Abstract: Disclosed here are airframe component assemblies including example embodiments with a root connected to an aircraft fuselage, a free section with a connection portion with holes, a slidable attachment section formed to fit between the root and the free section, and an elastomeric retention device coupled to the root and the slidable attachment section, the elastomeric retention device configured to exert a force to pull the slidable attachment toward the root.

Abstract: A fin deployment system for a projectile positioned in a chamber, the fin deployment system including a non-rotatable hinge pin shaft, a fin member, and a unidirectional ratchet collar member. The non-rotatable hinge pin shaft, which is coupled to the shell, defines a helically-oriented pathway. The fin member has a fin lug that couples the fin member on the hinge pin shaft for simultaneous axial and rotational movement along the helically-oriented pathway to a deployed position at an aft region of the projectile. Such movement is induced at least partially by application of a centripetal load and aerodynamic load as the projectile rotates upon launch from a chamber. The unidirectional ratchet collar member is disposed on the hinge pin shaft for unidirectional axial movement and radial expansion induced by the simultaneous axial and rotational movement of the fin member that retains the fin member in the deployed position.

Abstract: A deployment system, such as for deploying wings, includes a pair of hub assemblies that transmit linear motion provided by an actuator into a combination of rotational and axial motion. The actuator works on both hub assemblies, rotating (for each wing) a slew ring that is coupled to a lift bar that acts as a follower, following a pair of cam slots, to allow the wings to follow their desired course. In one embodiment the wings move axially away from a fuselage at the beginning of the deployment movement, followed by a primarily rotational movement, with the wings pulling in toward the fuselage at the end of the deployment process. The actuator includes a pair of threaded shafts (threaded in opposite directions) that rotate along with a pinion gear, driven by a motor, to translate a pair of retractor links that are coupled to the slew rings.

Abstract: Techniques are disclosed for providing retractable control fins on an underwater vehicle. The retractable control fins can be extended away from a main hull portion of the underwater vehicle and retracted inwards to a stowage region within the hull portion to protect the fins from damage and reduce an overall outer diameter (e.g., in the case of a cylindrical body) of the underwater vehicle. In some embodiments, the control fins are folded inwards to reduce the vehicle diameter. In other embodiments, the control fins are pulled inwards using a rotating structure designed to slide the control fins through an opening and into an inner portion of the hull to reduce the vehicle diameter. The retraction of the fins through the various retraction mechanisms reduces the envelope diameter of the underwater vehicle.

Abstract: A device for blocking a fin of a projectile, the fin including a fin base pivoting about a pivot pin secured to the body of the projectile between a withdrawn fin position and a deployed fin position, wherein the device includes at least one recess housing at least one shape of revolution pushed by a resilient means between a first surface borne by the fin and a second surface borne by the body of the projectile, at least one of the two surfaces forming a ramp that converges toward the other surface to tend to cause jamming of the shape of revolution between the two surfaces.

Abstract: A projectile including at least one pair of airfoil sections, deployable from housings located inside the body and emerging toward the outside of the projectile. The projectile includes a casing surrounding the body of the projectile and outer surface of which is in profile continuity with the body. The casing can pivot around body along longitudinal axis and includes, for each section, an opening having two zones. A first zone is indented to be positioned, by pivoting of the casing, so as to face a housing in order to allow the section to pass to allow it to be deployed, and second zone located as a recess lateral to the first zone, the recess being oriented along a direction substantially perpendicular to the first zone's longitudinal direction, the second zone having a width allowing the passage of a foot of the deployed section.

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

Abstract: The present invention is directed to a projectile configured to provide a submunition payload across a wide impact pattern, similar to that of a shotgun, at a range typically beyond the capability of standard shotgun rounds. The additional range is provided in some embodiments of the invention by allowing the tailoring deployment range of the submunition payload based upon a given threat.

