Abstract: Damage mitigating apparatus comprises totally extending hollow tubes, and projectiles attached to undeployed fabric and formed with a tube-receivable rod. Pressurized gas which is generated upon triggering of a gas generator flows through the tubes to propel the projection and to cause performance of at damage mitigating operation. In one embodiment, a damage mitigating aerial vehicle comprises sensors for detecting flight related characteristics and a communication unit for commanding activation of parachute deploying apparatus and of a lift generator deactivation unit following determination of a flight failure. In one embodiment, an aerial vehicle transmits a critical failure alarm signal to an unmanned aircraft traffic management system (UTM) station following detection of to failure, and the UTM elation transmits a warning signal to neighboring aerial vehicles that are predicted to be in a vicinity of the descent path of the failed aerial vehicle to avoid collision with the failed aerial vehicle.

Abstract: Herein we describe barrel-cleaning cartridges which can be loaded into a firearm and then fired to perform the task of cleaning the barrel of said firearm. The barrel-cleaning cartridges include a propellant, a flexible textile that assumes a general cup shape within the cartridge, and a particulate obturating media, some of which is encircled by the flexible textile. These components combine to form a good gas seal and to clean the barrel of a firearm, including elements of the barrel having variations in diameter. The obturating media comprises particles having an average particle size greater than 212 microns, and an average specific gravity greater than 1.1, and a hardness of less than 7 on the Mohs scale.

Abstract: A concatenated annular swing-wing tandem lift enhancer (CASTLE) is provided for augmenting aeronautical lift to a canister-launched missile. The CASTLE includes fore and aft housing sections and pluralities of mainstays, airfoils, wing grapples and tension supports. The fore and aft housing sections are disposed circumferentially around the missile along a longitudinal axis of symmetry. The front and rear mainstays are disposed angularly along each housing section. The airfoils stowed circumferentially around each the housing section. Each airfoil has an outer camber surface and an inner arc surface that provides leading and trailing edges ending at port and starboard tips. The wing grapples disposed on the inner arc surface. The supports connect the mainstays with corresponding the grapples such that the airfoils deploy radially outward and swing such that each leading edge faces forward in relation to the longitudinal axis. The supports can be flexible lanyards or else rigid struts.

Abstract: Devices and methods for detection of evidence of life or ore bodies on or near the surface of extraterrestrial bodies (e.g., Mars) are described. In particular, a ground penetrating probe capable of s conducting life detection or other experiments and transmitting the data from the experiments to a satellite relay is described. Methods of use for such devices and apparatus are described.

Abstract: A retaining mechanism which may be launched to capture an unmanned aerial vehicle (UAV) or the like. A projectile deploys dampener arms to stop projectile penetration into the target while forward retention arms deploy to prevent a backward removal from the target. The firmly embedded mechanism might feature tracking means or destruction means, or the target may be pulled away by the tether to be evaluated for information.

Abstract: A guided projectile that includes a warhead case, a cartridge case coupled to the warhead case, and a tail kit assembly positioned within the cartridge case. The tail kit assembly includes a hollow casing including a plurality of fin slots defined therein, a control fin selectively extendable from within the hollow casing through each fin slot of the plurality of fin slots, and a fin slot cover positioned within each fin slot with a minimum clearance fit such that the control fin is retained within the hollow casing. The fin slot cover is releasable from within each fin slot such that the control fin is deployable therethrough.

Abstract: A closed, self-contained ballistic apogee detection module for use in a projectile, such as a rocket, mortar round, or artillery round, fuses data from multiple built-in sensors, such as an accelerometer, a magnetometer, and a gyroscope, and processes the data using a microprocessor through a custom quaternion extended Kalman filter to provide accurate state and orientation information about the projectile so as to accurately predict apogee. The module outputs a signal indicating apogee detection or prediction which they projectile uses to initiate fuze arming, targeting control, airbody transformation, maneuvering, flow effector deployment or activation, payload exposure or deployment, and/or other mission activity. Because the system and method of the invention does not rely on external environmental data to detect apogee, it need not use a pressure sensor and can be completely sealed in and closed without requiring access to air from outside the projectile for barometric readings.

