Abstract: Sensor data that includes or more of the following: (1) aircraft state information associated with an aircraft or (2) parachute canopy state information associated with a parachute canopy is received. The parachute canopy is coupled to the aircraft at a point aft of a center of mass of the aircraft. It is determined, based at least in part on the sensor data, whether to generate a control signal associated with maneuvering the aircraft into a nose-up position. A recovery action is performed, including by deploying the parachute canopy; wherein a load on the parachute canopy is reduced in the event the aircraft is in the nose-up position compared to the aircraft being in a nose-down position.

Abstract: An aerial vehicle safety apparatus includes an expandable object and an ejection apparatus. The ejection apparatus includes a container that accommodates the expandable object and has an opening provided on one end side, a moving member provided in the container, the moving member including an emission base carrying the expandable object on a side of the opening, the moving member being movable along an inner wall of the container, and a driver that ejects the expandable object by moving the moving member toward the opening. A space located opposite to the opening when viewed from the emission base and surrounded by the container and the moving member communicates with a space located outside the space through a communication portion.

Abstract: A multi-modal aircraft recovery system is disclosed. In various embodiments, the system includes a first aircraft recovery parachute having a first set of physical attributes optimized for a first set of conditions and a second aircraft recovery parachute having a second set of physical attributes optimized for a second set of conditions different from the first.

Abstract: A selection is made between single stage and multistage parachute deployment for a vehicle based at least in part on vehicle state information. In the event multistage parachute deployment is selected, a drogue parachute is deployed during a first deployment stage and afterwards, a main parachute is deployed during a second deployment stage. In the event single stage parachute deployment is selected, at least the main parachute is deployed in a single stage where in the event the drogue parachute is deployed during the single stage, the drogue and main parachute are deployed simultaneously.

Abstract: Features for a high altitude lighter-than-air (LTA) system and associated methods. A zero-pressure balloon (ZPB) is attached in tandem with one or more variable ballast air super-pressure balloons (SPB) having a continuous skin and multiple SPB compartments. The ZPB provides lift for the system while the multi-compartment SPB uses a centrifugal compressor to provide a variable amount of ballast air by pumping in or expelling out ambient air. Various performance targets relating to ascent rate, descent rate, range and maximum altitude are achievable with various scaled versions of the basic design of the LTA system. Navigation and control techniques, such as high altitude station-keeping approaches, are made possible with the LTA system.

Abstract: A cargo harness comprising a first diagonal strap, a second diagonal strap overlapping the first diagonal strap at a X-crossing. The first diagonal strap may be coupled to the second diagonal strap at a first joint. The cargo harness may also include a cross strap having a first end, a second end and a sleeve disposed between the first end and the second end, wherein the first diagonal strap and the second diagonal strap pass through the sleeve and the sleeve overlaps at least a portion of the x-crossing. In one embodiment, the cargo harness may include a dual-point release strap assembly operably connected to the first and second diagonal strap for connecting a cargo load to a parachute harness.

Abstract: Wearable electronic devices that are designed to be worn on the head of a user while the user is swimming can determine swimming strokes and swimming performances of the user using motion sensors. Using a sound speaker, the wearable electronic device can play music and provide audio feedback to the swimmer. By comparing the swimming performance of the swimmer wearing the device with previously recorded swimming data, the wearable electronic device can provide audio comparison results to the swimmer while the swimmer is swimming in water. The wearable electronic device can also support similar functions for jumping actions.

Abstract: In an embodiment, a parachute deployment system includes a parachute coupled to a release via a first load path. The first path includes crown lines. The release is adapted to attach the parachute to a rocket via the crown lines, and disengage the parachute from the rocket if a load shifts from the first path to a second path. The system also includes a line constrainer between the release and the parachute. The crown lines pass through the line constrainer, and the line constrainer is adapted to restrict an extent to which the crown lines are able to extend away from a longitudinal axis. An example release includes a back plate configured to couple a tow line to crown lines and a soft pin. The pin is adapted to separate from the back plate in response to tensioning of the release line, causing the parachute to disengage.

