Abstract: A parachute has its suspension lines divided into groups, each group connected to the load through a linear actuator. During descent of the parachute, foreshortening of an actuator or of any group of adjacent actuators causes the parachute trajectory to move in the direction of the foreshortened actuator. Multiple parachutes connected to a single load, with each parachute being connected to the load through an actuator, can similarly have their trajectory controlled. The trajectory of the parachute can also be changed by a system of normally foreshortened actuators which lengthen by actuation. Simultaneous, rapid shortening of all actuators just before ground impact can be used to reduce the descent velocity at ground impact.

Abstract: A thin film polymeric membrane is made from a plurality of adjacent sections that are bonded together along longitudinal seams taken with reference to an axis of symmetry. The membrane is reinforced laterally by a continuous helical reinforcing fiber pattern that passes the reinforcing fiber(s) a plurality of times over each of the longitudinal seams. The membrane desirably is in the shape of a parachute or balloon envelope.

Abstract: The detonating valve for releasing openings of air bag landing systems for aircraft and spacecraft has a wedge type charge and a cover closing the opening, which cover is shorn off during the ignition of the wedge type charge. The cover is a thin-walled disk or a membrane, which is integrated either within the aircraft and spacecraft or within the air bag landing system.

Abstract: A water-impact release mechanism has a hub with a first sleeve coupled thto. The first sleeve has a plurality of circumferentially distributed holes therein. A spring assembly, coupled to the hub, extends into the first sleeve. In a relaxed state, the spring assembly obstructs the holes while, in a compressed state, the spring assembly does not obstruct the holes. A second sleeve, concentric with the first sleeve, is elastically coupled to the hub and biased away therefrom. The second sleeve has an inwardly-facing annular groove. A ball resides in each of the holes and is large enough to extend beyond the confines of its hole. When the bias of the second sleeve is overcome, the annular groove aligns with the holes in the first sleeve thereby allowing the radial outward movement of the balls. A plate, coupled to the second sleeve, extends radially outward therefrom to define a water-impact surface.

Abstract: A protective ballute for a payload launched from an airborne platform includes an elongated shroud member, gas delivery apparatus for filling the shroud member with a lighter-than-air gas to inflate the shroud member. A payload as ballast is provided at one end portion of the shroud member for rendering the ballute heavier than air. Flight control and guidance apparatus is carried by said shroud member for determining a flight path and attaining a predetermined target landing site. A mechanism carried by the shroud member releases the payload from the shroud member upon reaching the landing site while maintaining said shroud member in its inflated state. The shroud member then rises or "floats" away from said landing site to another removed location, or if desired will self-destruct.

Abstract: An airbag protection system for helicopters. Airbags are inflated either automatically or manually, or a combination of both, prior to the helicopter striking the ground, thus avoiding or ameliorating a crash. Proximity sensors detect a fast descent to trigger inflation of the airbags located beneath the helicopter fuselage so that they can cushion the impact with the ground. Venting of the gas from the airbags is also provided to release the gas from the airbags so as to prevent rebound of the helicopter from the ground.

Abstract: A safety system that will evacuate passengers on an airplane while in flight. The In-Flight Evacuation System operates while the airplane is still in flight. While in operation the In-Flight Evacuation System will systematically evacuate passengers from the airplane. During the process the seats will rotate 180 degrees to face the rear of the plane. The seats will move towards the rear of the plane due to a rotating device connected along the bottom of the seats. When evacuation is deemed necessary, the rear doors on the plane will opened. The seats will continue to be rotated until it reaches the evacuation doors. At that point the seats will disengage. The top portion of the seat complete with a survival kit will be released with the passengers as the bottom of the seat rotates into a open compartment beneath the passenger cabin. A parachute will be activated as the passengers leave the rear of the plane. The passengers will slowly ascend to earth.

