Abstract: A runway (21) is used to retrieve aircraft from the skies. During an emergency landing (57), an aircraft crash damage limitation system is deployed from a heated underground storage area (12, 22 and encircled H). A pair of parallel guide tracks (52) lift from bunkers (12 and 22) along the edge of the runway (21) and an aircraft recovery unit (18) is deployed from an apparatus storage area (12) at the approach. The guide tracks (52) provide nozzles (46) for complete runway foaming. Guide tracks (52) are further supported in deployment by a guide track retaining wall (64). The aircraft recovery unit is charged with fire suppressant agents (encircled F) and is locked into the guide tracks (52). A locking and acceleration/braking method is contained in magnetic flux bars (44 and 66). The aircraft recovery unit (18) is signaled to effect an air speed to ground speed match with the incoming distressed aircraft (57) by a control center (encircled E).

Abstract: A portable helipad adapted for use in rough terrain and for transport in a fully assembled state by a helicopter. A deck is supported by legs depending from the deck. Leg braces extending from the legs connect to brackets within an associated zone of attachment on the underside surface of the deck. The helicopter releasably engages the portable helipad for transport. The legs and associated leg braces are preferably extensible to permit the deck to be levelled over uneven terrain.

Abstract: A reusable single-stage-to-orbit spacecraft and a reusable launch assist platform provide a new system for space transportation. The platform has a frame with a cradle for supporting the spacecraft. Rocket engines attached to the launch assist platform propel the launch assist platform and the spacecraft substantially vertically through the atmosphere for release of the spacecraft. The launch assist platform returns to a predetermined landing site in a power-controlled, vertical descent.The spacecraft is in the shape of a cone having a large, rounded base with a primary load-bearing structure substantially perpendicular to the base. The spacecraft reenters the atmosphere in a base-first reentry, and is slowed and guided to a landing site by using a rocket engine in the base. The spacecraft lands base first on a resilient landing device.

Abstract: A control system includes at least one guiding device including a long range guiding water jet generator having a plurality of first nozzles each projecting a jet of water upwardly and a first illumination apparatus projecting a plurality of beams of light upwardly each in concert with the jet of water projected from each of the first nozzles so as to guide the flight vehicle along a predetermined direction when the flight vehicle is located at a longer distance relative to the guiding device and a short range guiding water jet generator having a plurality of second nozzles each projecting a jet of water upwardly and a second illumination apparatus projecting a plurality of beams of light upwardly each in concert with the jet of water projected from each of the second nozzles so as to guide the flight vehicle along the predetermined direction when the flight vehicle is located at a shorter distance relative to the guiding device.

Abstract: A portable helicopter landing pad especially suitable for deployment on an unprepared surface comprises a number of perforated metal mats which on being joined at their edges define a heliport of predetermined size and shape. Dual-purpose connectors releasably join adjacent mats to one another and anchor the edges of the mats to the underlying surface. If needed, moveable stiffening plates are provided for strengthening the assembled mats where the wheels or skids of the helicopter touch down. A rigid container is provided for transporting and storing the predetermined number of mats, connectors, and tools needed for a particular heliport. For larger installations, several containers are pre-packed to facilitate the transport and assembly of the required components. The container is designed to prevent the stacked mats, connectors, and tools from shifting while in transit. A removable cover retains the container's contents and further prevents them from slipping during storage and transport.

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: A duplex complementary carrier includes a flight vehicle floating above the ground, a control system moving on the ground for controlling movement of the flight vehicle, and a connecting system connecting between the control system and the flight vehicle. When the control system is moving on the ground, the flight vehicle above the ground is able to follow movement of the control system due to the connection provided by the connecting system such that the pressure of the control system on the ground and the frictional force of the ground on the control system are reduced by the buoyancy of the flight vehicle. The flight vehicle is able to move above the ground stably by the directing and guiding effects of the control system.

Abstract: A method is provided for controlling a carrier which is used to carry a flight vehicle, the method including (a) providing a carrier and a control system mounted on a lower side thereof; (b) sending a signal to a flight vehicle to decrease a velocity thereof for landing; (c) sensing a flight direction of the flight vehicle and instantaneous velocities thereof; and (d) accelerating the carrier to catch up with the flight vehicle at a location therebeneath and adjusting the velocity of the carrier to match with that of the flight vehicle such that the flight vehicle is able to smoothly land so as to be supported on a top surface of the carrier.

Abstract: A safety device for an emergency landing of an aircraft has a runaway. A unit for retarding the speed of the aircraft is mounted in the runway and includes a plurality of rows of juxtaposed rotary bearing members, each of which is provided with a friction surface, a plurality of rotatable shafts, each of which carries each row of the rotary bearing members, and a hydraulic unit provided in each row of the rotary bearing members. A unit for braking the speed of the aircraft is fixed in the runway downstream of the retarding unit and includes a plurality of rows of juxtaposed stationary bearing members, each of which is provided with a friction surface. A unit for supporting and guiding the aircraft to move on the runway includes a base slidable on the retarding unit and the braking unit and a preventing unit for preventing the aircraft from being released from the base after the aircraft lands on the base. The safety device further includes a fire-retarding fluid provided in the runway.

Abstract: An airship handling system is disclosed. The airship handling system of the invention includes a platform which rests upon a circular track, such that the platform may be aligned with the wind in order to facilitate the handling of a suitably equipped airship. The platform incorporates an arrester gear in order to bring the airship to rest at a specified point, a mooring system to hold the airship in position for subsequent handling operations, lifts and transfer track to remove a loaded module from the airship and replace it by a second loaded module, a further lift to transfer modules between the platform and the ground level station for loading and unloading, and an accelerator gear for accelerating the airship to take-off speed within the available length of the platform.

