Abstract: A projectile-launched aircraft system includes a projectile launcher including a triggering mechanism, a rotary-wing, hover-capable aircraft including a rotor assembly that includes at least one rotor blade, wherein the rotor blade includes a stowed configuration and a deployed configuration that is circumferentially spaced from the stowed configuration about a pivot axis, wherein, upon actuation of the triggering mechanism, the projectile launcher is configured to launch the aircraft along a flightpath.

Abstract: Aspects of the present invention relate to unmanned aerial vehicle launch technologies and methods for receiving at a head-worn computer (HWC) a plurality of images captured by an unmanned aerial vehicle (UAV) launched from a grenade launcher, and displaying the plurality of captured images in a see-through display of the HWC.

Abstract: A container for dropping from an aerial vehicle in flight comprises an upper wall, a lower wall, a plurality of side walls, and a plurality of air brakes comprising flat panels. A plurality of side air brakes, wherein each side air brake is connected to a corresponding side wall at or near an upper edge thereof, is freely pivotable around a side air brake pivot axis at or near the upper edge of the corresponding side wall from a passive position, in which the side air brake extends substantially parallel to the corresponding side wall, to a deployed position, in which the side air brake extends substantially transversely relative to the corresponding side wall, by air flowing between the side air brake and the corresponding side wall.

Abstract: A projectile and method of deploying a projectile includes a wing deployment system for deploying a wing of a projectile. The wing deployment system includes a stored energy release mechanism that is activated to generate an initial range of motion of the wing and a panel arranged on the wing and configured to cause an angular acceleration of the wing during the initial range of motion of the wing.

Abstract: A fuse is provided with a reversible airbrake intended for a projectile, wherein the airbrake is arranged such that errors which occur in the flight path of the projectile can be corrected by performing one or more extensions and retractions of the airbrake. The airbrake includes at least two braking surfaces symmetrically arranged each behind a respective protective device arranged on the casing surface of the fuse, wherein the brake surfaces can be extended and retracted in a rotational direction behind the at least two protective devices via a twist shaft arranged centrally in the fuse.

Abstract: Provided is a non-motorized flying unit. The non-motorized flying unit includes a body part having a head part and a tail part having an accommodation space and a through hole, an image capturing unit installed in the through hole and configured to obtain an image information, a protective window installed in the through hole, a plurality of shock absorbing devices installed at the end portion of the tail part, a weight installed at the end portion of the tail part, and a lighting device installed at an end portion of the plurality of shock absorbing devices. A propulsion unit which is detachably coupled to the tail part storing a propellant which, upon combustion, forms pressure in the propulsion unit to provide thrust to the body part.

Abstract: A projectile having a leading section and a trailing section coupled together to define a structure for delivering a plurality of flechettes. The trailing section includes aerodynamic control surfaces that are deployable to apply an aerodynamic braking force to the trailing section to separate the trailing section from the leading section. The flechettes surround an explosive charge in the leading section such that initiation of the explosive charge outwardly disperses the flechettes after the leading section and the trailing section have separated. The control surfaces optionally also may impart spin to the projectile to assist in dispersing the flechettes. Thus, aerodynamic force is employed to assist in removing the flechettes from their confining structure in the projectile before dispersing them.

Abstract: According to the invention, the balance weights of the missile are made from pellets whereof the particle size is at most equal to 1 mm which is enclosed in a closed package.

Abstract: A samara wing including a main wing with a leading edge and a trailing edge. An aileron has a leading edge and a trailing edge and is pivotally attached proximate the trailing edge of the main wing and separated therefrom by a gap. The aileron is rotatable between the first position where the trailing edge of the aileron is facing forward in a plummet mode of operation and a second position where the trailing edge of the aileron is facing rearward typically for an autorotation mode of operation.

Abstract: Methods and apparatus are disclosed for the controllable deployment of a samara wing from a spinning housing by use of an active deployment system. The active deployment system operates to deploy the samara wing as a function of time, for example a step function, or a monotonic function. The samara wing may be attached to a base, which may include a releasable portion. The active deployment system may include an electronic control unit and release means. Suitable release means include, but are not limited to pin actuators, explosively actuated cutters, and the like. Suitable electronic control units include programmable electronic sequencers and the like.