Abstract: A collapsible unmanned aerial vehicle has: a cylindrical structural body; a plurality of deployable mechanisms laterally distributed about the cylindrical structural body; a control unit; a portable power source; each of the plurality of deployable mechanisms comprising a lift-generating device, a pliable pylon and an actuation mechanism, the cylindrical structural body being terminally mounted to the pliable pylon, the lift-generating device being terminally mounted to the pliable pylon, the actuation mechanism being operatively integrated along the pliable pylon, the pliable pylon being selectively configured to be radially straightened from the cylindrical structural body and to arcuately collapsed into the cylindrical structural body via the actuation mechanism, the control unit and the portable power source each being electrically connected to the actuation mechanism; the control unit and the portable power source being mounted within the cylindrical structural body; and the portable power source being e

Abstract: A folding wing for a missile comprises a wing root, an upper wing part foldably supported at the wing root around a swiveling axis, at least one first elastically pre-stressed force element and a latching device. The at least one first elastically pre-stressed force element is coupled with the wing root and the upper wing part and is designed for permanently urging the upper wing part into a working position relative to the wing root through introducing a torque. The latching device is designed for arresting the upper wing part on reaching the working position automatically.

Abstract: A folding articulating missile fin having a sliding block detent mechanism and a guided missile. The folding articulating missile fin includes a sliding block detent mechanism composed of the sliding block elastically supported by a spring and sliding in a guide groove of a lower fin, a hinge pin allowing an upper fin and a lower fin to be unfolded, and a pair of upper and lower stop rings retaining opposite ends of the hinge pin, in which when the upper fin that has been unfolded is fully folded, the upper fin keeps folded in contact with the sliding block, and when the upper fin having been folded is unfolded, the upper fin remain unfolded and in contact with the sliding block. Accordingly, the structure related to the spring is simplified, and since a sliding-type mechanism is used, the folding fin can be quickly assembled.

Abstract: A folding wing comprises a wing root, an upper wing part foldable relative to the wing root, at least one guiding device, and an elastically pre-stressed force element. The upper wing part comprises an end edge and a profile foot, wherein the wing root comprises a base and an opposing receiving groove, which is designed to receive the profile foot in a flush manner and is delimited by two delimiting edges having a separation distance that at least equals the maximum profile thickness of the profile foot. The guiding device is arranged at one of the upper wing part and the wing root and is designed for guiding the profile foot in a variable distance to the ground of the receiving groove. The force element is coupled with the wing root and the upper wing part and urges the upper wing part into the receiving groove through the pre-stress.

Abstract: A deployment or hinge mechanism and, more particularly, a compact unmanned aerial vehicle (UAV) wing deployment mechanism is provided. The deployment mechanism includes a hinged mechanism that stows in a stacked configuration and deploys in a level configuration.

Abstract: A folding fin system includes a fin root and an upper fin part that is rotatably borne on the fin root. The upper fin part may be moved relative to the fin root between an unfolded and a folded position, and wherein the upper fin part and the fin root may be locked relative to one another using a slot-and-key system when the upper fin part is in the unfolded position.

Abstract: A projectile that includes strakes mounted about the perimeter of the midsection of the projectile and a pusher plate assembly mounted about the aft of the projectile so that a sub-caliber projectile may be fired from a larger caliber gun. The pusher plate assembly forms a seal with the bore at the aft end of the projectile. The strakes maintain the center line position of the projectile within the bore. The pusher plate assembly further designed to fragment upon exiting the bore while the strakes remain with the projectile to enhance aerodynamic qualities of the projectile in flight.

Abstract: The invention relates to a fin deployment mechanism (1) comprising a base unit (3), deployable fins (8) movably arranged on the base unit (3) and, in the retracted position, bearing against the base unit (3), as well as a gas-generating device, in which the fins in the retracted position are fixed to the base unit, and in which at least one gas duct (6, 7) is arranged in the base unit (3) so as to conduct pressurized gas generated by the gas-generating device to the bottom side of the fins (8), which in the retracted position bear against the base unit (3), in order to create a force which acts on the fins (8) for deployment of the same (8?). The invention further relates to an artillery projectile comprising a fin deployment mechanism.

Abstract: 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.

