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

Abstract: Apparatus for salvaging a hit indicating sensor, mounted on a towed drone serving as target simulator and being fastened by means of a cable to a towing craft; the hit indicator is severed from the drone and parachuted to ground either on cable release or by external command.

Abstract: A recovery system for decelerating/stabilizing and protecting space vehicles, boosters, astronauts, equipment and like payloads, including a paracanopy defined by a frusto-conical flexible uninflated skin forming a decelerator/stabilizer surface having a small inflated torus at it leading end and a larger trailing torus at its trailing end with an inflated annular protective sheath therebetween protecting the payload housed therein, duct means between the toruses and the annular sheath for forming a fluidically rigidified frame, and the fluidically rigidified frame maintaining the flexible skin in taut though uninflated condition during entry and recovery, The paracanopy further can include an inflated buoyant section for recovery at sea, and depending upon the payload to be recovered, the paracanopy can be deployed as a single structure from one end of the payload or from opposite ends of the payload as two separate cooperative structures.

Abstract: A safety chamber of the telescopic type usable for an airplane includes a plurality of wall segments, granular cushioning materials and a parachute. As long as it is not in use, the wall segments are accommodated in a contracted state in the space on the ceiling of the airplace. In the event of an occurrence of emergency the wall segments are lowered one after another to constitute a chamber in which a single seat assembly is incased together with passengers sitting thereon. When the lowermost wall segment reaches the floor of the airplace, a plurality of hooks around the lower edge thereof are engaged with recessed parts on the bottom of the seat assembly and at the same time the cushioning materials fall down from the ceiling while expanding by themselves whereby the hollow space in the expanded chamber surrounding the passengers is filled with cushioning materials for the purpose of preventing the passengers from the influence of shocks.

Abstract: An aerobraking orbital transfer vehicle which includes an aerobraking device which also serves as a heat shield in the shape of a raked-off elliptic or circular cone with a circular or elliptical base, and with an ellipsoid or other blunt shape nose. The aerobraking device is fitted with a toroid-like skirt and is integral with the support structure of the propulsion system and other systems of the space vehicle. The vehicle is intended to be transported in components to a space station in lower earth orbit where it is assembled for use as a transportation system from low earth orbit to geosynchronous earth orbit and return. Conventional guidance means are included for autonomous flight.

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

Abstract: There is shown and described a unique apparatus and method of safely supplying material of a loose (e.g. liquid) nature in remote or hostile environments on a cost effective basis in emergency conditions for example by air drop.

Abstract: One end of a hose is affixed to the underside of the object which may descend and whose impact has to be cushioned while the other end of the hose is pulled through the first end, the two ends are separately fastened permitting filling of the hose; a second hose may be inserted in the first one to provide separate filling spaces, one being the interior of the second hose and the other one being the gas space between the two hoses whereby different pressures permit selection of the resilient characteristics of the cushion.

Abstract: A low cost sonobuoy is constructed of plastic pipe and fittings. A simple design is used comprising a section of plastic pipe and two end caps. One end cap is tapered and adapted for having an antenna mounted thereon. The other end cap has a recess for storing a hydrophone, cable and plastic streamers. The hydrophone and cable are held in place by water soluble tape. The sonobuoy may be launched from aircraft and thus the plastic streamers trail from the second end cap to provide in-air stability. The sonobuoy is designed to be self-righting and self-scuttling.

Abstract: A device for the separation of a load from a belt assembly connected to it, especially of a parachute, which on impact with the earth compresses an impact component which is arranged on the impact side of the load and is released by the motion of impact. In order to achieve a safe separation which is free of delay, it will directly deal with the relative movement of the impact component or a mechanically connected part by the operation of the force of impact. The impact component can be developed as a landing shock absorber.

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

Abstract: 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: A parachute control apparatus for enabling control of an unmanned slave parachute from a manned simultaneously descending parachute is described. The apparatus includes two hand held master controllers each comprising a body and a thumb operable reciprocating plunger. The plunger is coupled to a potentiometer to provide proportional control. The parachutist carries a radio transmitter including an encoder responsive to the plunger movements and an antenna. A control signal receiver is attached to the load carried by the slave parachute and includes a receiving antenna and signal decoder operative to provide drive signals for a slave parachute control line drive. The drive includes a servo system, electric motors, gearboxes and winches for operating the slave parachute control lines.

Abstract: Two airplanes (A and B) combine in aerial maneuvers to accomplish pick up, transport and delivery of a payload (10) from and to designated surface locations (11). The payload (10) is connected to, carried in the open by and disconnected from the ends of cables (15) extending from each airplane during the aerial maneuvers. Such airplane maneuvers include orbiting 180.degree. apart while banking at prescribed angles to effect substantially vertical lifting and lowering of the payload (10) relative to the pick up and delivery surfaces (11).

