Abstract: An apparatus for the take-off, landing and taxiing of an aircraft without undercarriage system or with retracted undercarriage, wherein the apparatus comprises a ground-based undercarriage, the speed of which can be matched to the speed of the aircraft when landing, the ground-based undercarriage (10) is releasably connected to a slide system, which can be driven in a direction of movement, the ground-based undercarriage (10) has at least two coupling means, which enable interfaces of the aircraft (4) on the ground-based undercarriage (10) to be coupled, the ground-based undercarriage (10) can be moved along the slide system transversally to the direction of movement of the slide system to match the ground-based undercarriage (10) to the position of the aircraft (4).

Abstract: A landing area (1) adapted to be folded, stored and/or stowed on or in the holder (2) on which it is mounted. It is multi functional, removable, modular and can be adapted to the surface (22) of the holder on which it is supported, connected and/or from which the landing area (1) hangs. Mechanical elements (26) are provided for extracting the landing area (1) from its protection components (20) and for placing the landing area in a position where the landing area is adapted for landing of an air machine or vehicle once the reception elements (10, 11), defining the landing surface (12), are extended. The above-mentioned mechanical elements, or other members (25), are used for extending the reception elements (10, 11). The latter can also be folded, stored and/or stowed using the retraction components (24).

Abstract: An Airborne Elevator Apparatus capable of deploying at the same time multiple service loads at different altitudes in the Earth's atmosphere by physically separating tether weight carrier function from the service load weight carrier function of a common aerostat. The tether weight carrier function is performed by at least one airborne canopy assembly (20) filled with lighter than air gas, which has enough lifting power to support its own weight and the weight of the attached airborne cables (30). The service load carrier function is performed by several airborne booster assemblies (51). Designed to glide on the apparatus's airborne cables (30), an airborne booster assembly (51) filled with lighter than air gas has enough lifting power to carry its own weight and the weight of a service load at altitudes below the uppermost canopy. For stability purposes, the apparatus is designed to rotate around its vertical axis.

Abstract: An anchoring element (2) intended to be fixed on at least one external anchor point (4) of an aircraft's fuselage, comprising a fixing area (5) for ensuring the fixing of the anchoring element (2) on the external anchor point (4) and said anchoring element (2) comprising an anchor means for the connection to attaching means, characterized in that the fixing area (5) comprises means for fixing the anchoring element (2) also to a additional external anchor point (6) of the aircraft's fuselage and said fixing area (5) comprising an extension area (7) on which is located the anchor means.

Abstract: The invention relates to an anchoring harpoon intended in particular for an aircraft, capable of cooperating with an anchoring grate (2) of a platform, comprising jack means (3) including cylinder means (4) containing mobile piston means (5) provided with a rod (6) that extends beyond the cylinder means, the free end of which includes a harpoon head (7) that is hooked in the grate (2) and comprises retaining fmgers (8, 13, 14) that can be moved between a retracted position and an active position by control means (9). The invention is characterised in that the cylinder means (4) include at least two telescopic cylinder portions (10, 11) which can move between a position in which one portion is retracted inside the other and an active position in which one portion projects out from the other.

Abstract: An anchoring harpoon intended in particular for an aircraft, capable of cooperating with an anchoring grate of a platform, includes jack elements including a cylinder element containing mobile piston elements provided with a rod that extends beyond the cylinder element, the free end of which includes a harpoon head (7) that is hooked in the grate and includes retaining fingers (8, 13, 14) that can be moved between a retracted position and an active position by control elements (9). The control element (9) for controlling the movements of the fingers include a control piston (18) which can slide inside the rod of the jack and which is associated with a bistable actuator (19) of the fingers, capable of moving between a retracted position and an active position in which the fingers are deployed with the application of successive pressure pulses in the jack elements.

Abstract: An airship recovery system is disclosed including a first cushion pad configured to create a suction force on an outer portion of the airship to capture the airship during landing. An arm is coupled to the first cushion pad and movable between at least two different vertical positions. In an embodiment the air is movable in multiple degrees of freedom. An actuator device is coupled to move the arm. A sensor device is incorporated to detect the location of the airship relative to the recovery system. A controller is utilized to receive signals from the sensor device regarding the location of the airship and output command signals to the actuator to move the arm and the first cushion pad toward a desired contact location on the airship.