Abstract: A payload carrying device which is inserted into a remote area of interest by means of a projectile carrier to obtain data, or the like, from the remote area. The device has counter rotating main blades as well as tail blades carried on a tail rotor. The particular payload is carried in a canister which may also include a power source, a command and control unit and a motor, if hover or lateral flight is desired. The pitch of the tail blades is variable as well as their orientation around an axis, the combination of which generates a thrust vector in a particular direction for controlled lateral flight.

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 penetrator having a plurality of stacked penetrator segments is disclosed. Each penetrator segment has a nose portion and a rear portion. The rear portion of each penetrator segment has a rearwardly opening cavity therein and a plurality of fins pivotally mounted thereon. The penetrator segments are stacked such that the cavity of the forwardmost penetrator segment secureably contains the nose portion of the following penetrator segment such that there is a press-fit between the cavity and the nose portion. The following penetrator segments are similarly positioned such that the nose portion of each following penetrator segment is secureably positioned in the cavity of the immediately preceding penetrator segment. The fins of each penetrator segment are restrained in a stowed position when the cavity of the respective penetrator segment contains the nose portion of a following penetrator segment. An explosive element is located between each of the penetrator segments.

Abstract: A penetrator having a plurality of stacked penetrator segments is disclosed. One or more of the segments contains an explosive element Each segment has a nose portion and a rear portion. The rear portion of each segment has a rearwardly opening cavity therein and a plurality of fins pivotally mounted thereon. The segments are stacked such that the cavity of the forwardmost segment contains the nose portion of the following segment, and the following segments are similarly positioned such that the nose portion of each following segment is positioned in the cavity of the immediately preceding segment. The fins of each segment are restrained in a stowed position when the cavity of the respective segment contains the nose portion of a following segment.

Abstract: An aerial cargo container system for transporting cargo from an aircraft to the ground having a cargo box with a continuous side wall with six rectangular side panels, and rotor blades having stowed positions against alternating box side panels and deployed positions extending outwardly from the box in a generally horizontal plane. Each blade may include a lower panel and an upper panel that has two triangular sections behind the leading edge that forms an aerodynamic camber. The blades are hinged to a rotor hub secured across the top of the box. The upward deployment of the blades is limited by tethers extending from the blades down to a tether attach frame secured across the bottom of the box. The box and blades are preferably formed of corrugated paper or plastic material. The entire unit rotates with the load to create aerodynamic braking and lower cargo to the ground with a minimum of energy being translated to the cargo on impact.

Abstract: The present invention relates to a method and device for combating identified targets (F) using warheads (2) from a launching vehicle (1) flying over a target area, by separating from this launching vehicle (1) warheads (2) which act independently after separation, and including those targets which lie close to the flight trajectory of the launching vehicle (1) and those which lie well to the side of same flight trajectory. The invention is based on the use of that part of the kinetic energy of the launching vehicle (1) which the warhead (2) takes over from the same when it is separated in order to give the warhead (2) a looping trajectory or any other programmed flight trajectory, which carries it up to a starting height adapted to its active use, which lies considerably above the actual flight trajectory of the launching vehicle (1), and which, if so required, can carry the warhead (2) back to the geographical position where it was separated from the launching vehicle (1).

Abstract: A nose assembly and method for controlling the rotation and stabilizing the orientation of a vehicle during landing maneuvers. The vehicle includes a nose assembly that is coupled to an airframe thereof and that has a frame and flap assembly. The flap assembly includes an actuating means and a flap coupled to the frame such that the actuating means moves the flap from and between a fully retracted position and a fully extended position in response to a guidance signal received from a flight control computer. In a preferred embodiment of the present invention, the flap assembly includes a plurality of flaps each coupled to the nose assembly frame and an actuating means that selectively positions the plurality of flaps in response to a signal.

Abstract: A device, particularly a missile, includes a body having an appendage, e.g., a wing, normally folded in an inoperative position and to be unfolded to an operative position when the body is accelerated in the direction of the longitudinal axis of the body. The appendage is pivotally mounted about a first pivot axis extending perpendicularly to the longitudinal axis of the body, and also about a second pivot axis extending parallel to the longitudinal axis of the body. The center of gravity of the appendage is outwardly of the first pivot axis in the folded condition of the appendage such that the acceleration of the body produces a moment pivotting the appendage about the first pivot axis.