Abstract: A gun-launched, penetrating anchor projectile includes a dense, metallic, elongated penetrator having a central bore extending forward from its aft end. An expandable anchor in the form of a hollow cylinder is disposed aft of the penetrator. A spacer and hammer in the form of hollow cylinders are disposed aft of the anchor. A guide tube is disposed radially inward of the anchor, the spacer and the hammer. A semi-rigid cable has one end fixed in the central bore of the penetrator and extends aft through hollow interiors of the expandable anchor, the spacer, and the hammer. The other end of the cable forms a loop on which a pulley is mounted. A discarding sabot and fin assembly are disposed around the projectile.

Abstract: The Broadhead-Bullet and Sabot is a new type of sub-sonic hunting projectile combining capabilities of an expandable broad head arrowhead with that of a firearm-fired projectile. The Broadhead-Bullet and Sabot is for use in shorter ranges akin to shotgun slug ranges but is able to utilize the cost effectiveness, utility, and ease of use of existing firearms.

Abstract: The Broadhead-Bullet is a new type of sub-sonic hunting projectile combining capabilities of an expandable broad head arrowhead with that of a firearm-fired projectile. The Broadhead-Bullet is for use in shorter ranges akin to shotgun slug ranges but is able to utilize the cost effectiveness, utility, and ease of use of existing firearms.

Abstract: A new type of firearm projectile incorporating the functionality of a pivoting blade broad head with that of a firearm propelled projectile. The Broadhead Bullet is for use in shorter ranges akin to bow hunting ranges but able to utilize the cost effectiveness and utility of existing firearm platforms that can accommodate the caliber of the Broadhead Bullet.

Abstract: A kinetic anti-projectile vehicle includes a body, and extendible arms that extend radially from the body. The arms include a foam material, such as a shape memory foam. The foam material may be heated to expand it. The foam arms may be mechanically restrained while being heated. The mechanically restraint may be removed by heating, for example including a fusible link or a shape memory sold material. The foam material arms may include solid material, either in the form of solid material particles, such as high strength particles, or in the form of supports or restraints in the foam material. The extension of the foam arms increases the effective area of the vehicle for impacting a projectile. Impact on the projectile from the body and/or one or more of the arms may be sufficient to destroy, divert, or otherwise disable the projectile.

Abstract: A weapon interceptor projectile has a deployable frame for maintaining a deployable net in shape. The deployable frame may be an inflatable structure, including a flexible material inflated by a gas generator. The inflatable structure has a perimeter that supports an outside shape of the net, and a series of spokes or arms that couple the perimeter to a body of the projectile. The perimeter may have an airfoil cross-section shape, reducing drag of the frame and aiding in deployment. The perimeter may be have a circular shape, giving the net a circular area. The deployable frame allows the net to maintain its shape during flight, increasing its area and its ability to come into contact with an incoming weapon, such as a rocket propelled grenade (RPG).

Abstract: An electrified projectile, according to various aspects of the present invention, delivers a current through electrodes and through a target. The projectile stows the electrodes with a film and deploys the electrodes in the absence of the film. Deployment is accomplished by a release of torsion. A spur may include two electrodes and a loop. The spur may store the torsion and conduct the current.

Abstract: A warhead system for a projectile-intercepting munition, the warhead system includes a fuselage having an axis and one or more explosively-formed-projectile charge. The explosively-formed-projectile is with a length and configured to generate one or more explosively formed blade projectile propagating substantially perpendicular to the length, the explosively-formed-projectile charge assuming a deployed state wherein the length of the explosively-formed-projectile charge is non-parallel to the axis, the deployed state and the explosively-formed-projectile charge configured such that, when the explosively-formed-projectile charge is detonated in the deployed state, the explosively formed blade projectile propagates in a direction non-coplanar with the length of the explosively-formed-projectile charge and the axis of the fuselage.

