Abstract: An aircraft restraining system is utilised for securing and handling an aircraft on the deck of a ship. The system includes two elongate restraining beams which ere transversely movable from respective storage positions for engaging at least two spaced portions of an aircraft, such as wheel spurs. Each restraining beam includes a restraining member, such as a latch arrangement, for engaging the wheel spurs and restricting longitudinal movement of the spurs, and thus of the aircraft. At least one of the latches is movable along the respective beam to permit a secured aircraft to be rotated on the deck.

Abstract: A landing and anchoring mechanism for an airship takes advantage of the ship's supporting frame that has a row of cross-ribs interconnected by lengthwise beams arranged between neighboring ribs. In order to make it possible to land on any landing field even without conventional and costly apparatus, and to anchor the airship against the effects of wind and weather, a bi-pod landing gear is combined with an anchoring device. The landing gear is articulately connected to the supporting frame on the one hand and to the airship gondola by respective landing gear lateral rocker arms on the other hand. The bi-pod landing gear is arranged in a crosswise plane in front of the aerodynamic center of wind pressure of the airship. At least a portion of the anchoring device is provided on the floor of the airship gondola in the area of the attachment of the landing gear lateral rocker arms to the gondola floor.

Abstract: A landing apparatus for an airship or the like is composed of a windlass 2, 3 mounted on the lower part of said airship 1, a tugging hawser 4, 5 releasably wound in said windlass 2, 3, a mooring device 6, 7 connected to a leading end of said hawser 4, 5 and a lashing rope 9, 10 horizontally extended spaced relation from a landing space 8. The airship can be landed by its own power when the hawser 4, 5 hanging from the airship is engaged with the lashing rope 9, 10, and is wound by the windlass 2, 3. The airship can be landed on a narrow landing space 8 since the airship is not blown off by the wind.

Abstract: The invention is a mooring tower for a for a lighter-than-vehicle. In detail the invention includes a vertical tower having a vertical and lateral axis. A first support member is mounted on the top of said tower, which is rotatable in a horizontal plane about a vertical axis aligned with the vertical axis of the tower. A second support member is mounted by its first end mounted to the first support member and includes a telescoping second end. The second support member is rotatable in a vertical plane about its first end. The second support member includes an aperture extending therethrough from the first end to the second. A winch is mounted to the vertical tower having a mooring line extending through the aperture in the second member from the first end to and out the second end thereof. Thus a vehicle having the end of the mooring line attached to the nose thereof can be winched to the vertical tower.

Abstract: An anchoring system using a harpoon secured under a helicopter and a grid a platform includes a shaft, having near its end, fingers oriented and movable radially between a retracted position and an extended position. The shaft includes a device for moving and retaining the fingers in the extended position. The device acts from a state activated in response to the penetration into the grid. It furthermore includes structure for unlocking the fingers and resetting the moving and retaining device. Harpoons including such catching heads, which have the advantage of being light and simple in construction, and capable of being adaptable to all types of helicopters are also contemplated.

Abstract: A lightweight hard nose assembly for mooring a lighter than air vehicle to a mooring mast wherein the hard nose assembly includes a cone assembly which further includes a base ring attached to the lighter than air vehicle, a top plate, including a docking probe, and a plurality of struts connecting the base ring to the cone assembly. The hard nose assembly further include a plurality of guy lines, originating from the top plate and attached to the lighter than air vehicle at a plurality of patches. This lightweight nose cone assembly for lighter than air vehicles results in substantial savings in weight and cost and is more efficient than existing hard nose structures with battens.

Abstract: A control system for automatically loading and unloading a vehicle (10) from a cargo compartment comprises a plurality of distance measuring sensors (31,32,33,34) attached to specified locations on the exterior surfaces of the vehicle (54,56,57) and the cargo compartment (55). The sensors provide distance signals, indicative of the distance between each sensor and the nearest obstruction, to a microprocessor which compares each of the distance signals to reference signals indicative of the minimum allowable clearance between each specified location and an obstruction. During activation of an automatic loading/unloading switch (70), a winch (39) is activated to move the vehicle into or out of a cargo compartment if each of the distances is greater than the corresponding minimum allowable clearance.

