Abstract: A system enabling safe manned and unmanned operations at extremely high altitudes (above 70,000 feet). The system utilizes a balloon launch system and parachute and/or parafoil recovery.

Abstract: Aspects of the disclosure provide anti-tilt assemblies for reducing the strain of an air ballast when used to change the direction of a high altitude balloon. For instance, in one example, a balloon includes a balloon envelope having an air ballast and a plurality of support tendons and a payload assembly. The balloon also includes an anti-tilt assembly arranged between the balloon envelope and the payload assembly. The anti-tilt assembly includes a support structure having a plurality of line connections arranged at a top end of the support structure and a connection member at a bottom end of the support structure. The connection member is attached to the payload assembly. The anti-tilt assembly also includes a plurality of support lines connected at to one of the support tendons and to the connection member. In addition, each support line is arranged to pass through a corresponding one of the line connections.

Abstract: A shock-resistant memory device comprises a housing and a memory module. The memory module is disposed within the housing and surrounded by potting material to protect the memory module from damage during a shock event. The housing can include a port that accommodates a data connection between the memory module and a sensor from which data is desirably received by the memory module. During a shock event the connection between the memory module and the sensor may be severed, but data stored in the memory module can be retained in the memory module which is protected by the housing. To facilitate retrieval of the memory device subsequent to a shock event, a balloon can be affixed to the housing. The balloon can be configured to inflate subsequent to the shock event so that the shock-resistant memory device does not sink in water and to make the memory device more visible for recovery.

Abstract: Aspects of the disclosure relate to manufacturing balloon envelopes for use in high-altitude mesh networks for packet-data communications. As an example, a gore portion may be placed on a table such that the gore portion overlies a groove within the table. A tendon may be placed on the gore portion and within the groove. A portion of tubing may be placed over the tendon. The tubing may have one or more surface openings. Restraining tape is applied over the one or more surface openings in the tubing. A constant force roller is applied to secure the tendon to the gore portion and to secure the tendon to the tubing. As an alternative or in addition to the surface openings, double-sided restraining tape may be placed between the tendon and the tubing. The tubing and restraining tape may prevent undesired lateral and longitudinal movement of the tendon during deployment.

Abstract: Systems, methods, and devices are provided that combine an advance vehicle configuration, such as an advanced aircraft configuration, with the infusion of electric propulsion, thereby enabling a four times increase in range and endurance while maintaining a full vertical takeoff and landing (“VTOL”) and hover capability for the vehicle. Embodiments may provide vehicles with both VTOL and cruise efficient capabilities without the use of ground infrastructure. An embodiment vehicle may comprise a wing configured to tilt through a range of motion, a first series of electric motors coupled to the wing and each configured to drive an associated wing propeller, a tail configured to tilt through the range of motion, a second series of electric motors coupled to the tail and each configured to drive an associated tail propeller, and an electric propulsion system connected to the first series of electric motors and the second series of electric motors.

Abstract: A system enabling safe manned and unmanned operations at extremely high altitudes (above 70,000 feet). The system utilizes a balloon launch system and parachute and/or parafoil recovery.

Abstract: Aspects of the disclosure relate to techniques for manufacturing a balloon envelope including a duct for high altitude balloons. In one example, a first sheet of material may be provided. A premade duct may be arranged at least partially on the first sheet of material. The duct may include a first substance on an internal surface. A second sheet of material may be arranged over at least a portion of the duct. A heat sealing device may be applied to the second sheet of material to heat seal the first sheet of material to the second sheet of material. The heat sealing device may be applied over at least a portion of the duct in order to seal external surfaces of the duct to each of the first and second sheets of material and form a balloon gore. The first substance may keep the duct from being sealed to itself.

Abstract: An aerial balloon system comprising a payload platform suspended from an inflated balloon by means of a balloon cable, and an anchoring cable attaching the platform to an anchor point beneath it. The balloon cable and anchoring cable are attached to the payload platform by means of a connecting element pivotally attached to the platform. The platform may include a servo controlled pitch stabilizing system using the input from a pitch sensor mounted on the platform to control an angular actuator to change the angle which the platform makes with the pivoted connection element. Additionally, the platform may include a servo controlled orientation stabilizing system using the input from an orientation sensor mounted thereon to control the departure of the orientation of the platform from a predetermined orientation. This may be readily accomplished using a variable pitch rotor, the pitch being controlled by the orientation sensor signal.

Abstract: An inflatable structure mount is used for mounting a device to an inflatable structure. An example is mounting of radar panels to an inflatable structure within an airship. The mount includes the device, and inserts coupled to the back side of the device, which mechanically couple to flexures mounted on the inflatable structure. Some of the flexures may have slotted holes, used in positioning the inserts on the inflatable structure at positions that will allow the flexures to mate with the inserts. A jig or tool may be used as part of the installation process, to locate the flexures at points where they will properly engage the inserts. The flexures may also each face a center point that is underneath the device to be mounted. The flexures may engage the inserts in ways that allow for quick installation and de-installation of devices, and may allow for visual inspection of proper installation.

