Abstract: A pressure dependent parachute release device having a primary storage volume, a check valve between the primary storage volume and a secondary storage volume, a pressure operable valve, the outlet of which is connected to the inlet of a flow restrictor, with the outlet of the flow restrictor being connected to a pressure operated actuator. The inlet of the check valve and a primary port of the pressure operable valve are in fluid communication with the primary storage volume, and a secondary port of the pressure operable valve and the outlet of the check valve are in fluid communication with the secondary storage volume. The pressure operable valve is first set to a primary position, blocking communication from the secondary storage volume to the outlet. A pressure differential between the primary and secondary storage volumes shifts the valve to a secondary position allowing fluid communication between the secondary storage volume and the pressure operated actuator via the flow restrictor.

Abstract: An unmanned aerial vehicle that includes symmetrical wings, tail section and internal compartments. The wings which include the only control surfaces can be attached to either side of the aircraft. An engine and a payload are non-symmetrically attached modules. Assembly and disassembly is performed with quick release pin and plate latches, quarter turn fasteners and guides that prevent improper assembly. The compartments include quick release hatch covers for the various internal craft compartments.

Abstract: An aircraft which is capable of safely landing during an emergency landing is disclosed. The aircraft has a safety device which includes a plurality of auxiliary engines. Each auxiliary engine is movable so as to vary the thrust axis in a range between a substantially horizontal direction and a substantially vertical direction. The safety device also includes a plurality of gas bags contracted and disposed at a lower portion of the aircraft body so as to be instantly expandable at a necessary time, such as during an emergency landing.

Abstract: The orbital launch system is a three stage vehicle to launch orbital payloads. The system uses a turbofan powered aircraft as the first stage with an aerospacecraft attached by an underling aerospacecraft pylon at an aircraft engine mount for carriage. The aerospacecraft is the second stage and is powered by an ejector ramjet engine. The aerospacecraft has a cargo bay with cargo bay doors in its midsection. A booster rocket with payload is launched from the cargo bay by use of an ejection system. Normally the payload is mounted on a rocket booster to be placed in the proper orbit. The orbital launch system may also have a parachute drop recovery system to recover the booster rocket after it deorbits.

Abstract: Aircraft, in particular for travel and sporting purposes or as a plane for business travel, having a rescue system which, by means of a parachute, makes it possible to return at least the cabin including the persons contained therein, to the ground, wherein, in particular, a parachute arrangement is provided having at least one parachute, with this arrangement being stowed in a first region of the fuselage which is located forward of the center of gravity of the aircraft in the flight direction, wherein additional means are provided which exert a force effect in the manner that between the longitudinal axis of the aircraft (1) and its direction of movement an angle of substantially 90.degree. is formed (slip position) before the parachute (7.1, 7.2) is deployed.

Abstract: A safety airplane comprising a carrier portion and a saddle portion. An assembly is for retaining the saddle portion on the carrier portion. A structure is for releasing the saddle portion from the carrier portion, when there is a problem during flight. Paraphernalia is for gently lowering the saddle portion to the ground.

Abstract: Apparatus and method for recovering and arresting an aircraft on a floating platform is disclosed. The aircraft has a fuselage, a wing, and a source of propulsion for propelling the aircraft in flight. During landing approach, an inflatable cushion attached to the fuselage is deployed below the fuselage via inflation. In the inflated condition, a fastening material disposed on a downward facing surface of the cushion is thereby adapted to adhesively contact the floating platform deck so that the forward motion of the aircraft is slowed and arrested. In the preferred embodiment, the fastening material is one of male or female VELCRO.RTM. which is adapted to mate with corresponding VELCRO.RTM. material covering the platform deck.

Abstract: The invention is a compressed gas rocket apparatus for deployment of emergency parachutes, rescue lines and similar payloads. A pressurized vessel is equipped with a stopping or sealing mechanism which, when removed or punctured, causes the pressure vessel to be launched. A drag line connected to the vessel pulls the payload away from the launch point, in the direction of the pressure vessel travel.

Abstract: An aircraft includes a cockpit permanently connected to a fuselage base. At least one fuselage segment is detachably mounted to the support. In case of an imminent crash the segment is detachable from the remainder of the aircraft and can float to safety after being detached by having at least one parachute and an airbag secured to the segment.

Abstract: A device for protecting a helicopter and its occupants from damage during a crash or difficult landing. The device includes an inflatable bag attached to the bottom fuselage which covers a totality of the surface of the helicopter's bottom fuselage. The bag is inflatable into a trapezoidal shape having a very large volume, exceeding the helicopter's internal volume, for substantially cushioning the helicopter upon impact with the ground during a crash. The bag is equipped with distortion-control reinforcements for preventing toppling of the helicopter after a landing and bag air-pressure controlling and limiting devices.