Abstract: A sub-combat unit to be separated from a flying body, comprises a warhead, a target detector and two diametrically disposed carrier surfaces designed and arranged to impart to the sub-combat unit a rotation for scanning of the target area in a helical pattern during the fall of the sub-combat unit down towards the target area. The two carrier surfaces are pivotable between a closed position and an opened position in which the two carrier surfaces form a retarding area for controlling the fall velocity of the sub-combat unit and a flow influencing means is provided at at least one of the two carrier surfaces for creating a turbulent area immediately above the carrier surface for completely relieving the carrier surfaces even for large differences in the direction of the impinging wind.

Abstract: The invention relates to a sub-combat unit which is disposed to be separated from a flying body, for example a carrier shell or the like, over a target area, the sub-combat unit comprising a warhead (4), a target detector (5) and two diametrically located carrier surfaces (1, 2) which impart to the sub-combat unit a rotation for scanning the target area in a helical pattern during the fall of the sub-combat unit down towards the target area, and both of the carrier surfaces (1, 2) being pivotally disposed from a collapsed position to an opened position where both of the carrier surfaces form a retarding area for the fall velocity of the sub-combat unit. The sub-combat unit is designed such that the relationship between the largest main inertia moment and the other main inertia moments of the sub-combat unit lies within the range of between 1.05 and 1.15.

Abstract: A method is provided for retarding the movement of the flip-out target tracker during a final part of a flip-out without the contents or journalling of the target tracker being damaged. The flip-out target tracker is on a sub-combat unit which is transported by a carrier body to a predetermined target area in order to be activated at the target area during flip-out of the target tracker. The target tracker scans the target area during the braked fall of the sub-combat unit and identifies and combats targets by means of an integrated warhead. The retardation is effected with a flexible brake band. The brake band is initially folded and attached to the target tracker at a first anchorage point in the proximity of a portion of the target tracker which, during flip-out, moves the longest distance. The brake band is stretched past an elastically deformable damper body secured in a main portion of the sub-combat unit.

Abstract: A sub-combat unit is arranged to be separated from a flying body over a target area, and includes a warhead, a target detector and two diametrically disposed carrier surfaces, each connected to a carrier arm and pivotally disposed about its own shaft located in a plane which is normal to the line of symmetry of the warhead and pivotable from a collapsed position in which the carrier arms and carrier surfaces connect to the circumferencial surface of the sub-combat unit, and to a position opened at 90.degree. at which both of the carrier surfaces form a retarding area for the fall velocity of the sub-combat unit and to impart to the sub-combat unit a rotation for scanning the target area in a helical pattern during the fall of the sub-combat unit towards the target area.

Abstract: A device is provided for reducing the rate of rotation of a spinning submunition unit having a tail end provided with a deployable braking device, from a time after the submunition unit is ejected from a spin stabilized carrier projectile until the braking device is deployed. The device includes a plurality of bands arranged to form a star-shaped symmetrical band structure for placement around the braking device. Each of the bands has a free end provided with a wind pocket.

Abstract: A stabilization system for a towed aerodynamic body 1. The body is provided with two, contra-rotating tubular shrouds 3, 4 each fitted with a set of vanes 5, 6. When the towed body is disturbed by the towing aircraft's wake, the gyroscopic inertia caused by rotation of the shrouds exerts a damping effect on the subsequent oscillatory motion of the towed body. In one embodiment, the shrouds are coupled by wheels which constrain the shrouds to rotate in opposite senses. Hence gyroscopic precession effects due to each rotating shroud cancel.

Abstract: A weapon arranged to travel in a given orientation when in flight, has a body and a ribbon. The body has a payload casing and a spindle rotatably mounted at the rear of the payload casing. The ribbon is formed into a flexible loop for trailing behind the body in flight. This ribbon is attached to the spindle. The ribbon has an impelling surface shaped to apply a torque to the spindle when in flight.