Abstract: The present disclosure provides a balloon. The balloon may include an envelope comprising a fixed component. The balloon may include a stabilizing platform positioned beneath the envelope and operatively connected to the fixed component. The stabilizing platform may be configured to rotate around an axis vertically aligned with gravity. The envelope may comprise a heavier mass than the stabilizing platform. The balloon may also include a motor configured to exert a first force on the stabilizing platform in a manner such that the stabilizing platform rotates (i) more than a rotation of the balloon and (ii) around the axis, thereby counteracting the rotation of the balloon by causing the stabilizing platform to exert a second force on the envelope of the balloon.

Abstract: Methods and apparatus are disclosed for an apex fitting for securing to a high altitude balloon. An example apparatus involves: (a) a base plate defining an opening, where the base plate is configured to be securable to an exterior of a balloon envelope, (b) at least one stud coupled to the base plate and configured to be securable to a tendon, (c) a retention ring defining at least one opening configured to receive the at least one stud, (d) a fill-port body defining a cavity, wherein a flange is coupled to the fill-port body, wherein the fill-port body is arranged coaxially with and extends through the opening of the base plate such that the flange lies adjacent to the bottom surface of the base plate, and (e) a locking body coupled to the fill-port body, wherein the locking body defines an opening arranged coaxially with the fill-port body.

Abstract: The invention relates to a method for handling at least one wind turbine generator component 104, 106, 108. The method comprises the steps of loading said at least one wind turbine generator component 104, 106, 108 to an airship 100 at a site of loading, transporting the airship 100 with the at least one wind turbine generator component from the site of loading of the at least one wind turbine generator component to the site of installation of the at least one wind turbine component, and unloading said at least one wind turbine generator component from the airship at the site of unloading by means one or more guide elements 150 extending between the at least one wind turbine generator component and another wind turbine generator component or the ground, the sea, a vehicle at the ground, or at a vessel at the sea. The invention also relates to use of an airship for installing wind turbine generator components.

Abstract: A module in the form of a pallet or a closed container includes a grouping together of the electrical devices in an avionics bay, in which the electrical devices are interconnected and attached so as to facilitate the mounting and thus limit the time it takes to mount the electrical devices in the avionics bay.

Abstract: A flying air purifier includes a flying unit configured to fly within a space at a first elevation. The flying unit is also configured to fly within the space at a second elevation. The flying air purifier also includes an air purifier mounted to the flying unit and configured to remove particles from air within the space at the first elevation and at the second elevation. The air purifier includes an air inlet having a first charge and an air outlet having a second charge, wherein the second charge is opposite of the first charge.

Abstract: A method of determining the locations of loads in a vehicle in such a manner as to ensure mission safety in terms of loads being retained in the aircraft. On the basis of vehicle parameters, the anchor points available in this type of vehicle for retaining the loads are identified. As a function of the available loading volume(s), a possible loading configuration is calculated using at least some of the available anchor points, at least some of the retaining means, and the characteristics of the loads. The forces that might be exerted on the selected anchor points are verified as being less than maximum limits. The calculated loading configuration is confirmed, otherwise a new loading configuration is calculated.

Abstract: A part of composite material having a wedge between two zones, the second zone being shorter than the first zone, whose structure includes from its outer surface to its inner surface: a first section formed from at least two continuous sheets extending parallel to its outer surface, the gradient of the wedge being between 20% and 50%; a wedge in the shape of a triangular prism with its larger surface dimensioned in such a way that it forms a wedge having a gradient of less than 20%; a second section formed by a plurality of continuous sheets extending parallel to the surface bounded by the first section with the wedge placed upon it. The invention also relates to a process for manufacture of the part.

Abstract: The technology described herein provides for the creation of an atmospherically-lifted multi-tethered structure in a semi-stationary position in the atmosphere, which supports cabled cargo handling operations within the three-dimensional space beneath the structure, allowing cargo loads to move directly from source to destination in that same space (between the ground and the atmospherically-suspended structure itself). The design combines a highly configurable aerial platform with the usefulness of complex cargo transportation systems to enable transit both at high speeds over long distances, and at low speeds on the localized level. Constant atmospheric lift from buoyancy and wind effects allows for a flexible transportation infrastructure over a broad three-dimensional area.

Abstract: The invention relates to a method for handling at least one wind turbine generator component 104, 106, 108. The method comprises the steps of loading said at least one wind turbine generator component 104, 106, 108 to an airship 100 at a site of loading, transporting the airship 100 with the at least one wind turbine generator component from the site of loading of the at least one wind turbine generator component to the site of installation of the at least one wind turbine component, and unloading said at least one wind turbine generator component from the airship at the site of unloading by means one or more guide elements 150 extending between the at least one wind turbine generator component and another wind turbine generator component or the ground, the sea, a vehicle at the ground, or at a vessel at the sea. The invention also relates to use of an airship for installing wind turbine generator components.