Abstract: A harpoon head (6) for a system for anchoring an aircraft on a grating (4) is characterized in that a distal end of the harpoon head has an interchangeable insert (20).

Abstract: Apparatus and method for a continuous replenishing of the lift gas and maintaining the proper pressure and lift of a tethered medium altitude aerostat utilizing a novel feed tube running the entire length of the tether. A first end of the feed tube is connected to the aerostat while a second end is connected through a novel slip ring means to a pressure controlled helium ballast chamber and scrubber on the ground to maintain pressure and lift by a reversible compressing pump. A plurality of pressure and temperature sensors and tension gauges strategically placed inside and around the airship continuously monitor the temperature and pressure changes in the aerostat. A data retrieval and communication unit mounted on the aerostat collects measurement data from the pressure, temperature and tension sensors which is relayed to the ground station and the data is used to regulate lifting gas pressure inside the aerostat.

Abstract: A system for efficiently transporting hydrogen from where it can be economically made to where it is most needed using specially designed airships. Technologies such as geothermal, wind, solar, wave tidal or hydropower can be used to generate electricity in-situ or very near to the primary energy sources. This electricity can then be used to produce hydrogen directly from water through various methods known in the art. Hydrogen can be delivered from the place where it is produced to the place where it is needed using an airship in which the hydrogen gas can also be used for generating lift, providing propulsion energy and serving ancillary needs. In other embodiments of the invention, the airship of the present invention can be used to dramatically reduce the cost of transportation of freight, the cost of passenger transportation, and to save on the area required for landing at the points of loading/unloading and embarkation/debarkation.

Abstract: A launch and capture system for capturing a vertical take-off and landing (VTOL) vehicle having a thruster and a duct configured to direct airflow generated by the thruster includes a capture plate and an extension. The capture plate is configured to alter the airflow and generate a force attracting the duct to the capture plate. The extension is coupled to the capture plate, and is configured to at least facilitate holding the VTOL vehicle against the capture plate.

Abstract: Apparatus and method for a continuous replenishing of the lift gas and maintaining the proper pressure and lift of a tethered medium altitude aerostat utilizing a novel feed tube running the entire length of the tether. A first end of the feed tube is connected to the aerostat while a second end is connected through a novel slip ring means to a pressure controlled helium ballast chamber and scrubber on the ground to maintain pressure and lift by a reversible compressing pump. A plurality of pressure and temperature sensors and tension gauges strategically placed inside and around the airship continuously monitor the temperature and pressure changes in the aerostat. A data retrieval and communication unit mounted on the aerostat collects measurement data from the pressure, temperature and tension sensors which is relayed to the ground station and the data is used to regulate lifting gas pressure inside the aerostat.

Abstract: An aircraft landing assist apparatus is designed to be retrofit to existing aircraft having internal constructions that have been modified to support the apparatus. The apparatus is designed so that on rough landings of the aircraft on a ship deck, the apparatus will collapse in a controlled manner to avoid any damage to ammunition and/or fuel storage areas of the aircraft.

Abstract: An airship retrieval system comprises a plurality of aerodynamic pods releasably mounted in suitable locations about the external surface of the airship. Within the pod is a handling or a tether line that is attached at one end to the airship and at the other end to the pod. When a suitable control signal is sent to the pod, the pod is released and the handling line and pod falls toward the ground to enable retrieval of the airship.

Abstract: A system and method for docking an airship to a mooring mast includes a thruster that is mounted to the fore end of the airship. When activated, the thruster generates a thrust vector that is substantially perpendicular to the longitudinal axis of the airship and is selectively directional. In particular, the configuration of the thruster can be changed to vary the direction of the thrust vector around the longitudinal axis to maneuver a connector on the thruster into contact with the mooring mast. Engagement of the connector to the mooring mast then docks the airship to the mooring mast.

