Abstract: There are provided a safety apparatus and an aerial vehicle including the safety apparatus, in which a lid and an opening end of a container are fixed before operation more firmly than a conventional art to be less susceptible to an external environment. A safety apparatus includes a piston member, a cylinder that accommodates the piston member and is provided with a bore through which the piston member protrudes to the outside during operation, a push-up member that is pushed up in one direction by the piston member, an ejected object 16 that is pushed up while being supported by the push-up member, a gas generator that moves the piston member in the cylinder, and a lid 21 including a projection 21a. The projection 21a includes a second through hole 21c, and an engagement mechanism is configured when a pin member 22 is inserted into the second through hole 21c and a first through hole 18a provided in a container 18 to engage an opening end of the container 18 and the projection 21a.

Abstract: A landing device for a low gravity lander having a main body. The landing device comprises a number of leg-like rods attached to the main body, wherein, in a deployment position of the rods, each of the number of rods is inclined with regard to a plane of a first side surface of the main body such that the rods substantially extend in a direction of movement of the low gravity lander. Furthermore, the number of rods is made such that they bend or buckle under forces within a predetermined range by an impact due to a landing on a landing surface, thereby absorbing an impact momentum.

Abstract: A projectile has a front portion, a divider and a cylindrical portion. The front portion has a wall defining an interior cavity, which is closed by the divider. The cylindrical portion comprises a cylindrical sidewall having an outer surface and an inner surface. The projectile also has a plurality of depressions in the cylindrical sidewall. The depressions have an outlet adjacent the second end, an inlet toward the first end and a neck area between the inlet and the outlet. A width of the inlet is smaller than a width of the outlet. The depressions at the neck area have a curved sidewall, but a generally straight sidewall between the neck area and the outlet. The surface of the depression extends at a ramp angle from the outer surface of the sidewall at the inlet of the depression toward the inner surface of the sidewall at the outlet.

Abstract: An air-based-deployment-compatible underwater vehicle that may be configured to perform vertical profiling is described. The vehicle may be configured, during information transmission, to perform motion stabilization at a water surface. A body of the vehicle may have a cylindrical shape. Buoyancy control components of the vehicle may be disposed within the body. The buoyancy control components may be configured to adjust a volume and/or buoyancy of the vehicle to facilitate vertical profiling. Fins may be hingedly disposed on the body at one or more locations on the vehicle. The fins may be movable between a first configuration and a second configuration. The fins, in the first configuration, may be positioned substantially flat against the body. The fins, in the second configuration, may extend radially outward to slow descent and to provide motion stabilization. The fins may be pitched to rotate the vehicle about a longitudinal axis during vertical profiling.

Abstract: Apparatuses, vehicles, and methods to reduce loads applied to a store when the store is launched from the vehicle are disclosed. A particular apparatus includes a launch chamber and a flap. The launch chamber has a first portion configured to receive a store. A second portion is configured to be positioned over an opening in a hull of a vehicle. The chamber has a forward end and an aft end. The flap is positioned a distance from the aft end of the launch chamber. The flap has a first end rotatably mounted proximate to the first portion of the launch chamber and has a second end extending toward the second portion of the launch chamber. The flap is configured to rotate about the first end when the store impacts the flap due to the forces applied to the store by the fluid when the store is launched.

Abstract: Stores launch tubes and vehicles equipped with stores launch tubes are disclosed. According to a particular illustrative example, a stores launch tube includes a tube member and a flexible seal. The flexible seal couples an exterior of the tube member to a hull. The flexible seal acts as a pressure barrier against an ambient environment.

Abstract: A dispenser system provides a means to automatically deploy systems using a controlled dispense approach capable of providing desired operational flexibility. Components such as unattended ground sensors (UGS) are deployed according to a method which includes incorporating the components into an elongated ejection system to form a payload assembly, the ejection system including axially-displaced ejector bays each for holding respective components. Each ejector bay retains the respective components until a respective ejection event upon which the ejector bay ejects the components in a radial direction. The payload assembly includes a stabilizer such as a drogue parachute that substantially prevents the payload assembly from rotating about its elongated axis. A timing sequence for the ejection events is programmed into the ejection system to achieve a desired coverage pattern of the components after deployment.