Abstract: A multi-stage drive includes a linear actuator configured for linear movement along an actuation axis, and a control surface. The control surface is operatively connected to the linear actuator for rotation about a deployment axis in a deployment stage, and for rotation in a control stage about a control axis that is different from the deployment axis, so that movement of the linear actuator along the actuation axis drives rotation of the control surface in both the deployment stage and in the control stage.

Abstract: A temporary control fin stop system employs a housing coupled to a vehicle. At least one tang is coupled to the housing and positioned to engage a trailing edge of a fin. The tang is ablatively erodible at a predetermined temperature induced by a flight profile of the vehicle to allow unconstrained motion of the fin.

Abstract: An air vehicle, as well as a method for folding an air vehicle for storage, may include a fuselage and a wing connected to the fuselage. The wing may include two ends positioned opposite from each other, and the wing may be substantially perpendicular to the fuselage. At least one of the ends may define a space therebetween the fuselage and the wing. The space may be sized to receive a potion of the wing when the wing is wrapped around the fuselage.

Abstract: Obliquely folding articulating wing mechanisms that include a wing rotatingly connected to a base.

Abstract: An air vehicle that is launched from inside a launcher, includes a release mechanism for releasing fins of the vehicle from a stowed condition to a deployed condition. The release mechanism includes a pin that is located within a cavity in the fuselage of the air vehicle. Pressurized gasses initially fill the cavity in the fuselage. The launcher includes a reduced-pressure portion such as from a muzzle brake. When the air vehicle passes into the reduced-pressure portion of the launcher, the gas pressure behind the air vehicle is reduced. This causes the pressurized gas within the cavity to drive the release mechanism backwards out of the cavity. The length of the pin may be used to control the timing of the fin deployment, the delay between the initial movement of the release mechanism out of the cavity, and when the fins are released.

Abstract: A method and system for piloting a craft with a rear propulsion unit are disclosed. The method can include a servo loop where the attitude (?M) of the craft (1) is measured in the vicinity of the rear end (1R) of the craft, then the orientation (?) of the propulsion means (2), which can be oriented relative to the rear end (1R), is adjusted as a function of the attitude measurement (?M) in such a way that the craft (1) is stabilized on its flight path.

Abstract: The invention relates to a shell (1) arranged with extensible wings (3) having improved guidance characteristics during the gliding and final phase of the shell (1). The invention is characterized in that the extensible wings (3), via threaded wing fixtures (8), are movably arranged on rotatable axial guide shafts (6) on the shell body (2) for separate or simultaneous displacement of the wings (3) in the longitudinal direction A of the shell (1), for guidance of the shell (1) in the vertical and lateral directions during the trajectory phase of the shell, and in that the wings (3) are also rotatably arranged on radial guide shafts for controlling the angle of incidence of the wings (3) during the final phase of the shell (1).

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 aircraft includes a fuselage, horizontal front and tail empennages and take-off and landing wings, which wings are jointed to the fuselage by means of attachment joints, the axes of which are situated above the fuselage central line along the longitudinal axis of symmetry thereof so that the take-off and landing wings are arranged below the attachment joints along the longitudinal axis of symmetry of the fuselage. The outer surface of the wings is the extension of the outer surface of the fuselage and in a stow position the take-off and landing wings cover at least 30% of the fuselage surface area between the horizontal front and tail empennages.

Abstract: 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, such that the housings communicate at their intersection point, each housing being blocked by sealing device preventing any fluid from the exterior of the projectile body from passing through the housings when the control surfaces are deployed.

Abstract: Disclosed are a wing assembly including a wing movably accommodated in a launch tube, and a buffer unit detachably mounted to the wing to come in contact with the launch tube and configured to be separated from the wing after the wing comes out of an inner space of the launch tube, and an apparatus for launching a flying object having the same.

Abstract: A projectile (1) for a small arms weapon. The projectile (1) comprises a projectile body (3) and a plurality of external peripheral fins (2) pivotable from a radially un-deployed position to a radially deployed position. When in the radially deployed position, each fin (2) is moveable in longitudinal direction into an engaged position with the projectile body (3) for radially securing the fin (2).