Abstract: The Flying Multi-Purpose Aircraft Carrier (FMPAC) comprises a runway body which is provided with V/STOL capability by at least two rotary wings, located outside the two lateral ends of the runway body in a side-by-side configuration. The rotary wings are, preferably, of a large diameter helicopter rotor blade type, and are powered by respective shaft turbine engines. A substantially flat runway platform is provided along the middle portion of the runway body, between the left and right helicopter rotary wings. The runway platform is located as low as possible, in order to secure flight stability of the composite aircraft. The top surface of the runway platform has a substantially flat and rectangular-like shape defining a conventional runway, and may allow a fixed wing CA to take-off from or to land on it, during flight of the FMPAC, allowing the pilot of the CA to operate his aircraft with a considerable margin of error.

Abstract: An articulated heliport pad in which the pilot controls the rotation of a central disk for last minute changes in wind direction as well as the operation of a unique hold-down device.

Abstract: A system for the recovery of aircraft comprises a large net having sufficient length and width to accommodate an aircraft in its landing mode in water having floats around its periphery for supporting it in a body of water for receiving and supporting an aircraft for its recovery.

Abstract: A giant column of air is employed to assist in the vertical take-off and landing of an aircraft. The column of air is forced through movable louvers which steer the aircraft on the air column. A pressure differential occurs on top of the air column so as to center an aircraft on the air column. In order to illuminate the air column, a salt spray is introduced into the column and a laser source resonates the crystals of the salt thereby causing energy to be radiated from the column which may be detected and displayed by an approaching aircraft.

Abstract: A pivotable safety railing for a platform such as a helicopter landing pad is disclosed. The safety railing includes a suitable hand railing of sufficient height to protect a person on the landing pad, and mounted on a pivot shaft extending along an edge of the platform. The pivot shaft allows the railing to pivot downwardly to a horizontal position while a helicopter is landing or taking off, and to pivot upwardly to an upright, or vertical, position, when a helicopter is resting on the landing pad. The pivot shaft is driven by a suitable electric motor which is controlled by sensors located on the landing pad, the sensors causing the pivot shaft to be driven in a direction to move the railing to its horizontal position whenever there is no helicopter present on the pad, and causing the shaft to be driven in a direction to raise the railing to its vertical position whenever a helicopter has landed.

Abstract: A helicopter landing pad and hangar structure attachable particularly to the deck of a ship in a manner requiring a minimum of space on the deck during both helicopter landing and storage, and also requiring no penetration of the deck or other substantial modification of the ship structure, comprises an enclosure including a framework, side walls, and a plurality of panels supported at the top of the side walls and slidable horizontally to an inner retracted position closing the enclosure or to an outer extended position opening the enclosure and extending laterally past the side walls. A lifting platform is movable vertically to a lower position within the enclosure or to an upper position horizontally aligned with the plane of the panels.

Abstract: An emergency aircraft landing device is shown of the type having a base with a concave upper surface for receiving and supporting the fuselage of an aircraft. A plurality of resilient, elongate members are arranged in rows at spaced intervals along the upper surface and the rows are oriented normal to the upper surface for stopping the forward progress of an aircraft landing on the upper surface. An inflatable bag on either side of each of the rows supports the elongate members normal to the plane of the upper surface. The base is mounted on wheels and is powered by an electric motor for moving down a runway. A second electric motor is remotely controlled by a radio signal and operates a worm gear to position the front wheel of the device control the direction of travel.

Abstract: A takeoff and landing platform for V/STOL aircraft has features to reduce ground effect. The platform has a plurality of vanes mounted above a flat horizontal surface. Each of the vanes is curved to turn the jet stream from the vertical. The upper edges of all the vanes lie in a plane that is parallel with the horizontal surface. This plane is located at a distance from the horizontal surface that is about 0.5 to about 2.0 times the engine nozzle diameter at takeoff and landing of the type aircraft that use the platform.

Abstract: This invention provides a system for launching aircraft into free flight regime regardless of runway conditions, wherein a sled of the self-powered air cushion vehicle type is configured in plan form so as to accept in temporarily locked relation thereupon and in combination therewith an airplane in such manner that a successful take-off run in mutually aerodynamically compatible regime may be accomplished in spite of surface problems with the runway. Upon attainment of airborne speed, under control of the pilot the aircraft lifts off the sled into full free flight; and thus is airborne albeit the runway is at the time unusable by conventional wheel-geared aircraft; for example, as the result of a previous bombing attack on the runway by enemy aircraft. The sled incorporates self-propelling and directional guidance means for retrieval/reuse purposes, as well as a take-off abort control system.

Abstract: A mooring device for use, particularly in the mooring of an aircraft such as a helicopter on the deck of a ship includes a grid having an upper surface adapted for engagement by a harpoon carried by the aircraft. The grid comprises a plurality of substantially identical elements and retaining means secured to the deck and adapted to retain the elements in juxtaposed relationship. In one embodiment the elements are generally rectangular in plan and have an upper surface provided with both full and half apertures arranged so that when in said juxtaposed relationship, the elements combine to provide a generally continuous apertured upper surface.

Abstract: A portable heliport adapted to be transported by a helicopter is described. The heliport includes a pair of deck extensions having foldable, extensible legs and which are hinged to a central deck supported by extensible legs. The deck extensions are folded and allowed to unfold by a winch which is detachable from the central deck and whose winch support also supports the deck extensions for transport by the helicopter. The extensible legs have threaded tubes telescoping in fixed tubes and quick releasable internally threaded, split clamps attached to the fixed tubes hold the threaded tubes in adjusted positions. The threaded tubes may be screwed into or out of the split clamps for fine adjustments. The legs on one side of the deck are longer than those on the opposite side so that, when the legs are all in contracted conditions, the port is in a condition adapted to a moderate slope site.