Abstract: A device for securing at least one sling for transporting a load under a helicopter, the securing device comprising at least a first strap and at least a second strap, a connection mechanism configured, in the closed state, to connect the straps, to form a comprehensive security strap capable of supporting a sling and, in the open state, to release the straps for releasing the sling, and an actuator configured to open the connection mechanism following a mechanical effort being introduced, the connection mechanism comprising cascading reduction means configured to reduce the resistance force during the opening of the connection mechanism generated by the load connected to the sling.

Abstract: To provide a parachute device capable of quickly and reliably opening a parachute even when an airflow effect during flying or falling of a flight device cannot be immediately obtained. A parachute device (4) includes a parachute (400), a parachute accommodation section (40) configured to accommodate the parachute, at least one flying body (43) connected to the parachute, and an ejection section (41) configured to hold the flying body and to eject the flying body held, and the flying body includes a flying body main body section (44) engaged with the ejection section, and a gas generating device (45) disposed in an internal space (440) defined by the ejection section and the flying body main body section, and configured to generate gas.

Abstract: A device for unlocking a system for closing a container by means of a tie, such as a rope or strap, in particular a tie tensioned between closing eyelets, includes a cutting tool (O) capable of cutting the tie in order to unlock the closing system. It also includes an actuation member linked to the cutting tool, the actuation member being capable of being manipulated manually by a user in order to cause the cutting tool (O) to move into a position for severing the tie.

Abstract: A parafoil for operation at high altitudes, in low density air, or at low airspeeds, and methods for opening same. Some versions of the parafoil comprise flexible members connected to the parafoil canopy. When the parafoil canopy is in a stowed configuration, the members are deformed, storing elastic energy. When the canopy is released from its stowed configuration, the members spring back to their undeformed shapes, thereby opening or assisting with opening the canopy. The flexible member may also be attached to a base structure, which is attached to the payload. The members may comprise rods or hollow tubes that can be flexed using a fulcrum near the base structure, or a spacer plate, so that the ends connected to the canopy are restrained by a parachute bag containing the stowed or packed canopy. The parachute bag can be opened prior to or during detachment of the parafoil from the flight vehicle.

Abstract: A parachute release mechanism includes a housing, a strap hinge pin pivotably mounted to the housing, a cord coupled to the housing, and a cord tensioner coupled to the housing and coupled to the cord, wherein the cord tensioner is configured to impart a desired tension to the cord. The strap hinge pin is pivotable between a secured position and a released position, wherein in the secured position the strap hinge pin is configured to support a suspension strap for a payload and in the released position the suspension strap is enabled to disengage from the strap hinge pin. The cord is configured to retain the strap hinge pin in the secured position.

Abstract: A one-time flare mechanism system for use with an aerial payload system is describe which uses minimal actuation force to produce a reliable flare with minimal shock to the payload, parafoil and rigging.

Abstract: A system to deploy a parachute is disclosed. In various embodiments, a plurality of rockets are attached to a perimeter of the parachute. Each of the rockets is configured to fly initially in a first direction substantially in a direction of deployment of the parachute and to fly subsequently along a trajectory that includes a component that is substantially perpendicular to the direction of deployment and extends radially from a center of the parachute.

Abstract: A system to deploy a parachute is disclosed. In various embodiments, a plurality of rockets are attached to a perimeter of the parachute. Each of the rockets is configured to fly initially in a first direction substantially in a direction of deployment of the parachute and to fly subsequently along a trajectory that includes a component that is substantially perpendicular to the direction of deployment and extends radially from a center of the parachute.

Abstract: An impact mitigation system for an aircraft and method of deploying the impact mitigation system is disclosed. A state parameter of the aircraft is obtained. The state parameter is used with an aircraft performance model to determine an acceleration capability of the aircraft. A trajectory of the aircraft is predicted using the state parameter of the aircraft and the acceleration capability of the aircraft. A location of an object with respect to the aircraft is determined and the impact mitigation system is deployed when the predicted trajectory indicates a contact with the object at a predicted contact velocity higher than a threshold velocity at a future time.

Abstract: A parachute system includes a parachute which is coupled to a rocket via a first load path, which includes a tow line, one or more upper parachute lines, and one or more lower parachute lines, and a second load path, which includes a release line. The rocket is configured to tow the parachute via the tow line. There is a lower parachute line restrainer which when released permits the lower parachute lines to extend to full length. There is also a release which is configured to open in the event a load switches from the first load path to the second load path; when the release is open, the parachute and the rocket are permitted to separate.