Abstract: A selection is made between single stage and multistage parachute deployment for a vehicle based at least in part on vehicle state information. In the event multistage parachute deployment is selected, a drogue parachute is deployed during a first deployment stage and afterwards, a main parachute is deployed during a second deployment stage. In the event single stage parachute deployment is selected, at least the main parachute is deployed in a single stage where in the event the drogue parachute is deployed during the single stage, the drogue and main parachute are deployed simultaneously.

Abstract: The present invention relates to a parachute deploying apparatus, comprising: a) a manifold with which is releasably coupled a single vessel within which pressurized gas is generated; b) a gas generator which cooperates with said vessel; c) a plurality of hollow tubes which extend obliquely and upwardly from, and are in communication with, said manifold; and d) a plurality of projectiles, each of which formed with a rod that is receivable in a corresponding tube and to each of which is connected a cord that is also connected to a corresponding portion of an undeployed parachute, wherein the pressurized gas which is generated upon triggering of said gas generator is flowable through each of said tubes to propel said plurality of projectiles in different directions and to cause said parachute to become deployed.

Abstract: An aircraft includes an airframe parachute system. The parachute system includes an activation system, an extraction system, a harness system, and a parachute assembly.

Abstract: An aircraft includes an airframe parachute system. The parachute system includes an activation system, an extraction system, a harness system, and a parachute assembly.

Abstract: An aircraft includes an airframe parachute system. The parachute system includes an activation system, an extraction system, a harness system, and a parachute assembly.

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 cargo hook assembly employing a connector strap and a frame attached to a lower kicker, a clamp, an upper kicker, and a shaft assembly. A transverse flange of the connector strap engages a ledge of the lower kicker and propels the lower kicker towards the frame. A clip of the lower kicker rotates the clamp towards a closed position. A tongue of the clamp engages the shaft assembly at a tongue groove. A remote electrical module, a remote mechanical module, and a local mechanical release rotate the shaft assembly to engage or disengage the shaft assembly from the upper kicker and tongue.

Abstract: A method and apparatus for processing video information for a vehicle. A number of prior images is selected from images generated by the vehicle. An object is seen in the number of prior images. A model of the vehicle is displayed in the number of prior images in a current position of the vehicle and with a size that is based on the current position of the vehicle relative to the object in the number of prior images.

Abstract: Indicating a movement of an ultrasonic tag is accomplished by a transducer operable to provide electrical signals caused by the movement. The movement can cause mechanical vibrations, sound vibrations, or pressure in the transducer, to generate the electrical signals. A controller can detect the electrical signal from the transducer generated by the movement, whereupon the controller obtains tag data and modulates the tag data to be supplied to a powered up emitter. The emitter transmits the modulated tag data in a transmission to an ultrasonic tag reader using an ultrasonic carrier sound wave.

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 harpoon head (6) for a system for anchoring an aircraft on a grating (4) is characterized in that a distal end of the harpoon head has an interchangeable insert (20).

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: 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 maintaining equipment with variable length side transverse strap segments in with the one side fastening strap, includes two pairs of saddle straps connected via saddle straps, to either the back transverse strap, back straps crossing the container backrest, or extension of the side transverse straps. The latter extends into a side fastening strap. A loop at a location locatable from the waist to the leg straps is run through by the side fastening strap or the side transverse strap. Strap tightening can occur at hooking or thereafter, allowing adjustment of the side transverse strap and the side fastening strap to maintain the container on the solo skydiver's back or maintain the passenger to the tandem pilot during freefall. Unlocking and/or loosening after canopy deployment elongates the side transverse strap with shortening of the side fastening strap allowing backward movement of the lower back and progression of the leg straps.

Abstract: According to certain embodiments, an aerial delivery system configured to be deployed from an aircraft comprises a base, a sleeve generally configured to be positioned on the base, a bag configured to receive at least one liquid and a lid assembly attached to the bag using at least one strap. In some embodiments, the strap is attached to the bag in a manner that causes the bag to be selectively compromised once the aerial delivery system is deployed from an aircraft. In one embodiment, the system comprises a cellulose-based material. In other arrangements, the bag comprises polypropylene.

Abstract: According to certain embodiments, an aerial delivery system configured to be deployed from an aircraft comprises a base, a sleeve generally configured to be positioned on the base, a bag configured to receive at least one liquid and a lid assembly attached to the bag using at least one strap. In some embodiments, the strap is attached to the bag in a manner that causes the bag to be selectively compromised once the aerial delivery system is deployed from an aircraft. In one embodiment, the system comprises a cellulose-based material. In other arrangements, the bag comprises polypropylene.