Abstract: An aircraft landing assist apparatus is designed to be retrofit to existing aircraft having internal constructions that have been modified to support the apparatus. The apparatus is designed so that on rough landings of the aircraft on a ship deck, the apparatus will collapse in a controlled manner to avoid any damage to ammunition and/or fuel storage areas of the aircraft. In one embodiment the apparatus includes a plurality of support struts that each include an eccentric bushing. A locking pin can be used to selectively position the eccentric position to adjust the overall length of its associated strut.

Abstract: An environmental data collection system and method is provided having an internet link for providing an additional level of security for a remotely controlled data collection platform having a security alarm for protecting the platform and the environmental subject of the study. A novel lighter-than-air platform having a novel snorkel for detachably securing, mooring and providing buoyancy control is provided for the collection of data in the form of real time audio and video linked to the internet and subscribers. The novel snorkel is flexible and retractable into the novel airship to provide remote buoyancy control of the airship together with silently operating electrical motors for allowing the novel airship to be remotely controlled and moved at will to track and monitor wildlife and make environmental measurements necessary for the protection of the environment, wildlife and the operation of the novel airship.

Abstract: A landing arrangement for an aircraft comprises an aircraft support assembly (22) to support the aircraft (10) when the aircraft is on the ground. The aircraft support assembly (2) is movable between a first ground engaging condition (22b) in which the aircraft nose (24) is spaced above the ground by a first distance (X) and a second ground engaging condition (22C) in which the aircraft nose (24) is spaced above the ground by a second distance (Y). The second distance (Y) is less than the first distance (X).

Abstract: The present invention relates to a device for lashing down a rotorcraft wing, said wing being provided with at least first and second adjacent blades P and P?, the ends of said blades being provides with respective endpieces. In addition, the device comprises a main cord CP having a first end CPE1 fastened to first fastener means 5? arranged on a second end CPE2 secured to a second blade P? and having a second end CPE2 secured to a second fastener means M1 arranged on a first endpiece of the first blade P. The lashing-down endpiece includes first fastener means 5 for fastening to a first main cord CP and second fastener means M1 for fastening to a second main cord CP.

Abstract: An aircraft landing assist apparatus is designed to be retrofit to existing aircraft having internal constructions that have been modified to support the apparatus. The apparatus is designed so that on rough landings of the aircraft on a ship deck, the apparatus will collapse in a controlled manner to avoid any damage to ammunition and/or fuel storage areas of the aircraft.

Abstract: This invention solves problems associated with prior-art soft-dock mechanisms by placing all active components of a soft-dock system on the chaser side of the mechanism, leaving the target side of the mechanism completely passive (i.e., requiring no power expenditure or self-actuated moving parts to operate). In particular, the active components are supported on the end of a flexible cable attached to the probe, or chaser, side of the device. These components act as a sort of spring-loaded “trap.” Once the end of the probe passes into a receptacle on the target side, the mechanism is triggered, engaging it in such a way that it can no longer be pulled out of the receptacle until it is reset. The soft-docking cable may be replaced with a rigid, semi-rigid or jointed post that is used to bring a capture mechanism into engagement with its corresponding receptacle or receiving structure.

Abstract: A mooring facility for a tethered gas balloon comprises a building structure containing a hemispherical basin capable of receiving the lower portion of an inflated lighter-than-air gas balloon for mooring the balloon. The surface of the bowl structure is complementary to the surface contour of the lower portion of the balloon. A gondola is suspended beneath the balloon and occupies a central recess in the bowl structure when the balloon is moored. The balloon is tethered by a cable and can be raised and lowered between an elevated operating position and a lowered moored position. The facility avoids the need for a large space requirement and can be erected or installed in a built-up area in or adjacent to a town or city.

Abstract: Methods and apparatuses for capturing and recovering unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be captured at an extendable boom. The boom can be extended to deploy a recovery line to retrieve the aircraft in flight. The boom can be retracted when not in use to reduce the volume it occupies. A tension device coupled to the recovery line can absorb forces associated with the impact of the aircraft and the recovery line.

