Abstract: A fuze booster includes a first explosive charge having a cavity with an annular portion of the first explosive charge encircling a first axial portion of the cavity and a semi-annular portion partially encircling a second axial portion of the cavity. The annular portion abuts the semi-annular portion. An explosively-inert material abuts the semi-annular portion, abuts the annular portion, and partially encircles the second axial portion of the cavity. A second explosive charge abuts the explosively-inert material, abuts the semi-annular portion, and partially encircles the second axial portion of the cavity. The second axial portion of the cavity is thus completely encircled by a combination of the semi-annular portion, the explosively-inert material, and the second explosive charge.

Abstract: Aspects of the disclosure relate to terminating flight of a balloon that may include separating a connection between a balloon envelope and a payload of the balloon. In one example, a payload separation apparatus includes a first shaft configured to attach to the envelope, a second shaft configured to attach to the payload, a pair of arms, and a bracket arranged to secure the pair of arms to the first shaft. In another example, a system includes a flight termination assembly having a cutting edge configured to cut an opening in the envelope and a payload separation apparatus. The apparatus includes a first shaft configured to attach to the envelope, a second shaft configured to attach to the payload, a pair of arms, and a bracket configured to secure the pair of arms to the first shaft. The system also includes a controller configured to activate the cutting edge.

Abstract: Aspects of the disclosure relate to terminating flight of a balloon that may include separating a connection between a balloon envelope and a payload of the balloon. In one example, a payload separation apparatus includes a first shaft configured to attach to the envelope, a second shaft configured to attach to the payload, a pair of arms, and a bracket arranged to secure the pair of arms to the first shaft. In another example, a system includes a flight termination assembly having a cutting edge configured to cut an opening in the envelope and a payload separation apparatus. The apparatus includes a first shaft configured to attach to the envelope, a second shaft configured to attach to the payload, a pair of arms, and a bracket configured to secure the pair of arms to the first shaft. The system also includes a controller configured to activate the cutting edge.

Abstract: A system of reconnaissance for the staging of a mission in a target area of a remote location in space is disclosed, including satellite surveillance means; a plurality of radio beacon/video camera transceiver means; communication means connecting the satellite surveillance means with the plurality of radio beacon/video camera transceiver means; communication means connecting the plurality of radio beacon/video camera transceiver means with at least one base station; and analysis means to analyze video, positional and other data from the target area.

Abstract: An apparatus and method for attachment of a payload or store to the external surface of an aerial vehicle includes a single point release feature. The apparatus includes an elongated base having a first distal end and a second distal end. A retention receptacle including a hollow tube is disposed adjacent the first distal end and is configured to removably receive and retain the store or payload. In addition, a release receptacle housing a release mechanism assembly is disposed adjacent said second distal end. When the release mechanism assembly is in the closed and locked position, the store or payload is retained to the vehicle via a spring loaded lock pin advanced into the retention receptacle. When the release mechanism assembly is in the open and unlocked position, the store or payload may be disengaged from the vehicle.

Abstract: Certain exemplary embodiments can provide a system, machine, device, manufacture, circuit, composition of matter, and/or user interface adapted for and/or resulting from, and/or a method and/or machine-readable medium comprising machine-implementable instructions for, activities that can comprise and/or relate to, providing a guided descent from a release zone and toward an entry zone.

Abstract: A system is provided for the force decay triggered release of a device, the system comprising: a base; a plurality of retention rods extending from the base; a rotationally movable actuator, to which a linear force is configured to be applied, converting the linear force to a rotational force; a plurality of retention pins, the retention pins being coupled to the actuator, and each the pin being removably disposed within a retention rod of the plurality of retention rods, such that a rotation of the actuator withdraw each the pin from respective the rod; a force triggered detent, the detent allowing the rotation of the actuator when the rotational force exceeds a threshold level.