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 subwarhead adapted for separation from a missile, for example a carrier shell or the like, over a target area comprises an active part, a target detector and an arrangement which imparts a rotation to the subwarhead for scanning of the target area in a helical pattern during the descent of the subwarhead towards the target area, the target detector being arranged displaceably in order to allow a free view at the side of the active part. Two diametrically situated aerofoils are pivotable, each on its own shaft situated in a plane which is at right angles to the axis of symmetry of the active part, from a folded position, in which the aerofoils connect with the outer surface of the subwarhead, to a position folded out by 90.degree., in which the two aerofoils form a braking area for controlling the rate of descent of the subwarhead.

Abstract: A flexible wing which is connected to a submunition provides a substantia vertical descent and provides torque which power submunition electronics. The flexible wing is deployed in a low drag configuration to avoid collision with other submunitions. The flexible wing is canted to allow rotation of the wing.

Abstract: A subwarhead which is adapted to be separated from a missile over a target area comprises an active part, a target detector and an aerofoil, the target detector and the aerofoil being pivotably mounted each on its own bearing shaft parallel with the line of symmetry of the active part in order to allow pivoting out of the target detector and of the aerofoil from a folded position to an unfolded position at the side of the active part in order to allow a controlled movement of scanning of the target area. Both the target detector and the aerofoil are provided with one or more displaceably arranged additional aerofoils for the purpose of increasing the braking area of the subwarhead in order to reduce the descent rate.

Abstract: A projectile base plug with enhanced separation capability has a body which fits into an end of a spinning projectile casing and drag-producing vanes being spaced apart about the circumference of the object and pivotally mounted thereto for movement between stowed and deployed positions. Upon ejection of the base plug from the projectile casing, the vanes are released from stowed positions within the aerodynamic outline of the base plug where they have no substantial effect on the flight of the projectile, to deployed positions by centrifugal force generated by the spinning body where they project into the air stream and produce drag on the ejected base plug.

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 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 invention discloses an improved conventional munition employing a dual omblet configuration including dual shaped charges and a design which uses a Misznay-Schardin end plate with a shaped charge. Both bomblets are separately enclosed by fragmenting warheads that are positioned in tandem. the tandem bomblet design results in a nesting arrangement of the fragmenting warhead, or sub-munition, to produce maximum packaging efficiency. A forward sub-munition of a tandem bomblet will nest within a cavity of a shaped charge of an aft sub-munition.

Abstract: A grenade device for use with and for ejection from an artillery shell is ovided. The device includes a stabilizing propeller and a grenade body. The propeller has two opposite blades disposed on opposite sides of a rotation axis. Each blade has an upper tilted portion and a lower substantially flat portion and a connecting return bend tip portion. Each such portion has a leading edge and a trailing edge. Each upper tilted portion has a transverse angle of attack. The upper tilted portions bave a common longitudinal upper projected axis. The lower flat portions also have a common longitudinal lower projected axis. The common longitudinal upper projected axis and the common longitudinal lower projected axis form a projected displacement angle therebetween. The propeller is made from a flexible metal or fabric ribbon. The blades are folded in a nested arrangement before descent. During descent, the blades unfold to their overall aerodynamic shape. The propeller has a windmill type of rotation during descent.

Abstract: The disclosed projectile has a tube forming a mortar, a munition contained in the tube, at least three deployable fins, solidly joined to the tube, and firing means triggering the ejection of the munition. During operation, when the projectile, released from an aircraft, lands on the ground for example, the fins form a pedestal in the mortar tube and, upon the command of the firing means, the munition is ejected to a certain distance from the tube.

Abstract: Projectile steering apparatus and method employing the autogiro principle. Two rotatable blades are swung out from a longitudinal slot in a flying projectile. The blades are shaped to rotate as a result of the air stream rushing past the projectile. Steering is effected by altering the orientation of the blades with respect to the projectile in synchronism with rotation of the projectile. By varying the autogiro pattern produced by the pair of blades, it is possible to impart a force for correcting the projectile trajectory.