Abstract: A landing gear for loads including cargoes and/or personnel is removably ured to the load. At least one tiltable jet engine forms part of the landing gear and automatically controls the descent movement. A stabilizing mechanism forms part of the landing gear and provides a positioned control for the landing gear and load during descent. Preferably two solid fuel rockets are provided for supporting the load during descent. The rockets are tiltable about an axis extending across the longitudinal axis of the landing gear. The tilting is controlled by a computer on board in accordance with a program present in the computer whereby the landing is substantially independent of local wind conditions and other external factors.

Abstract: An air launchable sonobuoy having two separate liquid chemicals which react pon mixing to form an expanded, rigid foam flotation device. Upon deployment in the air, windflaps release a preloaded plate within a submersible housing and urge the chemicals to mix and foam in an elastic envelope. After water impact, an orifice in the housing permits water to fill the voids at a rate sufficient to allow the housing to remain afloat until foaming and erection of an antenna within the envelope is complete. As the envelope expands, a latch releases it from the housing and permits the housing when flooded to sink to the desired depth determined by the payout length of a cable within the housing connected to the flotation device.

Abstract: An airborne buoy droppable from an aircraft into water, comprising, as a float, a balloon which inflates during its fall. Before being dropped the balloon is protected by a hood locked by a bent blade bearing on a wedge. During the fall, the scoop-shaped mechanical parts lift up, a cloth placed below an opening in the scoops inflates and frees the hood by drawing back the wedge fixed on the tongue forming an extension of the cloth.

Abstract: A system for transferring cargo at sea by helicopter includes an automatily activated self inflatable apparatus for reducing the velocity of the cargo if jettisoned or inadvertently dropped into the sea and for keeping the cargo afloat until retrieval may be accomplished. The cargo is lifted by a support sling attachable to a helicopter suspension cargo hook and simultaneously connected to a second sling in parallel to the helicopter through the rapidly deployable retardation and floatation device. Release of the support sling causes the cargo to drop and initiate deployment and inflation of the ribs of the parachute thereby retarding the cargo's descend and providing buoyancy for its floatation.

Abstract: An assembly of a payload and container is described whereby a payload supt having a base with a perimeter enclosed by a sidewall forming a cup for receiving a tubular container is provided. A first and second tie are connected to one end of the tubular container, and are terminated in an elastic ring. The first and second ties have a length which will permit the elastic ring to be placed in an annular groove in the exterior sidewall of the cup, thereby fixing the payload support to the container. During free flight of the assembly, air flow moves the first and second ties away from the container freeing the elastic ring from the annular groove in the cup whereby the container separates from the payload support.

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: Apparatus is described for releasing a storage container from an inflatable upport such as a parachute, comprising a container for holding the inflatable support, an attachment mechanism extending through the container, linear slide means engaging the attachment mechanism and a storage container when tension is applied to the attachment mechanism, and means for holding the attachment mechanism in tension until the inflatable support is inflated, whereby the storage container remains fixed to the inflatable support until tension on said attachment component is relieved.

Abstract: A load support is arranged to be connected to a parachute and has a center guide tube slidably receiving a landing rod. This landing rod is of a sufficient length to project beyond the lower end of the guide tube so as to engage the ground ahead of the load support. A slidable friction connection is provided between the landing rod and the load support for cushioning the landing shock of such support. Brake pads are used as the friction connection, and such brake pads are associated with adjustment apparatus comprising a rotatable holder for the brake pads and a cam and cam follower assembly which serves to adjust the compression of the brake pads on the rod upon rotation of the holder. A pinion and gear connection is provided between the holder and the support to provide the rotatable adjustment.

Abstract: A tow plate including a retention assembly and a removable clevis assembly made up of a main clevis member and a drogue clevis member engageable with the main clevis member. A first latch mechanism latches the main clevis member to the retention assembly. A second latch mechanism latches the drogue clevis member to the main clevis member. To effect force transfer, the entire clevis assembly is released by unlatching the main clevis member from the retention assembly, with the drogue clevis member latched to the main clevis member. To effect drogue jettison, the drogue clevis member alone is released by unlatching it from the main clevis member, while the main clevis member remains latched to the retention assembly.