Abstract: An exemplary stores launch tube includes an outer tube and an inner tube. The inner tube is disposed interior the outer tube and is configured to reduce load as a store exits therefrom. The inner tube may be made of a flexible material. At least one load-reducing device may be disposed between the inner tube and the outer tube. The inner tube may be received within a canister that has an outer casing that is attachable to the outer tube. Alternately, the inner tube may be attached directly to the outer tube. The inner tube may include more than one tube section. If desired, filler material, such as foam, may be disposed between the inner tube and the outer tube. The outer tube may have a substantially circular cross-section, or an oval cross-section, or any cross-section as desired to accommodate structural considerations.

Abstract: A dispenser system provides a means to automatically deploy systems using a controlled dispense approach capable of providing desired operational flexibility. Components such as unattended ground sensors (UGS) are deployed according to a method which includes incorporating the components into an elongated ejection system to form a payload assembly, the ejection system including axially-displaced ejector bays each for holding respective components. Each ejector bay retains the respective components until a respective ejection event upon which the ejector bay ejects the components in a radial direction. The payload assembly includes a stabilizer such as a drogue parachute that substantially prevents the payload assembly from rotating about its elongated axis. A timing sequence for the ejection events is programmed into the ejection system to achieve a desired coverage pattern of the components after deployment.

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 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: A target-penetrating aerial bomb includes a penetrator of hard steel or similar material that contains an explosive charge. A rocket motor is formed as an annular chamber and surrounds the penetrator. The bomb includes a guidance and control unit that guides the bomb on a glide path after release from the delivery aircraft, and steers the bomb onto a dive line. Once the bomb is aligned on the dive line, the guidance and control unit fires the rocket booster to accelerate the bomb to the target. A fuse ignites the explosive after target penetration.

Abstract: An air-dropped ammunition includes an ammunition body having a rearward portion; a firing pin accommodated in the rearward portion; a stabilizing band being received in a folded state at least partially in the rearward portion of the ammunition body; and a device for securing the stabilizing band to the firing pin. The device includes a disk having an upturned rim. The disk engages face-to-face one of two overlapping ends of the stabilizing band, and the upturned rim is oriented away from the overlapping ends. The overlapping ends and the disk are firmly attached to the firing pin.

Abstract: An aerodynamic device, such as a projectile includes an elongated forebody, and an aft section secured to the forebody. The aft section acts as a d control device, and includes a connecting member that extends integrally in a conically shaped flared section, for generating a lift force to help stabilize the projectile during forward flight. The aft section further includes a flange that extends from the flared section, and that provides velocity decay and optimal drag, in order to limit the projectile flight and descent within a predetermined safety or emergency range. The flared section is defined between an innermost edge positioned adjacent to the connecting member, and an outermost edge positioned adjacent to the flange.

Abstract: The invention relates to a braking and heat protection shield (1) for a spacecraft (5), said shield being situated at the front of the spacecraft to oppose a flow of gas striking the spacecraft, and including at least one gap (3a, . . . , 3d) shaped to present a through section to the flow that increases with increasing angle of incidence of the spacecraft, to create an aerodynamic force couple tending to return the spacecraft towards a position of lesser incidence.

Abstract: A method of separating a sub-combat unit from a protective canister. The method comprises the steps of discharging the sub-combat unit from the protective canister by causing a displacement of a driving sabot within the protective canister. The driving sabot is displaced by an elevated gas pressure generated by the combustion of a gas-generating pyrotechnical charge. The displacement of the sabot imparts a trajectory to the sub-combat unit. The displaceable driving sabot is prevented, by arrest means interconnected between the driving sabot and the canister, from accompanying the sub-combat unit in its new trajectory. A division of the protective canister into a plurality of parts is caused. The division ensures a change in at least one of the trajectory and the velocity of the parts of the canister.

Abstract: An apparatus and method is disclosed for decelerating and absorbing impact of a re-entry vehicle suitable for payloads that are relatively light as well as payloads weighing several tons or more. The apparatus includes four inflatable legs displaced equidistantly from each other around a capsule or housing which contains a payload. The legs are inflated at a designated altitude after entering Earth's atmosphere to slow the descent of the re-entry vehicle. Connected between each of the four legs are drag inducing surfaces that deploy as the legs inflate. The drag inducing surfaces are triangularly shaped with one such surface being connected between each pair of legs for a total of six drag inducing surfaces. The legs have drag inducing outer surfaces which act to slow the descent of the re-entry vehicle.

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 device with a stabilizing ribbon fastened to the rear of the body of a bomblet includes a first loop of ribbon with a relatively long lengthwise dimension and a second loop of ribbon with a relatively short lengthwise dimension. The two loops are fastened to the same point on the rear of the body and are rotationally integral with each other. The device improves the deployment of the stabilizing ribbon and the aerodynamic stabilizing and braking of a bomblet.