Abstract: Methods and apparatuses for capturing and recovering unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be captured by a recovery line in flight, a process that can be aided by a line capture device having a retainer with two portions spaced apart by a distance great enough to receive the recovery line, e.g., to capture the recovery line with increased security. The line capture device can be operatively mounted on a lifting surface of the aircraft.

Abstract: An aircraft landing assist apparatus is designed to be retrofit to existing aircraft having internal constructions that have been modified to support the apparatus. The apparatus is designed so that on rough landings of the aircraft on a ship deck, the apparatus will collapse in a controlled manner to avoid any damage to ammunition and/or fuel storage areas of the aircraft.

Abstract: An apparatus for illuminating the messenger cable of a helicopter includes a helicopter having a floor and including a RAST system; the RAST system comprising a messenger cable with a connector attached to one end for lowering to a landing deck of a ship, the RAST system further comprising a winch for raising and lowering the messenger cable, a housing attached to the floor of the helicopter through which the messenger cable is raised and lowered, a top of the housing including an opening through which the messenger cable passes, a sheave attached to the top of the housing and over which the messenger cable passes and a pulley attached to the housing and over which the messenger cable passes; a luminescent cover attached to a portion of the messenger cable adjacent the connector; a light mounted on the top of the housing for charging the luminescent cover; and a limit switch mounted on top of the housing for stopping upward motion of the messenger cable.

Abstract: An apparatus for inflating and deploying an aerostat having a nose section and a tail section includes a cylindrical container for housing the deflated portion of the aerostat. The cylindrical container is formed with an open end and defines a longitudinal axis. A feed hose extends from a gas source, through the container to a hose end that projects axially from the open end of the container. The deflated aerostat is initially folded to juxtapose the nose and tail of the aerostat. Next, the nose of the aerostat is attached to the feed hose end and the remaining portion of the aerostat is folded and inserted into the container. As the tail section is inflated outside of the container, aerostat cloth is drawn from the container. A mechanism is provided to control the release of cloth from the container and maintain pressure in the inflating aerostat within a predetermined range.

Abstract: An environmental data collection system and method is provided having an internet link for providing an additional level of security for a remotely controlled data collection platform having a security alarm for protecting the platform and the environmental subject of the study. A novel lighter-than-air platform having a novel snorkel for detachably securing, mooring and providing buoyancy control is provided for the collection of data in the form of real time audio and video linked to the internet and subscribers. The novel snorkel is flexible and retractable into the novel airship to provide remote buoyancy control of the airship together with silently operating electrical motors for allowing the novel airship to be remotely controlled and moved at will to track and monitor wildlife and make environmental measurements necessary for the protection of the environment, wildlife and the operation of the novel airship.

Abstract: A mooring device adapted particularly for an aircraft, includes at least one line (18) or the like ensuring connection between an anchoring point (20) on the aircraft and the ground, elements (26) for dynamically controlling the tension of the line (18) as a function of variations of the distance separating the anchoring point (20) on the aircraft to the ground.

Abstract: The object of the invention is a mooring device adapted particularly for an aircraft, comprising at least one line (18) or the like ensuring connection between an anchoring point (20) on the aircraft and the ground, characterized in that it comprises means (26) for dynamically controlling the tension of the line (18) as a function of variations of the distance separating the anchoring point (20) on the aircraft to the ground.

Abstract: An apparatus for inflating and deploying an aerostat having a nose section and a tail section includes a cylindrical container for housing the deflated portion of the aerostat. The cylindrical container is formed with an open end and defines a longitudinal axis. A feed hose extends from a gas source, through the container to a hose end that projects axially from the open end of the container. The deflated aerostat is initially folded to juxtapose the nose and tail of the aerostat. Next, the nose of the aerostat is attached to the feed hose end and the remaining portion of the aerostat is folded and inserted into the container. As the tail section is inflated outside of the container, aerostat cloth is drawn from the container. A mechanism is provided to control the release of cloth from the container and maintain pressure in the inflating aerostat within a predetermined range.

