Abstract: The present application provides a system for unmanned aerial vehicle (UAV) parachute landing. An exemplary system includes a detector configured to detect at least one of a flight speed, a wind speed, a wind direction, a position, a height, and a voltage of a UAV. The system also includes a memory storing instructions and a processor configured to execute the instructions to cause the system to: determine whether to open a parachute of the UAV in accordance with a criterion, responsive to the determination to open the parachute of the UAV, stop a motor of the UAV that spins a propeller of the UAV, and open the parachute of the UAV after stopping the motor of the UAV for a first period.

Abstract: A method of releasing spacecraft from a rocket includes arranging spacecraft in a stack on a rocket, launching the rocket until it attains orbital velocity, imposing a flat spin on the rocket, and releasing the entire stack from the rocket during the flat spin. In one aspect, the method includes applying a compressive load along a length of the stack, launching the rocket until it attains orbital velocity, imposing a flat spin on the rocket, and releasing the compressive load to allow the entire stack to separate from the rocket during the flat spin.

Abstract: A system includes a satellite structure and a dedicated Payload Attaching Fitting PAF for releasable attachment to said satellite structure. The satellite structure an external load-carrying structure; and external vertical planar panels. The external vertical planar panels have internal reinforcements or embedded structures or skin thickness reinforcements, each configured for exerting the structural reinforcement function of diagonal beams in a truss structure architecture.

Abstract: A system for securing spacecraft to a rocket and deploying the spacecraft into orbit includes a stack having a plurality of spacecraft arranged in layers, with each spacecraft being releasably mated with at least one spacecraft in an adjacent layer, and at least one hold down and deploy assembly configured to, in a first configuration, secure the layers of the stack together and secure the entire stack to the rocket, and, in a second configuration, release the entire stack from the rocket into orbit such that the layers passively separate.

Abstract: The disclosure provides a connection and separation device driven by memory alloy wires, including an active end and a passive end. The active end includes a housing, an outer sleeve, fixed sheets, compression springs, a rotating sleeve, a base, memory alloy wires, guide wheels, a lock pin, a limiting sleeve I and a limiting sleeve II. The passive end includes a screw rod, a loading nut, a separation element and an adaptor. The upper end of the screw rod is provided with a threaded section matched with the loading nut, and the lower end of the screw rod is provided with multi-layer oblique protrusions. The multi-layer oblique protrusions extend into the upper part of an accommodating space formed by the limiting sleeve I and the limiting sleeve II.

Abstract: The system (S) to separate at least two mechanical elements (E1, E2), comprises a holding device comprising a connecting screw integral with a mechanical element (E1) and held by a nut segmented in portions (4n) arranged between the connecting screw and an outer envelope integral with the other mechanical element (E2), the system (S) comprising a force generator generating a thrust force (F) in a longitudinal direction (X-X) and comprising an energy accumulator comprising a sealed chamber with a colloid of a porous matrix and liquid, the chamber deforming in the longitudinal direction (X-X) to adapt to the change from a compressed to a decompressed state in order to generate the force (F), and an activatable actuating element to, either apply a predetermined pressure to the chamber to keep the colloid in the compressed state, or not apply the predetermined pressure to allow the change in state of the colloid.

Abstract: The invention relates to a separation device for a spacecraft or launcher. The separation device includes an inner housing divided into at least two portions locked to each other by a locking device in a locking position. The locking device is arranged to move between a locking position and a releasing position. The separation device includes an initiator including means for providing high pressure fluid to an expansion chamber when the separation device is switched from a locked state to a released state. The high pressure fluid in an expansion chamber moves the locking device from the locking position to the releasing position when the separation device is switched from the locked state to the released state. The separation device comprises a dampening arrangement arranged to attenuate a peak load when the separation device is switched from the locked state to the released state.

Abstract: A set including a first element with a cylindrical shaped part, a second element having a cylindrical shaped groove with a circular opening in an outer surface of the second element, and a mechanical locking device. The mechanical locking device includes a tongue groove, a displacement groove and a flexible tongue in the displacement groove, and is configured to lock the cylindrical shaped part to the cylindrical shaped groove. The flexible tongue is configured to cooperate with the tongue groove for locking the cylindrical shaped part to the cylindrical shaped groove. The flexible tongue is configured to be reshaped and displaced in the displacement groove during locking, and spring back to a locked position. The flexible tongue is configured to exert a spring force on the tongue groove in the locked position.