Abstract: Flare munition for battlefield illumination is provided that includes: (a) at least one electrical flare body; (b) an electrical energy source connectable with the flare body; and (c) an electrical or electronic control device for connecting the electrical flare body with the source of energy during a specified time interval. The flare munition can be fired from a weapon or can be launched as a bomb and allows safe and simple subsequent recovery of the corresponding flare body because no pyrotechnic flare charge is used. Instead, an electrical flare body is used that emits light in the visible and/or infrared wavelength range depending on its intended purpose.

Abstract: A system and method of detecting, processing, and selectively responding to radio frequency transmissions detected by at least one projectile deployed above a geographic area.

Abstract: A system and method of detecting, processing, and selectively responding to radio frequency transmissions detected by at least one projectile deployed above a geographic area.

Abstract: A method for controlling the drag area growth of a parachute canopy during airborne descent with sensors attached to the payload for facilitating modification of the schedule of release of a parachute canopy reefing mechanism. A control processor is included that can receive and/or calculate a schedule for disengaging the reefing on the parachute. One or more wireless transmitters at the payload transmit the releasing signal from the payload to the reefing mechanism normally located adjacent the parachute canopy. The control processor can also be configured to receive input information from multiple sensors attached to the payload that monitor parameters such as altitude, position, load force, dynamic pressure, time and others to facilitate instantaneous recalculation of the disreefing schedule responsive to such conditions.

Abstract: An apparatus for controlling the drag area growth of a parachute canopy during airborne descent with sensors attached to the payload for facilitating modification of the schedule of release of a parachute canopy reefing mechanism. A control processor is included that can receive and/or calculate a schedule for disengaging the reefing on the parachute. One or more wireless transmitters at the payload transmit the releasing signal from the payload to the reefing mechanism normally located adjacent the parachute canopy. The control processor can also be configured to receive input information from multiple sensors attached to the payload that monitor parameters such as altitude, position, load force, dynamic pressure, time and others to facilitate instantaneous recalculation of the disreefing schedule responsive to such conditions.

Abstract: A submunition is formulated for destroying a target in a target area. Accommodated in a casing are a signal processing unit connected to a radar antenna and/or an infrared sensor and/or another target-detecting sensor. The submunition further has target recognition software and a charge provided with a covering. To increase the versatility of use and to simultaneously improve detection and decision certainty and reliability, the target recognition software has a software interface for the transfer of at least one parameter specific to the target area.

Abstract: The locking and stabilizing device for grenades utilizes a solid nylon ring and multiple nylon ribbons that are attached to the ring at regular intervals around its circumference. During storage, the ring surrounds and locks the slider of the grenade in its storage position. But upon deployment, under aerodynamic forces the ring moves away from the slider, releasing the slider. When the slider is thusly released, it slides out and brings the detonator in place to be impacted upon by the pin when the grenade hits the target, thus detonating the grenade. The multiple ribbons extending from the ring unfurl due to the aerodynamic forces and provide stability to the grenade flight.

Abstract: A non-lethal cargo projectile includes a projectile body; a nose cap attached to a front of the projectile body; a boattail attached to a rear of the projectile body; a fin assembly including a boom attached to the boattail; a parachute assembly disposed in a front of the projectile body; a cable connecting the parachute assembly to the boattail; a fuze disposed in the boattail; a first pair of half cylinders disposed in the projectile body behind the parachute assembly; a first circular disc disposed at a front end of the first pair of half cylinders and a second circular disc disposed at a rear end of the first pair of half cylinders; a second pair of half cylinders disposed in the projectile body in front of the first circular disc enclose the parachute assembly; and a payload disposed in a space defined by the first pair of half cylinders and the first and second circular discs.

Abstract: A cruise missile, such as the Tomahawk cruise missile, is adapted to deploy decoys in an area as the missile progresses along its preprogrammed course. Each decoy is shaped to be compatible with and ejected from the Tomahawk and has a preprogrammed control unit operating a transmitter connected to an extendible antenna. False beacon signals and/or false message signals are transmitted from each of the decoys to deceive and confuse defensive forces, such as enemy searchers looking for a downed airman.