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: 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 method and apparatus for rapidly severing a decoy towline extending from an aircraft by a mechanical spring actuated cutting blade and a thermal fuse type of release mechanism eliminating a pyrotechnic actuation device. The cutting blade is biased toward cutting engagement with the towline by a preloaded coil compression spring retained in the loaded position by a length of a polymer cord. The polymer cord has a heater wire wrapped about a portion of the cord which is connected to a DC voltage supply. The heater wire melts the cords when electrically connected to the DC power supply which releases the restraint on the spring which then drives the cutting blade into severing engagement with the towline.

Abstract: An apparatus for packing a parachute is presented, the apparatus including an expander member extending along a longitudinal axis and having at least a ramp portion that extends in the direction from a first end of the expander member to a second end of the expander member. The ramp portion has an outer surface expanding in perimeter shape from the first end to the second end of the expander member. A channel defined from inner surfaces of the ramp portion extends along the longitudinal axis from an opening at the second end of the expander member towards the first end. The first end of the expander member is configured to engage a substantially unexpanded loop of a stowage device and to expand the perimeter shape of the loop as the loop is moved along the longitudinal axis from the first end to the second end.

Abstract: A surveillance vehicle (10) comprising a vessel (11) and a parasail (12). The vehicle (10) is loaded, in a pre-launch condition, into a mortar tube for projection therefrom towards an area of interest. In this pre-launch condition, the vessel (11) resembles a conventional mortar round and the parasail (12) is stowed within the vessel (11). Upon arrival at the area of interest, the parasail (12) is deployed from the vessel (11) and instrumentation collects survey data.

Abstract: A reefing slider for providing improved line management and canopy deployment characteristics of a ram air inflated airfoil type canopy. During initial descent of the parachute the slider, secured by retaining elements, is held against the canopy in the upper reefing position where it mechanically restricts canopy deployment while giving the canopy time to achieve proper orientation following the drop from the launching aircraft. Upon sufficient air flow into the canopy cells, the retaining elements separate, releasing the slider and enabling full opening of the canopy.

Abstract: A reefing slider for providing improved line management and canopy deployment characteristics of a ram air inflated airfoil type canopy. During initial descent of the parachute the slider, secured by retaining elements, is held against the canopy in the upper reefing position where it mechanically restricts canopy deployment while giving the canopy time to achieve proper orientation following the drop from the launching aircraft. Upon sufficient air flow into the canopy cells, the retaining elements separate, releasing the slider and enabling full opening of the canopy.

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: 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 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: A hybrid parachute, method of deploying a parachute and method of landing a payload. The hybrid parachute utilizes a reefing system that provides for the initial deployment of a deceleration stage that is configured to withstand the stresses of high-speed and/or high altitude openings. The deceleration stage has operating characteristics similar to known high-speed parachutes. After sufficient deceleration has been achieved with the deceleration stage, reefings are released deploying one or more low-speed high drag stages of the device. The high drag stage(s) provide the landing characteristics of a low-speed parachute, including the possibility of controlled descent and landing.

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: A load assisted release system for releasably connecting cargo to a primary delivery vehicle, including a releasable connector and a bridle. The bridle includes a bridle attachment point, a slack loop, a first stage release link connecting a slack loop upper end to a slack loop lower end, and a responsive point in the bridle responsive to a releasing of the first stage release link to cause the releasable connector to release the bridle from the primary delivery vehicle once the first stage release link is released and the responsive point has moved away from the slack loop upper end the second predetermined distance. The releasable connector is configured to connect the bridle to the primary delivery vehicle, and a release force required to move the responsive point in the bridle the second predetermined distance is generated by the cargo as it moves away from the primary delivery vehicle.

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

Abstract: An apparatus for dissipating shock load in a parachute delivery system has at least one strip of material having a first end, a second end opposite the first end, and a predetermined length. The apparatus also has a piercing member having a first portion for piercing through the strip of material and a second portion that defines an opening. The strip of material passes through the opening in the piercing member. The first end of the strip of material is configured to be attached to parachute suspension lines. In a preferred embodiment, the strip of material is a strip of woven webbing. When a predetermined tensile force acts upon the strip of material and the piercing member such that the first end of the strip of woven webbing is pulled in one direction and the piercing member is pulled in an opposite direction, tension is produced which causes the piercing member to stretch and break the lateral fibers of the strip of woven webbing.