Abstract: An electrified projectile, according to various aspects of the present invention, delivers a current through electrodes and through a target. The projectile stows the electrodes with a film and deploys the electrodes in the absence of the film. Deployment is accomplished by a release of torsion. A spur may include two electrodes and a loop. The spur may store the torsion and conduct the current.

Abstract: A method for protecting a second location against a first projectile fired from a first location at the second location. The method including: firing at least one second projectile toward the first projectile; and increasing a footprint of the second projectile via a deployment from the second projectile to prevent the first projectile from striking the second location. The method can also include detonating a charge upon contact of the first projectile with the deployment; timing an operation of the second projectile to increase an amount of damage and/or redirection of the first projectile; tracking the first projectile and guiding the second projectile to intercept the first projectile based on the tracking and/or the various launching platforms so as to increase the likelihood of protection against the first projectile.

Abstract: An article for neutralizing an enemy weapon comprising an interceptor and a deployable net attached to the interceptor, said deployable net remaining attached to the interceptor upon deployment, is disclosed. A method of neutralizing an airborne enemy weapon comprising launching an interceptor, with a capture sock, towards the enemy weapon and deploying the capture sock just prior to the interceptor encountering the enemy weapon is also disclosed. The capture sock remains attached to the interceptor upon deployment.

Abstract: A method for protecting a second location against a first projectile fired from a first location at the second location. The method including: firing at least one second projectile toward the first projectile; and increasing a footprint of the second projectile via a deployment from the second projectile to prevent the first projectile from striking the second location.

Abstract: A non-lethal projectile carrier includes a base having a plurality of hinges, each hinge including a tab; and a payload case attached to the base, the payload case comprising a plurality of petaloid members, each petaloid member including an opening in a rear surface for insertion of a corresponding tab; wherein upon exiting a gun tube the petaloid members open and fold toward the base. Each petaloid member includes a lip on one edge and an undercut on another edge so that adjacent petaloid members form lap joints. The hinges are defined by zones of small cross-sectional area in the base.

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 method for non-lethal crowd and personal protection. The method includes: firing non-lethal bullets towards a person; and deploying portions on the non-lethal bullets prior to impacting the person to decrease its impact pressure on the person.

Abstract: A method for non-lethal crowd and personal protection. The method includes: firing non-lethal bullets towards a person; and deploying portions on the non-lethal bullets prior to impacting the person to decrease its impact pressure on the person.

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: A projectile includes members that deploy upon impact with a target. The projectile includes a nose piece with a portion that shears off upon impact with the target, causing the nose piece to be pushed inside the projectile. As the nose piece is pushed inside the projectile, the nose piece pushes on members that deploy outwardly and lock into place, thereby greatly increasing the damage done to the target. The projectile is easily assembled by placing the two members through an axial cylindrical hole into slots, then placing the nose piece into the axial cylindrical hole. The deployable members are held within the body of the projectile in flight, and only deploy when the projectile strikes a target, greatly increasing the damage to the target.

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: An interceptor device for protecting a platform against an incoming threat is provided. The interceptor device comprises a housing and a countermeasure device. At least one detonating charge is capable of deploying the countermeasure device. A controller device housed by the housing is capable of directing the detonating charge(s) to deploy the countermeasure device at least partially radially outward of the housing, corresponding to the threat trajectory. A sensor device is in communication with the controller device, and comprises a range-finding apparatus including one of a LADAR, a RADAR, and a LIDAR device, capable of sensing the threat and/or a range thereof, at least partially radially outward of the housing, and notifying the controller device if the threat is sensed, to cause the controller device to direct the detonating charge(s) to deploy the countermeasure device to impact the threat in the intercept zone. Associated systems, and methods are also provided.