Abstract: Apparatus or a device for use in the jettisoning and flotation of a susped load, particularly an underwater listening buoy, comprises a parachute for suspending the load during descent between jettisoning and flotation, and at least one inflatable float for maintaining the load at a predetermined depth in a body of water. The float comprises a pillow-shaped inflatable ballonet fixed in the central portion of the parachute. It may have an inflation sleeve coupled at one end to the ballonet for inflating the ballonet with the superatmospheric pressure generated by the descent of the parachute. A tension member may be provided fixed at one end to the free end of the sleeve and at its other end to the load so as to extend the sleeve downwardly during descent. The inflation sleeve preferably is of frustoconical form and divergent toward its lower free end.

Abstract: A floor mounted rotatable arm assembly which supports a removable parachute holder. A release mechanism operates the parachute holder to release a parachute after the arm assembly has been rotated from a stowed position faired with the floor of the aircraft cargo space, wherein the parachute is face-up, to a deployed position aft thereof, wherein the parachute is face-down and available for release.

Abstract: A disconnect device for an aircraft survival kit including a container and a lid secured thereto with a torso harness and anti-rotation strap associated therewith. The disconnect device includes a body adapted to be mounted relative to the kit, with the body including a recess, in accordance with one embodiment, adapted to enclose a portion of the kit therein, and a support assembly extending outwardly from the body and including a cavity adapted to receive an end of the harness therein. A locking device is provided and adapted to extend through the support assembly and the end of the harness to provide securement of the harness to the kit so as to obtain removal of the harness from the disconnect device for replacement thereof when the locking devise is disengaged such that the lid may remain secured to the container when the harness is replaced. The support assembly includes a pair of spaced apart arms integrally joined with the body and defining the cavity for receiving the end of the harness therebetween.

Abstract: A buoy capable of being dropped onto water from an aircraft, comprising a balloon which inflates during the descent through a forced intake of air through adjustable openings at the base of the balloon. Inside the balloon there is a flexible membrane allowing the air to enter through holes, the balloon remaining inflated to the maximum pressure encountered during the descent. Pockets with openings are traversed by the air and prevent the balloon from rotating during its descent.

Abstract: This invention is directed to a marker which can be dropped from an aircraft, such as an airplane or a helicopter, so that the pilot of an airplane can see the marker on the ground or on the growing plants and trees, and know, when he is in the aircraft, where the aircraft has flown for spraying fertilizer, insecticides, herbicides and the like. The drop marker comprises a base member which may be unitary or integral. The drop marker upon falling from the aircraft towards the ground is of such a construction that the base member divides in two pieces. The drop marker also comprises a folded streamer strip. One end of the streamer strip is attached to the first piece of the base member and the other end of the streamer strip is attached to the second piece of the base member. The drop marker unfolds upon falling from the aircraft toward the ground.

Abstract: The present invention relates to a speed retarding mechanism for aerial bs launched from a high velocity vehicle and designed to provide a high drag stabilizer capable to withstand release in air stream velocities moving at 2600 feet per second. The mechanism includes a balloon consisting of a top and bottom panel joined on the perimeters and having valve openings through its bottom panel. When the load has been braked to an acceptable velocity the valve closes the openings causing the balloon to collapse and become a streamer providing a high energy impact.

Abstract: A banner in the form of an elongated sheet of flexible material is attached to an air dropped sonobuoy for stabilization of the sonobuoy during descent as well as for descent speed control, entry angle control, and wave action damping once the sonobuoy is floating at the surface of the ocean. The banner is roller furled and stored on top of the sonobuoy. When the sonobuoy is dropped, the banner unrolls and streams out behind the sonobuoy during descent. It is a feature of this drogue apparatus that it is deployed by the time that the sonobuoy has descended a distance corresponding approximately to the length of the banner. The banner is not released when the sonobuoy hits the water in order to enable it to stream out over the surface of the water to provide wave damping action.

Abstract: An inflatable landing bag having a valve for release of the inflating fluid from the landing bag as the pressure of the inflating fluid of the landing bag rises above a given level, such valve including a sleeve comprised at least in part of a woven stretch fabric having interstitially variable inflating fluid porosity such as to control release of inflating fluid from the landing bag.

Abstract: A personnel evacuation and survival device for individual crewmen aboard p having a quick don harness to which is attached a personnel lowering device and an automatically deployable encapsulating life raft. From an appropriate evacuation station aboard the ship, the crewman uses the device to suspend himself clear of the side and lower himself on a lifeline, the pay-out of which is controlled to provide a safe rate of descent. During the descent, a raft package is automatically released and a life raft is inflated which completely encapsulates the crewman prior to water entry.

Abstract: A shock absorbing mobile adapter is provided with four members in spaced apart relationship and six shock absorbing arms connecting each member to the other three members and forming an irregular tetrahedron.