Abstract: A crew capsule 2 is connected to the body 3 of a spacecraft by a releasable coupling comprising a housing 6 secured to the capsule, a sleeve 9 secured to the body 3, and clamps 11-15 engaging interrupted thread 10 on sleeve 9 and having hooked ends engaging a flange 7 on housing 6. In an emergency during launch, an hydraulic ram 21 energized by a pump 24 is actuated to rotate the clamps 11-15, which are circumferentially interconnected, relative to the sleeve 9 to disengage the clamp threads from the sleeve thread sections 10; then explosive charges 25 are fired to separate the capsule 2 from the body 3, the capsule subsequently descending by parachute.A similar releasable connection may be used between segments of a Solid Rocket Booster, or between the passenger cabin and other parts of a passenger-carrying aeroplane.

Abstract: An emergency spin recovery parachute is housed within a centrally mounted housing on the aft end of an aircraft and is connected to a ring fitting within the housing. Two selectively latching shackles, connected to separate towlines are openly disposed adjacent the ring fitting. The towlines extend in opposite directions from the housing along the aircraft wing to attachment points adjacent the wing-tips, where the other end of each towline is secured. Upon pilot command, one of the open shackles latches to the ring fitting to attach the towline connected thereto, and a second command signal deploys the parachute. Suitable break-away straps secure the towlines to the aircraft surface until the parachute is deployed and the resulting force on the towline attached to the parachute overcomes the straps and permits the towline to extend to the point of attachment to exert sufficient drag on the spinning aircraft to permit the pilot to regain control of the aircraft.

Abstract: This invention relates to aircraft and specifically to devices for disconnecting the winds in a rapid manner. The frame of the wings is atached to the frame of the fuselage with exploding bolts. The skin of the wings is secured to the skin of the fuselage with rivets that also explode or a burnable tape is placed under the skin to sever the skin. A control arrangement is provided that simultaneously ignites the exploding bolts and the rivets or the tape to disconnect the wings from the fuselage.

Abstract: A parachute for a powered model airplane in which the parachute is ejected downwardly by an ejection cartridge which may be installed for ejection of the parachute after the parachute is packed into its container in the airplane, and just prior to the take off of the airplane.

Abstract: A parachute-type safety lowering or descent system (10) for helicopters or other types of hovering aircraft includes a rotor hub assembly (12) to which is secured to the top thereof a parachute housing (14), for containing the safety lowering parachute, through means of a dual set of vertically spaced ball bearings (52, 58) for rotationally isolating the parachute housing (14) from the induced rotation effects of the hub rotor assembly (12) under normal aircraft operating conditions. In an emergency, however, such as, for example, in the case of a rotor, rotor blade, rotor hub assembly, or rotor drive engine failure, malfunction, fracture, or separation, the safety lowering parachute will be deployed whereupon the entire weight load of the aircraft will be borne by the safety parachute.

Abstract: An emergency landing system for an aircraft, particularly a helicopter, in which a plurality of rocket members are mounted on the fuselage of the aircraft and directed downward about the center of gravity of the fuselage. The rocket members are activated to direct upward reactive forces by the energization of a proximity switch located on the fuselage and adapted to sense the ground level when the fuselage has descended within a predetermined elevation above the ground level so that the downward movement of a disabled aircraft is substantially decelerated to provide a soft landing for the aircraft. The landing system may be adapted for use on a fixed wing aircraft by directing the rocket members to exert reactive forces rearward as well as upward to retard the forward as well as downward movement of a disabled fixed wing aircraft.

Abstract: A dual system for ballistic deployment of a parachute (40) caused by explosion of a powder charge (54) to propel a projectile (52) away from an air vehicle, pulling the parachute (40) away from the air vehicle and allowing the parachute to inflate free of the air vehicle. The powder charge (54) is exploded alternatively by the pilot pulling a pull handle (12) to send an igniting current to fire cap (55), or by the pilot pulling handle (70) to activate a spring driven firing pin (80) to fire cap (82); the firing of cap (55) or the firing of cap (82) will explode the powder charge (54).

Abstract: A device which corrects aerodynamic spin wherein a parachute 38 exerts anti-spin forces on an aircraft 10 to effect spin recovery. The dual parachute towlines 30 and 32 are each attached to the parachute 38 and are attached to the rear fuselage equidistant to and on opposite sides of the aircraft centerline, at 25 and 27. As the parachute 38 is deployed during spin, the parachute force 40 acts through only the towline 30, and exerts its force outboard of center on the aircraft 10. As a result, the parachute exerts not only an anti-spin torque, but additionally causes the aircraft to roll, creating a gyroscopic anti-spin rolling moment. The additional anti-spin rolling moment facilitates spin recovery by permitting a relatively smaller parachute to accomplish spin recovery equivalent to that of a larger parachute attached to the center of the rear fuselage.