Abstract: A standoff delivery system is responsive to GPS coordinate signals and in-flight GPS signals to deploy a torpedo at a remote location that avoids the limitations and hazards attendant conventional deployment by full size aircraft. A gliding rigid winged unmanned aircraft carries the torpedo to a desired remote location. A GPS receiver on the aircraft enters GPS coordinate signals representative of the remote location and receives GPS signals representative of the location of the unmanned aircraft. A control signal generator produces control signals in response to both of the GPS signals and feeds control signals to servos that displace control surfaces to pilot the unmanned aircraft. The torpedo is released and descends via parachute in response to GPS signals that are representative of at least the proximity of the remote location. This system provides for clandestine deployment of a torpedo without exposing manned aircraft to danger.

Abstract: The recoverable airborne instrument platform accurately determines its present position and uses this data to execute a predetermined flight plan and ultimately guide its descent to a predetermined landing site. This is accomplished by installing the instrument package payload in the aerodynamic exterior housing of the recoverable airborne instrument platform, which has a plurality of moveable control surfaces thereon to autonomously control the altitude, attitude and flight path of the recoverable airborne instrument platform. A navigation circuit contained within the aerodynamic housing determines the geographic location of the recoverable airborne instrument platform as well as the location of at least one predetermined recovery site. The determined position data is used to dynamically calculate a flight path which allows the guidance control circuit to both execute a predetermined flight plan and controllably descend the recoverable instrument platform to a selected predetermined recovery site.

Abstract: Process for guiding an elongated missile, equipped with booster motor, sustainer, power source, control electronics, payload, and search head, from above, upon a target, such as a helicopter, where the missile, after ballistic flight, is braked before the target area by a drogue chute and is diverted into a position that is essentially perpendicular to the earth's surface over the target area so that the search head of the missile, which is suspended from the drogue chute, will be pointed downward, whereupon, after the search head has locked on the target, the drogue chute is separated and the missile is guided to the target by the sustainer, characterized in that, immediately prior to, before, or after the moment of drogue chute deployment, a lateral motor, located in the center of gravity of the missile, is turned on so that, first of all, in order to accelerate the tilt-off of the missile into the vertical, there is generated a force that is added vectorially to the force of gravity and that thereupon one

Abstract: A delivery apparatus (11) for full-calibre submunitions or the like payloads (12) which are coaxially stacked in its load space (19) results in a system which operates in a fault-free manner when, for ejecting the payloads (12), detachment of the load space (19) from the rocket motor (17) disposed therebehind and detachment of the ogive (14) from the opposite end of the load space (19) are each promoted by a pyrotechnic charge (28, 31), with the load space (19) being braked as a result of being positioned transversely beside the trajectory (26) of the separated motor (17) which flies further along the trajectory and past the load space in a stable configuration and with the load space (19) only then being turned by a braking parachute (23) connected to its end (22). The load space tail (18) which thereafter then faces forwardly in the direction of flight is opened by detachment of a cover (25) and the load space (19) is pulled away from the payload stack (12--12) by means of the braking parachute (23).

Abstract: For attacking semi-hard target objects (21) even in a semi-covered position (for the avoidance of the munition-technical expenditure on the intelligent search-fuse submunition with P-charge against hard targets), there is provided a scatter munition whose warhead (22 ) descends into the target area (12 ), hanging on a rotational parachute (13), and triggers off a fragment cone of heavy metal balls (23) inclinedly downwardly as soon as a search-fuse sensor (19) which is oriented parallel to the operative direction acquires a target object (21) on the basis of its own radiation, its radiation shadow or its contour relative to the surrounding target area (12).

