position removed from the aerodynamic stowed position where the control surfaces extend from the surface of the body to interact with airflow over the body. The control surfaces are made of a material that includes a shape-memory alloy. Heating the control surfaces causes the shape-memory alloy to move the control surfaces from the aerodynamic stowed position to the deployed control position. By selectively extending and retracting the control surfaces, the control system provides the ability to control the missile's direction of travel or to reduce roll about a longitudinal axis of the body. | 04-23-2015 |
20160102952 | Very Low-Power Actuation Devices - A munition including: a control surface actuation device including: an actuator comprising two or more pistons, each of the pistons being movable between an extended and retracted position, the retracted position resulting from an activation of each of the two or more pistons; and a movable rack having a portion engageable with a portion of the two or more pistons to sequentially move the rack upon activation of each of the two or more pistons; and a control surface operatively connected to the rack such that movement of the rack moves the control surface; Where the actuator comprises three pistons; the portion of the rack is a plurality of spaced portions and the portion of the piston is an end portion of the piston exposed when the piston is in the extended position or the movable rack is linear and moves linearly. | 04-14-2016 |
20160169642 | Rudder System | 06-16-2016 |
20160176503 | Mechanisms for Deploying and Actuating Airfoil-Shaped Bodies on Unmanned Aerial Vehicles | 06-23-2016 |
244300280 | Longitudinally rotating | 8 |
20090008496 | Wing-Unfolding Apparatus, Folding Wing Assembly, and Vehicle with Folding Wing Assemblies - 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. | 01-08-2009 |
20090090809 | METHOD OF INCREASING THE RANGE OF A SUBCALIBRE SHELL AND SUBCALIBRE SHELLS WITH LONG RANGE - The invention relates to a method for increasing the range of shells ( | 04-09-2009 |
20110180655 | DEVICE FOR SIMULTANEOUS DEPLOYMENT OF THE CONTROL SURFACES OF A PROJECTILE - A simultaneous deployment device for the control surfaces of a projectile for which each control surface is intended to be pivoted by a motor after its deployment to ensure the piloting, each control surface being held within the projectile and deployed towards the exterior of the projectile by the expansion of elastic means, each control surface being deployed by a rotation with respect to a control surface support and following a deployment axis that is crosswise to that of the projectile, wherein the elastic means are common means to ensure the deployment of all the control surfaces, the expansion of the elastic means generating a push stress directed along the axis of the projectile and being exerted on a push plate which transmits the push stress to as many slides as there are control surfaces to be deployed, each slide cooperating without slipping with a matching profile integral with a base of the control surface to make this pivot with respect to its support and first releasable locking means that maintain the elastic means in the compressed position. | 07-28-2011 |
20120068002 | GUIDED MISSILE - A missile ( | 03-22-2012 |
20120074256 | COMPRESSION SPRING WING DEPLOYMENT INITIATOR - A wing deploy initiator for deploying guidance wings of a rocket or missile, such as the APKWS, provides enhanced wing deploy performance with reduced complexity, cost, and likelihood of failure. The invention includes a cam which is driven between the stowed guidance wings by at least one compression spring, thereby forcing the guidance wings outward through slots in the fuselage of the rocket or missile. Oblique flat sides of the cam can push against beveled edges on the wings. The cam can be attached to spring mandrels, and the cam and mandrels can pass through a retaining plate as the springs decompress. Embodiments can exert sufficient push force to enable the wings to break through frangible slot covers. An embodiment applicable to the APKWS includes only 13 parts, and can exert up to 10 lb push force on each wing after 0.3 inches of wing travel. | 03-29-2012 |
20120175460 | MULTI-STAGE FIN DEPLOYMENT ASSEMBLY - A multi-stage fin deployment assembly includes a rotary actuator configured to release a first spring-loaded stage that, when deployed, releases a second spring-loaded stage to deploy a set of deployable member or fins. By chaining these spring-loaded stages together, a relatively small input force, as provided by the rotary actuator, causes the second spring-loaded stage to generate a relatively large output force on the fins. This multistage force magnification makes it possible for the deployment assembly to utilize smaller actuators that require less power and take up less space, compared to conventional locking mechanisms. | 07-12-2012 |
20130193265 | Steering Section for Guided Munition - A steering section for guided munition comprises a steering body having n control surfaces folded inside or deployed protruding from the external surface. The steering section comprises a locking mechanism for the n control surfaces folded inside the steering body having a lock support secured thereto, a fixed sleeve secured to the lock support comprising a locking barrel, a mobile sleeve surrounding the fixed sleeve and slideable longitudinally along the locking barrel, the mobile sleeve comprising, on the outside of the fixed sleeve, a free end collaborating with the n control surfaces to keep them folded inside the steering body, a translational-locking device locking the translational movement along the mobile sleeve along the locking barrel deactivatable by unlocking force to trigger translational sliding movement of the mobile sleeve along the locking barrel and release the n control surfaces which can then move from their folded position into their deployed position. | 08-01-2013 |