Abstract: A method and system for delivering pressurized propellants to a rocket engine, that has significant advantages over the current state-of-the-art. One of the propellants, the "pressurizing propellant", is at least partially vaporized and the vapor is in pressure communicating relationship with other propellants on board the rocket-propelled vehicle. This vapor pressure pressurizes the propellants to a sufficient degree that they can be charged directly to the rocket engine, or the pressure may be boosted through pumps, if required. Moreover, the pressurized vapor may be used in other applications on board the vehicle, such as orbital adjustment, attitude control, station keeping, and the like. In several embodiments, the propellants are contained in variable volume reservoirs, exemplified by bladders and diaphragms. These variable volume reservoirs are preferably not subjected to tensile stresses when expanded, and are preferably designed for controlled volume reduction, when being drained of propellant.

Abstract: A two-stage wingless reusable aerospace vehicle having upper and lower stages that take off from a take-off area and separate at a separation point along a first trajectory. The separation forces are generated by air retained between the upper and lower stages, which is at a pressure higher than ambient pressure at the separation point. The lower stage is then propelled along a return trajectory to a landing area. After separation from the lower stage, the upper stage continues to an Earth orbit for deployment of a payload. After deploying the payload, the upper stage moves out of the Earth orbit, re-enters the Earth's atmosphere, and returns to the take-off and landing area. The upper and lower stages are powered by liquid oxygen and kerosene engines.

Abstract: A personnel guided aerial delivery device is disclosed which can be used to safely and precisely deliver personnel, cargo, or a combination of both from an aircraft in flight, to a precise target or location. In the preferred embodiment, the aerial delivery device generally consists of a large "ram-air" type gliding parachute, a "drogue" parachute, an encapsulated crew module, a "fly-by-wire" control system, and a landing impact attenuation system. The aerial delivery device can employ an onboard human pilot to navigate the module. The use of a skilled pilot allows the aerial delivery device to be guided to a designated landing site.

Abstract: The deployable wing of the present invention comprises an internal structure having diverging leading edge spars attached to a keel spar and cross spars to form a delta wing configuration. This internal structure is enclosed within a volume defined by a fabric sail having an upper section, a lower section, and fabric ribs disposed therebetween. This fabric sail volume is internally pressurized through a ram air intake at the nose stagnation point. This deployable wing can be folded, extracted from an aircraft and deployed in the air.

Abstract: This invention discloses an apparatus for stabilizing a payload assembly including a payload, a maintaining apparatus for at least temporarily maintaining the payload in an airborne environment, and an elongate connection apparatus, which when extended has a vertical length greatly in excess of the combined vertical lengths of the payload and the maintaining apparatus, whereby angular stabilization is a function of the vertical length of the connection apparatus when extended.A method for stabilizing a payload assembly is also disclosed.

Abstract: It is known to use a rigid cone to provide stability to a body being towed by an aircraft. However, such cones are useful over a limited range of speeds. The invention provides a drag-producing aerodynamic device in which the cross-sectional area of the structure producing drag is variable. The cross-sectional area of the structure producing drag decreases as the towing speed, and hence the dynamic air pressure acting on the structure producing drag, increases and vice versa.

Abstract: The invention relates to a braking and heat protection shield (1) for a spacecraft (5), said shield being situated at the front of the spacecraft to oppose a flow of gas striking the spacecraft, and including at least one gap (3a, . . . , 3d) shaped to present a through section to the flow that increases with increasing angle of incidence of the spacecraft, to create an aerodynamic force couple tending to return the spacecraft towards a position of lesser incidence.

Abstract: A landing process and arrangement for payloads from aerospace missions with a steerable gliding body deployable at high altitudes for accurately returning the payload to the earth surface wherein delicate and stressable elements of the payload are to be recovered. The gliding body is filled with a light gas during its deployment, and the aerostatic lift must be lower than the weight of the landing unit. The payload is divided into a body with delicate elements and a body with stressable elements, wherein the body with the stressable elements is suspended on a pulling element at a spaced location under the other body. After the lower body has come into contact with the ground, the upper body is maintained suspended aerostatically.