Abstract: A clamp element, in particular a band clamp, has a first end portion and a second end portion which are arranged at a distance with respect to one another. A first element engages on the first end portion and a second element engages on the second end portion. The elements are or can be brought into engagement with one another by an engagement portion, and the engagement portion is formed between the end portions.

Abstract: A nose or tail assembly for a flight vehicle is provided in which the deployment of the canards or fins is driven by energy imparted by the shroud when it is released. A tip section is rotatably coupled to a base, and both are stowed in a volume between the shroud and nose/tail assembly. As the shroud is released, a drive feature engages the tip section to rotate and join the base to form a complete canard or fin. This eliminates the need for storing the canards or fins in or wrapped around the body and eliminates the need for a complex deployment mechanism occupying an internal volume of the body. Although viable for all sizes of flight vehicles, the shroud-driven deployment system scales to very small diameter vehicles in which internal volume is not available to store either flight surfaces or deployment mechanisms.

Abstract: An electronic device may be provided with wireless communications circuitry and control circuitry. The wireless communications circuitry may include centimeter and millimeter wave transceiver circuitry and a phased antenna array. A dielectric cover may be formed over the phased antenna array. The phased antenna array may transmit and receive wireless radio-frequency signals through the dielectric cover. The dielectric cover may have first and second opposing surfaces. The second surface may face the phased antenna array and may have a curvature. The curvature of the second surface may include one or more recessed regions of the dielectric cover. The one or more recessed regions of the second surface may serve to maximize and broaden the coverage area for the phased antenna array. The first surface may be conformal to other structures in the electronic device.

Abstract: Disclosed is a surgical ancillary device, preferably Y-shaped, including three contact portions intended to come into contact with three corresponding reference areas of an operation area, and a unit for determining an orientation coordinate system of the ancillary device in a Galilean orientation coordinate system. At least one of the first and second contact portions, and preferably both, includes a concave or convex end, for example a roller that is optionally mounted so as to be rotatably movable, or a gutter-shaped element. Each end comes into contact with two reference points in the corresponding reference area, which is respectively convex or concave. These two points accurately guide the rotation of the ancillary device in order to bring the third contact portion into contact with the third reference area. The orientations of the ancillary device define the orientation coordinate system, the determination of which can therefore be accurately reproduced.

Abstract: A missile includes a separable nose cone having an ejectable shell cooperating with a support element. The missile has a body with a main longitudinal axis and a nose cone having a shell connected by a rear end thereof to a support element of the missile and defined around a secondary longitudinal axis. The support element has a housing, and the rear end of the shell has a thickness adapted to be received in the housing in a contacting manner. The housing is configured to allow the shell to pivot and to maintain contact while the orientation of the shell is such that the secondary longitudinal axis is at an angle smaller than an ejection angle in relation to said main longitudinal axis, and to end the contact when the secondary longitudinal axis is at an angle higher than or equal to the ejection angle in such a way as to eject the shell from the missile.

Abstract: A space propulsion module for fitting to spacecraft is provided. The space propulsion module includes a solid propellant chemical thruster including a main body, and at least one electric thruster. The at least one electric thruster is mounted on main body of the solid propellant chemical thruster.

Abstract: The subject of the invention is a device for the in-flight conditioning of equipment of cryogenic circuits of an aircraft, which device includes means for bleeding air from outside the aircraft, means for extracting nitrogen from this air using a nitrogen separator of the OBIGGS type and means for distributing this nitrogen around the equipment. The device notably includes means for distributing nitrogen around the various pieces of equipment of cryogenic circuits using a system of piping provided with calibrated orifices.

Abstract: Various enhanced rocket fairings and associated mechanisms are discussed herein for split fairings with two fairing halves. In some implementations, electrically-actuated base clamps are included to deploy the rocket fairing by applying a spring force between a corresponding fairing half and a payload adapter, which directs movement of the fairing halves upwards and away from the payload adapter until release of the fairing halves. In other implementations, electrically-actuated fairing mechanisms are included to hold together a first fairing half and a second fairing half, and separate the first fairing half from the second fairing half using a spring force. In further implementations, one fairing half includes a tab feature configured to overlap a second fairing half. The tab feature can deform inward under a pressure differential between an exterior and a payload envelope to reduce a gap between the two fairing halves.

