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

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

Abstract: A 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.

Abstract: 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.

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: 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: 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.

Abstract: A folding control surface assembly includes a torsion shaft, a base, and a control surface hingedly attached to the base via the torsion shaft, such that the torsion shaft biases the control surface toward an unfolded configuration with respect to the base. A vehicle includes a body and at least one folding control surface assembly. The at least one folding control surface assembly includes a torsion shaft, a base attached to the body, and a control surface hingedly attached to the base via the torsion shaft, such that the torsion shaft biases the control surface toward an unfolded configuration with respect to the base.

Abstract: A locking mechanism for securing an articulated folding wing assembly in a fully extended position by means of a tapered locking plunger urged by a coiled compression spring to contact a complementary mating surface formed on the wing assembly. The spring urged locking plunger is released from a retracted position by rotation of the wing assembly from the folded position to the extended position. A folding mechanism for rotating the wing assembly through a compound angle from the folded position to a rigid and positively locked fully extended position is provided wherein the extended wing may be rotated about its longitudinal axis to provide directional control to the vehicle.

Abstract: 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.

Abstract: A system, device and method provide an exhaust assembly adapted for use with a mass ejection drive system to produce rotational torque about the principle axis of the drive system. Representative features generally include a vane suitably configured to at least partially engage a mass ejecta stream to apply a net rotational torque about the principal axis of the drive system, and a tailfin coupled to the at least one vane. The tail fin is configured to selectively deploy from an at least partially stowed position in order to decrease the application of net rotational torque about the principal axis of the drive system.

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

Abstract: A projectile 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 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 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 launcher has programmable keys that activate a programming device to communicate with a flying toy to set up any one of multiple different motions of the toy. This is affected when the flying object and the launcher are connected together. Different combinations of program keys include changing of speed and landing procedures. The flying toy includes a receiver that operates a motor, and the flying object is clipped on the launcher and ejected after a user triggers the release button on the launcher.

Abstract: 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.

Abstract: 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.

Abstract: The inventive multi-environment engine (1) comprises a body (2), wings (4, 5) and a propulsion system (8), wherein at least one wing is foldable between a first levitation flying position, a second levitation position for travelling on a water surface and a third diving position.

Abstract: A reconnaissance system that comprises a projectile (10) that has an opening (17) through which images of a target area can be acquired. The projectile (10) is launched from a portable launcher (30) towards the target area, and comprises image acquiring means (13, 14) for acquiring images of the target area through the opening (17) and for transmitting the images to a remote station (70); means for stabilizing the projectile (10) and/or the image acquiring means (13, 14) while flying in a nearly-parabolic trajectory above the target area; and a remote station (70), for receiving and displaying the transmitted images that comprises a monitor (71) for displaying the transmitted images.

Abstract: In order to move a textile braking element (16) which is in the form of an annular disk and which is deployed radially under the effect of centrifugal force rapidly into a contour which is stable in respect of shape and which is always properly defined even under afflux flow conditions, a cloth (33) which is cut in the form of a circular ring is provided by virtue of radially extending tucks or darts, with a reduced outside periphery (32) in such a way that the opening movement is thereby limited to the shape of a flat obtuse-angled hollow truncated cone which, by means of reinforcing bands (34) which are sewn on along generatrices of the frustoconical surface, is pivotably mounted to the holding ring (15) at the inside periphery (31) while along the outside periphery (32), it is provided with a peripherally extending accumulation of mass (29) for increasing the centrifugal deployment forces; wherein in the front end region of the stowage space (14), the ring (15) is axially fitted into the contour of the fus

Abstract: Methods and apparatus are provided for a missile that includes a housing, a fin, and a first actuator. The housing has a slot formed therethrough. The fin is disposed within the housing proximate the slot. The first actuator is coupled to the fin and configured to selectively move the fin at least partially in and out of the housing through the slot.

Abstract: A fin locking mechanism for locking in place, and subsequently unlocking fins for installation on a missile having a plurality of otherwise moveable fins. Where the fins are mounted to a crank arm, there is a locking detent, with a locking notch, integral to the crank arm. A spring loaded locking plunger has an end which fits into the locking notch. The locking plungers are mounted into the assembly housing locking plunger channels. A base plate is spaced from the locking detent such that when one end of the locking plunger is fitted into the locking notch, the other end of the locking plunger is slidably pressed against the base plate by the spring loading, and the locking plunger is relatively perpendicular to the base plate. The base plate also has a plurality of locking plunger recesses, wherein when one end of the locking plunger resides in the locking plunger recesses, the other end of the locking plunger will not reach the locking notch and therefore the fins will be unlocked.