Abstract: An end guide for a cord attachment device includes a cloth. The cloth is configured to fold over, unto, and overlap itself. The cloth has three portions. The first and second portions are longer than a third portion. The cloth is folded axially about a central longitudinal axis. The central longitudinal axis spans from the proximal end to the distal end of the cloth. The folding causes the first and second portions to overlap. A plurality of flutes are configured in the cloth by a plurality of stitch lines running parallel to each other and extending through first and second sides (the front and back) of the cloth and extending through the overlap of the first and second portions. At least one of the plurality of stitch lines are located between each of the flutes. The flutes span to both the proximal and distal ends of the cloth.

Abstract: An end guide for a cord attachment device includes a cloth. The cloth is configured to fold over, unto, and overlap itself. The cloth has three portions. The first and second portions are longer than a third portion. The cloth is folded axially about a central longitudinal axis. The central longitudinal axis spans from the proximal end to the distal end of the cloth. The folding causes the first and second portions to overlap. A plurality of flutes are configured in the cloth by a plurality of stitch lines running parallel to each other and extending through first and second sides (the front and back) of the cloth and extending through the overlap of the first and second portions. At least one of the plurality of stitch lines are located between each of the flutes. The flutes span to both the proximal and distal ends of the cloth.

Abstract: The present disclosure provides a parachute deployment system. The system may include a deployment spring arranged on a launch platform with a parachute that is foldable and positionable on an opposite side of the deployment spring from the launch platform. The system may also include a bridle line attached to the parachute, and a lanyard line having a first end and a second end. The first end of the lanyard line may be attached to the deployment spring, and the second end of the lanyard line may be attached to the launch platform. The system may also include a trigger system configured to initiate deployment of the parachute. Upon deployment, the deployment spring may be configured to launch the parachute and the bridle line substantially perpendicular to the launch platform. After deployment, the deployment spring and the lanyard line may be configured to hang from the launch platform.

Abstract: A trap system is presented for deployment of a reserve parachute. The trap system includes a trap line with a first end coupled to a main parachute and a trap attached to a surface of the container. The trap includes an outer perimeter to removably hold the trap line and an interior to removably hold the reserve bridle. A kit is also presented for converting a parachute container into an improved parachute container to deploy a reserve parachute. The kit includes an attachment to be secured to a surface of the parachute container. The attachment includes a trap line with a first end configured to be coupled to the first end of the RSL lanyard, and a trap secured to a region of the attachment, with an outer perimeter to removably hold a second end of the trap line and an interior to removably hold the reserve bridle.

Abstract: A separating mechanism for releasing an equipment bag. The mechanism includes a base assembly, a removable soft loop assembly, an attachment ring, and a retention member. The base assembly includes a base member, an aperture, and one or more base assembly rings. The soft loop assembly includes a soft loop base and a soft loop. The soft loop is inserted through the aperture and a first of the base assembly rings. The soft loop base is configured to not be pulled through the aperture. A last of the base assembly rings is inserted through the attachment ring. The retention member is inserted through the soft loop to restrain the first base assembly ring. The base assembly rings are sequentially engaged to couple the attachment ring with the base member. The retention member is pulled out of the soft loop to release the base assembly rings thereby releasing the attachment ring.

Abstract: A dual purpose deployment line for a parachute system is disclosed. The system includes a main line and a plurality of cascading release loops disposed proximate a first end of the main line. The plurality of cascading release loops are configured to be releasably secured to an aircraft anchor ring. The deployment line includes a release pin secured to a first end of the release line, where the release pin is in communication with the plurality of cascading release loops and adapted to pull free and release the cascading release loops from the anchor ring when a parachute is deployed. An optional locking pin is adapted to selectively secure the plurality of cascading release loops in place when desired to retain the deployment line to the anchor ring when the parachute is deployed and the release pin is pulled free.