Abstract: One example embodiment includes an aircraft system. The system includes a body comprising a payload and a propulsion system. The propulsion system can be configured to enable launch of the aircraft system. The system also includes a shrouding system that substantially encloses at least a portion of the body in a shrouded state. The shrouding system includes a fairing portion and a sleeve portion that are arranged as detachably coupled with respect to each other and with respect to the at least a portion of the body. The fairing portion can separate from the sleeve portion in a deployed state and the body can become axially separated from the sleeve portion in the deployed state. The aircraft system can switch from the shrouding state to the deployed state during a detach stage of the launch of the aircraft system.

Abstract: A method and device enable the linear separation of two elements attached to each other through two connecting surfaces which are conical in this example, of a first element and a second element respectively, using thermite placed on the other side of the wall of the outer element, facing a connecting arrangement placed between both connecting surfaces. An electrical triggering of the thermite causes a quick and local warming-up, at the connecting arrangement which, after melting, enables both elements to be separated.

Abstract: A method and device enable the linear separation of two elements attached to each other, through two respective connecting surfaces of these two elements. A connecting layer is placed between both connecting parts. Thermite is used to melt this connecting layer. The thermite can be placed on the other side of the first connecting part towards the first element, a heat protecting plate completing this assembly. The thermite can also be placed in grooves provided on the connecting surface of the second connecting plate to be directly in contact with the connecting layer.

Abstract: A space vehicle system, a method of manufacturing the space vehicle system, and a method of launching the space vehicle system are disclosed. The method of manufacturing the space vehicle system may include disposing a first space vehicle with an upper core structure upon a second space vehicle with a lower core structure such that loads of the first space vehicle are transmitted to the lower core structure of the second space vehicle.

Abstract: A ring coupling includes a first cylindrical body defining an outward facing coupling surface extending in a circumferential direction. A second cylindrical body defines an inward facing coupling surface extending in the circumferential direction. A retainer ring is engaged to the coupling surfaces of the first and second cylindrical bodies to prevent axial disengagement of the first and second cylindrical bodies. The cylindrical bodies can be coupled without relative circumferential rotation of the first and second cylindrical bodies.

Abstract: An arrangement for locking arming conditions to prevent unintentional arming of SAI-units of ammunition units when the ammunition unit is subjected to external threats. A ring shaped shape memory alloy is provided in cooperation with a recess in a plunger arranged in connection to the SAI-unit and a fixed recess to prevent the plunger from axial movement when subjected to heating by changing the shape of the essentially ring shaped shape memory alloy to lock the plunger relative to the fixed recess.

Abstract: A device for coupling with a space satellite before the satellite is launched for the purpose of de-orbiting said satellite and/or returning it to Earth. The device includes: controller for controlling the device; propulsion system operatively connected with the control means; receiver for receiving control signals operatively connected with the control means; powering system for electrically powering the device; coupler for mechanically coupling the device with the satellite before the satellite is launched. The propulsion system is enabled by the controller on receipt of control signals for deorbiting the satellite and transferring it to a given orbit.

Abstract: An AUV is described that includes an external, deployable payload releasably attached to the exterior of the AUV. The release mechanism between the payload and the AUV is relatively simple and low cost. The payload is mounted external to the AUVs hull and does not significantly increase the cost of the AUV to which it is attached. There are no complex release mechanisms or intermediate launch systems attached to the AUV. Therefore, the described AUV can deploy payloads, such as sensors, that would normally be deployed from a manned platform. This can increase the payload capability of a small expendable AUV without increasing volume or cost of the AUV.

Abstract: An assembly comprising two parts temporarily connected by a connecting element surrounding the assembly. The connecting element being subjected to an internal deformation stress. The assembly having stress-keeping means with controlled stress relief, which connect two opposite ends of the connecting element so as to counteract the internal deformation stress. The assembly includes attaching means for attaching the connecting element to each of the parts. The attaching means includes at least two layers of cured adhesive which respectively coat the parts and make a surface connection between each of these parts and the connecting element. The internal deformation stress is at a sufficient level to enable the connecting element to be unsecured from the parts by extending to a rest position, when the stress-keeping means are controlled so as to release the ends of the connecting element.

Abstract: An expansion tube of a detonating pyrotechnic rupture piece is open next to pre-established rupture zones and, inside said open expansion tube there is disposed a sealed bladder which contains a pyrotechnic fuse.