Abstract: A protective device for securing to a parachute-carried load to protect the same during landing, comprising a supporting base (2) for the load, a shield (6) extending around the periphery of the supporting base (2) and forming an upside down dome, with the supporting base forming the bottom thereof, a central deformable damping block (28) disposed under the supporting base (2), and a protective shield (29) for protecting the central damping block (28) arranged to support said element and linked to the strap (6) by means of high tensile cables (30) adapted to hold the central damping block (28) held between the supporting base (2) and the protective shield (29).

Abstract: An energy attenuation system for absorbing at least a portion of the force impulse imparted to an occupant of an aircraft during a crash. The energy attenuation system comprises a seat and an air bag module. The air bag module includes an air bag positioned and deployable below the seat. The air bag allows the seat and its occupant to move in the direction of the applied impact forces under a controlled stroking force. Accordingly, the occupant may be exposed to a force having a magnitude substantially less than the magnitude of the force on the aircraft.

Abstract: An inflatable safety apparatus comprising an exterior shell and a chamber located inside the exterior shell. Inflation means, capable of inflating the apparatus are contained within the exterior shell. A tether is secured to the inflation means. In the event of an emergency at a high altitude location, an individual secured an end of the tether to a fixed object at the location, enters the chamber and exits the location via a window or balcony to free-fall to the ground below. As the tether becomes taught and disengages the inflation means, the inflation means are actuated and cause the exterior shell to fill with gas and inflate. When the apparatus strikes the ground, the individual contained within the chamber is unharmed due to the protective layer of gas which surrounds the chamber and is contained by the exterior shell.

Abstract: An airborne sensor system and method for placing a tethered payload in a near-stationary horizontal and vertical position at a desired location in relation to a target. The system includes an aircraft flying in a near-circular flight path, a tether connected at a first end to the aircraft and at a second end to a payload section, and an electronic device or devices for determining the location of the payload section. In addition, the airborne sensor system may include an apparatus for moving the payload section horizontally to the desired location and maintaining it at that location, independent of moving the aircraft.

Abstract: A load glider has, between the parachute surface and the load, a device in which a reversible transfer of mechanical energy from the main lines to the steering lines takes place, so that essentially only frictional forces are to be overcome during the operation of the steering lines. The device includes two differential gears, which are arranged in parallel and are accommodated in housings in which a steering line is wound up on a roller with a larger diameter and a main line is wound up on the other roller with a small diameter. Gears, which can be driven by pinions driven by electric motors, are flanged onto the larger rollers.

Abstract: A container for air transport and for deliberate drops, for which purpose container (1) is connected to a braking system (3, 4, 6), permits an accurate drop by virtue of the fact that it is provided with a control that has a navigation system and actuating means for a passive steering device (4, 6), that can produce lateral directional changes of container (1) during a braked descent. Preferably the container is provided on its underside with a large-volume shock absorber (7 to 10) that is under low pressure at most.

Abstract: An apparatus comprises a deformable structure surrounding a volume, and means for suspending a fragile cargo in spaced relationship above an impact zone on said deformable membrane. The apparatus is designed to: prevent damage to fragile cargo therein; lengthen a duration of the cargo impact period; reduce terminal vertical freefall velocity of the cargo relative to a terminal vertical freefall velocity of the cargo alone; and lengthen a duration of a cargo/craft fall period for falls from extreme heights. Preferably, the apparatus is spherical in shape, substantially transparent, and has a plurality of flexible strut members for suspending the fragile cargo in spaced relationship above an impact zone of said apparatus.

Abstract: An air-launchable gliding sonobuoy store includes a canister enclosing an flatable membranous wing folded in a collapsed state with an electroacoustic system. After launching, the wing inflates and a steering mechanism controls the wing glide path by skewing the trailing edge thereof. Upon reaching the sea, the wing serves as a buoy with the electroacoustic system transducer depending therefrom.

