Abstract: A reefing system comprising an annular flexible membrane having a centrally located vent opening and a plurality of guides symmetrically spaced around the periphery of the membrane. The reefing system retards or slows opening of the canopy of a parachute in order to reduce the shock normally encountered with parachutes.

Abstract: A releasing device for a parachute which is ready for use and folded and disposed in a receptacle and held together by securing string against the force of an unholding preloaded spring. The release device includes a breaking device for disconnecting the securing string and a control for actuating the breaking device at predetermined conditions. The control actuates the breaking device by an electric control signal derived after an initialization operation and depending on a barametric pressure which is present and further depending on the presence of a given pressure change rate. The breaking device comprises an energy storing device which is releasable by the electric control signal for disconnecting the securing string.

Abstract: The invention provides a release device for a secondary parachute canopy intended to operate when during a descent after a main parachute canopy should have been opened by normal operation, the rate of descent exceeds a chosen value indicating some form of failure of the main canopy, comprising a negative rate diaphragm arranged to experience atmospheric pressure on a first side and a reference pressure on the opposite side, an operating member which is movable between a canopy retaining position and a canopy releasing position by movement of the diaphragm, a valve arranged to selectively open the chamber to atmospheric pressure to inhibit operation of the diaphragm, an air bleed arranged to allow air to enter the chamber during a descent to balance the atmospheric pressure on the diaphragm, and a float valve sensitive to rate of descent arranged to close the bleed when a chosen rate of descent is exceeded, thus to trap the reference pressure in the chamber and to apply operating differential pressure to the

Abstract: A parachute release apparatus having a spring powered release mechanism for coupling to the ripcord of the parachute, with a latch retaining a spring powered piston of the release mechanism against the force of the spring. A spring powered timing mechanism is locked out above a preestablished altitude by an aneroid assembly, but operative thereafter. A manually settable interlock coacts with a catch arm to set the spring of the timing mechanism upon winding, with an arming cable assembly actuating the interlock to a release position upon separation of the parachute wearing aviator from the seat or the aircraft. The timing mechanism includes a timing disc viewable through a window only when the release mechanism has been set and when the timing mechanism has been wound.

Abstract: A single multi-line cutter is connected to each of a cluster of parachutes by a separate short tether line that holds the parachutes, initially reefed by closed loop reefing lines, close to one another. The closed loop reefing lines and tether lines, one from each parachute, are disposed within the cutter to be simultaneously cut by its actuation when a central line attached between the payload and the cutter is stretched upon deployment of the cluster. A pyrotechnic or electronic time delay may be included in the cutter to delay the actual simultaneous cutting of all lines until the clustered parachutes attain a measure of stability prior to being disreefed. A second set of reefing lines and second tether lines may be provided for each parachute, to enable a two-stage, separately timed, step-by-step disreefing.

Abstract: A reefing line pressure reducer and a reefing line cutter assembly are deibed. The pressure reducer is an element which can be incorporated into a reefing line cutter assembly to reduce pressure at the tie-off knot of a reefing line by enlarging and rounding the surface area circumscribed by the knot. The subsequent reduction of pressure at the tie-off knot reduces the likelihood of reefing line failure and consequently, poor system performance or canopy failure. The reefing line cutter assembly consists of a pyrotechnically actuated reefing line cutter, a cutter bracket, and a reefing line pressure reducer.

Abstract: A parachute system for an airman ejected from an aircraft in an ejection seat includes at least one drouge parachute housed within a rigid hollow container. In conventional manner, the drogue parachute is connected by lines with releasable attachments on the seat, one of the lines being further connected with the main parachute so that the latter will be deployed after release of said attachments. The container is formed as a projectile mounted in a gun mounted on the ejection seat. The container has, at its end facing away from the direction in which it is fired, a closure connected with the lines and with the drogue parachute. When the container and closure are fired from the gun, and the closure is arrested abruptly by the lines, the container continues in its trajectory whilst the drogue parachute is drawn from the container and deployed by the lines.