Abstract: A foldable deployable panel device (12) attached to a body (16) of an object is disclosed. The device includes a panel pivotally attached to the body by a first pivot element (40/42) at a first pivot position and a second pivot element (29) at a second pivot position. The first pivot element (40/42) is disengageable from the first pivot position, when the panel (12) is aligned in a predetermined orientation. The second pivot element (29) is fixed at the second pivot position, when the first pivot element (40/42) is engaged at the first pivot position. The panel (12) is urged by an energy storing element (28), when the first pivot element (40/42) is disengaged from the first pivot position, to move into a deployed position.

Abstract: A missile has a flight termination system that includes deployable lift surfaces that deploy forward of a center of gravity of the missile. When deployed, the lift surfaces cause the missile to rotate about its longitudinal axis. This rotation eventually increases in rate until the missile nears a natural roll frequency of the missile. As the missile nears or reaches its natural roll frequency, the missile's nose pitches up, angle of attack diverges and the missile tumbles, resulting in rapid termination of flight by loss of aerodynamic lift, vertical plunging and crashing. The lift surfaces may be curved surfaces that conform to the shape of a fuselage of the missile, prior to the deployment of the lift surfaces. The lift surfaces may be canted slightly relative to a missile longitudinal axis when the lift surfaces are deployed, so as to provide a sufficient rolling moment to overcome aerodynamic damping or resistance (roll drag) of the missile.

Abstract: A foldable deployable panel device attached to a body of an object is disclosed. The device includes a panel pivotally attached to the body by a first pivot element at first pivot position and a second pivot element at a second pivot position. The first pivot element is disengageable from the first pivot position, when the panel is aligned in a predetermined orientation. The second pivot element is fixed at the second pivot position, when the first pivot element is engaged at the first pivot position. The panel is urged by an energy storing element, when the first pivot element is disengaged from the first pivot position, to move into the deployed position.

Abstract: Some embodiments pertain to a projectile that includes a casing and a plurality of fins which are secured to the casing. Each of the fins is movable between a stowed position and a deployed position. The fins are typically in the stowed position during storage and launch, and move to the deployed position as soon as possible after launch. Each fin includes a first foil that has a first set of openings and a second foil that includes a second set of openings. The first sets of openings in the first foils are aligned with the second sets of openings in the second foils when each of the fins is in the stowed position. The first sets of openings in the first foils are not aligned with the second sets of openings in the second foils when each of the fins is in the deployed position.

Abstract: A system and process for the aerodynamic stabilization of rocket-assisted artillery projectiles launched from smooth-bore cannons comprises multiple stabilization fins stowed circumferentially and held by a cap until muzzle exit. At muzzle exit, the cap separates and allows the fins to self-deploy using the energy stored within the fin material, which is either shape memory alloy or spring steel. The fins are then locked into place and serve to stabilize the projectile without interfering with the discharge of hot propelling gasses from the rocket nozzle.

Abstract: Some embodiments pertain to a projectile that includes a casing and a plurality of fins which are secured to the casing. Each of the fins is movable between a stowed position and a deployed position. The fins are typically in the stowed position during storage and launch, and move to the deployed position as soon as possible after launch. Each fin includes a first foil that has a first set of openings and a second foil that includes a second set of openings. The first sets of openings in the first foils are aligned with the second sets of openings in the second foils when each of the fins is in the stowed position. The first sets of openings in the first foils are not aligned with the second sets of openings in the second foils when each of the fins is in the deployed position.

Abstract: 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.

Abstract: 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.

Abstract: A supercavitating projectile is disclosed that has deployable fins. The fins are pivotally coupled to the body of the projectile. The fins have two primary states: stowed within a recess at the surface of the projectile and deployed to a radially-extended position relative to the body of the projectile. The fins deploy as the projectile leaves its launch tube. The fins function as a control surface, interacting with the wall of the vapor cavity in which the supercavitating projectile travels.