Abstract: A system for reducing the ground impact of a load in a parachute air drop system having the parachute canopy attached to a first platform and the load attached to a second platform. The first platform and second platform are connected together by a plurality of elastic cords. The elastic cords are held in a relaxed state by a steel cable connected between the platforms. A ground probe supported on a line a predetermined distance below the cargo load has switch contacts which close when the probe reaches the ground to operate a cable cutter. The cable cutter cuts the steel cable connected between the platforms to permit the cargo to free fall under the restraint of the elastic cords. The partially unloaded canopy and the air mass inertia under the canopy is used to slow the cargo load velocity just prior to touch down.

Abstract: An improved safety air cushion bag which is constructed with a main body of the air cushion bag, an air outlet port or hole formed in one part of the air cushion bag main body, a gas-permeable cloth covering the air outlet port, and at least a single reinforcing member for preventing the gas-permeable cover cloth from breakage or bursting at an excessive load being applied to the air cushion bag at the shock of collision, the reinforcing member being attached separately to the air outlet port, or formed integrally with the air cushion bag main body at the part of the air outlet port, in a manner to extend across the air outlet port with both ends thereof being joined to the peripheral edges of the air outlet port in the air cushion bag main body.

Abstract: A helicopter carried, towline recovery buoy system including a package coining a retrieval line, inflatable buoys, and buoy inflating devices. A support and release mechanism releases the package response to dropping of the towline. The buoys and retrieval line are automatically deployed to permit recovery of the towline by grappling from a helicopter.

Abstract: A system for ejection of a crew member from an aircraft is disclosed. In one embodiment a mass is fired from a mortar or similar ejection device and the mass has attached to it a pendant which is resilient. As the pendant reaches the limit of its length as a result of the motion of the mass, the stretch force therein pulls down the seat pan upon which the crew member is resting and a divestment device is actuated. The crew member is then accelerated upward and out of the aircraft. Once the crew member is clear of the aircraft, the pendant's weak link separates just before the peak loading is reached and the action of the pendant initiates deployment of the parachute. The mass and pendant then separate and carry on out of the area of the pilot in a ballistic trajectory. In a second embodiment of the invention, a slipping clutch mechanism is utilized such that as the pendant runs off the clutch spool, and tightens, the pendant spool begins to rotate against the clutch torque feeding out more line.

Abstract: A remote elevated platform (REP) for positioning a payload from an aircraft nd maintaining its position unattended, comprises a lifting body, a payload designed to be suspended from the lifting body, a tether line and a mooring system. The platform is dropped from the aircraft and the lifting body is deployed by opening it up by means of a static line or a barometric device. The mooring system is then released and it starts falling freely but attached to the tether line. The mooring line then strikes the surface and fixes itself in the ground. In a body of water, a float and sea anchor is deployed instead.

Abstract: A pair of sector-shaped wings stored in a pair of spaced apart elongated housings strapped vertically to the back of the user and adapted to be deployed from the housings utilizing rotatably mounted handles secured to the wings. Each housing has a longitudinal opening through which a wing is packed into a housing and deployed therefrom. Each wing comprises a pliable sheet of material which is secured to its respective housing along one side margin and secured to a rigid strip at another side margin. The strips are pivotly mounted and carry the handles which allow the wings to be manipulated by the arms of the user for accomplishing sky diving maneuvers.

Abstract: An elongated, cylindrical case has an intermediate partition dividing it into a canister and a housing. A parachute is attached into the housing with deployment means releasable by a timer. After a predetermined time has elapsed, the timer withdraws radial pawls to release an end cap from the housing, allowing the parachute to be deployed. The canister is equipped with a special end cap capable of hermetically sealing the canister so that it may convey any of a variety of cargo via airdrop. This end cap is essentially a cylinder, recessed at both ends. A disk is held adjacent the inner end of the cylinder by a center post that passes through central holes in the cylinder by the disk and is pivoted to a plurality of radial pawls that may be extended or withdrawn by rotation of the center post, so that they may engage a shoulder in the end of the canister. The center post is equipped with means for locking it in one position so that the end cap cannot be removed by accident from the canister.

Abstract: A hang glider in the form of an aerial wing of airfoil shape is disclosed. The wing is defined by an outer envelope of flexible material inflatable to the airfoil shape and having a plurality of chambers therein each receiving an inflatable bladder. Air inlet openings are provided in the bottom portion of the envelope adjacent the leading edge of the wing. Either the bladders or the chambers are inflated with a gas lighter than air and, during flight, air enters the openings and fills the available space in the others of the bladders or chambers to provide a complete smooth airfoil shape for the wing. Shroud lines are employed to suspend a person beneath the wing during flight.