Abstract: According to the invention, the device (1) comprises a bolt (6) including a locking member (9) which is mounted such that it can slide with respect to a first component (2) and can adopt a locked position in which the locking member (9) retains the second component (3) and an unlocked position in which the locking member (9) releases the second component (2), the transition from the locked position to the unlocked position taking place under the action of pyrotechnic means (5). In addition, a branch (4) that is at least partially deformable under the action of the pyrotechnic means (5) is arranged with respect to the bolt (6) in such a way that the transition from the locked position to the unlocked position takes place by means of the deformation of said branch (4).

Abstract: The present invention discloses a low foreign object damage nose weight for affixing to a either a standard or kinematic decoy flare comprising a thin walled nose cup having a closed end, an open end, an internal cavity, and at least one sidewall attached to said closed end and surrounding said internal cavity; and a metal powder disposed within the internal cavity for weighing down the forward end of the decoy flare, said nose cup capable of being affixed to a forward end of a decoy flare such that said powder is jettisoned from said nose cup upon burn out of a flare pellet subassembly of said decoy flare thereby reducing the weight of the nose cup and the possibility of foreign object damage to aircraft, ground troops, ground equipment and buildings resulting from the falling nose weight.

Abstract: A staged rocket apparatus includes first and second stages connected by a releasable connector. A plurality of pressurized gas struts are connected between the first and second stages and provide a separating force urging the first and second stages apart. The gas struts are held in a telescopingly collapsed first position by the releasable connector. The separating force is maintained at a minimum value so long as the releasable connector holds the struts in their first position. When the releasable connector is disconnected the separating force increases due to gas flow through a metering passage having a progressively increasing flow area from a high pressure chamber to a low pressure chamber.

Abstract: According to the present disclosure, devices, systems, and methods are disclosed in which two substantially parallel flanges are provided with rupture areas, respectively, located in the same element of the elements to be connected. In the disclosed device, the rupture areas and the portions of the flanges outside the rupture area are arranged so as to prevent the connected elements from catching after the separation thereof, and to limit the vibrations induced in the element in said rupture areas.

Abstract: A system for separating a first component and a second component is provided. The system includes a first joinder flange having at least one first fastener feature for coupling the first joinder flange to the first component. A second joinder flange is provided having at least one second fastener feature for coupling the second joinder flange to the second component. A separation portion is coupled between the first joinder flange and the second joinder flange, the frangible joint having at least one groove extending along width of the separation portion. An explosive member is arranged adjacent the separation portion. Wherein the first joinder flange includes at least one integral shock attenuation feature formed therein between the explosive member and the at least one first fastener feature.

Abstract: An expansion tube of a detonating pyrotechnic rupture piece is open next to pre-established rupture zones and, inside said open expansion tube there is disposed a sealed bladder which contains a pyrotechnic fuse.

Abstract: An elastomeric charge holder includes one or more holes formed therein into which is disposed an explosive charge. The elastomeric charge holder further includes one or more metal wires also disposed within the elastomeric charge holder. The elastomeric charge holder may be over molded or over extruded over each of the one or more metal wires, thereby retaining each of the one or more wires in place during use of the elastomeric charge holder. The one or more wires are also a better match of thermal coefficients to a metal confinement tube that holds the elastomeric charge holder, which results in improved retention of the elastomeric charge holder in place, particularly during initiation of the explosive charge.

Abstract: According to the invention, this piece comprises: e base section piece (1) provided with a projecting longitudinal heel (4) delimiting a longitudinal groove (7), a longitudinal pyrotechnic cord laid in said groove; and a plurality of consecutive section piece portions (2) fixed one after the other to said base section piece (1) by first fixing means (9). Between the consecutive section piece portions (2) are second fixing means (18), distributed along said base section piece (1) and independent of said first fixing means (9), enabling said pyrotechnic cord to be fixed and positioned relative to said base section piece (1).

Abstract: Temporary connection and pyrotechnic separation device with a longitudinal axis (X) comprising a pyrotechnic expansion tube (14) mounted in a space (11) formed in a connection zone between a first (2) and second assembly (4) to be separated, the second assembly (4) being formed of a stack of plies (12.1, 12.2) bonded together, the two assemblies (2, 4) being connected to each other by two metal parts (10.1, 10.2), said metal parts being fixed onto the first assembly and bonded onto the outer plies (12.1) of the second assembly (4), the bonding area between said outer ply (12.1) and the adjacent inner ply (12.2) is less than the bonding area between two inner plies (12.2) forming a fuse ply, such that, when the pyrotechnic expansion tube (14) is used, the outer ply (12.1) separates from the adjacent inner ply.