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 Reconfigurable Nose Control System (RNCS) is designed to adjust the flight path of spin-stabilized artillery projectiles. The RNCS uses the surface of a projectile nose cone as a trim tab. The nose cone may be despun by the action of aerodynamic surfaces, to zero spin relative to earth fixed coordinates using local air flow, and deflected by a simple rotary motion of a Divert Motor about the longitudinal axis of the projectile. A forward section of the nose cone having an ogive is mounted at an angle to the longitudinal axis of the projectile, forming an axial offset of an axis of the forward section with respect to the longitudinal axis of the projectile. Another section of the nose cone includes another motor, the Roll Generator Motor, that is rotationally decoupled from the forward section and rotates the deflected forward section so that its axis may be pointed in any direction within its range of motion.

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 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.

Abstract: A MEMS type flow actuated out-of-plane flap apparatus includes a substrate defining a plane; a duct attached to the substrate, the duct and the substrate defining a fluid flow channel; and a rotatable flap having a flow receiving portion and an extension portion. The flow receiving portion being disposed in the fluid flow channel where, in an actuated position of the flap, a fluid flow against the flow receiving portion causes rotation of the flap and movement of the extension portion out of the plane of the substrate.

Abstract: A missile has fins that rotate about a single axis to deploy from a stowed position to a deployed position. A foil longitudinal axis of each fin is angled relative to a shaft of the fin, such that a single-axis rotation of the shaft moves the foil from the stowed position to a deployed position. A coil spring may provide both torsion and compression forces to rotate the fin into the deployed position and lock it into place. Torsion rotates the shaft until it reaches a seat on a bushing that is around the shaft. Then compression forces from the spring engage a keyed protrusion on the shaft with a corresponding keyway in the bushing, locking the shaft in place. There may be an additional lock once the fin is deployed, such as a spring-loaded pin in the missile body that engages a depression in the shaft.

Abstract: A hold down device positioned on the projectile to exert a known spring force in opposition to the centrifugal force provides an inexpensive, light weight and reliable delayed fin deployment mechanism for boosted fin-stabilized spinning projectiles. When the forcing moment produced by the centrifugal force acting on the fin exceeds the opposing moment produced by the hold down device, the hold down device will release the fin allowing it to swing into its deployed position. Thus, proper selection of the spring force and positioning of the hold down device will cause the fins to deploy at a predetermined spin rate. The spin rate can be correlated to a time or travel distance of the projectile from launch. The incorporation of the hold down devices requires minimal design changes to existing rockets and may, in some cases, be retrofit to the existing base of rockets if desired.

Abstract: An apparatus for deploying a wing of a guided missile comprises a fixed wing fixedly coupled to a body of a guided missile, a rotary wing rotatably coupled to the fixed wing, and a deploying portion for rotating the rotary wing into an unfolded state from a folded state by providing a torsion force to the rotary wing. In the apparatus, a folded degree of the rotary wing can be maximized.

Abstract: The Dual-Sliding Fin Lock Assembly provides a simple, cost-effective and secure locking mechanism that engages on the initial opening stroke of a fin of a flying object, using a minimal number of parts that are easy to manufacture. Two sliding locks, each having a protruding step, engage with two fin lugs each of which has a corresponding notch. When a step and a notch fit together, they form a contact plane which may be straight horizontal or inclined to ensure robust locking operation without the need for extremely tight tolerances on the individual parts or on the assembly. Since the sliding locks do not rotate around the pin that holds the fin lugs, they engage the fin lugs to arrest the rotation of the fin and retain it securely in the deployed position for the duration of the object's flight, guiding the object more accurately toward its destination.

Abstract: This disclosure relates to a method of limiting the yawing motion on the trajectory of an artillery shell during the firing phase using a sliding driving band and completely folded-in guide fins. The shell is converted as soon as possible outside the mouth of the barrel of the firing piece by fold-out of the guide fins into a fin-stabilized artillery shell. Any form of non-uniform fin fold-out is avoided by virtue of all the guide fins being interconnected to form a system which gives all the fins the same movement pattern and the same fold-out speed in each phase of fin fold-out. This disclosure also includes a shell in which synchronization of fin fold-out includes a rotatable control ring that is arranged around the axis of the shell and is connected to the rotation spindles of all the fins.