Abstract: A dual purpose deployment line for a parachute system is disclosed. The system includes a main line and a plurality of cascading release loops disposed proximate a first end of the main line. The plurality of cascading release loops are configured to be releasably secured to an aircraft anchor ring. The deployment line includes a release pin secured to a first end of the release line, where the release pin is in communication with the plurality of cascading release loops and adapted to pull free and release the cascading release loops from the anchor ring when a parachute is deployed. An optional locking pin is adapted to selectively secure the plurality of cascading release loops in place when desired to retain the deployment line to the anchor ring when the parachute is deployed and the release pin is pulled free.

Abstract: A dual purpose deployment line for a parachute system is disclosed. The system includes a main line and a plurality of cascading release loops disposed proximate a first end of the main line. The plurality of cascading release loops are configured to be releasably secured to an aircraft anchor ring. The deployment line includes a release pin secured to a first end of the release line, where the release pin is in communication with the plurality of cascading release loops and adapted to pull free and release the cascading release loops from the anchor ring when a parachute is deployed. An optional locking pin is adapted to selectively secure the plurality of cascading release loops in place when desired to retain the deployment line to the anchor ring when the parachute is deployed and the release pin is pulled free.

Abstract: A parachute can be opened automatically without requiring manual operation. In addition, the parachute is capable of staying balanced during the course of landing. The parachute comprises: a spherical canopy, an air guide member and four assistant canopies. The air guide member is a rotation symmetrical structure with respect to the central axis, each of the cylindrical members is also a rotation symmetrical structure with respect to the assistant central axis, and the assistant canopies are also symmetrically arranged with respect to the central axis, so as to maintain the parachute in a stable and balanced state when the parachute is falling.

Abstract: The safety device comprises a first bridle connecting a pilot chute of the reserve parachute to a deployment bag, a second bridle connecting the main parachute to the first bridle, a pin fastened to this first bridle and passed in a releasable manner in a loop formed on a locking bridle fastened to the locking pin and passed through a loop fastened to the second bridle and two eyelets formed through the first bridle.

Abstract: Embodiments of the invention relate to systems and methods for a self-deploying vehicle drag device. In one embodiment, a drag device for a vehicle can be provided. The drag device can include a chute body, wherein the chute body is connected to the vehicle. The drag device can also include at least one collapsible member mounted to the chute body, wherein the at least one collapsible member and chute body are maintained in respective compressed configurations until deployed. Furthermore, the drag device can include at least one device adapted to release the chute body from the vehicle, wherein the chute body and the at least one collapsible member are deployed in expanded configurations with respect to the vehicle.

Abstract: A programmable electronic initiation device that monitors flight parameters to accurately initiate parachute disreefing or disconnect. Tracking elapsed time commencing with a startup trigger and directly measuring atmospheric conditions; temperature and pressure are used for altitude or speed calculations in addition to monitoring the acceleration sensor and liquid contact sensor for impact sensing. The device is user programmable via a software application for initiation based upon elapsed time, altitude, speed, and/or upon landing. The device may also be separated into a sensing module and an actuating module, and linked wirelessly to allow control of one or multiple actuating modules by one sensing module.

Abstract: A skydiving equipment with a drogue parachute to capture the deployment bag until the opening, and to suspend the parachutist(s) in a horizontal position during the free fall, while distributing the tension forces of the drogue parachute such that the ripcord operation is effortless, includes a first fastening strap bearing a lower tab and a second fastening strap bearing an upper tab to fasten the drogue parachute drogue bridle to the parachute pack at the desired level of the main container. A three-ring system connects the upper tab and the lower tab to the drogue parachute drogue bridle and is operational to effortlessly cause the release of the upper tab and the lower tab out of the drogue bridle simultaneously or successively, while the main container opens at a different time.

Abstract: In various examples, a speed limiting apparatus (100, 200) includes a garment (102, 202)) configured to be worn by a user (10). The garment includes an enclosure (110, 220). A speed limiting assembly (120, 220) is coupled to the garment. The speed limiting assembly includes a chute (136, 236) disposed within the enclosure with the chute in a storage configuration (120A). The chute is deployable from the storage configuration to a deployed configuration (120B). A deployment bladder (130, 230) is separate from the chute. The deployment bladder is positioned proximate the enclosure and the chute such that at least partial inflation of the deployment bladder opens the enclosure and deploys the chute. In another example, a method of using a speed limiting apparatus is provided.