Abstract: A regional aircraft boarding pier can be provided at an airport concourse in place of one or two conventional large aircraft boarding bridges. The regional aircraft boarding pier includes a primary passenger bridge between the airport concourse and a hub. A number of secondary passenger bridges extend from the hub to individual regional aircraft. In this way, an equivalent number of passenger seats can be serviced as between large and regional aircraft, and large and regional aircraft can be docked at a common airport terminal. Consequently, passengers can more efficiently and conveniently transfer between connecting flights that are on both large and regional aircraft. The hub of the boarding pier can take a number of configurations to optimally use the space available. The hub can also support large aircraft boarding bridges as well as the secondary passenger bridges docked to smaller, regional aircraft.

Abstract: Recovery of a towed body, in one embodiment in the form of a decoy which is initially stowed in a receptacle or canister and which is allowed to pay out behind an aircraft on a towing cable wrapped around a spindle, is accomplished by snaring or lassoing a portion of the towing cable and by dragging it to a further spindle which is driven so as to cause the lasso and a portion of the towing cable to wind up around the driven spindle. When a sufficient amount of the cable is wound around the driven spindle, the cable end secured to the canister is severed to allow all of the rest of the towing cable to be wound up. In one embodiment, a telescoping saddle or docking cradle is provided which extends from the canister to receive the retracted towed body so that it may be secured to the moving vehicle from whence it can be recovered, refurbished, and redeployed.

Abstract: A collapsible airship batten assembly (20) is disclosed for airships (22). The assembly (20) is deployed upon inflation of the containment chamber, and is freely collapsible during the deflation process. The preferred embodiment includes the folding nose batten assembly (20), comprising a central deployment guide beam (50), a spoke hinge hub (56) rigidly affixed to the aft end of the central beam (50), a set of spokes (58), the first ends of which are adjustably connected to and emanating out from the spoke hinge hub (56), a nose spar hinge hub (46) slidably mounted on the central beam (50) for movement along the length of the beam (50), a set of nose spars (42), the first ends of which are attached to the exterior of the airship skin (36) and adjustably connected to the seconds ends of the spokes (58), and the second ends of the nose spars (42) translate inwardly to movably connect with the nose spar hinge hub (46).

Abstract: A method of launching inflatable airship apparatus (3) for subsequent ascent to high altitude for operation as an airship having a hull (4) formed from an inflated flexible gas containment envelope (5), payload (15), drive motor (6) mounted at the stern of the hull and cables (26,27), for supporting the payload (15) within the hull (4), connected to the drive motor (6) and to the hull at, or adjacent to, a nose portion of the hull. The method comprises partially inflating the gas containment envelope (5) with a lighter than air gaseous medium to cause the nose portion to rise within a vertical launch enclosure (10) to position the partially inflated gas containment envelope (5) in a launch position, and subsequently releasing the partially inflated gas containment envelope (5) from its launch position through an open top of the vertical enclosure so that the envelope ascends clear of the vertical enclosure (10) and lifts the payload means (15) and drive motor (6) by means of the cables.

Abstract: A remotely controlled movably powered shuttle frame has foundation pads attached thereto at all four corner portions for separating skid pads of a helicopter from the flight deck of a marine vessel, wherein both the skid pads and the fight deck are outfitted with hook and loop fabrics. Skid blades displaced from retracted positions underlying the foundation pads are extended from the shuttle frame underlying a landed aircraft whose weight has been lifted off the flight deck by lifting arms pivotally mounted on the foundation pads. The aircraft carried by the lifting arms on the shuttle frame after the skid blades are retracted is shuttled by wheeled movement of the shuttle frame to a desired location on the flight deck.

Abstract: A system and method for docking a space object to a space travel vehicle is disclosed. The space travel vehicle includes a frame assembly which may be deployed into an at least generally funnel-shaped profile at the desired time. A web of sorts is attached to the frame assembly and is disposed into an at least generally funnel-profile by the deployment of the frame assembly as well. In one embodiment the web is in the form of a plurality of Velcro tape members. A space object contacting the web is detachably adhered thereto by including suitable fasteners on the space object as well. Retraction of the frame assembly directs the space object into a space object receptacle of the space travel vehicle, detaches the tapes from the captured space object, and retains the captured space object within the space object receptacle. After the captured space object has been retrieved, the frame assembly may thereafter be deployed to capture another space object in the above-described manner.