Abstract: A device which corrects aerodynamic spin wherein a collapsible boom 42 extends an aircraft moment arm and an anti-spin parachute force 24 is exerted upon the end of the moment arm to correct intentional or inadvertent aerodynamic spin. This configuration effects spin recovery by means of a parachute 30 whose required diameter 32 decreases as an inverse function of the increasing length of the moment arm. The collapsible boom 42 enables the parachute 30 to avoid the aircraft wake 50 without mechanical assistance, retracts to permit steep takeoff, and permits a parachute 30 to correct spin while minimizing associated aerodynamic, structural and in-flight complications.

Abstract: A wing contained emergency descent system incorporates a plurality of bays positioned within the wing structure of an aircraft. Each bay opens upwardly and outwardly of the wing through the upper surface thereof and supports a tray positioned within the bay. The tray contains one or more parachute packs and is positioned to be elevatable through the actuation of a pair of doors. The doors form a part of the upper skin of the aircraft wing and each includes an operating arm depending therefrom. The operating arm engages the tray such that the arm elevates the tray, and parachute pack thereon, into the air stream flowing over the wing when the panel or doors are opened.

Abstract: An ultralight aircraft and/or pilot recovery system includes a parachute having a canopy connected by means of a plurality of shroud lines to a first elongated cable having a length to position the parachute clear of the aircraft engine and propeller with a second cable for connecting the parachute to the frame of the aircraft and including a harness worn by the pilot which includes a pouch for containing the canopy folded within an inner pouch to permit the pilot to grasp and toss the chute clear of the aircraft for deployment for recovery of the aircraft. An alternate embodiment provides for connecting the parachute to the harness worn by the pilot and securing the harness to the aircraft to thereby give the pilot the option to recover the aircraft or cut loose from the aircraft for pilot recovery only.

Abstract: An aircraft or spacecraft is landed with the aid of a paraglider type parachute and with a braking booster rocket which emits its jet in the landing direction. The glide number of the paraglider is selected to provide the craft for the landing with an extremely "inefficient" glide number so that the ratio of drag to lift is about 1. Thus, the total drag of the combination paraglider and craft corresponds about to the maximum forward thrust of the craft, whereby a pinpoint landing may be accomplished.

Abstract: A parafoil for supporting a flying machine, which parafoil has a forwardly extending central section open at the front to scoop in air during flight, and wings attached to the rear of the central section and which receive air into the interior thereof either directly or from the central section, said wings being divided into compartments of equalized pressure, and restraining elements attached to the parafoil central section in front of the parafoil wings and to the outer ends of the parafoil wings, thereby in flight to hold down the front of the parafoil central section and hold down the parafoil wings in an inverted U-shape.

Abstract: A flying body such as an aircraft or a re-entry vehicle is enabled to land substantially horizontally with the aid of one or several glider parachutes also referred to as paragliders, which are stored in an upper body zone and ejected during the landing. The lift capacity of the paraglider is so dimensioned that it replaces the lift loss of the wings due to the low landing speed, whereby the weight of the flying body is kept in equilibrium to the sum of the wing lift and of the paraglider lift. The paraglider resistance or drag is compensated by the engine thrust and an ascending or descending flight is accomplished by modulating the engine thrust.

Abstract: A tow target system for use with a remotely piloted aircraft, including deployment of the target(s) from wing launchers on a tow line, braking of the tow line, release of target and tow line from the aircraft, and parachute recovery of the jettisoned target. A dual tow reel and two tow target launchers are provided on the carrier aircraft for sequential operation of more than one towed target. Signals received from the ground control only the target deployment from its carrier and the later jettisoning of the towed target when desired. The braking system has automatically operative control means for pay-out speed, slowing, and stopping of the reels at predetermined line lengths. The parachute recovery is automatically initiated by aerodynamic control forces when target release is commanded.

Abstract: Aircraft safety apparatus includes front and rear parachutes mounted at the front and rear portions of the aircraft for adding to the buoyancy thereof during emergency landings. Devices are provided for moving the parachutes into their operating positions. A plurality of auxiliary jet propulsion units containing fluid under pressure propel the aircraft to aid in its manueverability should the aircraft malfunction in flight, as well as during emergency landing procedures. At least some of the jet propulsion units are directed transversely to the body of the aircraft to direct fluid under pressure laterally to cause lateral reaction movement of the aircraft for steering purposes while the aircraft is descending under parachute assist.