Abstract: A shock strut assembly for an aircraft landing gear includes a trunnion fitting, a compressible oleo strut subassembly, a wheel subassembly, an energy dissipating subassembly, and a mechanical load control subassembly. The oleo strut subassembly includes a cylinder member having an upper end mounted in combination with the trunnion fitting by means of the mechanical load control subassembly and a piston member having a lower end affixed in combination with the wheel subassembly and an upper end slidably inserted in the cylinder member. The energy dissipating subassembly includes a cylindrical cutter member secured in combination with the cylinder member and the trunnion fitting and a frangible tube member mounted in concentric combination with the cylinder member so that the lip of the upper end thereof is disposed in abutting engagement with the cutter member.

Abstract: An air-launchable gliding sonobuoy store includes a canister enclosing an flatable-membranous wing folded in a collapsed state with an electroacoustic system. After launching, the wing inflates and a steering mechanism controls the wing glide path by skewing the trailing edge thereof. Upon reaching the sea, the wing serves as a buoy with the electroacoustic system transducer depending therefrom.

Abstract: A shock energy absorbing device provides shock protection for the riser l employed to attach an aerodynamic deceleration device to a primary body during deployment of the system into an airstream. During deployment, for example, by dropping an unopened parachute and attached load or by rocket delivery of the unopened parachute and attached load, the parachute is made to open at a desired altitude wherupon very large shock tension forces are generated which are applied to the line. In order to protect the line from failing under these forces and to reduce the requirement for a bulky, heavy line, a shock absorber is provided in the form of a block having one or more breakable web portions formed therein and through which the riser line is threaded. Upon deployment of the system into an airstream, the shock tension forces operate to fracture some or all of the breakable web portions thereby dissipating the shock energy generated during deployment and protecting the riser line from failure.

Abstract: An object of the invention is to provide an escape apparatus which enables persons to promptly escape from an elevated place such as a building and an aircraft, and is easy to handle. An aerial floating flier such as airfoil or a parachute is folded and contained in a case, and by throwing out such a case or an aerial floating flier in folded state into the air, the aerial floating flier is spread in the air, thereby allowing to escape from a site of an accident by hanging from the aerial floating flier and descend slowly on the ground.

Abstract: A rocket engine protection system for a recoverable rocket booster which is arranged to land in a salt water body for recovery. The system includes an inflatable water impermeable elastomeric bladder that may be fabricated of a silicone impregnated woven Kevlar material and which is stowed in a deflated condition on a rotatable arm that is journalled to the lower portion of the nozzle of a liquid rocket booster. The deflated bladder and the rotatable arm are protected by a pod cover that is hinged to the outer portion on the nozzle. During the controlled descent of the liquid rocket booster by parachute for landing in a salt water body the pod cover is released and opened upwardly by a gas cylinder actuator. The rotatable arm which is biased by a torsion spring is then permitted to rotate around to position the deflated bladder in a deployed position within the interior of the lower portion of the nozzle. The bladder is then inflated to form a plug within the nozzle.

Abstract: A rocket engine protection system for a recoverable rocket booster which is arranged to land in a salt water body in substantially a nose down attitude. The system includes an inflatable bag which is stowed on a portion of a flat annular rim of the aft skirt of the booster. The bag is hinged at opposing sides and is provided with springs that urge the bag open. The bag is latched in a stowed position during launch and prior to landing for recovery is unlatched to permit the bag to be urged open and into sealing engagement with the rim. A source of pressurized gas further inflates the bag and urges it into sealing engagement with the rim of the skirt where it is locked into position. The gas provides a positive pressure upon the interior of the bag to preclude entry of salt water into the skirt and into contact with the engine. A flotation arrangement may assist in precluding the skirt of the booster from becoming submerged.