Abstract: A deceleration element is provided for attachment to a tail end of a submunition unit for deployment when the submunition unit is ejected from a spin stabilized carrier projectile for reducing velocity and spin of the submunition unit. The deceleration element includes two approximately circular, air-tight, planar textile fabric layers of essentially the same size having a diameter exceeding the diameter of the submunition unit and circumferentially sewn together to form an inflatable interior between the two fabric layers. The fabric layer disposed closest to the tail end of the submunition unit is clamped by fasteners to the tail end of the submunition unit and has a front side facing the tail end of the submunition unit for encountering air when the deceleration unit is deployed. At least four air capture pockets are disposed at the front side of the one fabric layer and are distributed at regular intervals in a circumferential direction.

Abstract: A deceleration device for a submunition unit ejectable from a spin stabilized carrier projectile includes a deployable deceleration element. The deceleration element is packaged in textile package including an essentially circular disc, at least three straps connected and arranged radially to the disc, with each strap having a free end and provided with a loop and a closing line received through the loops for pulling the loops together to close the package about the deceleration element. An activation line is connected to the closing line and held by the textile package for releasing the closing line for allowing the package to open for deployment of the deceleration element after the activation line is released from the package by being stretched in a controlled manner.

Abstract: The invention concerns a perforating munition for targets possessing high mechanical strength. A perforating munition, released at very low altitude to prevent destruction by ground-air defense systems, possesses a braking system constituted by a parachute (24) to give the velocity vector of the munition a position that is as close as possible to the vertical, thus enabling an improvement in the effectiveness of the munition on impact. To improve the positioning of the velocity vector with respect to the vertical, the munition has a curvature correction device comprising a back projector (13) that is fixedly joined to the rear part (2) of the munition and is positioned in a ring-like way around a front part (1) of the munition, so as to reduce the curvature of the munition in order to increase the effectiveness of the munition.

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 curved grid fin that is constructed of strips of thin gauge metal such as teel honeycomb secured together in a grid pattern with the honeycomb structure enclosed around a periphery thereof by a thin support structure that is secured thereto in a conventional manner and with a base structure secured to the thin support structure to provide a fin that is designed to be mounted on a missile to provide a fin structure that can control or guide a missile as well as provide a breaking or deceleration means for control of a missile or payload.

Abstract: A braking fabric or canvas which is fastened to the base of a carrier projectile which contains articles of submunition, through the intermediary of a fastening device, wherein the canvas is spread apart or unfolded after the separation of the base from the carrier projectile and is provided for the retardation and change in the trajectory of the base relative to the articles of submunition. The braking fabric is connected by a central surface section thereof with at least one plate element forming the fastening device. This connection between the at least one plate element and the braking fabric is preferably effectuated through an adhesive connection. Naturally, it is also possible to select a different type in effecting the connection; for example, such as a riveting connection, a combined adhesive and riveting connection, or any other suitable type of connection.

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: 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 decelerator structure for attachment to a munition to be deployed formed of a first triangular section of cloth with apexes and straight sides to provide a back wall and a second equally shaped and sized section of material to form a front wall with the sections joined and having scoops at the apexes on the front wall with openings inside the scoops with a central anchor on the front wall so that the walls expand equally due to inner air pressure to form a rounded rear wall and a rounded forward wall with straight sides.

Abstract: A projectile comprising a projectile body having a rear end; and a deceleration element composed of a sheet of material at the rear end, the deceleration element having an edge region and being deployable from a folded condition to an expanded condition with the aid of rotation of the projectile, the deceleration element, when in the expanded condition, having the general form of a disk with a periphery defined by the edge region and being effective for decelerating the projectile, and wherein the deceleration element is constructed such that the edge region has a higher mass density than the remainder thereof.

Abstract: A spin stabilized carrier projectile having a longitudinal axis comprising: a projectile body; and at least two submunition bodies disposed in, and ejectable from, the projectile body, the submunition bodies being spaced along the axis, each submunition body having a folded, expandable deceleration means for reducing the velocity and spin of the submunition body upon ejection from the projectile body, the deceleration means including a sheet of material for producing air resistance, and the deceleration means having different dimensions for respectively different submunition bodies so that each respective submunition body is decelerated less than the submunition body disposed behind the respective submunition body.