Abstract: In a system for the tilting of a suspended object, this object is suspended from a suspension point by three suspension lines, the suspension lines being each fixed to the object by a fastening point. A suspension point is deflected and tautened by a roller. The tilting of the object is then achieved by the translation of the roller with respect to the object. This shifting is obtained, for example, by a pyrotechnical thrustor fixed to the object. Application: sub-munitions suspended from a parachute.

Abstract: In a system for the tilting of a suspended object, this object is suspended from a suspension point by three suspension lines, the suspension lines being each fixed to the object by a fastening point. A suspension point is deflected and tautened by a roller. The tilting of the object is then achieved by the translation of the roller with respect to the object. This shifting is obtained, for example, by a pyrotechnical thrustor fixed to the object. Application: sub-munitions suspended from a parachute.

Abstract: A cover or apron interposed between a ballute and the aft cover of a submtion for delaying deployment of the ballute and preventing the ballute from contacting the aft cover during deployment.

Abstract: A parachute deployment system for use with an illuminating flare warhead propelled by a rocket motor. The system employs a compact two-stage parachute system which includes a main parachute arranged within a main parachute cover and a drogue parachute arranged within a drogue chute cover. The main parachute pack and the drogue parachute are configured to be positioned in a side-by-side, detached relationship within the warhead. An extraction line separably connects the drogue parachute pack to the rocket motor and a support line connects the drogue parachute pack to the main parachute pack such that upon separation of the rocket motor from the warhead, the drogue parachute pack is extracted from the warhead prior to extraction of the main parachute pack. Upon deployment of the drogue parachute, the drogue parachute cover remains attached to the extraction line and acts as a deflector, inducing radial forces which act upon the rocket motor to prevent it from colliding into the warhead.

Abstract: A system for controlling the arming and firing of a weapon that is suspended from a parachute at an oblique angle and spun so as to be aimed over a spiral rotational scanning pattern on the earth as the parachute descends toward the earth. The weapon is supported by a platform so that the weapon is aimed in a predetermined direction relative to the platform. A detection system is supported by the platform and aimed in the same direction as the weapon for detecting predetermined radiation characteristics from targets of opportunity. A ranging system is supported by the platform and aimed in the same direction as the weapon for determining the range to the earth in such direction.

Abstract: A deceleration device for a submunition unit includes a cartridge releasably attached to the submunition unit. A releasable package including at least one pocket is disposed in the cartridge and is connected to the cartridge by a packaging line. An auxiliary parachute and a rotation parachute are disposed in the cartridge, with at least the rotation parachute being accommodated in the at least one pocket of the releasable package and the auxiliary parachute being disposed in a pocket separate from the at least one pocket. The auxiliary parachute is connected to the cartridge and the rotation parachute is connected to the submunition unit. A deployment mechanism causes the auxiliary parachute to be deployed in advance of the rotation parachute after the cartridge is released from the submunition unit and the rotation parachute to be deployed after the cartridge is decelerated by the auxiliary parachute for decelerating the submunition unit.

Abstract: A submunition unit provided with a rotary parachute (3) as the sole parachute. The parachute, after release, initially is unable to be fully deployed due to reef loops (16) provided on the rigging lines (15) and held by a releasable holding device arrangement (4, 5, 6) and therefore acts as a deceleration and stabilization parachute at high flight velocities. The reef loops (16) are released after a predetermined period of time to permit the rigging lines (15) to fully extend and parachute (3) to become fully deployed or opened.

Abstract: The recoverable airborne instrument module is implemented using an aerodynamic housing which has at least one moveable control surface thereon. In operation, the recoverable instrument module is carried aloft by balloon to enable its instrument package payload to perform a series of meteorological measurements. The exterior housing of the recoverable instrument package has an aerodynamic shape, such as a delta wing airframe with a controllable rudder. A navigation circuit contained within the housing references the radio frequency transmissions of a plurality of beacons to determine the altitude and geographic position of the instrument package. This information, as well as data identifying the location of at least one predetermined landing site is used to dynamically calculate a flight path to controllably descend the instrument module to a selected one of these landing sites.