Abstract: There is provided aircraft securing apparatus for securing an aircraft against toppling on the deck of a ship or the like. The apparatus includes a rotatable arm pivotal in a plane substantially parallel to the deck to engage a downwardly-projecting probe of an aircraft. A releasable clamp is mounted on the arm and is adapted to be slidable from a stored position to a probe-engaging position, and a sensor is provided on the arm for sensing engagement of the probe by the arm and actuating locking of the clamp about the probe. A drive motor is provided for effecting rotation of the arm.

Abstract: Bird droppings on the propellers and tail sections of parked aircraft are substantially prevented by mounting the present apparatus on the horizontal surfaces thereof which normally present suitable bird perches, the present apparatus having one or more upwardly extending peaked portions which provide no approximately horizontal perchable surface to birds, thereby substantially eliminating accumulation of bird droppings on the supporting structural components of the aircraft.

Abstract: The invention comprises a restratining tie down apparatus for tieing down a movable abject, such as an aircraft, in a straight line connection between the stationary object and the aircraft. The restraining tie down apparatus has a storage compartment or container which is adapted to be fixed upright in the ground with with an opening at the top which is flush with the top surface of the ground. A tie down device is removably mounted within the container. The tie down device has a frame with a pair of side panels and a spool is rotatably mounted between the side panels. An elongated flexible belt is wound on the spool with its inner end attached to the spool and its outer end having a hook attached thereto. A second hook is attached to the frame of the tie down device. A spring is mounted to the frame with one end attached to the frame and its other end attached to the spool to urge the spool to rotate on the frame in a direction to wind the belt onto the spool.

Abstract: An offshore mooring buoy for mooring a crude oil tanker and the like includes a hawser tension sensing member and a control circuit for generating indicator signals in response to predetermined mooring tension forces exerted on the buoy under varying sea conditions. A mast mounted on a mooring platform of the buoy includes a vertically-spaced array of colored indicator lamps which provide visual indication to the ship's crew of a range of acceptable, stand-by, and unacceptable mooring loads exerted on the buoy and the hawser. The circuit is also operable to energize a horn when a predetermined sustained mooring force is exerted on the buoy as a back-up signal or when weather conditions impair visual observation of the indicator lamps.

Abstract: A device for gripping, handling and transporting helicopters, particularly on board ships, platforms and the like, includes a pair of gripping units located parallel to a longitudinal axis of the vessel and capable of moving transversally to the axis and parallel to one of the respective transverse guides, and under the action of drive units which are independent of one another, and traversing units parallel to the longitudinal axis of the vessel, and connected with corresponding longitudinal guides, along which the former are guided under the action of further independent drive units upon cocking the helicopters wheels.

Abstract: The invention relates to a device for increasing the stability, especially the lateral stability, of a helicopter placed on board (1) having a tricycle landing gear (2, 6), when it is set down on a moving platform.The device comprises two lateral stabilizers (13), each equipped with a wheel (16) for support on the platform and connected to the structure of the helicopter by an essentially rigid support, comprising a leg (17), about the axis of which the wheel (16) can turn, the leg (17) itself being connected to the structure by a rigid and transverse component which may be a pivot axle if the leg can be raised, or a slidingly fitted arm if the stabilizer (13) is additional. The stabilizers may also be integrated into a towing trolley.Application to the equipment of helicopters placed on board, having a tricycle landing gear.

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: An aircraft securement device includes a sliding shaft, typically mounted to the aircraft landing gear. The shaft resembles a harpoon and is lowered through a wire grid when deployed. Tab-like members spring outwardly from the lower shaft end and engage the lower surface of a grid so as to retain the aircraft thereto.

Abstract: An RPV, comprising means for engaging a snag line carried as part of a securing system which "snags" means (for example hook) on an RPV and assists the RPV to a safe landing, the snag line extending from a winch unit proximate the proposed landing area of the RPV to a position on the ship to which it is removeably secured and the end thereof carrying means to be secured to means on the RPV.