Abstract: A method for enhancing an aerodynamic performance of an unmanned projectile. The method including at least one of the following: (a) morphing a cross-sectional shape of the projectile after launch thereof; (b) morphing a longitudinal shape of the projectile after launch thereof; (c) bleeding a fluid at a base of the projectile during flight thereof: (d) varying a base cone angle of the projectile as a function of speed thereof; (e) deploying at least one wing from a body of the projectile after launch thereof; and (f) deploying a fin from the body of the projectile after launch thereof.

Abstract: A hypersonic vehicle having in one or more embodiments a control surface that is movable to a deployed position. The control surface is movable in a pivotal manner that establishes a gap between the leading edge of the control surface and the outer surface of the vehicle to provide a flow path. The gap allows a boundary layer along the outer surface of the vehicle to pass through the flow path with out separation from the outer surface, to further improve the effectiveness of the control surface.

Abstract: A fin control assembly includes a housing, an arm configured to couple to a fin and to steer the fin relative to the housing, and a locking member disposed within the housing. The locking member is configured to (i) lock the arm in a substantially fixed state to inhibit movement of the arm relative to the housing when the locking member is in an engaged position, and (ii) unlock the arm from the substantially fixed state to allow the arm to steer the fin relative to the housing when the locking member moves from the engaged position to a disengaged position. The locking member has a cylindrical body portion and a cylindrical end portion, which is eccentric with the cylindrical body portion, to enable the locking member to lock the arm in the substantially fixed state while the arm holds the fin in a neutral location.

Abstract: Asymmetrical Control Surface System for Tube-Launched Air Vehicles places one control surface, such as a wing or a horizontal tail, above horizontal midplane axis of an air vehicle, such as a tube-launched missile, and the opposing control surface below the midplane axis. Such asymmetrical arrangement of the control surfaces increases the lift and maneuverability of the air vehicle during flight. For stowage inside the tube prior to launch, each control surface slides into its corresponding slot in the body of the vehicle, making the entire control system compact.

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

Abstract: The invention relates to a canard fin unit intended for guiding artillery projectiles (1) fired on ballistic trajectories, which comprises a number of identical canard fins, deployable from a first passive, retracted position into a second active position once the projectile (1) associated with the fin unit has been launched from the barrel from which it is intended to be fired, the canard fins (3a–d) in the active position being individually controllable. The invention resides in the fact that each canard fin (3a–d) is individually supported and controlled in its own swivel arm (6a–d), extending in the longitudinal direction of the projectile, which arm is in turn pivoted about its own swivel shaft (7a–d) arranged transversely to the direction of flight of the projectile, the swivel arms (6a–d) of all canard fins (3a–d) being moved together from the retracted to the deployed position by one and the same operating element (10), displaceable in the longitudinal direction of the projectile.

Abstract: A fin assembly includes a fin base, a fin tip rotatably connected with the fin base, and means for selectively locking the fin tip in a chosen configuration. A vehicle includes a body defining a cavity therein and defining an opening through a wall thereof, a fin control mechanism disposed within the cavity, and a fin base having an axle extending through the opening and engaged with the fin control mechanism. The vehicle further comprises a fin tip rotatably connected with the fin base, and means for selectively locking the fin tip in a chosen configuration. A method for configuring a fin assembly on a vehicle includes providing a fin tip rotatably connected with a fin base being operably coupled with the vehicle and selectively locking the fin tip in a first position relative to the fin base.

Abstract: An articulated wing (20) is readily deployable from a stowed configuration that occupies minimal volume to an extended configuration for flight. The wing (20) includes a frame (24) having a pair of beams (30) spaced by one or more ribs (36), and a flexible covering material (26) over the frame (24) that defines the surface of the wing (20). Each beam (30) typically has multiple segments (40), and each segment (40) is pivotally connected to an adjacent segment (40) at a joint (42). A flexible actuation line (52) extends past each joint (42) and is attached to a portion of the beam beyond the joint. The beam (30) also includes portions that act as stops (46). The stops (46) limit the range of angular motion through which the respective segments (40) can rotate relative to one another. Consequently, when tension is applied to the line (52), the segments (40) rotate until respective stops (46) prevent further rotation. Tension in each line (52) keeps the wing (20) in its extended configuration.

Abstract: A method and structure for a full-bore artillery projectile fin deployment device comprising a projectile stabilization fin comprising an aperture and a movable pawl; a rod comprising a head portion and a shaft portion terminating with a beveled tip configured for engaging the pawl; a tailboom configured for housing the fin, wherein the tailboom comprises a hollow bore configured for receiving the rod; a pin slotted through the aperture and attached to the tailboom; and a bias member adjacent to the head portion of the rod. The rod is slotted to simultaneously engage a plurality of fins. The tailboom comprises a forward end and a rearward end and a slot configured for permitting the fin to articulate out of the tailboom, and wherein the tailboom connects to a projectile. Additionally, the power source for the device is the naturally occurring launch accelerations.