Abstract: A parachute associated with an object unfolds faster in an airstream if the object is first accelerated in the direction of descent. This principle can be applied advantageously to a mine system combating military targets from the air because the time between starting from an ambush position in the terrain to the onset of searching movements in the air can be shortened.

Abstract: A submunition which is arranged to be separated from a missile or projectile for example, a shell canister or the like, over a target area including an active part, in the form of a warhead, a target detector and means for imparting to the submunition a controlled rotation for scanning of the target area in a helical pattern during the descent of the submunition towards the target area. The target detector is displaceable in order to allow a free view at the side of the warhead. The two diametrically situated aerofoils are pivotable from a folded position, in which the aerofoils connect with the outer surface of the submunition, to a 90.degree. unfolded position, in which the two aerofoils form a braking area for controlling the rate of descent of the submunition. The two aerofoils are pivotally arranged via a double joint.

Abstract: Submunition which is deployable through the intermediary of an artillery projectile, and in which the submunition includes a releasing device for a braking parachute which is stowed in the tail end region of the submunition. The releasing device is activatable through the intermediary of a retarding element which, in turn, is releasable in dependence upon the exit of the submunition from the casing of the carrier projectile.

Abstract: Disclosed is a new type of penetrating projectile, the penetrating capacity of which is improved and more efficiently controlled, notably through a solution to the problems of obliquity. A projectile of this type has a front element forming the active part, fixedly joined to a tube. The tube has a closed end which contains a propellant charge for the propulsion of the element and an igniter for the charge, responding to the impact of the element on a target. In reaching the target, the projectile penetrates it slightly under the effect of the velocity and it is only at this instant, or slightly after it, that the penetration proper takes place. The penetration thus takes place without obliquity. This projectile can be used as an individual munition or sub-munition.

Abstract: A parachute pack sack with a submunition body affixed directly to grappling ropes of a parachute is expelled from a rapidly flying container which is mounted under a flight aggregate or flies independently. A pyrotechnic cutting device is actuated by a grappling rope after the tightening of the latter and, by means of a cutting piston driven by a combustion unit, cuts a pack sack closing line which results in an opening of the pack sack and in a deployment of the parachute. The combustion unit may be ignited with an adjustable start of the burning time whereby differing flying ranges and dispersion ranges of the submunition body can be achieved.

Abstract: A bomblet projectile includes a projectile body, a fuse housing on the body at the rear end thereof; and an unwindable stabilization band for stabilizing the position of the projectile while dropping. The band forms, in the deployed state, a loop having leg portions terminating in fastening regions secured to the fuse housing and a dome portion flanked by the leg portions. The band has a length and different widths along the length. The band has its greatest width in the dome portion and its smallest width in the leg portions, externally of the fastening regions.

Abstract: The disclosed device comprises, in the first element, on which the second element is mounted, a peripheral housing opened outwards, a circlip engaged in said housing, comprising teeth capable of getting engaged in retaining means of the second element, and a means to bring the ends of the circlip closer together in order to retract it and to bring out the teeth of the retaining means controlled by a delay means. The disclosed device is particularly suited to the locking and unlocking of sub-munitions parachute containers.

Abstract: In a missile for setting down a load ejected from the missile after its launch, with at least one parachute that is attached to the load being packed in a container mounted in the missile, and with the cords of the load-carrying parachute being attached to an intermediate member coupled to the load, the intention is to reduce the size of the operational parts to be transported with the missile and improve the operation thereof during the setting down process. For this purpose it is envisaged that the container should be in the form of a two-part casing having an upper part which can be sprung open, and a plate-shaped lower part having a portion fixedly connected to the load and a support disk as the intermediate member attached to cords of the parachute. The support disk is capable of being folded out from the lower part portion while remaining connected thereto by a connecting element.