Abstract: A pilot chute device is connected to a parachute canopy for deploying the parachute canopy out of a container adapted to be closed and opened and within which the parachute canopy is foldable. The pilot chute device includes an inflatable pilot chute adopted to assist the deployment of the parachute canopy, the inflatable pilot chute being foldable into the container, and a spring device adopted to push the inflatable pilot chute outside the container when the container is opened. The spring device is dispensed apart from the inflatable pilot chute, between the pilot chute and the parachute canopy.

Abstract: A parachute inlet control system is configured to provide an improved inflation profile for solo and/or clustered parachutes. An inlet parachute is coupled to a main parachute via a plurality of lacing loops and/or reefing rings. The lacing loops may be passed through the reefing rings and/or may be routed around one or more of the main parachute suspension lines. The inlet parachute is located in the inlet area of the main parachute, and causes the inlet of the main parachute to rapidly form a desirable shape. The inlet parachute and lacing loops function as a reefing means, and prevent full inflation of the main parachute until a reefing cutter has functioned. In this manner, parachute failures, such as those due to leading and/or lagging parachutes in a parachute cluster, may be reduced or eliminated.

Abstract: The disclosure provides a parachute release device which may include a connecting element capable of connecting to an aircraft and to a parachute and a locking mechanism capable of releasing the connecting element from the aircraft upon being actuated by an actuator, wherein the parachute may be connected to the connecting element by a multiplicity of points, wherein the locking mechanism is adapted to inhibit a force from being applied to the actuator and wherein the device may be suitable for use in small weights aircrafts due to its small size and weight. The disclosure further provides a method for releasing a parachute from an aircraft, the method may include activating an actuator capable of releasing a locking mechanism, wherein the locking mechanism is adapted to release a connecting element from an aircraft upon being actuated, wherein the connecting element is adapted to connect a parachute and wherein the locking mechanism is adapted to inhibit a force from being applied to the actuator.

Abstract: The recovery and rescue system includes a sail (5) with rigging (10) fitted around a spreader conduit (4), with an intake and outlet nozzle, wherein a starting system (6) is provided, including mechanical (12-13) and electromechanical (17-18) opening mechanisms, in the first case operated by a manual lever (16) and in the second case operated by a button (19). Air driven through the intake of the spreading conduit (4) activates the starting system (6) in order to spread the sail (5) and by parachute means retain or brake the aircraft wherein the said system assembly is fitted. Said system can be housed inside the aircraft in a container provided for the purpose.

Abstract: The safety device comprises a first bridle connecting a pilot chute of the reserve parachute to a deployment bag, a second bridle connecting the main parachute to the first bridle, a pin fastened to this first bridle and passed in a releasable manner in a loop formed on a locking bridle fastened to the locking pin and passed through a loop fastened to the second bridle and two eyelets formed through the first bridle.

Abstract: A pilot chute device is connected to a parachute canopy for deploying the parachute canopy out of a container adapted to be closed and opened and within which the parachute canopy is foldable. The pilot chute device includes an inflatable pilot chute adopted to assist the deployment of the parachute canopy, the inflatable pilot chute being foldable into the container, and a spring device adopted to push the inflatable pilot chute outside the container when the container is opened. The spring device is dispensed apart from the inflatable pilot chute, between the pilot chute and the parachute canopy.

Abstract: In one form of the invention, a deployment control for releasing a rocket recovery device such as a parachute includes an electrical heating element extensible along a heat-severable reach of an elongate retainer capable of being wrapped closely about the recovery device to retain the recovery device in a compact form until the reach is severed as the result of electricity being supplied to the heating element to thereby release and deploy the recovery device. In other forms, an apparatus for cutting a heat meltable retainer to release and deploy a rocket recovery device includes a heating element extending along at least a short reach of the retainer, and a control device for supplying electricity to the heating element for heat severing the retainer reach.

Abstract: A life parachute for ultra-lightweight aircrafts or for lightweight aircrafts includes a canopy of the parachute fitted with a pole opening and at least some wedge-shaped section of the canopy at the top half of its height is fitted with a discharge valve of air from the inside space of the canopy and a slider is installed at suspension parachute cords. The slider is formed in a ring fitted with a central opening surrounded with netting having, at least in peripheral edges, a local stiffener. Through openings are formed for the suspension parachute cords. The discharge valves are in the width of the single wedge-shaped sections, overlapped with parachute material, with a bottom open end. The discharge valves of the air are formed either with loose vents or at the open end of the parachute material. The slider is, advantageously, in the form of a regular polygon composed of single tetrahedral parts of the netting which are connected to one another through the local stiffeners.