Abstract: The present invention relates to a new and unique structure in a collapsible decelerator for aerial bodies launched from a high velocity vehicle and designed to provide a high drag stabilizer capable of withstanding release in air stream velocities from subsonic to supersonic. The decelerator preferably includes a hollow inflatable star, the outermost points of which have hooded valve openings through which regulated airflow enters and inflates the star to decelerate the body to which it is attached. The new and unique capability comprises an angular offset of each air scoop to create desired rotational speed in the selected direction.The amount of angular offset and protrusion into the air stream controls the magnitude of spin rate, the direction of angular offset controls the direction of spin.

Abstract: A spin stabilized carrier projectile comprising: a projectile body having a rear end; at least one submunition projectile disposed in, and ejectable from, the projectile body; and a projectile bottom disposed at, and ejectable from, the rear end of the projectile body, the projectile bottom having a side surface facing the submunition projectile and containing a recess, and a folded, expandable deceleration element for reducing the velocity and spin of the projectile bottom upon ejection from the projectile body, the deceleration element including a sheet of material fastened in the recess for producing air resistance, and the deceleration element being deployable from a folded condition to an expanded condition with the aid of rotation of the projectile bottom.

Abstract: The design of low cost, safe to use cluster bombs is a prime military objective of aircraft weaponization. Present barriers to cost and safety result from the needed complex dispersion system of the submunition cargo. Spin-up, propulsion of the submunitions, projection of the submunitions and cutting of the walls of the bomb require usually explosives or propellants and always involve complex designs, which are costly to fabricate. The present invention overcomes the deficiencies of the prior art by providing for a novel, simple and inert ejection and adequate dispersion system of the submunition cargo, of multi-purpose, anti-tank, anti-personnel, incendiary bomblets wherein the bomblets are dispersed through the nose end and the aerodynamic forces of the air impinging on the high speed bomblets cause these to fan out and provide for an area coverage which is equivalent to that obtained by the prior more complex and costly dispersal systems.

Abstract: A braking arrangement for a spin-stabilized projectile, which provides for an increase in the effective surface on the projectile which is contacted by onflowing air, and which is activated in dependence upon the time of flight. There is provided a braking sail which is radially outwardly stretchable or expandable by means of centrifugal masses or flyweights.

Abstract: The present invention relates to an improvement in a collapsible decelerator for aerial bombs launched from a high velocity vehicle and designed to provide a high drag stabilizer capable of withstanding release in air stream velocities from subsonic to transonic. The decelerator preferably includes a hollow inflatable star, the outermost points of which have hooded valve openings through which regulated airflow enters and inflates the star to decelerate the munition to which it is attached. The improvement comprises an offset mounting piece to create a side force on the decelerator, expanding the coverage pattern of deployed bodies. The amount of offset controls the magnitude of the side or lateral force on the device during descent.

Abstract: A telescopic warhead for a submunition ejectable from a carrier projectile the explosive charge of which is made up of submunitions scatterable and housed in the front portion of the carrier projectile, characterized in that the telescopic head includes a telescopic sliding skirt formed of a plurality of cylindrical elements, which are preferably metallic. The telescopic warhead, during storage, does not reduce the inside space requirement of the carrier projectile which leaves the inner volume available in front of the explosive charge whether the telescopic warhead is in a storage configuration or in an expanded configuration.

Abstract: The present invention relates to a collapsable decelerator for aerial bombs launched from a high velocity vehicle and designed to provide a high drag stabilizer capable of withstanding release in air stream velocities moving at 2600 feet per second. The deceleration includes a hollow inflatable star, the outermost points of which have hooded valve openings through which regulated airflow enters and inflates the star to decelerate the munition to which it is attached.

Abstract: Apparatus for stabilizing a weapon launched from an aircraft. The weapon is rovided with a plurality of concentric rings mounted on the nose of the weapon for reducing nose lift. The tail of the weapon is provided with a plurality of wedge shaped fins positioned on a decreasing tail diameter which increases the tail stability while minimizing tail lift. The outer faces of the fins are of a multi-tiered construction with angled portions connecting the tiers.

Abstract: An aerodynamic braking arrangement for projectile components which are to be salvaged, such as detonators, consisting of a drag parachute having a high air-resistance index and of cables which connect the projectile components with the parachute. The drag chute is formed as a brake basket which consists of two cup-shaped tops at the ends thereof constituted of metal or plastic material, which are separated from each other along the axial direction of the projectile through the intermediary of at least one space formed of metal or plastic material, wherein the cables are fastened to one of the tops.