Abstract: Lighting devices for an aerostat tether wherein the tether is used as a communication antenna. The lighting apparatus includes a split core transformer having a plurality of turns of secondary winding with the electrical portion of the tether constituting a single turn primary. The secondary voltage is provided to a voltage limiter which reflects excess energy back into the primary circuit, with the output of the voltage limiter being fullwave rectified and regulated to a predetermined DC value for operating a strobe light.

Abstract: A restraining device for an aircraft with wheels having tires thereon, comprised of a base plate upon which is mounted a restraint members to prevent movement of the tire when it is positioned on the base plate. The restraint members are hinged on one side of the base plate to allow for opening and closing. This movement is an arc laterally across the base plate. The restraint members in the closed position are secured to the base plate by latches mounted on the base plate located laterally across from the hinges.

Abstract: A parking trolley for light aircraft (1) with a couple of landing wheels (3,3), and a nose or rear supporting wheel (3'), comprising a mainly T-shaped frame (2) with adjustable supporting surfaces (4, 5,6) for the landing wheels (3,3) and the supporting wheel (3'). The T-frame is supported by wheels (12,13,14) at the free ends of the frame, the wheels being adjustable and lockable in a position with the turning axes of the wheels in parallel for transport of the parking trolley and light aircraft on the trolley by the aid of a traction vehicle. Furthermore, wheels (12,13,14) are adjustable to positions with their turning axes directed as radii of a turning point (9), alternatively a turning point (10) at a distance from turning point (9), which is connected with an anchoring means (11) in the ground, via a turning bolt.

Abstract: An RPV for use on shipboard, the RPV having a lower support (for example a plurality of legs) comprising a plurality of broad pads at the lower end, a downwardly extending probe (or finger) extending from each pad, the lower end carrying wings within the probe that may be extended from the probe to extend laterally for securing below a grid through which each probe (or finger) may extend.

Abstract: The invention concerns reception and securing device for a hooking system used for mooring loads or vehicles onto a platform 1, of the type including one upper perforated plate 3, and support means 7 for said plate, connected together by pillars 8.The said support means are made up of one lower plate 7 of approximately constant thickness in contact with said platform 1, in combination with said pillars 8 which comprise two shoulders 15 and 16 respectively in contact with said upper and lower plates, to make a strong unit and to provide a constant separation between said upper perforated plate and said lower plate. The thickness of said lower plate 7 is thin comparatively to the thickness of said upper plate, for example lower than or equal to 1 cm. The device comprises means for securing said upper place to said platform, said means being one spacer 8 which consists of a set of legs welded to said platform, said upper plate 3 being attached to each leg by a screw.

Abstract: An improved tether having a central strength member comprised of layers of synthetic fibers surrounded by a thin weatherproof plastic barrier. A current carrying metallic braid surrounds the weatherproof barrier and in a portion of the tether is of a higher strength and denser weave copper than in other areas. An outer protective jacket surrounds the metallic braid and one or more windows are formed by removing a short longitudinal section of the outer jacket above an area of the tether which has the high density metallic braid. The weatherproof barrier, at least in the area where windows are formed, is heat sealed to form a seamless barrier. A relatively soft copper wire is wound around the metallic braid in the window area so as to transfer lightning induced currents in the metallic braid of the tether to a grounding system.

Abstract: A unidirectional clamping mechanism for clamping a visibility enhancement device such as a strobe light to an aerostat tether subject to deployment and in-haul operation. The clamping mechanism includes diametrically opposed rollers each having a single tooth ratchet and pawl arrangement which allows unlimited rotation in one direction and limited or no rotation in an opposite direction such that when deployed, the strobe lights will not move down the tether but during an in-haul operation the mechanisms may be stacked one on top of the other while the tether is rapidly pulled through them.

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: An airship telescopic boom adapted for mounting on an airship for securing airship mooring lines when docking the airship. The boom may be used for the handling of a fuel line in the refueling of the airship, transferring of airship supplies and equipment, and similar applications. The boom reduces the requirement for a large ground crew and possible injury to related personnel.

Abstract: The present invention relates to a point landing method for a flying object, e.g., an aircraft (manned or unmanned), a helicopter, a missile, in a location which may be stationary, e.g., a ground plot or the roof of a building or a moving one, e.g., a car, ship, train.