Abstract: For suspending a sub-munition from a plate carried beneath a parachute, an arm is hinged with the plate and the body of the munition, and a structure has two positions for which the sub-munition is respectively vertical or inclined. The structure also includes a system of guiding the tilting between the two positions. The center of gravity of the sub-munition moves downwards on a vertical line during tilting of the sub-munition to an inclined position. The device forming the subject of the invention enables the swinging caused by tilting the sub-munition into an inclined position to be avoided, and it is simple and economical to manufacture.

Abstract: An article of submunition which is harnessed as a rotating load through the intermediary of a connecting device to the shroud lines of a parachute. The connecting device is designed as a torque or rotational moment-transmitting spreader arrangement for the radial spacing of the coupling of the shroud lines to a spin line carrying the load; whereby a coupling device is positioned between the connecting device and the spin line, in which the coupling device is constructed as a load-dependent slip coupling for the reduction of the torque which is transmitted from the spin line to the connecting device.

Abstract: An ejectable or launchable member which possesses a storage space for a parachute. An ejectable member of the type which is under consideration herein has the dimensions of the constructional elements reduced in the periphery of a parachute cassette, so as to resultingly provide for savings in deployment weight, and at a given caliber, to be able to increase the amount of storage space which is available for the parachute.

Abstract: A stand device or emplacement for a mine, especially for an air-deployable mine which is equipped with a search head, and which includes supporting legs articulated to the housing of the mine. The stand device for the mine has the supporting legs articulated to a cardanic or gimbal suspension in the upper region of the mine housing, and incorporate telescopable legs wherein, in dependence upon the setting of the mine housing on the ground, the spread apart support legs render these releasable for the outward extension and raising of the mine housing above the ground.

Abstract: A projectile has at two parts (3, 4) axially arranged one behind the other and mutually linked, of which at least one contains a deployable parachute (6, 6'). In order to achieve a design that ensures a smooth and reliable separation of the parts (3, 4), followed by the deployment of the parachute (6, 6'), both parts (3, 4) are mutually linked by radial bolts (19) that can be radially actuated by the gas pressure generated by at least one pyrotechnic load (15) and radially moved by the gas pressure, thus separating the two parts (3, 4). The pyrotechnic load (15) can be ignited by a fuse (9).

Abstract: The invention relates to a projectile including a cylindrical receiving chamber (4) delimited by an interior wall (3) for a braking parachute (17) which can be ejected by way of a piston (9) that is longitudinally displaceable in the projectile, with the piston (9) being chargeable by an ignitable pyrotechnic charge (10). The braking parachute (17) is encased in a longitudinally divided sleeve (18) one side of which is in engagement with the piston (9). In order to completely or partially recover the projectile and not to impede deployment of the braking parachute (17), it is provided that the rear of the receiving chamber (4) is sealed by a cover (23) which can be ejected by way of the piston (9), is equipped with a rotational imbalance (26) and is in engagement with the other side of the sleeve (18). The braking parachute (17) is fastened to the piston (9).

Abstract: A device for neutralizing military objects by means of sub-munitions released by a mother rocket onto mobile targets on the ground. Each sub-munition (1) is provided with a military charge (2) and a wide range sensor (3) and descends while suspended from a parachute and turns uniformly about a vertical axis of symmetry (10), the angle formed by the firing axis (5) and the vertical being constant. Superimposed upon this rotational movement of the sub-munition, the periodic oscillatory movement of an orientable mirror (14) permits varying the direction of the optical axis (8') with respect to the firing axis during the detection phases of a target and the guiding of the sub-munition towards the detected target. Thus at each oscillation period of the orientable mirror the complete image of the circular area on the ground is obtained. In the last phase of firing, when aimed at the target, the optical axis is maintained in the direction of the firing axis.