Abstract: A parachute having a canopy with a number of suspension lines has a pair of losing flaps attached to opposite sides of the canopy. Holes in flaps match locking loops on an apron and the suspension lines are bighted to hold the canopy shut as the parachute is deployed. The suspension lines are incrementally pulled free from the apron while the parachute skirt remains closed. As the suspension lines reach the locking loops and are pulled free from the locking loops, air enters the skirt to cleanly open the canopy thereby preventing unwanted parachute opening anomalies.

Abstract: A ram air parachute assembly adapted for deployment by use of static line suitable for use at high altitudes and high drop speeds, the parachute assembly comprising a ram air parachute 21, a pilot parachute 23, attached by a bridle line 22, and slideable square 25 to the ram air parachute, and being packed in a parachute bag 10 attachable to an aircraft by way of a static line 11.

Abstract: An apparatus and method for airplane deployment over water of survival kit apparatus is provided. A pair of deflated, inflatable rafts are contained in a rigid container shell having a removable tail cone. A stabilizer drogue may be used to longitudinally stabilize the container prior to tail cone release and assist with the tail cone removal after release. The tail cone is mechanically released and removed from the container shell at a predetermined time after deployment from an aircraft, thereby pemitting the container shell contents to be removed. The life rafts are contained in the container shell so that one life raft having associated with it an aerodynamic brake is released after the tail cone has been removed, with the container and second life raft continuing their trajectory downwards. The rope joining the two life rafts is continuously payed out as the first left raft falls to the water and the container with the second life raft therein continues its trajectory.

Abstract: For use with a parachute used after ejection from an aircraft, a discard assembly for disconnecting a parachute deployment mechanism from the parachute in response to the opening of the parachute by a preselected amount. The discard assembly includes a pair of releasably interconnected rods enclosed in a slidable housing. An actuator assembly is coupled to the housing and to the parachute and slides the housing away from one of the rods, thereby allowing them to disconnect, upon opening of the parachute by the preselected amount. The actuator assembly comprises a pair of rings coupled to the parachute on opposite sides of the parachute vent, and a pair of lanyards coupled to the housing and to the parachute, with each lanyard passing through one of the rings. The force generated by the transverse expansion of the opening parachute is transmitted via these rings and lanyards to actuate the discard assembly.

Abstract: A vacuum-packed assembly for the compact storage of compressible survival equipment is provided. The assembly includes a compressed article of survival equipment, such as a sleeping bag, life raft, or parachute within a flexible, evacuated, heat-sealed envelope of gas-impermeable material. An outer envelope of thicker, more durable material is preferably employed for protecting the inner envelope. The outer envelope is also evacuated. If a parachute is stored within the assembly, an actuation neck is provided for allowing the envelopes to be ruptured upon deployment of a drogue or pilot parachute. Both the drogue parachute and an aircrewman can be connected to the parachute externally of the vacuum envelopes without risking vacuum integrity.

Abstract: A mechanical thruster for positively separating two releasably joined components under a controlled time delay. The thruster is particularly useful for mechanically opening canisters containing survival kits as they are being dropped from an airplane to a target. The thruster comprises an adjustable mechanical timing means which is actuated when a pin is pulled from it. After a predetermined time delay, the timing means actuates a plunger mechanically associated with it, which plunger dislodges a locking piston. This locking piston in locking position mechanically holds a thruster body about a barrel of the device. Once the locking piston is displaced, the thruster body is propelled away from the barrel.

Abstract: An electronic system for selecting the proper mode sequence for deploying a ecovery parachute from an aircraft ejection seat. The system senses altitude, airspeed, and sink rate; and compares these to predetermined reference signals. The system also incorporates logic circuits and time delay circuits. The logic circuits are arranged to select one of four time delays depending on the status of the various parameters relative to the reference signals.