20140291441 | ROCKET NOZZLE ASSEMBLY - In one example, a rocket nozzle assembly is disclosed that has stowed and deployed positions, and includes a casing including an outer wall and an inner surface, at least a portion of the inner surface defining a diverging region, wherein the casing defines a plurality of fin slots, and wherein each of the plurality of fin slots extend through the outer wall of the casing and the inner surface of the casing, and wherein the diverging region defines a bell-shaped contour. The assembly further includes a plurality of fins pivotally engaged to the casing, wherein in the stowed position, each of the plurality of fins extends into the diverging region through a respective one of the fin slots, and wherein in the deployed position, each of the plurality of fins extend outwardly from the casing. | 10-02-2014 |
244300290 | Radially rotating | 7 |
20100276534 | CANARD-CENTRIC MISSILE SUPPORT - A canard includes a first section and a second section. The first section is configured for the coupling of radial forces to a fuselage of an air vehicle, and the first section is coupled to the second section via a hinge somewhere along the radial extent of the canard. An edge of the first section near the hinge provides a load support for the air vehicle within a launch canister. | 11-04-2010 |
20100282895 | LOW COST DEPLOYMENT SYSTEM AND METHOD FOR AIRBORNE OBJECT - 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. | 11-11-2010 |
20120091256 | PROJECTILE - Projectile for a small arms weapon having a barrel. The projectile comprises a projectile body; a plurality of external peripheral fins; a coupling for each fin to mount the fin to the projectile body to enable pivotal movement of the fin from an un-deployed position to a deployed position and to enable displacement of the fin in a radial direction of the projectile body; and means to bias displacement of the fin in the radial direction. | 04-19-2012 |
20130056578 | PROJECTILE - A projectile ( | 03-07-2013 |
20150338200 | WING DEPLOYMENT MECHANISM - Wing deployment mechanism for deploying a pair of wings from an airborne body, wherein their deployment in motion, each one around an axis, defines the wings' deployment plane relative to the airborne body, and wherein the mechanism is characterized by that it comprises a propelable assembly mounted in the airborne body and suited to a rotational motion around an axis that is substantially orthogonal in its direction to the wings' deployment plane, a pair of arms that are linked, each one, on its one side to the assembly and at distance from the assembly's rotation axis, and on its other side to an end of one of the wings and at a distance from the axis around which the rotational motion of the wing in the wings' deployment plane is enabled, and wherein the link of each one of the arms is performed in a manner that enables angular motion of each of the arms relative to the assembly and to the end of the wing unto which it is linked, and wherein propelling the assembly to rotational motion and actuating a momentum for turning the wing as a result by the arm that is connected to it bring about concurrent rotational motion of the pair of wings in opposing directions and to their deployment on the wings' deployment plane, a method for deploying a pair of wings from an airborne body that is implementable in such mechanism and an airborne body equipped with such mechanism. | 11-26-2015 |
20160097618 | FIN DEPLOYMENT SYSTEM - A projectile having a fin deployment system disposed about its circumference. The fins are initially contained by a fin cover that is removed by aerodynamic force. The fins are then rotated around a rotational axis parallel to and offset from the central axial axis of the projectile body by the centrifugal forces created by the rotation of the projectile as the projectile passes through a barrel of a gun system or tube launcher. The fin deployment system can also have locking systems that lock the fins in the deployed position and prevent the fins from rotating back into the retracted position after deployment. | 04-07-2016 |
20160169643 | Folding Fin System | 06-16-2016 |
244300300 | Extending beyond rear of missile | 1 |
20110024549 | DEPLOYABLE FAIRING AND METHOD FOR REDUCING AERODYNAMIC DRAG ON A GUN-LAUNCHED ARTILLERY SHELL - A deployable fairing is driven off of high-pressure gun gases to reduce aerodynamic drag and extend the range of the artillery shell. An artillery shell is provided with a fabric fairing and a piston attached thereto in a rear section of the shell in a stowed state and a chamber. During launch high-pressure gun gasses are captured and stored in the chamber. Once the shell clears the end of the artillery tube, the pressure aft of the shell drops from the high pressure inside the tube to atmospheric pressure outside the tube. The high pressure gun gasses stored in the chamber act over the top surface of the piston to drive the piston aft against the much lower pressure behind the projectile to deploy the fabric fairing attached thereto to reduce the base area of the projectile creating or extending the boat-tail of the shell, hence reduce aerodynamic drag. The aft driven piston engages a locking mechanism that locks the piston in a deployed position. | 02-03-2011 |