Abstract: This invention concerns a sound proof hangar for airplanes with a wide entrance (3) for aircraft (7). To provide a sound barrier at the open side, the entrance opening is limited, at least on one side, by a series of deflecting surfaces (10), the inner edges of which are directed, in horizontal section, towards the hangar interior and the external edges of which are directed laterally. The deflecting surfaces (10) can be moved between a closed position which partly or completely closes the entrance opening (3) and a position which opens the entrance opening (3).

Abstract: A tethered balloon having a spherical balloon proper inflated with a gas whose specific gravity is lower than that of the outside air, a gondola attached to the bottom of the balloon proper, a vertical stabilizer attached to the balloon proper, a connecting assembly attached to the balloon proper, a tether connected to the connecting assembly, and a tether holder having a drum to take up and pay off the tether and placed on the ground. The connecting assembly is positioned opposite to the vertical stabilizer with the gondola disposed in between. A straight line connecting the center of the balloon proper and the connecting assembly is inclined with respect to the central axis of the balloon connecting the center of the balloon proper and the center of gravity of the whole balloon. The balloon is transversely stable because little force acts on the balloon in a direction perpendicular to the wind.

Abstract: Apparatus is disclosed for moving an aircraft across a deck surface from a landing position to a stowed position. The apparatus comprises a pair of control beams (26, 28). The control beams are propelled along longitudinal (6, 8) and transverse rails (22, 24) to engage and then position a landed aircraft ready for the aircraft to be guided securely to its hangar by a self-propelled shuttle unit (58). When not in use, the control beams may be stored in the hangar.

Abstract: Coupling a landed helicopter to a positioning device, on a ship deck, for example, has up to now been carried out by an operator in such a way that the operator manually operates a grasping means (18), engaging with a longitudinal side of the helicopter, and stops it. The coupling device and method according to the invention use an optical device (30) on at least on grasping mechanism (18) and a reflection means, corresponding to an optical device on the helicopter. The optical device (30) locates the helicopter regardless of the helicopter's landing position, and moves the grasping mechanism (18) by means of corresponding control systems in simple fashion to an exact coupling position without any need for intervention by an operator.

Abstract: The invention is a cable restraint system for an aircraft having first and second main landing gears equally spaced from the longitudinal axis of the aircraft; the system for securing the aircraft from movement during engine run-up testing when the aircraft is positioned such that the main landing gears are in front of and the longitudinal axis thereof is aligned with a ground attachment fitting mounted to the ground. In detail, the system includes first and second coupling members. First and second cables having first and second ends, have their first ends attachable to the ground attachment fitting and the second ends attached to the first and second coupling members, respectively. A third cable is attached by its ends to the first and second coupling members. Fourth and fifth cables having first and second ends, are attached by their first ends to the first and second coupling members and attachable by their second ends main landing gears.

Abstract: A long arm for an aircraft turnaround apparatus mounted at one end to the floor of an aircraft hanger for swinging about a vertical axis causing a nose-wheel carriage at the free end of the arm to follow a semicircular path. The nose-wheel of an incoming aircraft runs onto the carriage such that its imaginary lateral rotation axis is practically coincident with the arm axis so when the arm swings, the aircraft's ground supported landing gear traces a semicircle. The carriage has a chock bar which stops the aircraft from overtraveling the carriage. One chock bar version requires manual insertion and removal and another automatically latches in the stopping position but is unlatched by an aircraft leaving the carriage after which a spring restores the chock to the latched position. An optional spring system can restore the arm and carriage to a nose-wheel receiving position after a turned around aircraft has departed.

Abstract: A wind resistant habitable dwelling which includes the fuselage of an aircraft rotatably mounted on a support column. The tail fin of the fuselage is retained to allow the dwelling to pivot about the support column and point into the direction of the prevailing wind. The fuselage of the aircraft has points along its undercarriage support framework for attachment of a rotatable support column, which is cylindrical in shape. The support column includes a bearing assembly and a gearing system. The bearing assembly defines a single axis of rotation that is perpendicular to a level ground surface, so that the fuselage is capable of pivoting about the support column within a plane parallel to the level ground surface. The gearing system, which is also attached to the fuselage of the aircraft, is driven by motors and is capable of being further controlled by both dampening and braking assemblies housed in the support column. Access to the support column is provided by a ground level hatchway.