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: A radar decoy ribbon packed within a dispenser body is launched from an aircraft by creating, within a launch tube, gas pressure sufficient to expel a frangible retaining plug from the outer end of the tube, driving the dispenser body into the airstream. The body has a pair of drag vanes which open in the air stream. As the dispenser recedes from the craft, the ribbon, one end of which is attached to the aircraft by a towline, is paid out of the body. Once the ribbon is fully deployed, a drogue maintains tension on the ribbon until the towline is severed.

Abstract: A device for reducing the rotational speed of an ammunition unit, for instance a submunition unit, and at the same time imparting to the ammunition unit a lateral speed includes a body arranged to be swung out from the ammunition unit and be released in a specific outswung position. The body preferably consists of a band which is wrapped about the outer peripheral surface of the ammunition unit. One end of the band is fixed to the ammunition unit in such a way that the band is released in a specific outswung position.

Abstract: Apparatus is disclosed which provides for the controlled deployment of a flexible samara blade used to orient and decelerate a submunition cannister which is dispensed at altitude and allowed to free fall to earth. Spin pins are anchored in and extend outwardly from the downstream end of the cannister. Placement of the pins is such that the flexible samara blade can be wrapped around the pins to place the blade in a stowed condition within the periphery of the cannister end prior to launch of the submunition. Caps on the pins are used to inhibit the stowed blade from slipping off the pins. The blade is wrapped around the pins in a direction opposite to the direction of rotation of the submunition during launch. Launching the submunition in a spinning state creates a centrifugal force in the weighted tip of the samara blade causing the wing to unwrap from the stowed to the deployed state. The pins keep tension in the unfolding wing and preclude erroneous twist-up of the flexible blade.

Abstract: The sub-munition is provided with an arming device comprising a striker member, movable substantially in the direction of its longitudinal axis, and a detonator carried by a slide movable from a first position in which the detonator is located out of the path of the striker member to a second position in which the detonator is brought into the path of the said member and beneath it; the striker member is provided with a threaded stem screwed into a threaded hole of a bush movable axially on the body of the sub-munition in such a way that the striker member is brought from the said first to the said second position upon unscrewing of the stem from the threaded hole; a pair of strip form flexible elements are connected to the striker member, one end of which flexible elements is fixed to the striker member and each of which can be disposed, when the sub-munition is expelled from the projectile, in a twisted configuration in such a way that the aerodynamic forces acting on them cause a moment to be transmitted t

Abstract: A missile separation system for fixedly attaching a rocket motor section a payload section has cofunctioning attaching and retarding means integrated to retain plural sections of a missile system in mated relationship until a predetermined point in the missile flight path.

Abstract: An air dispensed assembly in the form of a submunition cannister is disclosed which has the capability to perform a lateral maneuver during the final 1500 ft. of descent before impact. Maneuvering is accomplished by deploying a samara blade shaped wing from the rear of the submunition cannister after ejection from the casing of the launching shell. The wing is sized and provided with an angle of attack which causes the cylindrical shaped cannister to spin as it descends downward at approximately a constant rate of descent. A passive infrared sensor in the nose of the cannister provides target information to a data processor which generates steering commands to appropriately alter the wing angle of attack so as to bring about a corrective lateral change in direction. When within lethal range of the sensed target, the warhead in the submunition is detonated.

Abstract: A missile on-board flight pitch, yaw and roll control drag actuator system. The system having a plurality of control panels operated by an actuator drive. The actuator drive accurately positioning the panels in a desired position in the airstream of the missile for controlling the flight, orientation and speed of the aircraft.

Abstract: An orientation and stabilization device for a submunition is disclosed. A w profile cylindrical submunition body has a single fin attached thereto at an asymmetrically located position with respect to the central axis of the cylindrical body. The fin is tip weighted in such a way that, when the submunition falls through the air, a constant spin and vertical velocity is established, with the major axis of the cylindrical body disposed at an angle to the descent path.

Abstract: A plurality of fins for a missile which are capable of being folded to conform to the general cylindrical contour of the missile body and which are biased to unfold to an erect position and which includes an interconnection mechanism for connecting all the fins together to ensure simultaneous erection and for distributing the erection moment of individual fins to all fins; said interconnection means further being capable of acting without interfering with the movement of the fins for flight control without need for disengagement after erection.

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.