Abstract: A mechanism to alter the flight path of a projectile after launch. A plurality of fins are disposed around the projectile and are held in place by one or more caging wires, depending on fin design. In one embodiment, auxiliary fins are connected to adjacent main fins which are held in a stowed position. When released, the fins deploy and present a continuous surface to the airstream for maximum braking action. In another embodiment, each fin is divided into fin segments which are individually deployable to alter the spin or course of the projectile by deflection. Additionally, all of the fins may be deployed to provide a braking action. All of the fins are tied together to distribute and reduce encountered loads when deployed.

Abstract: An extendable wing system for a fluid-born body has a forward wing and an aft wing pivotably coupled together at a location outward of their wing roots. A linkage mechanism mounted on the body provides both pivoting of the wing roots about a pivot point and translation of the wing roots and their pivot points to extend the joined wings from a stowed position to a deployed position. Translation of the forward wing root pivot point allows the stowed wing system to occupy additional space toward the nose of the body, thereby allowing use of wings having a longer wingspan and greater aspect ratio. The linkage mechanism can also be used to incorporate flight control, such as roll and pitch control, directly into the wing system. In another embodiment, the wings can incorporate actuator elements on or within the wings to effect flight control by deformation of the wing structure.

Abstract: A fin deployment system for missiles and munitions that deploys and activates straight flat fins for roll control authority. The fin deployment system employs numerous design features, among which are the following: A wrap-around fin concept generates space-savings within a projectile body whereby the fins are arranged in a wrapped configuration around a boomtail structure. The fins may be constructed of a super-elastic material; the system eliminates mechanical means of deploying the wrapped fins, eliminating the need for springs to deploy the fins. The fin deployment achieves substantial space savings for increasing the onboard towing capacity of electronic packaging or lethality in the missiles and munitions systems, while at the same time providing a good roll control authority during flight by enabling a straight fin deployment resulting from the use of super-elastic materials.

Abstract: The center of pressure of a projectile is caused to move upon the occurrence of an event that changes the static margin, such as the jettisoning of a body previously attached to the projectile, as noted above. In particular embodiments, this is achieved by a flare disposed toward the rear of the projectile. The flare has petals that deploy from a first, stowed position to a second, deployed position upon the occurrence of said event. In the stowed position, the petals are aligned with the air stream, in order to minimize drag. In the deployed position, the petals project into the air stream in such a way as to move the lift center rearward. A slide ring within the flare has sufficient inertia that it shifts aft in response to an acceleration that occurs when the attached body and the projectile are separated from one another. The slide ring is linked to the petals in such a way that the petals are deployed by the displacement of the slide ring.

Abstract: A projectile comprises an imaging seeker at a front of the projectile; a front warhead behind the imaging seeker; a power supply; an electronics unit connected to the power supply and comprising a microprocessor circuit board, a voltage regulator circuit board, an inertial measurement circuit board and a fuze and safe and arm circuit board, all electrically connected to each other, the microprocessor circuit board also being connected to the imaging seeker; a rear warhead, the front and rear warheads being electrically connected to the safe and arm circuit board; a rocket motor electrically connected to the electronics unit; foldable fins mounted at the rear of the projectile; a shell that encases the front warhead, the power supply, the electronics unit, the rear warhead and the rocket motor; and a maneuver mechanism disposed in the shell and electrically connected to the microprocessor circuit board.

Abstract: A locking device with a solenoid release actuator includes a housing, a plunger axially slidable within the housing, a biasing member for biasing the plunger in a first direction, one or more locking balls, and the locking balls disposed in an aperture in the housing, the plunger having a portion thereof containing at least one recess for receiving the balls, a member to be locked being held in a first locked position with the plunger in a first locking position and the balls in a radially outward position, the plunger being positioned axially such that the recesses therein are not in alignment with the apertures, and a solenoid coil disposed in the housing around the plunger, for inducing a magnetic force to move the plunger against the biasing member such that the recesses align with the apertures and the balls are movable radially inward into the recesses thereby releasing the locked member.

Abstract: Method and arrangement for extending the range of fire of a fin-stabilized artillery missile. The fin-stabilized artillery missile (1), which is fired in a ballistic trajectory, has fins (3-6), which have been given a sawtooth-shaped leading wing edge (7) that has been found to give the missile (1) an extended range of fire and improved manoeuvrability.

Abstract: A method for enhancing an aerodynamic performance of an unmanned projectile. The method including at least one of the following: (a) morphing a cross-sectional shape of the projectile after launch thereof; (b) morphing a longitudinal shape of the projectile after launch thereof; (c) bleeding a fluid at a base of the projectile during flight thereof: (d) varying a base cone angle of the projectile as a function of speed thereof; (e) deploying at least one wing from a body of the projectile after launch thereof; and (f) deploying a fin from the body of the projectile after launch thereof.