Abstract: A rocket deceleration system for a spacecraft, comprises a first set of active canted rockets for attenuating a horizontal velocity of the spacecraft and a portion of the vertical velocity thereof. A second set of active canted rockets attenuate the remainder of the vertical velocity. A third set of available canted rockets attenuate a wide range of horizontal velocities, regardless of the vehicle roll position about its vertical axis. The first set, second set and third set of rockets form a ring and combine to form a total number of rockets being divisible by the numeral 6. Each rocket is 180.degree. from an opposing rocket on the other side of the ring. A programmable controller identifies rockets to be fired to attenuate horizontal and vertical spacecraft velocities.

Abstract: An apparatus and method is disclosed for decelerating and absorbing impact of a re-entry vehicle suitable for payloads that are relatively light as well as payloads weighing several tons or more. The apparatus includes four inflatable legs displaced equidistantly from each other around a capsule or housing which contains a payload. The legs are inflated at a designated altitude after entering Earth's atmosphere to slow the descent of the re-entry vehicle. Connected between each of the four legs are drag inducing surfaces that deploy as the legs inflate. The drag inducing surfaces are triangularly shaped with one such surface being connected between each pair of legs for a total of six drag inducing surfaces. The legs have drag inducing outer surfaces which act to slow the descent of the re-entry vehicle.

Abstract: An annular spinning parachute is composed of an annular canopy symmetrical about an apex, suspension lines of substantially the same length and interconnected together at the canopy apex and extending radially outwardly therefrom across the canopy and downwardly therefrom for coupling to an object supported by the parachute, and centerlines interconnected with the suspension lines at the canopy apex and extending downwardly therefrom for coupling to the object supported by the parachute. The annular canopy includes fabric panels each having a generally trapezoidal shape defined by a pair of opposing inner and outer borders with the outer border being greater length than the inner border and a pair of opposing side borders of substantially the same length.

Abstract: Deployable device composed of rigid panels connected by articulations to a support (2). First panels (4), or arms, pivoting more than second panels (6), or main panels, in order to move from the folded-up position to the deployed position, are preferably smaller than the said second panels. Triangular linking panels (7) are placed between the first and second panels and articulated on them. The actuating means preferably lock the device both in the deployed position and in the folded-up position.

Abstract: Aerodynamic braking device, intended in particular for decelerating a space object penetrating an atmosphere at high speed, essentially constituted by a circular ring (2) made from canvas, of general shape close to that of a truncated cone but whose cross-section through an axial plane exhibits an outward concavity, and by a supporting structure (6, 7, 8) designed to apply a tangential tensile stress to the said ring in an axial plane, and preferably comprising at least two parallel rigid rings (6, 7), between which the canvas ring is stretched, and struts (8) arranged in order to retain the distance between the two rigid rings by resisting the loads resulting from the tension of the canvas.

Abstract: This invention relates to an aerodynamically braked vehicle deployment device. The deployment device system generally comprises a spool member. A tow line is bifilar wound about the spool member in a manner wherein one end of the tow line is attached to an aircraft while the other end is attached to a towed vehicle. The towed vehicle and the deployment device are deployed simultaneously, and the spool, by nature of its bifilar winding, assumes a position between the aircraft and the towed vehicle. An aerodynamic braking means is interfaced to the spool in a manner operable to provide a braking force during payout of the towed vehicle to control the payout speed of the towed vehicle. At the end of the towed vehicle payout, the deployment device is adapted to disengage itself from the tow line and propel itself away from the tow line and clear of the towed vehicle.

Abstract: This invention relates to a mechanically braked vehicle deployment device. The deployment device comprises a spool member having a guide member rigidly connected thereto. A tow line is bifilar wound about the spool member in a manner wherein one end of the tow line extends through the guide member and is attached to an aircraft while the other end extends from the spool member and is attached to a towed vehicle. The towed vehicle and the deployment device are deployed simultaneously, and the spool, by nature of its bifilar winding, assumes a position between the aircraft and the towed vehicle. A braking assembly is interfaced to the spool member in a manner operable to provide a braking force during payout of the towed vehicle to control the rotational speed of the spool during tow line payout. At the end of the towed vehicle payout, the deployment device is adapted to disengage itself from the tow line and propel itself away from the tow line and clear of the towed vehicle.