Abstract: An interceptor device adapted to protect a platform associated therewith against an incoming threat having a trajectory by intercepting the threat in an intercept zone is provided. Such an interceptor device comprises a housing defining an axis and a countermeasure device operably engaged with the housing. At least one detonating charge is housed by the housing and is operably engaged with the countermeasure device. A controller device is in communication with the at least one detonating charge, wherein the controller device is housed by the housing and is configured to direct the at least one detonating charge to deploy the countermeasure device at least partially radially outward with respect to the axis of the housing and in correspondence with the trajectory of the threat to thereby cause the countermeasure to impact the threat in the intercept zone. Associated apparatuses, systems, and methods are also provided.

Abstract: A hinged explosively formed projectile warhead system eliminates exposure of soldiers to harm in wall breaching operations by providing a lethal mechanism that can be deployed at safe distances, simultaneously breaching a man-sized hole and removing one or more rows of rebar in reinforced concrete structures or barriers. The warhead system employs both a missile system and explosively formed projectile warhead technology delivered to the target from a tube launched platform. A set of warhead arms is attached to the aft end of a missile body by means of a set of hinges. The warhead arms are initially folded against the missile body. After launch of the warhead system, the warhead arms fold away from the missile body. The angle at which the warhead arms are folded from the missile body determines the area of a hole breached by the warhead system in a reinforced concrete target.

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: A method for non-lethal crowd and personal protection. The method includes: firing non-lethal bullets towards a person; and deploying portions on the non-lethal bullets prior to impacting the person to decrease its impact pressure on the person.

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 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 restraining net launching device includes a planar restraining net which is tightly packed into a cylindrical shape having an outside portion. This restraining net, when planar or unfurled, includes a perimeter which is heavier than a remainder of the net. A launcher is provided in which the packed net is loaded, and from which the packed net is launched toward a target when desired. The launcher includes rifling which engages the outside portion of the packed net during launching. A source of propelling gas is used for propelling the tightly packed restraining net out of the launcher during launching. When the launching device is fired, the rifling of the launcher engages the outside portion of the packed restraining net to cause the tightly packed restraining net to rotate about the longitudinal axis and hence to unfurl after exiting the launcher with the heavier perimeter radially outermost.

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: 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: 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 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: An intercept device for flying objects made of a light-weight, packable structure made of a pliable, tear resistant material that can be expanded to a large web-like structure by means of a deployment device, into the path of a flying weapon. To capture, hold and reduce the velocity of intercepted flying objects, activatable resistance bodies are incorporated into uniformly distributed masses that are connected to the perimeter of the web like structure. Contractable sections of the web, made of cable-like structures, connected to perimeter masses, act as drawstrings upon collision with flying object. This causes closure of the web around the flying object as a result of the mass's inertia and added resistance from deployable resistance structures that place tension on drawstring structures of the web. The flying object is subsequently captured within the web, held secure and it's velocity rapidly reduced.

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: An apparatus for deploying a propeller assembly from a folded configuration to a deployed, operational configuration, the apparatus comprising a propeller assembly hub which in conjunction with a propeller hub nut maintains an aerodynamically efficient shape after the propeller assembly is deployed, the propeller hub nut which is diametrically large enough to allow assembly of a drive shaft and a drive shaft bevel gear and includes a cavity to accept a spring detent, a propeller blade which protrudes from a journal located in the surface of the propeller assembly hub where when in its folded configuration, the propeller blade is in the same parallel axial direction as the drive shaft and when deployed is nutated to a radially outwardly extending operative position in response to rotating of a propeller blade bevel gear, the drive shaft rotated about its axis where one end engages a prime mover and a second distal end engages the hub nut, drive shaft bevel gear fixed to the drive shaft near the distal end whic

Abstract: A projectile attachment is disclosed that has open-biased arm members that can be either mounted directly onto the projectile base or may be mounted to a mutual connection means which is then attached to the projectile base. The arms are compressed into a restrained position so that they may be inserted into the casing of the bullet. Upon firing, the arms extend to the unrestrained position. Upon impact the projectile penetrates the target then the extended arm members engage the target surface to cause widespread damage while slowing the projectile. The members may optionally have hook-like ends.