Abstract: A hang glider attitude recovery device that may be rapidly deployed with a minimum of pilot action comprises a drag element having an effective point of attachment rigidly spaced above the point from which the pilot is suspended, and a mechanism for activating the drag element at a point clear of upper structural members. The separation between the attachment point and suspension point provides a lever arm which is responsible for the operation of the device. When the hang glider is in a position where the lever arm is inclined from the vertical (hang glider out of attitude), activation of the drag element provides an upward force at the upper end of the lever arm, which force produces a moment that tends to bring the suspension point back into a position under the attachment point. In the preferred embodiment, the drag element comprises a small parachute stowed within the tubular king post.

Abstract: This invention relates to an arrangement providing the safe descent to the ground of the fuselage of an aircraft when it has been disabled. The pilot of the aircraft when it is disabled actuates any suitable control mechanism on the dash panel to automatically release a parachute, the cables depending therefrom being affixed to the center of gravity of the aircraft for the safe descent thereof under the action of the parachute. The parachute is stored within a cradle or the like housing which is maintained in inoperative position within a storage well provided in the fuselage and this storage well is closed by a releasable closure member to which the cradle is affixed.

Abstract: An aircraft letdown system is deployable in the event of power failure or mechanical failure over inhospitable terrain or in the event of environmental conditions which preclude VFR or IFR landings. A parachute system, which is attached to the aircraft at a point in approximate vertical alignment with the aircraft center of gravity, is selectively energized by the pilot when it becomes apparent that a safe normal landing cannot be made. On energization, the parachute canopy and the shroud lines are repositioned from the place of storage to a location external to the aircraft and deployed in the conventional manner. To alleviate the shock of landing to the passengers and cargo, a specially constructed impact absorbing landing gear is extended and the occupants are further protected from the landing shock through impact absorbing seats.

Abstract: An airplane parachute device includes parachutes and release mechanism mounted in the upper surface of the aircraft's fuselage. A releasable hatch, covers each parachute and release mechanism, and is in operable communication with the pilot's compartment to allow for remote controlled release. The parachutes are under similar remote control and are ejected from the parachute compartments by a coiled spring system. Each parachute is aided in opening by an inflatable collar affixed to the outer rim. A shock absorbing piston is mounted to the bottom of the parachute compartment and to the tether lines of the parachute.

Abstract: A balloon has an airfoil-shaped member connected to its top surface. The airfoil-shaped member has a top curved skin with a plurality of parallelly-spaced partitions which form therebetween a plurality of air passageways for air. Upon the descent or lateral movement of the balloon, the airfoil-shaped member is expanded to provide a vertical stabilization of the balloon and to afford better control of the balloon during the lateral travel thereof.

Abstract: A parachute system removably mounted on an aircraft. The system comprises a container removably and releasably attached to an aircraft fuselage. The container has a lid which is biased open and a locking mechanism which maintains the lid closed until a parachute is to be deployed. A drogue chute ejecting mechanism ejects a drogue chute when the lid is opened, and the drogue chute deploys a main chute stored in the container and which is connected to the container. A coupling attaches the container to the aircraft fuselage and is disconnectable so that the chute system can be jettisoned from the aircraft.

Abstract: This invention relates to a control system for the release of a parachute contained within an aircraft adapted to be towed by a cable secured thereto, the cable being electrically conductive and having electrical contact to a control system in the aircraft, and an electrically conductive contact ring on the contour of the aircraft and being insulated with respect to the skin of the aircraft, whereby in case of separation of the cable from a towing aircraft, the cable touches the contact ring and closes a circuit composed of the contact ring, the cable, and the control system which releases the parachute.

Abstract: A powered remotely piloted vehicle which is not controllable at the low landing speeds necessary for landing on a platform of small area is provided with a para-foil type wing deployable at the beginning of a recovery sequence, and is further provided with a rocket ejectable line which is passed to the landing platform and winched in so that the composite flight vehicle and deployed para-foil wing is drawn towards the platform after the manner of a kite.

Abstract: An apparatus is disclosed for arresting uncontrollable motions of model araft. A signal is used to deploy a parachute when a model aircraft is in a motion, such as a tailspin, from which the operator cannot recover by manipulating the flight surfaces. After the model aircraft has been stabilized to a point where the operator can arrest the uncontrollable motion the parachute is jettisoned and normal flight resumed. The deploy and jettison signals may be sent using a single channel of a multi-channel transmitter and are completely independent of each other.