Abstract: An expandable throat plug for use in the recovery of a rocket engine nozzle in an engine assembly is disclosed herein having a deployment device carried on the exterior of the engine assembly including an actuator for advancing an extendable column and an arm normal thereto so that the expandable throat plug can be deployed into and inside the nozzle. A telescoping extension shaft deploys the plug interiorly of the nozzle whereby a pressurized medium expands the plug into conformal engagement with the inner surface of the nozzle to seal and close the throat opening.

Abstract: Air deflectors are mounted on the top and bottom of the counterweight assembly in an elevator system to deflect air in the elevator hoistway to the sides of the counterweight as the latter moves up and down in the hoistway. The deflectors ensure that air turbulence is not directed toward the car as the car and counterweight pass each other in the hoistway. A quieter and smoother passenger ride is thus accomplished. In an ultra high-speed elevator system, the counterweights may be completely enclosed in an aerodynamic jacket. Cable connections and compensating rope connections to the counterweight are all made inboard thereof to ensure that the counterweight is free of turbulence-inducing protuberances.

Abstract: A low-altitude, retro-rocket, load landing apparatus for decelerating the rate of descent of a load and counteracting sideward wind drift. The apparatus includes a support assembly having a tilting mechanism for adjustably coupling a rigid support member to the load for pivotal movement about a horizontal axis offset from the center of gravity of the load, a retro-rocket rigidly coupled to the support member, a plurality of sensors for determining wind direction, wind speed and altitude of the load, and a control assembly coupled to the sensors, rocket and tilting mechanism for actuating the tilting mechanism in response to output signals from the sensors. Actuation of the tilting mechanism varies the rocket's thrust direction and counteracts sideward wind drift.

Abstract: The present invention discloses an emergency escape unit to be used in case of an emergency such as a fire, an earthquake or the like, such that the user safely escapes from a high building with the use of this escape unit. In the emergency escape unit of the present invention, a light-weight gas such as helium, air or the like, filled in a bomb may be quickly released into a sack-like canopy, causing the canopy to be expanded in the form of an umbrella, so that the air resistance during descent is quickly increased, enabling the user to fall slowly. When helium is used as the light-weight gas to be released into the sack-like canopy, provision is made such that buoyancy is generated.

Abstract: The invention is directed to either a satellite or missile deployed to a high altitude location at a desired position above a target. Once at the proper position a drogue chute is deployed to slow reentry and then a high-altitude balloon or paraglider is deployed to maintain the invention above the target area. Once deployed, the invention utilizes onboard sensors to collect target information which is communicated to an over-the-horizon (from the target) receiver.

Abstract: The invention is a carrier for use in air dropping cargo from an aircraft, the carrier comprising a pallet suspended from a parachute. The pallet has struts which absorb shock and prevent cargo roll over when the pallet lands, the struts being deployed into a shock absorbing, anti-roll-over position by the drag of the parachute when it opens. The pallet includes shock absorbing supports between its upper and lower surfaces to further protect air dropped cargo upon landing.

Abstract: A braking fabric or canvas which is fastened to the base of a carrier projectile which contains articles of submunition, through the intermediary of a fastening device, wherein the canvas is spread apart or unfolded after the separation of the base from the carrier projectile and is provided for the retardation and change in the trajectory of the base relative to the articles of submunition. The braking fabric is connected by a central surface section thereof with at least one plate element forming the fastening device. This connection between the at least one plate element and the braking fabric is preferably effectuated through an adhesive connection. Naturally, it is also possible to select a different type in effecting the connection; for example, such as a riveting connection, a combined adhesive and riveting connection, or any other suitable type of connection.