Abstract: The present invention relates to a fin-stabilized artillery shell (1) comprising a body part (8, 26, 36) which can be axially displaced rearwards, in the direction of flight of the shell, once the latter has left the barrel from which it has been fired, and which in the original position is fully retracted in the shell (1), and in which a number of deployable fins (18, 24, 29-30, 42-47) are in turn secured, and from which the fins are automatically deployed as soon as the body part has reached its rear position in which it is locked relative to the rest of the shell. One of the advantages of the invention is that in the flight position it gives the shell a greater length than is permitted by the charging position of the artillery piece launching the shell. This gives the shell considerably better stability in its trajectory towards the target.

Abstract: A fin cover release and deployment system designed for high G forces of gun-launched missiles. In one embodiment, a pyrotechnic actuator drives actuator arms to first release and eject the fin slot covers, followed by deployment of the fins radially outward to the steering position. Following complete ejection of the covers, the fins are driven outwardly by cam surfaces along the latch arms, followed by a spring and wedge mechanism installed interiorly of the fin steering shaft to lock the fins in the fully deployed state. In another embodiment, a motor and rotating threaded shaft replace the pyrotechnic actuator.

Abstract: A missile, either a powered missile or an unpowered projectile, includes a freely-rolling tail assembly having an odd number of fins. Having an odd number of fins may reduce oscillations caused by the rotation of the freely-rotating tail. This may make a more stable platform for a seeker, such as an uncooled focal point array or other imaging infrared (IIR) or millimeter wave radio frequency (MMW) seeker, in the body of the missile. Also, minimizing oscillation by using an odd number of fins may facilitate control of the missile.

Abstract: A method for protecting a second location against a first projectile fired from a first location at the second location. The method includes: firing at least one second projectile toward the first projectile; and deploying one or more projections from the second projectile to increase its footprint and increase the probability of destroying or changing the trajectory of the first projectile.

Abstract: Actuators already present as an integral part of the control systems of missiles and the like are used to activate and control the deployment of fins and the like without the need for separate explosively or mechanically driven fin deployment systems. Springs located in hinges on the fins accomplish the complete deployment of the fins after proper orientation by the actuators.

Abstract: The present invention relates to a fin-stabilized missile (1) of the type which is intended to be fired at high acceleration towards a defined target along its trajectory and which can be guided in the trajectory and which, for stabilizing it in the trajectory, is provided with stabilizing fins (3, 32) arranged at its rear end, and control elements (6, 7) which are arranged at its front end and are intended to guide the latter, and whose rear part, in which the fins are secured, consists of a body part (4, 31) which can rotate freely relative to the main part (1, 29) of the missile about a bearing (14, 36) arranged concentric to the longitudinal axis (L) of the missile (1).

Abstract: The center of pressure of a projectile is caused to move upon the occurrence of an event that changes the static margin, such as the jettisoning of a body previously attached to the projectile, as noted above. In particular embodiments, this is achieved by a flare disposed toward the rear of the projectile. The flare has petals that deploy from a first, stowed position to a second, deployed position upon the occurrence of said event. In the stowed position, the petals are aligned with the air stream, in order to minimize drag. In the deployed position, the petals project into the air stream in such a way as to move the lift center rearward. A slide ring within the flare has sufficient inertia that it shifts aft in response to an acceleration that occurs when the attached body and the projectile are separated from one another. The slide ring is linked to the petals in such a way that the petals are deployed by the displacement of the slide ring.

Abstract: The present invention relates to a long-range artillery shell (1) that is fin-stabilised in its trajectory and which is designed to be fired in a rifled gun barrel and thus has a slipping driving band (8) as main contact surface with the inside of the barrel, and has a so-called base-bleed unit (3) with a number of stabilization fins (9-14) that are deployable after the shell has left the barrel.

Abstract: A projectile (12) to be fired from a rifled barrel (66) is described. At its tail (10) it has control surface vanes (14) which can be pivoted out from a sub-calibre launch position into an over-calibre functional position. To protect the inwardly folded vanes (14) and to protect further ballistic and sensor structures at the tail end of the projectile (12), a securing pot (18) is temporarily fixed to the tail (10) of the projectile (12), the securing pot having a pot peripheral portion (22) and a pot bottom (24). There is a pressure chamber (32) between the tail end face (26) of the projectile (12) and the pot bottom (24) of the securing pot (18). The pot bottom (24) has at least one propellent gas inlet (34) which opens into the pressure chamber (32). When the projectile (12) is fired from the barrel propellent gas flows through the propellent gas inlet (34) into the pressure chamber (32) so that a correspondingly high propellent gas pressure is produced in the pressure chamber (32).

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