Abstract: The present disclosure generally relates a high strength, low weight, and low shock rocket body separating joint for the purpose of joining rocket bodies, and method of assembly thereof. The solution combines a radax joint, joined by fasteners, with a flattened bladder and inflation system coupled thereto. Upon activation of the inflation system, the bladder is pressurized and exerts a separating force between the members of the radax joint, overcoming the load carrying capability of the fasteners and breaking apart the radax joint.

Abstract: Some embodiments pertain to a projectile that includes a propellant and a casing that encloses the propellant such that the casing acts as a reaction chamber during flight of the projectile. The casing includes a plurality of flechettes. When the projectile strikes (or is near) a target, a large internal sheer pressure forms within the casing. This sheer pressure causes the flechettes to sheer apart at the thinnest sections of the casing. Once the thin sections of the casing are sheered apart, the flechettes will be unconstrained such that the flechettes take individual flight paths.

Abstract: The present invention relates to an apparatus for splitting and removing a shroud from an airborne vehicle, that comprises a shroud that includes two components, linkable one to another along their lengths, and wherein upon being fastened one to the other, they form a shroud with a lengthwise axis and an inner space, and having a base sector around the circumference of the bottom part of said shroud, and wherein said base is connectable to said airborne body and a fastening assembly for fastening said two components of said shroud one to the other, and wherein said fastening assembly is given to be torn on stretching upon detonation of a pyrotechnic charge and a piston assembly that disassembled at the completion of the piston's stroke, and is operable by said pyrotechnic charge, and wherein said piston assembly serves for timed tearing of said fastening assembly.

Abstract: The present disclosure generally relates a high strength, low weight, and low shock rocket body separating joint for the purpose of joining rocket bodies, and method of assembly thereof The solution combines a radax joint, joined by fasteners, with a flattened bladder and inflation system coupled thereto. Upon activation of the inflation system, the bladder is pressurized and exerts a separating force between the members of the radax joint, overcoming the load carrying capability of the fasteners and breaking apart the radax joint.

Abstract: The present invention discloses a low foreign object damage nose weight for affixing to a either a standard or kinematic decoy flare comprising a thin walled nose cup having a closed end, an open end, an internal cavity, and at least one sidewall attached to said closed end and surrounding said internal cavity; and a metal powder disposed within the internal cavity for weighing down the forward end of the decoy flare, said nose cup capable of being affixed to a forward end of a decoy flare such that said powder is jettisoned from said nose cup upon burn out of a flare pellet subassembly of said decoy flare thereby reducing the weight of the nose cup and the possibility of foreign object damage to aircraft, ground troops, ground equipment and buildings resulting from the falling nose weight.

Abstract: Temporary connection and pyrotechnic separation device with a longitudinal axis (X) comprising a pyrotechnic expansion tube (14) mounted in a space (11) formed in a connection zone between a first (2) and second assembly (4) to be separated, the second assembly (4) being formed of a stack of plies (12.1, 12.2) bonded together, the two assemblies (2, 4) being connected to each other by two metal parts (10.1, 10.2), said metal parts being fixed onto the first assembly and bonded onto the outer plies (12.1) of the second assembly (4), the bonding area between said outer ply (12.1) and the adjacent inner ply (12.2) is less than the bonding area between two inner plies (12.2) forming a fuse ply, such that, when the pyrotechnic expansion tube (14) is used, the outer ply (12.1) separates from the adjacent inner ply.

Abstract: A separation device for separating parts along a seam includes a frangible structure and a pressure tube assembly within the frangible structure. The pressure tube assembly includes a pressure tube which contains an explosive detonation assembly/cord that can be initiated to expand the pressure tube, and break the frangible structure with a shock force. The pressure tube assembly also includes a explosive manifold that is recessed in the frangible structure, not protruding from an outer surface of the frangible structure. The explosive manifold receives the ends of the pressure tube, and includes a detonator for detonating the explosive detonation assembly/cord. The explosive manifold has circular-cross-section fittings for accepting a circular ends of the pressure tube. By not having any part of the pressure tube assembly protrude from the frangible structure, improved performance may be achieved. Having circular fittings also improves the seal between the pressure tube and the explosive manifold.