Abstract: A stowage pack containing a lanyard is disclosed for use on military airct to provide for arming and safe release of bombs and mines (stores) and for opening of stabilizing and drag fins.The stowage pack is connected with a shackle on board the aircraft and packages a non-magnetic lanyard which is connected at its opposite ends, respective, to the pack and to the store. Once the store is released from the shackle and falls away from the aircraft, the lanyard pulls pins to arm the store or open fins or a parachute compartment. After the store falls farther, it breaks the lanyard at a weak section near the pack and they fall away together, leaving only the pack connected with the aircraft shackle.

Abstract: A reserve parachute for deployment under low descent speeds includes a rubber ring packed with the canopy and rigging lines and attached to the canopy in the region of the canopy apex and being disposed concentric with respect to a vent hem of the canopy. Upon deployment the ring expands to increase profile drag to ensure the canopy mouth faces substantially downwardly during deployment. The peripheral hem of the canopy at the canopy mouth is stiffened with a tape loop treated with polyurethane so that the peripheral hem springs apart upon deployment. An inhibitor tie is attached to a loop of the folded rigging lines within the pack to permit only a part of the rigging to be released initially; the inhibitor tie breaks at a predetermined tension in the lines to permit the remainder of the rigging lines to be released and to permit fully canopy deployment.

Abstract: A parachute deployment sequencer includes two sequencer systems in electromagnetic shielding housings. Each housing contains two bellows connected to pitot tubes, a third bellows for measuring ambient pressure and three switch contact sets connected in series, each contact set being operated by one of the bellows. Each housing also contains a battery actuated by seat ejection and a deployment firing circuit with a series switch circuit in between. After ejection, deployment is initiated when all three switches are closed.

Abstract: This invention refers to those containers for emergency equipment such as life rafts, etc. which normally must be firmly restrained under rough exposure and wear conditions but must have a foolproof quick-release and quick-deploy feature. It has a new and unique configuration of multi-layers of prior-art fasteners which will assure this functional operation in a direct foolproof manner, unlike prior art.

Abstract: A gliding parachute of the flexible, multi-cell airfoil type having a length to width ratio in the range of approximately 2:1 to 2.85:1, a maximum camber height to chord ratio in the range of approximately 0.1:1 to 0.2:1, a wing span to load attachment distance ratio of approximately 2:1, and an attachment point approximately 25% to 45% of the chord aft of the leading edge. The suspension lines and the fabric sections of the wing are dimensioned to impart a side to side curvature to the inflated wing. The gliding parachute has superior maneuverability and lift. A special pilot chute and bridle assembly are provided so that upon deployment of the main chute the pilot chute will automatically collapse to substantially reduce its drag, thereby improving the glide ratio of the main parachute.

Abstract: An improved device for the air dropping of platform-mounted cargo is presed wherein a multi-staged parachute system allows for a rapid descent during the initial phase of the trajectory and then reduces the rate of descent during the terminal stage to allow for a safe landing.

Abstract: An actuation assembly for use in conjunction with an instrument, such as a parachute oxygen system, etc., is disclosed having a handle adapted to be manually gripped by the user of the actuation assembly and mounted relative to housing means that is fixedly secured to a strap or the like, with positionment of the handle in releasably confined position relative to the housing means until use of the actuation assembly is desired. Releasing means operatively associated with the housing means and the handle is provided to maintain the handle in the confined position relative to the housing means such that only upon the application of a predetermined force to the handle is it removable from the confined position. Coupling means for connecting the handle to the instrument to be actuated is provided such that upon removal of the handle from the confined position a force is applied through the coupling means to the instrument for actuation of the system associated therewith.

Abstract: A powered aircraft has a jettisonable fuel tank releasably secured in the bottom of its fuselage. A valve is arranged to shut off fuel flow from the tank upon releasing of the tank from the fuselage, whereupon a parachute connected to the tank is released to slow the descent of the tank. Additionally, a reserve fuel tank in the fuselage is normally connected to the jettisonable fuel tank, and the valve is so arranged that fuel flow communication is normally maintained between the jettisonable fuel tank and the aircraft engine while fuel is prevented from flowing from the reserve tank to the engine. However, when the jettisonable fuel tank is released from the fuselage, the valve shuts off the flow of fuel from the jettisonable fuel tank and establishes open communication between the reserve tank and the engine to permit continued operation of the aircraft under power of the engine.