Abstract: An apparatus for training aircraft pilots wherein the apparatus includes a boom defined by a central bracket, a large rigid arm and a small rigid arm collectively supported on a vertical mast for pivotal movement about horizontal and vertical axes. The large and small arms extending outwardly from the mast along a common longitudinal axis, the outward end of the small arm being provided with an adjustable balance weight and the outward end of the big arm being provided with a sling for suspending an aircraft at its center of gravity.

Abstract: A helicopter rapid securing and traversing system for securing a helicopter upon landing on the deck of a ship for subsequently traversing it from its landing position, the system comprising a housing reciprocal from a position remote the landing area to a position adjacent the landing area of the helicopter, the housing carrying a shock absorber and sensing structure extending across the housing for contacting a probe or other projection extending from the helicopter on the exterior of the helicopter when the helicopter has landed on the deck of the ship and the housing is brought to engage the probe or other projection, the shock absorbing bar and sensing structure for slowing and stopping the movement of the housing when the probe or projection is engaged and for cushioning the engagement and for sensing the position of the probe or projection, a carrier on the housing extending across the housing and carrying a securing structure thereon for securing the housing to the probe or projection on the helicopte

Abstract: An inflatable hull has an integral nose section comprising an array of trapezoidal fabric sections secured to form a frustro-conical volume. A nose cap is secured to the end of the frustrum with a conical array of tensioned ropes secured at their ends to the hull. The conical volume side walls at the nose taper to the cone axis at an angle such that a vertical load at the nose apex or an axial load on the region of the nose next to the apex does not bend, collapse or otherwise damage the nose section to provide a soft mooring attachment for the aerostat.

Abstract: An apparatus for moving aircraft on flat surfaces with the aid of cables which, on the one hand, act on the aircraft and, on the other hand, pass to winch drums via guide pulleys which are in part displaceable is characterized in that, for moving aircraft, in particular helicopters, multi-drum winches are provided on a ship's deck with the winch drums being drivable via differential transmissions by two motors which are controllable by means of a joystick operable in the sense of the intended movement of the aircraft.

Abstract: A docking device for space vehicles is disclosed wherein one coupling member of one vehicle is constructed as resiliently alignable telescopic rod having a head with latch structure which head is inserted in a coupling funnel of the other vehicle and having a latch trap in its bottom; the head sliding along the funnel wall during insertion and the latch is actuated thereby. The alignment of the rod may be controlled by a homing beacon.

Abstract: A load moving system, for moving articles such as a helicopter (18) form a port hangar (19a) to a starboard hangar (19b) or vice versa, wherein four trolleys (2 and 13) run on two rails (R) and are cabled to two after winches (3) and two forward winches (14). Vertical roller fairlands (12) act as cable runners. Two control positions (4 and 15) are provided from which the system may be operated.

Abstract: A system for retrieval and/or launching an aircraft capable of hovering flight (for example an aircraft having a thrust vectoring capability or a helicopter) includes gantry means 3, 5 for mounting on a surface station (for example a naval vessel 1), and an aircraft capable of hovering in a stationary position with respect to the gantry. The gantry and the aircraft are provided with complementary engagement means 9, 10 which are releasably engageable to allow the whole of the weight of the aircraft to be carried by the gantry. The engagement means on the aircraft are provided in the region of its center of gravity. In a retrieval sequence, the aircraft hovers with its engagement means 10 within a notional window with respect to the engagement means 9 of the gantry and the engagement means are then engaged.

Abstract: The present invention relates to a mechanism for docking and joining space craft, whereby one craft may be captured by remote control then hauled in towards the other, to which it is then joined. According to the invention, this mechanism is characterized in that it comprises, mounted on the captor craft, a steerable, extensible and retractable boom provided at its free end with connecting means adapted to cooperate with complementary connecting means provided on the craft to be captured.

Abstract: From one or more lighter than air bodies, carrying wind energy catching rotor devices, like windmills, turbines or the like, the caught energy is mechanically transmitted to earth by at least one endless cable-rope transmission. Each of the cables is led over an individual sheave fitted to a turntable on earth (ground, ship, float or so), from which it drives a stationary machine, like a generator or such, and cable guide rolls are provided as needed. All functions of force-transmission, consisting of energy transmission, wind-resistance and upward-floating forces and steering are performed by the turntable through the endless energy transmission cable(s), and no tethering or other force-transmitting cables are applied. In addition a loose, very low tensioned communication line for control, gas supply and the like extends from the turntable to the floating parts. Cable guide rolls are provided as needed.