Abstract: A parachute container system including: a reserve compartment; a main compartment; a reserve parachute pathway configured to enable a mechanical connection between a reserve parachute canopy and a reserve parachute connection point external to the parachute container system when a reserve parachute canopy is positioned in the reserve compartment; and a main parachute pathway configured to enable a mechanical connection between a main parachute canopy and a main parachute connection point external to the parachute container system when a main parachute canopy is positioned in the main compartment. When the parachute container system is positioned on a parachutist at least a portion of the reserve compartment is disposed between the main compartment and the parachutist.

Abstract: An automatic activation device for a parachute has a pressure input for inputting a pressure value and is provided for operating in selectable working configurations according to which a reference pressure is determined either on the basis of the input pressure value or on the basis of a QNH value. Preferably the device can also operate in another selectable working configuration, where a preset time and a reference fall down speed are used.

Abstract: A system and method of deploying a parachute system, wherein the system functions with a timed delay or without a timed delay. The system can include a primary static line and a release-away line, wherein the primary static line is connected to a main chute and also to a soft link. The soft link can be cut by a cutter, thereby releasing the parachute system from an aircraft. Alternatively, the primary static line may contain a cable, wherein the cable features a three or more loop assembly that allows for release of the primary static line from the aircraft. The system may also utilize a three ring assembly or other mechanical actuation device. The system may include a drogue chute as well as a main chute.

Abstract: An article of manufacture, a retractable safety ripcord device for use with a reserve parachute; the device uses a non-metallic flexible line between a first end with handle, a second end with a loop and at least one rubber shock cord integrated into the line. Also used is a single handle and reserve pin releasably attached via the loop wherein the pin separates from the loop after activation.

Abstract: Having described and examined the nature of my invention and the manner in which it is to perform, I claim: 1. A parachute comprising of one canopy having devices attached to harness and cords connecting to said harness to the other edge of the canopy in combination connected to devices which automatically deploys canopy in 2 seconds and also informs user of correct procedures on use of said parachute with the added feature of a pull cord which may be considered an important improvement from the point of a safety factor.

Abstract: A releasable deployment line for a parachute system is provided. The releasable deployment line may include a first segment of material including an aircraft end configured to be operably connected to an aircraft, and a release end configured to be operably connected to a first section of a multi-ring release system. The replaceable deployment line may further include a second segment of material including a container end configured to be operably connected to a parachute container, and a ring end configured to be operably connected to a second section of the multi-ring release system and a third segment of material. The third segment of material may include a parachute end configured to be operably connected to a parachute within the parachute container, and a pin end configured to be operably connected to a retaining pin associated with the first section of the multi-ring release system.

Abstract: A parachute deployment deceleration assist device for a jumper is disclosed that includes an inverted pocket formed from at least one web of material. The device further includes at least one removable harness attachment means fixed to a peripheral edge of the pocket. Each harness attachment means is selectively attachable to a harness assembly of a parachute between a canopy thereof and the jumper, preferably at a connector link and within easy reach of the jumper when the parachute is fully deployed. In use, before the canopy is inflated the inverted pocket inflates and aids in the deceleration of the jumper, reducing the shock experienced by the jumper upon full inflation of the canopy. Once the canopy is fully inflated and the jumper is falling at a substantially constant speed, the jumper may reach up to remove the device from the harness assembly.

Abstract: A parachute control system is actuated primarily by drogue parachute drag force. Drag force is used as a proxy for vehicle airspeed. The control system uses altitude and force sensors combined with a chronograph to determine the state of a deployed drogue parachute. It then compares the sensed condition with a condition defined by preset altitude, force, and time values. Once both altitude and drogue parachute drag force are below certain maximum values and within pre-determined time windows, an event trigger signal is generated.

Abstract: A reefing apparatus for controlling inflation of a gliding wing parachute which has a generally rectangular or trapezoidal canopy with four outer corners. The reefing mechanism includes a primary reefing loop with four supplemental reefing loops movably secured thereto by loops and connected through mounting rings to the four corners of the canopy to retain it in a general cloverleaf shape during initial stages of deployment and responsive to cutting of the primary reefing loop for release thereof for allowing full deployment or deployment into another reefed stage of the gliding wing canopy. The suspension lines are divided into four groups primarily defined by the corner closest to the point of attachment between the suspension line and the canopy.

