Abstract: Systems for controlling flow effector control surfaces. The system comprises a flow effector control coupled to an elongated bar at one end of the bar. The elongated bar is coupled at the other end to the middle of a T-shaped member. A compliant link is coupled to the bar between the control surface and the T-shaped member. At each end of the T-shaped member is coupled a shape memory alloy wire which acts as an actuating means. When one of the shape memory alloy wire contracts, the elongated bar pivots about the compliant link and activates or retracts the flow effector control surface.

Abstract: A system and method are disclosed for determining relative motion between ship-based combat system elements using accelerometers. Relative motion between combat system elements can introduce error into the targeting information provided to the weapons system, and thus the system facilitates compensation for such relative motion. The system includes accelerometers mounted on radar systems, inertial navigation system (INS) sensors, and weapons systems. An algorithm is disclosed in which the raw accelerometer signals are filtered, then combined with ship INS attitude signals in a displacement calculation module (DCM). Within the DCM, the signals are manipulated to calculate, for each combat system element, the translational and rotational displacements due to hull modal vibration and the translational and rotational displacements due to force vibration. The sum of these values represent the movement of each of the affected combat system elements.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A missile (10) comprising a projectile body (20), a payload (60) contained within the nose portion (30), wings (70) stowed within the mid portion (40), and fins (80) stored within the tail portion (50). The wings (70) can be deployed during intermediate stages of the flight path when lift is advantageous, and re-stowed during terminal stages when an almost vertical angle-of-attack is desired. The fins (80) function as stabilizing components during the early ballistic stage of the flight path and function as guiding components thereafter.

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 wing pivot mechanism that is configured to pivot two wings about a single pivot axis of a vehicle, such as an aircraft. The wing pivot mechanism includes a hub, a set of gears positioned at least partially within an interior region of the hub, and two wings that are rotatably connected to the hub. Each wings includes a gear surface extending therefrom. Each gear of the hub assembly engages a gear of a respective wing such that rotation of the gears of the hub assembly causes rotation of the gears of the wings and pivoting of the wings about the single pivot axis in opposite rotational directions between a stowed position and a deployed position. A releasable locking mechanism is provided for locking the wings in a fixed rotational position in both the deployed position and the stowed position.

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

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

Abstract: A 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 mai

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

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

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

Abstract: A 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 stowable wing structure incorporates a wing having a span equal to a fuselage length and movable from a stowed position longitudinally aligned with the fuselage to a deployed position perpendicular to the fuselage. A pivot offset laterally from a centerline of the fuselage and aft from a symmetry point on the centerline with a corresponding offset forward toward the leading edge from a chord centerpoint on the wing allows rotation of the wing from the stowed position to the deployed position with the rotation resulting in an aft position of the chord center point relative to the fuselage symmetry point.

Abstract: A position controller capable of controlling the depth or lateral position of a towed array. The position controller comprises a tubular fuselage from which a pair of wings may be extended over a range of sweep angles between fully open and stowed positions. In fully or partly open positions, two wings present a positive angle of attack relative to the axis of the fuselage. In the stowed position, the wings are fully retracted into a wing receptacle within the fuselage for unfettered passage into and out of a submarine on the array deployment and retrieval handling system.

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: A portable unmanned air vehicle and launcher system that includes a foldable unmanned air vehicle having a pressure tube; a launch gas reservoir for holding launch gas; a launch tube operatively connected to the launch gas reservoir and having a free end that is positioned in the pressure tube of the air vehicle; a free piston positioned within the launch tube; and a free piston stop to prevent the free piston from leaving the launch tube. A first portion of the launch gas in the launch gas reservoir is released into the launch tube and forces the free piston from an initial position to an end position at which the free piston is stopped by the free piston stop.

Abstract: A guided projectile has a deployment system for deploying a deployable structure, such as a fin, another type of control surface, or an antenna. The deployment system includes a single-piece body that has a hub body and a resilient tab. The resilient tab presses against a stepped surface of a guided projectile body. As the deployable structure is extended, the deployable structure body rotates about a shaft in a central hole or aperture in the hub body. The resilient tab presses against the stepped surface on one side of an edge of the stepped surface during a first (relatively stowed) part of this deployment. At a certain point, as the contact between the tab and the stepped surfaces reaches the edge (the step of the stepped surface), the resilient tab changes position. The change in position of the resilient tab keeps the deployable structure from retracting again.

Abstract: An apparatus includes means for biasing a first airfoil of a vehicle toward a fully deployed position, means for restraining the first airfoil in a stowed position, means for releasing the first airfoil from the stowed position, means for restraining the first airfoil in a partially deployed position, and means for releasing the first airfoil from the partially deployed position. A method includes restraining an airfoil in a stowed position, releasing the airfoil from the stowed position, and biasing the airfoil from the stowed position toward a fully deployed position. The method further includes restraining the airfoil in a partially deployed position, releasing the airfoil from the partially deployed position, and biasing the airfoil from the partially deployed position toward the fully deployed position.