Abstract: A device for securing helicopters and the like with respect to a support surface such as the deck of a ship has a pair of arresting beams adapted to be mounted on the support surface. The arresting beams are pivotally connected together for arcuate movement between spaced positions in which they define a sector-shaped target area and co-operating positions in which the beams close onto a probe depending from a helicopter to be secured. Hydraulic cylinder and ram devices are provided for moving the beams. The beams can be locked with respect to one another by, for example, a catch and keeper assembly. They can also be locked angularly with respect to a pivot axis of the arresting beams.

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 satellite retrieval system (10) wherein first and second pairs of coacting parallel bars (40), and (94) are separately mounted in spaced parallel planes on the front of a spacecraft (14). The bars of one pair are at right angles to bars of the other pair, and together the two pairs of bars effect a variable aperture adapted to close around a rod (26) extending from a second spacecraft (22) to thereby effect the capture of the latter.

Abstract: A boom formed by spring biased telescoping tubes is gimbaled at one end to a docking or probe space vehicle and at the opposite end to an electromagnet probe with the gimbaled joints spring biased to axially align the assembly. A light weight conical drogue fixed to the captive space vehicle mounts a passive iron target at the cone apex. The electromagnet guides itself into contact with the target during space coupling. The tubes telescope against springs which dampen impact along with columb dampening created by the telescoping tubes. A switch mounted to the electromagnet automatically energizes the retraction motor upon contact with the passive iron target. A retraction wire functions to initially pivot a plurality of radial rigidizing struts into contact with the circular edge of the light weight drogue cone to automatically align the spacecraft for pitch and yaw.

Abstract: An aircraft is provided utilizing a spherical balloon filled with buoyant gas such as helium at a pressure substantially greater than atmospheric so that its dimensions are substantially unaffected by changes in atmospheric pressure or temperature. The aircraft may take the form of a self-propelled and self-contained airship, or may be merely a passive device for providing lift and intended to be towed by and controlled from a helicopter. The spherical balloon is mounted on a normally horizontal axle having end portions projecting from opposite sides of the balloon, and includes a rigid load supporting yoke including two arms extending upwardly from a central load supporting structure and each with an upper end suspended from the axle.

Abstract: An aircraft weather vane and mooring device having a turntable rotatably mounted about a depending central shaft. A friction brake assembly engages the center shaft to prevent rotation of the turntable under normal wind conditions. The turntable comprises a plurality of radially extending crossarms having a low profile configuration. The crossarms are supported for rotation on ground engaging rollers at spaced-apart locations along the crossarms. Weather panels can be detachably secured between adjacent crossarm members.

Abstract: Apparatus and method for recovering and arresting an aircraft or other vele. A boom is swivelly connected to a support structure via braking mechanism. The boom is pivotally connected to the brake mechanism such that it can also pivot in a second, different plane intersecting the plane of rotation of the brake mechanism. A shear pin prevents pivoting of the boom in the second plane until the boom has experienced a predetermined load in that plane. The distal end of the boom distant from the brake mechanism is provided with structure for engaging the aircraft. When the aircraft is flown at and captured by the boom, the weight and motion of the aircraft breaks the shear pin, causing the boom to move in the second plane until engaged by a stop. This rapid change in position of the engaging end of the boom in the second plane prevents the aircraft from pendulating about the boom.

Abstract: A device for starting an aircraft engine which is capable of being started by rotating a propeller connected to the crankshaft of the engine. The device comprises an anchor device for fixedly positioning on the landing surface below the propeller; this anchor device can be held in place by a portion of the aircraft itself; in one case, the nose wheel and in another case, a separate extension arrangement. A holding device is provided for connection to the anchor device for holding the propeller and the crankshaft of the engine against rotation in a proper starting position while a rotative device is provided for connection to the anchor device for placing a biasing force on the propeller for rotating it. The anchor device has forwardly extending arms, or members, with an attaching device fixed below the propeller, the holding device and rotative device are each fixed between the propeller and the attaching device.