Abstract: An apparatus includes a heat-to-detonation transition manifold, a heat pipe connected to the transition manifold, a linear shaped charge, and a transfer line connecting the heat-to-detonation transition manifold and the linear shaped charge. An apparatus includes a thermally-activated pyrotechnic train and a linear shaped charge coupled with the pyrotechnic train. A method includes initiating a deflagrating material at a predetermined temperature or within a predetermined range of temperatures, initiating a detonating material with the deflagrating material, and initiating a linear shaped charge with the detonated material.

Abstract: A multi-stage missile with plural stages adapted to be physically coupled to and decoupled from adjacent stages and a processor disposed on a single stage for controlling each stage thereof. In the illustrative embodiment, the processor includes a field programmable gate array. In the illustrative embodiment, the processor is disposed on stage 4 of a four-stage missile and performs guidance and navigation functions for each stage and control functions for stages 2, 3 and 4. In a specific embodiment, a serial bus interface is included for coupling the processor to electronic circuitry on each of the stages of the missile. In the best mode, the interface is an IEEE 1394b interface with a physical layer interface and a link layer interface.

Abstract: A staged rocket apparatus includes first and second stages connected by a releasable connector. A plurality of pressurized gas struts are connected between the first and second stages and provide a separating force urging the first and second stages apart. The gas struts are held in a telescopingly collapsed first position by the releasable connector. The separating force is maintained at a minimum value so long as the releasable connector holds the struts in their first position. When the releasable connector is disconnected the separating force increases due to gas flow through a metering passage having a progressively increasing flow area from a high pressure chamber to a low pressure chamber.

Abstract: A missile includes several subvehicles that are initially mechanically coupled to a missile main body, and a separation system for separating the subvehicles from the missile main body. The separation system has a single triggering mechanism to simultaneously provide energy to separate all of the subvehicles. This advantageously provides only a single shock to the system by actuating the system to separate the subvehicles. By limiting the shocks to the single shock of actuating the energy system and the shocks of the mechanical disengagement of the individual subvehicles, the disengagement system has improved performance. The subvehicles may be separated from the main body in radial directions substantially perpendicular to a central axis of the main body. This may provide for smoother disengagement, with less tipping, and may provide for greater, more uniform spacing between the disengaged subvehicles.

Abstract: Disclosed is a separation device of an ejector motor for a portable missile, capable of being separated from a missile without any additional separation devices after ejecting the missile. An ejection rocket motor and a separation device are integrally formed. Ejection is performed by a thrust generated while the ejection rocket motor is combusted, and separation is performed by cutting off shearing bolts with using a force generated from a separation cylinder when the combustion of the ejection rocket motor has been completed. This operation and configuration may minimize a weight and a space occupied by a general ejection and separation device in a missile system.

Abstract: A multi-stage vehicle separation system and method that facilitates an active separation on the booster by igniting a small quantity of propellant in the dead volume between the second stage rocket motor nozzle and the booster dome. In the most general embodiment, the invention includes a nozzle; a first fuel propellant disposed within the nozzle; a thermal barrier separating the first and second fuel propellant, an environmental seal protecting the second fuel propellant and an arrangement for activating the first fuel propellant. The nozzle is disposed in an upper stage of a two-stage vehicle. An arrangement such as a V-Band clamp is included for retaining the lower stage of the two-stage vehicle. Electronic commands release the lower stage and activate the first propellant in a timely manner to effectively separate the lower stage from the upper stage. The embedded propellant is activated with an arm fire device.

Abstract: Disclosed is a separation device of an ejector motor for a portable missile, capable of being separated from a missile without any additional separation devices after ejecting the missile. An ejection rocket motor and a separation device are integrally formed. Ejection is performed by a thrust generated while the ejection rocket motor is combusted, and separation is performed by cutting off shearing bolts with using a force generated from a separation cylinder when the combustion of the ejection rocket motor has been completed. This operation and configuration may minimize a weight and a space occupied by a general ejection and separation device in a missile system.

Abstract: The present invention relates to an apparatus for splitting and removing a shroud from an airborne vehicle, that comprises a shroud that includes two components, linkable one to another along their lengths, and wherein upon being fastened one to the other, they form a shroud with a lengthwise axis and an inner space, and having a base sector around the circumference of the bottom part of said shroud, and wherein said base is connectable to said airborne body and a fastening assembly for fastening said two components of said shroud one to the other, and wherein said fastening assembly is given to be torn on stretching upon detonation of a pyrotechnic charge and a piston assembly that disassembled at the completion of the piston's stroke, and is operable by said pyrotechnic charge, and wherein said piston assembly serves for timed tearing of said fastening assembly.