Abstract: The improvement refers to an inflatable device for quick expansion of parachutes for low altitude jumping, comprising elements of bags firmly connected to the canopy and sheathed into by tubes of the expansion structure, as well as lines tied between those bags and tubes, the object of the improvement being to permit a reduction of the dimensions of the expansion structure and to increase its expansion speed.

Abstract: There is disclosed an electronic barometric staging unit or aerial cargo delivery actuator for use with cargo carrying or recovery parachutes having an electronic pressure sensing assembly for initiating actuating of a deployment or staging line cutter such that parachute canopy directing and deployment occurs as a programmed function of a barometrically corrected altitude. The invention features a two-part housing assembly carrying the relatively expensive portion of the assembly that is reusable and an expendible or discardable portion of the assembly so that by recovering or retrieving the electronic module, it may be mated up with a new portion so as to substantially reduce the cost of subsequent usages of the apparatus. Since the barometric transducer per se is solid state and of extremely light weight, deceleration moments due to impacting the ground do not in any way impair its operation so that it may be recovered for re-use.

Abstract: A clamp assembly is provided for a dual parachute release mechanism for a litary personnel-type parachute which enables the automatic power cable to be in a condition to function for initiating parachute deployment, even though the manual ripcord cable and housing may have been previously released accidentally and prematurely.

Abstract: A parachute container for aircrew ejection seats is designed with a rigid dy having a reduced volume and weight, and which is hermetically sealed and filled with an inert gas to extend service life without maintenance, the container being provided with a detachable, flexible cover to permit the container to expand in volume proportional to the reduction of external atmospheric pressure. The cover is made of an elastomeric material having elastic memory capable of returning to its preformed shape as atmospheric pressure increases, repeated in operations from sea level to high altitudes.

Abstract: A parachute having improved opening characteristics wherein a plurality of distender members are secured about the margin of the canopy for swinging movement between a collapsed position along the canopy and an opening or distending position transverse to the canopy, and flexible guying members connected to each distending member for swinging the latter to its distending position when a load is applied to the shrouds.

Abstract: Apparatus is provided for preventing premature, manual operation of a parute activated during ejection by airload tensional forces on the parachute container and harness riser strap system, which is accomplished by slidably mounting the ripcord handle assembly with respect to the riser strap.

Abstract: This invention is an improvement in the art of parachutes. A parachute has a pilot chute and a main chute and provides that the main chute is locked in place and is not released until the pilot chute is properly deployed. This improvement may also provide for the actuating of the release of the main chute by the deployment of the pilot chute. This improvement in turns allows other improvements such as providing the individual parachutes with alternative mountings of the pilot chute for left and right handed people.

Abstract: Parachute containers formed of a central panel and overlapping flaps which are held together by pull apart intergripping fastening arrangement. The fastening arrangement is constructed such that it releases in response to pulling in a flap opening direction so that the flaps are automatically opened by the action of releasing the fastening arrangement thereby eliminating the need for elastic straps, springs etc.

Abstract: A drogue parachute deployment system for an ejection seat comprises a dro parachute mounted in a bag on the seat, a rocket motor, and a tow line attached between the parachute and the rocket motor. Upon firing of the rocket motor, the bag is caused to rip and the parachute is deployed.

Abstract: A compact aneroid actuated explosive initiator for releasing a parachute upon descent to a predetermined altitude includes a firing pin releasably restrained by a rotatable sear that is urged toward release position. Cocking is achieved by compressing a driving spring without moving the firing pin, but concomitantly releasing a first restraint upon release of the sear. A second restraint upon release of the sear is provided by trigger levers under control of an aneroid barometer whereby the sear can be released and the firing pin driven by the firing spring only after cocking has been accomplished and a selected barometric condition exists.