Abstract: An airship and a magnetically operated anchoring assembly adapted to provide rotation of the airship with respect to the ground, includes a gondola mounted to an envelope structure adapted to house lighter-than-air gas as well as any enclosures which may be used for containing the gas and a magnet device mounted to and operable from the gondola for attraction to a magnetically attractive anchoring structure secured to the ground. As preferably embodied, the magnet device is adapted to permit rotation of the gondola about the anchor point and the gondola is mounted to the envelope so as to be positionable at various desirable points under the longitudinal axis of the airship. Alternatively, the magnet may be mounted to a generally front-facing portion of the airship and the anchoring structure includes a mast with a magnetically attracting cylinder rotatably mounted to the mast at a height sufficient to enable mating with the magnet device on the airship.

Abstract: A device for rapidly securing and releasing a helicopter is provided. The vice effects positive haul down of an aircraft from a landing attitude above a landing pad aboard ship to a predetermined landing position on the pad, among other uses, through a plurality of rotatable spring-loaded over-center dogs clamped onto the free end of a haul-down cable and a sliding, cylindrical spring-loaded latching device which maintains the dogs in clamped relationship with the haul-down cable. The haul-down cable is instantly released upon freeing of the dogs.

Abstract: A method of and apparatus for anchoring an airship containing lighter-than-air gas includes positioning one or more magnets, flush with the edges of a support member attached to the airship for enabling the magnet to contact a magnetically attractive anchoring structure affixed to the ground when anchoring is desired, and, when ascent is desired, bearing against the anchoring structure with the support member to separate the magnet from the anchoring structure. The support structure may comprise a hollow shaft attached to a downwardly-facing portion of the airship, with a relatively large area base portion at its other end, having a cavity formed in the bottom of the base portion in communication with the hollow portion of the shaft. The magnet is coupled to a lifting device which bears against the top end of the shaft to control the magnet's position in the cavity.

Abstract: The present apparatus for securing a flying craft to a starting and landing rea is especially intended for helicopters. In order to secure such a flying craft with a simple, yet effective device, the starting and landing area is provided with a perforated landing platform or plate. A valve below the perforation is connected to an evacuating pump. The flying craft is provided with landing gear capable of sealing the cavity when landing and to start the evacuation pump. In this manner the flying craft is held in position by the vacuum created in the cavity in the manner of a suction cup.

Abstract: A VTOL launching and retrieval system comprising a single stud type primary landing gear and a mechanical arm equipped with a clamping device arranged to take hold of the VTOL while it is held in upright position using its own flight control system and it is either fully airborne or to some extent supported on its stud. The system allows an orderly transfer of the VTOL motion control from that by means of its flight controls to that by means of the mechanical arm which may be of flexible type, allowing to move the VTOL to stabilize in space its grasping digits or to move the VTOL from the landing site to a hangar.

Abstract: A portable tie-down device detachably mounted to a recessed anchor having a plurality of crossbars. The tie-down device includes a stationary stabilizer plate having a like plurality of depending torque lugs engaging the sides of the crossbars and a body member rotatable between two positions and having a like plurality of engaging dogs alignable with the torque lugs in one position and engageable with the anchor crossbars in the other position for detachably securing the tie-down device to the anchor. A manually operable locking bolt carried by the body member and selectively engageable with a locking groove in the stabilizer mechanically locks the rotatable body member to the stabilizer on the one position, thereby locking the tie-down device to the anchor.

Abstract: A gondola, or cabin structure, is attached to a lighter-than-air gas-containing structure by mounting apparatus enabling rotation of the longitudinal axis of the gas-containing structure through about 90.degree. with respect to the orientation of the gondola. Propulsion devices are mounted on the gas-containing structure to provide propulsion force generally parallel to the longitudinal axis of the gas-containing structure for generating forward thrust during flight and downward or upward thrust during, respectively, descent or ascent. Accordingly, the present invention embraces a method for effecting descent or ascent, which includes the steps of orienting the gas-containing structure in a generally vertical configuration and initiating downward or upward thrust.