Abstract: A missile includes a missile body having a nose, a tail, and a center of gravity therebetween. A plurality of blades are arranged symmetrically around the missile body at a location between the nose and the center of gravity. The blades are deployable from a stowed position folded flat against the body of the missile to a deployed position extending outwardly from the body of the missile, and are mounted so as to be biased toward the deployed position. A retaining wire extends circumferentially around the body of the missile and captures the blades thereunder. The retaining wire may be controllably severed by a pyrotechnic device to release the blades to extend to the deployed position. The extended blades cause the missile to tumble from a first stable orientation to a second stable orientation, permitting it to be quickly pointed in the opposite direction without expenditure of fuel.

Abstract: By means of multi-member, spreadable righting assemblies, a supporting area can be enlarged in connection with a rightable drop unit, the torque required for righting can be reduced, and the stability can be enhanced. In order to provide that a base of each righting assembly does perform the desired, defined movement, at least one guide member (for example a parallel guide means) is included. The afore-mentioned improvements can be attained practically without an increase in the volume or in the weight of the drop unit.

Abstract: A projectile with rear and front sections able to deliver payloads of submunitions contained inside the projectile after separation of the rear from the front section. The rear section is fitted with an assembly of thin blades. When both sections are assembled, the blades are partially in the rear section and partially in the front section, and when the two sections are separated, the blades spread out. The assembly is such that the length of blade that spreads out is greater than the length of blade that was in the front section before separation of the two section.

Abstract: A two-stage release self-righting mechanism and method employ a pair of primary and secondary releasable holder assemblies which respective hold upper and middle portions of leaf spring arms in a stowed position against the side wall of a load such as a submunition launcher tube. The primary holder assembly is released first which permits release of a portion of the energy stored by the spring legs, causing them to partially extend from the stowed position to a partially deployed position and partially erect the submunition. Then, a short time later, the secondary holder assembly is released, permitting release of the remaining energy stored by the spring legs, causing them to fully extend to a fully deployed position and complete the erecting of the submunition.

Abstract: A projectile with rear and front sections able to deliver payloads of submunitions contained inside the projectile after separation of the rear from the front section. The rear section is fitted with an assembly of thin blades. When both sections are assembled, the blades are partially in the rear section and partially in the front section, and when the two sections are separated, the blades spread out. The assembly is such that the length of blade that spreads out is greater than the length of blade that was in the front section before separation of the two section.

Abstract: A braking mechanism for a rotating flying object. The braking mechanism includes a planar fabric sheet having a central attachment base portion that can be secured to the flying object. The fabric sheet is adapted to be stored in a folded-up readiness state in the flying object, and, when released and unfolded, is adapted to form a braking surface that encircles the flying object. The braking mechanism further includes a plurality of reinforcing strips that each extend radially between the central attachment base portion and an outer rim of the braking mechanism and are distributed about the periphery of the latter. Each reinforcing strip extends from the central attachment base portion to the rim and back again to at least partially form two layers and to form loop-like pockets at the rim, with centrifugal weights being disposed in these pockets.

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 warhead adapted to be mounted to a conventional missile fired from anti-tank weaponry is formed with a piercing cone secured to a base containing a source of knockout gas and an actuator assembly. Upon piercing an aircraft fuselage, a collar encircling the cone translates rearwardly causing deployment of panels pivotally secured to the base portion and connected to the collar via connecting rods. Movement of the collar into wedging contact with the base of the piercing cone deploys the panels to their maximum extended position and simultaneously actuates the trigger assembly causing the knockout gas to be delivered into the aircraft interior through the piercing cone projecting through the fuselage into the interior.