Abstract: The invention relates to bombs intended to be released at a very low altitude so as to damage high mechanical resistance surfaces and more particularly antirunway bombs equipped with a downward or acceleration propulsive unit. Each bomb comprises means for braking and orienting it during its initial fall, so as to position the bomb in a plane activating an upward propulsive unit. These means are formed of at least one parachute placed at the head of the bomb. With the activation position reached, the upward propulsive unit causes the bomb to rise and, during the final fall of said bomb, a downward propulsive unit, placed in front of the upward propulsive unit, accelerates the final fall of the bomb so as to accumulate high kinetic energy at the time of impact on the ground.

Abstract: This invention relates to a releasable body, comprising outspreadable arms articulated at one of the ends of said body and actuation means adapted to pass said arms, in the course of aerial descent of said body, from a position folded along said body to a spread out position substantially perpendicular to said body in order to brake descent thereof, wherein it comprises first means for controlling said actuation means to control retraction of said arms along said body when the latter has reached the ground after its aerial descent, said body then being in standby state, and second means for controlling said actuation means to control outspreading of said arms to pass from the standby state to an active state in which the arms support the body on the ground. The invention is applied to releasable bodies provided with aerodynamic braking means.

Abstract: The disclosure relates to a submunition disposed to be separated from an aeronautical body, for example a shell carrier canister or the like above a target area, the submunition essentially including a warhead (5), a target detector (6) and a device which imparts rotation to the submunition for scanning the target area in a helical pattern (4) during the fall of the submunition towards the target area. The target detector (6) is pivotally disposed on a carrying shaft (12a) parallel to the line of symmetry (5a) of the warhead in order to permit outward activation of the target detector (6) from a collapsed position where the optical axis of the target detector coincides with the line of symmetry (5a) of the warhead to an activated position where the optical axis of the target detector is parallel with the line of symmetry (5a) of the warhead, so as to permit free scanning vision for the target detector (6) beyond the warhead (5).

Abstract: A bomblet has a casing and a targeting device provided with a reflector swingably secured to the casing. The reflector has a position of rest in which it is situated within a cross-sectional outline of the casing and a working position in which it is in a deployed state externally of the casing. A first guide arm is articulated to the reflector to provide for a relative pivotal motion about a first pivotal axis, and to the casing to provide for a relative pivotal motion about a second pivotal axis. A second guide arm is articulated to the reflector to provide for a relative pivotal motion about a third pivotal axis, and to the casing to provide for a relative pivotal motion about a fourth pivotal axis. All the pivotal axes are parallel to and spaced from one another and are perpendicular to the central longitudinal axis of the bomblet. The guide arms guide the reflector in a swinging motion from the position of rest into the working position.

Abstract: A carrier projectile for aerodynamically braked submunition which can be ejected rearwardly from the tail end of the carrier projectile while contacting a cup-shaped base of the projectile. The carrier projectile has the inner edge of the fabric of a braking sail retained within the cup-shaped recess of the base of the projectile, with the outer edge of the fabric of the sail being equipped with centrifugal masses or flyweights mounted in proximity to the opening of the cup-shaped recess in the base. Provision is made to arrange the fabric of a radially outwardly tensionable braking sail in the already available recess in the base of the projectile, the braking sail being extended through the pulling action exerted thereon from the centrifugal flyweights.

Abstract: A flail is provided which reduces the spin of a projectile in a recovery system which includes a parachute, a cable connected to the parachute, a swivel, and means for connecting the swivel to the projectile. The flail includes a plurality of flexible filaments and a rotor for attaching the filaments to the front end of the projectile. The rotor is located radially with respect to the spinning axis of the projectile. In one embodiment, the projectile includes a first nose cone section housing a deployable spin damping assembly; a second nose cone section, housing a deployable parachute assembly; a shell section, supporting the first and second nose cone sections during flight of the projectile; a mechanism for releasing the first nose cone section from the second cone section; and a mechanism for releasing the second nose cone section from the shell section.