Abstract: The present invention relates to a lifesaving parachute, for moving people in danger to the ground safely in the case of accidents causing the loss of lives, such as fire of a high-storied building, earthquake and the like, which includes a main body having straps for a user to wear the parachute, stick elements formed of a unit length and fixed to the main body along a periphery thereof, elastic elements connected to connection elements of the stick elements for applying elastic force to the stick elements in a spreading direction of the stick elements, and an empty receiving case having an opened lower part for receiving the main body as folded.

Abstract: A device, system and method of reserve parachute deployment comprising; a reserve bridle 2 connecting the reserve deployment bag 5 to the reserve pilot chute 4, and a lanyard 3 connecting the main parachute 1 to the reserve bridle 2 with a releasable attachment and a retention means of this attachment. This connection being placed onto a holding flap 17 of the reserve container 22, by releasable holding means. The system and method of realization allows the reserve parachute to be activated without cutting-away a main parachute, in a manner that the holding means are not released, while if the main parachute is cut away then the holding means release without the retention means doing so.

Abstract: A method of severing an extraction line connected between an extraction parachute and a cargo load when the cargo load fails to eject from an aircraft. The method comprises the steps of spacing a cutter from the extraction line; spring-biasing the cutter in the direction of the extraction line; mechanically restricting the cutter with restricting means from engaging and severing the extraction line; and disabling the restricting means in response to a radio signal from a transmitter on the aircraft so that the cutter is released and severs the extraction line.

Abstract: The device enables the gradual opening of the parachute canopy, round or square, during the spreading phase of the canopy (12), by an arrangement on the lower surface (30) of the canopy (12), combined with an arrangement on the slider (26) comprising at least a magnetic element (Z) provided on the canopy, which is attracted by at least another element (M) which is positioned on the slider (26). The device ensuring the holding of the slider (26) on bottom of the canopy during the spreading phase, thus ensuring that the slider (26) will not be displaced before the woven fabric (50) takes the shape of a dome (42) during this spreading phase prior to the inflating phase of the canopy (12), as it was the case in the prior art.

Abstract: An article of manufacture, a retractable safety ripcord device for use with a reserve parachute system is disclosed, comprising: At least one non-metallic means for connecting between an operator end with attachment means and a pin end with pin end with attachment means, and; at least one elastic spring means integrated into said means for connecting. Optional handles and reserve closing pin may also be used with versions of the invention.

Abstract: A continuous disreefing apparatus has a sleeve that has a diameter and is made from a flexible, resilient material that allows the sleeve to diametrically contract when the sleeve is under tension and to diametrically relax when such tension is substantially reduced or removed. The sleeve has a portion thereof configured for connection to a parachute suspension line. The continuous disreefing apparatus includes a reefing line that extends through the sleeve and is arranged for movement through the sleeve wherein the rate at which the reefing line moves through the sleeve is controlled by the amount of tension on the sleeve.

Abstract: An automatic activation device for a parachute. The device comprises pressure input means for inputting a pressure value. The device is provided for operating in selectable working configurations according to which a reference pressure is determined either on the basis of the input pressure value or on the basis of a QNH value. Preferably the device can also operate in another selectable working configuration, where a preset time and a reference fall down speed are use.

Abstract: A continuous disreefing apparatus has a sleeve that has a diameter and is made from a flexible, resilient material that allows the sleeve to diametrically contract when the sleeve is under tension and to diametrically relax when such tension is substantially reduced or removed. The sleeve has a portion thereof configured for connection to a parachute suspension line. The continuous disreefing apparatus includes a reefing line that extends through the sleeve and is arranged for movement through the sleeve wherein the rate at which the reefing line moves through the sleeve is controlled by the amount of tension on the sleeve.

Abstract: A device for severing an extraction line connected between a cargo load and an extraction parachute when the cargo load fails to eject from an aircraft. The device comprises a cutter spaced from and spring-biased in the direction of the extraction line; a housing for the cutter; elements for mechanically restricting the cutter from engaging and severing the extraction line; and elements responsive to a radio signal from a transmitter on the aircraft for disabling the restricting means so that the cutter is released and severs the extraction line.