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

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

Abstract: An aircraft includes a fuselage, and first and second freewings. Each of the first and second freewings is separately mounted to the fuselage and independently freely pivotable about respective pivot axes. The aircraft includes an angular rate sensor configured to measure a roll rate of the fuselage and to output a first roll rate signal. The aircraft includes a controller in communication with the angular rate sensor and configured to receive a second roll rate signal from the pilot and to compare the first and second roll rate signals to generate first and second control surface control signals. The aircraft includes at least one control actuator in communication with the controller and configured to actuate a first control surface of the first freewing and a second control surface of the second freewing in response to the first and second control surface control signals, respectively, to control the roll rate of the aircraft.

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 air-launched aircraft includes deployable wings, elevons, and vertical fins that deploy from a fuselage during flight. The aircraft may include a control system for operating the elevons, a communication system, and batteries for powering the systems. In addition, the aircraft may include a payload module that mates with an interface in the fuselage. The payload module may include any of a variety of payloads, including cameras, sensors, and/or radar emitters. The aircraft may be powered or unpowered, and may be very small, for example, less than on the order of 10 kg (22 pounds). The aircraft may be employed at a low cost for any of a wide variety of functions, such as surveillance, or as a decoy. The deployable surfaces of the aircraft may be configured to deploy in a pre-determined order, allowing the aircraft automatically to enter controlled flight after being launched in a tumbling mode.

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: 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: The invention relates to an actuator system for a projectile having a first and second pair of opposing steering fins disposed in a transverse plane of the projectile. The first pair of opposing steering fins includes a first fin and second fin. The second pair of opposing steering fins includes a third fin and a fourth fin. The actuator system comprises a first motor assembly configured to control the position of the first pair of opposing steering fins, and a second motor assembly configured to control the position of the second pair of opposing steering fins. The first motor assembly and second motor assembly are mounted axially along an axis of the projectile such that a first portion of the first motor assembly is telescopically received within a second portion of the second motor assembly.

Abstract: This disclosure relates to a method and an arrangement for low or non-rotating artillery shells fired from launch weaponry, and which introduces a portion of the barrel pressure built up in the barrel during the launch phase into a chamber arranged in the low or non-rotating artillery shell which is delimited in at least one direction by an element which is movable relative to the rest of the shell when a differential pressure between the chamber and the external environment of the shell is sufficient to move the element. The moveable element may be a protective casing covering fins of the artillery shell.

Abstract: A winged vehicle includes an elongated fuselage, and a wing mechanism affixed to the fuselage. The wing mechanism has a wing-support-body track affixed to and extending lengthwise along the fuselage, a translating wing-support body engaged to and translatable along the wing-support-body track, and exactly two deployable cantilevered wings. Each deployable cantilevered wing has a wing pivot mounted to the translating wing-support body so that the deployable cantilevered wing is pivotable about the translating wing-support body. The two deployable cantilevered wings are each pivotable between a stowed position and a deployed position. An actuation mechanism is operable to controllably move the translating wing-support body along the wing-support-body track and to controllably move the two deployable cantilevered wings between the stowed position and the deployed position.

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: Apparatus for stowing and deploying a plurality of control surfaces of a guided air vehicle comprises: a housing including: a plurality of slotted openings along an outside surface thereof; and a corresponding plurality of cavities within the housing, each cavity extending to the outside surface of the housing through the slotted opening corresponding thereto and configured to accommodate span wise stowage of a corresponding control surface of the plurality, and each cavity having a section including an angled ledge and side wall support surface to accommodate stowage of the corresponding control surface in a span wise canted position with respect to the corresponding slotted opening.

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 self-propelled projectile which will maintain a straight trajectory through air or water.

Abstract: A deployment device for a fin of a projectile incorporating a hinge fixed to the projectile body which allows said fin to make a pivoting movement along at least one axis, wherein said hinge comprises a support for said fin mounted able to tilt over with respect to an axis substantially perpendicular to the projectile axis, said fin being linked to said support by a rod whose axis is substantially parallel to said projectile axis when said fin is in the folded position and substantially perpendicular to said projectile axis when said fin is in the deployed position, said rod itself being able to pivot with respect to said fin support when such said support tilts over, this pivoting of said rod being controlled by driving means.

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 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.

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 the 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 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: 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 the 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. Detents lock the slide ring in its displaced position.

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: 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 projectile for a weapon comprises an axially movable firing pin, an initiator actuable when impinged by the firing pin, a plurality of external peripheral fins movable from a radially inward position to a radially outward position when the projectile leaves the weapon, fin engaging means for moving each fin from the radially inward position to the radially outward position and for maintaining each fin in the radially outward position, and internal actuating means for actuating the fin engaging means to engage and thereby move the fins to deploy from the radially inward to the radially outward position as the projectile leaves the weapon.

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: 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 tacital base for a guided projectile includes a base structure, and an adaptor structure for securing the base structure to a forward section of the projectile. The base further includes a plurality of fin slots. A plurality of deployable fins are pivotally mounted to the base structure and supported for movement between a stowed position and a deployed position.