Abstract: A parachute system having a parachute canopy having a skirt, and a plurality of gores spaced about the skirt. The plurality of gores is defined by first and second groups of gores. The parachute system includes a slider having a plurality of through-holes, a line loop attached to the slider, a first reefing line extending through the first group of gores and having a pair of ends attached to the line loop, and a second reefing line extending through the second group of gores and having a pair of ends attached to the line loop. A corresponding group of suspension lines passes through a corresponding through-hole in the slider. Each suspension line in each group of suspension lines is attached to a corresponding gore. A single reefing line cutter is engaged with the line loop and configured to cut the line loop after a predetermined amount of time has elapsed so as to release the reefing lines and allow the slider to slide down the suspension lines.

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 deployment brake release system for use with an airborne guidance unit (AGU) of a parachute suitable for precision cargo delivery. The parachute includes deployment brake lines secured at one end to the edge of the canopy and connected at the other end through looped ends to motor control lines. The motor control lines are, in turn, engaged with the motor of the AGU. The deployment brake release system includes at least one hook mount having a hook secured to the AGU frame. The looped ends of the deployment brake lines are engaged with the hook during rigging so that, upon deployment, opening forces are applied to the hook mount rather than the motor. After full canopy inflation, the motor, via the motor control lines, pulls on the brake line looped ends to disengage them from the hook, transferring subsequent canopy loads to the AGU motor for the remainder of the flight. A method for releasing the deployment brake lines is also disclosed.

Abstract: A reefing assembly for a circular parachute having a canopy including a skirt portion, and suspension lines attached to the skirt portion. The assembly includes a tension structure bounding a central opening and having a plurality of straight segments. A plurality of cords, each cord having two ends, are each fixed to one end of one of the tension structure straight segments to define a loop, and a plurality of rings slidably disposed on each of the loops. Each of the rings is slidably connected to at least one of the suspension lines. The rings are clustered together at a central portion of their respective loops, and upon deployment of the canopy, slide along their respective loops to become substantially equidistantly disposed on their respective loops. The assembly facilitates a restrained opening of the canopy and thereby reduces opening shock load.

Abstract: A container apparatus for an object to be dropped, which contains an object to be dropped functioning as a point marker or a hydrographic conditions measuring device or the like and is dropped by a transport airplane such as an aircraft flying in the air to a water surface of sea, lake or the like, or to land or the like. The container apparatus follows a substantially uniform trajectory after being dropped by the transport airplane, and after being dropped, reduces the flight speed thereof to a fixed speed, to release the object to be dropped housed therein.

Abstract: A guided aerial delivery device which can be used to safely and accurately deliver a payload and supplies from an aircraft in flight to a specific target location in a reduced time. The aerial delivery device uses an overloaded ram-air drogue parachute controlled by a guidance system to steer the payload towards the intended target. When a selected altitude is reached, a recovery parachute is activated and the payload descends the remaining distance under the recovery parachute.

Abstract: The present invention is directed to a parachute reefing system having a flexible ring section. The flexible ring section has a circumference. The reefing system includes a plurality of equidistantly spaced loops attached to the flexible ring section and a plurality of link members wherein each link member is attached to a corresponding loop and sized to allow at least one suspension line to pass therethrough. The reefing system also has a cross-connecting section comprising pair of intersecting members that are attached to the flexible ring section. The intersecting members are attached to each other at an intersection point that is coincident with the center of flexible ring section. The reefing system has a position cord having a first end attached to the intersection point and a second end opposite the first end. A yoke is attached to the second end of the position cord and has a vertex and at least two legs that extend from the vertex. Each leg extends from the vertex to a distal end.

Abstract: An automatic controlled parachute includes a parachute canopy, a flight controller and risers connecting the canopy to the flight controller. Pneumatic actuators are connected along the risers. The flight controller operates the pneumatic actuators to control the length of the risers. The direction of flight of the parachute is controlled by the length of the risers.