Abstract: A bomblet projectile includes a projectile body, a fuse housing on the body at the rear end thereof; and an unwindable stabilization band for stabilizing the position of the projectile while dropping. The band forms, in the deployed state, a loop having leg portions terminating in fastening regions secured to the fuse housing and a dome portion flanked by the leg portions. The band has a length and different widths along the length. The band has its greatest width in the dome portion and its smallest width in the leg portions, externally of the fastening regions.

Abstract: A method and device for protecting a first stage liquid rocket booster from impact damage and environmental damage so as to permit recovery from a sea water landing and reuse without major rehaul of the rocket engine of the booster. A cylindrical double walled structural member encircles the nozzles of the rocket engine and precludes impact damage after the booster has landed nose first in the water. A flexible water impervious sleeve means is carried within the double walled structural member and deployed prior to impact. The sleeve extends from the booster and collapses inwardly upon itself to prevent entry of sea water into the rocket engine and associated equipment.

Abstract: A braking mechanism for a rotating flying object. The braking mechanism includes a planar fabric sheet having a central attachment base portion that can be secured to the flying object. The fabric sheet is adapted to be stored in a folded-up readiness state in the flying object, and, when released and unfolded, is adapted to form a braking surface that encircles the flying object. The braking mechanism further includes a plurality of reinforcing strips that each extend radially between the central attachment base portion and an outer rim of the braking mechanism and are distributed about the periphery of the latter. Each reinforcing strip extends from the central attachment base portion to the rim and back again to at least partially form two layers and to form loop-like pockets at the rim, with centrifugal weights being disposed in these pockets.

Abstract: A decelerator structure for attachment to a munition to be deployed formed of a first triangular section of cloth with apexes and straight sides to provide a back wall and a second equally shaped and sized section of material to form a front wall with the sections joined and having scoops at the apexes on the front wall with openings inside the scoops with a central anchor on the front wall so that the walls expand equally due to inner air pressure to form a rounded rear wall and a rounded forward wall with straight sides.

Abstract: A personnel lowering or descent control device. The device includes a housing adapted to be secured to a person intending to descend from a higher to a lower elevation, and containing a line adapted to be secured at one end to a fixed point at said higher elevation. The line is wound on a reel rotatably mounted in said housing. A brake assembly, including a centrifugal brake controls the rate of rotation of said reel and thereby the rate of descent. A mechanical brake on said housing provides a manual control of the rate of rotation of the line supply reel. The descent line is trained on a plurality of capstans mounted within the housing for absorbing energy and providing a capstan ratio effective to reduce applied line tension to slow the descent of an object supported by the said descent device.

Abstract: A skyboard which is an apparatus using the combination of a specially designed surfboard and a parachute to enable the rider to ride the skyboard in a manner similar to the rider's positioning on a surfboard and which will enable the rider to ride the air currents of the sky in a much more exciting manner than through conventional gliders or hand gliders. The skyboard is a lightweight object formed in the general shape of a surfboard and which is modified to include at least a pair of front wings and a pair of rear wings on its lateral sides, a pair of fins on its underside and a pair of foot or shoe binders on its upper surface to accommodate and hold the rider's feet or shoes.

Abstract: A Shuttle type of aircraft (10) with an escape hatch (12) has an arcuately shaped pole housing (16) attachable to an interior wall and ceiling with its open end adjacent to the escape hatch. The pole housing 16 contains a telescopically arranged and arcuately shaped primary pole member (22) and extension pole member (23) which are guided by roller assemblies (30,35). The extension pole member (23) is slidable and extendable relative to the primary pole member (22). For actuation, a spring actuated system includes a spring (52) in the pole housing. A locking member (90) engages both pole members (22,23) through notch portions (85,86) in the pole members. The locking member selectively releases the extension pole member (23) and the primary pole member (22). An internal one-way clutch or anti-return mechanism prevents retraction of the extension pole member from an extended position. Shock absorbers (54)(150,152) are for absoring the energy of the springs.