Abstract: A method and a system of assembling a launch vehicle vertically on an aboveground platform are presented in the present invention. The method of the present invention enables a rapid assembly of the launch vehicle; thus substantially reducing the final cost of the launch vehicle. The system of the present invention includes a plurality of specially designed tools that enable the rapid assembly of the launch vehicle.

Abstract: A modular launch pad for a launch vehicle which comprises a frame and a plurality of building units separably connected to the frame by means of connectors. The building unit comprise a concrete slab and a peripheral frame made of U-shaped channel sections connected to one another to form a frame, wherein the legs of the U are directed inwardly to engage the major surfaces of the slab. At least one of the legs of the channel sections is partially embedded in the slab so that the outer surfaces of the legs lie flush with the portion of the major surface extending between the legs. A plurality of longitudinally and transversely extending reinforcement bars are embedded in the concrete slab and a plurality of connecting means are secured to the slab. The pad has a launch vehicle mount for supporting a launch vehicle and defines exhaust gas channels in flow communication with an exhaust gas opening in the mount.

Abstract: An aircraft adapted for flight in helicopter mode with its longitudinal axis oriented generally vertically and in airplane mode with its longitudinal axis oriented generally horizontally is provided with the capability of launching and landing with the tail end directed skyward. The invention also includes improvements to the controllability and efficiency of aircraft in helicopter mode provided by the stabilizer wings and relative rotation of the fuselage section about the aircraft's longitudinal axis. The aircraft has an elongate boom positioned between the rear fuselage and the stabilizer wings for engagement with a base structure. The base structure may be attached to a building, a trailer transporter, a ship or some other structure. The base may be a beam having latching arms that swing inward when pressure from the boom is applied, then trap the boom in a recess between the latching arm and beam, thereby suspending the aircraft.

Abstract: An installation for landing a tethered balloon comprises a balloon which is brought back down towards the ground (9) by means (11) of a return cable (2), and which has a gondola (6) which is hollow in its center to allow the return cable (2) to pass therethrough, and it also includes means for winding the return cable (2) out and in, which means are mounted in a cavity (10) in the ground. According to the invention, the installation also includes a landing platform (3) covering the cavity (10) and including an opening (12) through which the return cable (2) passes, which opening is centered on the vertical outlet axis (12a) of the return cable (2).

Abstract: A sensor mount apparatus includes a loop for carrying a sensor payload. An upper portion of the loop includes at least one upper attachment point for receiving at least one upper tether line. A lower portion of the loop includes at least one lower attachment point to connect the sensor mount apparatus to a lower tether line. The sensor mount apparatus further includes an upper plate mounted to the loop, a lower plate for carrying a sensor payload, and a slide mechanism mounted between the two plates. The slide mechanism operates to slidably move the lower plate relative to the upper plate so that the lower plate and sensor payload attached to the lower plate move to a position where the sensing device of the sensor payload is not obstructed by the loop. Where the sensor payload is an optical sensor, such as a camera, the camera may be positioned to see an unobstructed, three hundred sixty degree field of view.

Abstract: A device for gripping, guiding and moving wheeled-type helicopters, particularly on board ships, platforms and the like, comprising a pair of crossmembers (6) located parallel to longitudinal axis (X--X) of the vessel and capable of moving transversally to such axis, in engagement with corresponding means of transverse guidance (2) integral with the ship's deck (3), each under the action of appropriate means of operation (7,8a, 8'a), independent of one another, and of further means of movement (12, 13) parallel to the longitudinal axis of the vessel, in engagement with corresponding longitudinal means of guidance (1), there being also provided a gripping and lifting arrangement (10,100) integral with each crossmember (6) and capable of moving in relation to the latter in order to grip, lift and guide the helicopter after landing, irrespective of its relative position with respect to deck (3) and its orientation with respect to longitudinal axis (X--X) of the vessel, and to position it in alignment with at lea