Abstract: The invention relates to a method for positioning an airship 100 at a wind turbine generator. The method comprises the step of docking the airship 100 at the wind turbine generator with a forwards docking section, a rearwards docking section, a sideways docking section, or an upwards docking section of the airship being connected to the wind turbine generator. After the airship 100 has docked, at least one wind turbine generator component or at least one person is unloaded from the airship or loaded from the wind turbine generator to the airship. Docking of the airship 100 may be performed at one of the following components of the wind turbine generator: the nacelle 116, the hub 118, the tower, one or more of the blades 120, the foundation, or a substation of the wind turbine generator. The invention also relates to use of an airship 100 for being connected to a wind turbine generator and for loading or unloading wind turbine generator components or personnel to or from the wind turbine generator.

Abstract: An airship includes a substantially rigid keel with a balloon suspended from a fore of the keel and a balloon suspended from the aft of the keel. Motor booms extend laterally from the keel between the fore and the aft. Motors with propellers thereon are coupled to the end of each motor boom. The balloons are preferably coupled to the keel through cradles which support portions of the balloon above the keel and restrain the balloons to pivoting motion in a fore and aft pitching direction. A deployment system is disclosed including filing of the balloons within balloon deployment bags on the ground, and then opening the bags at time of launch. The keel and other structural elements can be in the form of a truss, rigid hollow cylindrical tubes, or air beams and stressed skin sheets, or combinations thereof. The airship achieves high altitude controlled flight above the stratosphere.

Abstract: Disclosed is a system for generating power from sunlight collected substantially above the earth's surface, comprised of an airborne platform which supports an apparatus to collect sunlight, an apparatus to convert sunlight to electricity, and an apparatus to transmit the electricity to a selected location on the earth's surface. The invention collects solar energy above the clouds and transmits the energy to a receiving station on the ground via a cable, thereby avoiding the attenuating effects of clouds and pollution, resulting in an improved solar power generation system.

Abstract: A system for generating power from sunlight collected substantially above the earth's surface comprises an airborne platform which supports an apparatus to collect sunlight, an apparatus to convert sunlight to electricity, and an apparatus to transmit the electricity to a selected location on the earth's surface. The airborne platform collects solar energy above the clouds and transmits the energy to a receiving station on the ground via a microwave transmission system, avoiding possible attenuating effects of clouds and pollution.

Abstract: A system for generating power from sunlight collected substantially above the earth's surface comprises an airborne platform which supports solar power generation system to collect sunlight, convert the sunlight to electricity, and to transmit the electricity to a selected location on the earth's surface. The solar power generation system is coupled to the airborne platform by a support which can be manipulated by a control system to move the solar power generation system away from a shadow that might be cast by the airborne platform.

Abstract: A non-permanent system for the unloading and loading of ocean-going cargo vessels is described using a cargo transfer system which is supported by dirigibles or airships. The cargo transfer system is comprised of a moving transfer cable, a cargo lifting device and a cargo staging device. The system is used to transfer cargo between at least one sea terminus and at least one land terminus. Cargo is moved along the transfer cable from one terminus to another by means of dirigibles or airships. The sea-terminus of the system may be a floating temporary dock or a large ocean vessel such as an aircraft carrier. The system can be developed so that it is fully transportable and can be assembled and launched from a large ship, as well as recovered for movement to another location. The system may also be used at inland ports. The system can be sized to the port requirements using one transfer system or multiple systems.

Abstract: A load patch for attaching concentrated loads to a flexible inflated structure such as a high-altitude airship is stiff in the direction of the applied load so as to carry the load, and is attached to the inflated structure for a very short distance through T-tape so as to minimize strain concentration in the inflated structure due to the stretching of the inflated structure. Since the load patch must be attached for a long length transverse to the load to distribute the applied load, it is transversely compliant to minimize strain concentration in the inflated structure due to stretching of the inflated structure.

Abstract: A propulsion assembly for attachment to the enclosing material of an airship which includes a base which is positioned proximate to the enclosing material. An extension member having opposed ends projects away from the base and includes opposed ends. A motor assembly is attached to the end of the extension member opposed to the base. A mounting assembly is attached to the enclosing material and a plurality of pre-tensioned guy cables connect the mounting assembly to the extension member.

Abstract: A system is disclosed for lifting a rocket into the upper atmosphere and establishing forward flight at several hundred miles per hour, before the rocket engines are ignited and the rocket is released from the lifting system. The main subassemblies of this lifting system comprise: (1) an array of large helium-filled dirigibles, of a size that can provide hundreds or thousands of tons of lifting force; (2) a tank-holding assembly that will be tethered to the dirigibles, and that will contain pumps and high-pressure tanks, to recapture and store the helium for use in subsequent launches; and, (3) a winged platform, with wings that can be rotated vertically during liftoff, and horizontally to establish forward flight after a desired altitude has been reached, and having conventional aircraft engines on each wing. This system enables safer, less expensive, and more efficient launching of rockets and heavy payloads into space, using easily reusable subassemblies.

Abstract: A method for applying pressure to the area of a composite part masked by a secondary feature comprises the steps of positioning a pressure augmentation strip in contact with the masked area, securing a pressure transfer wedge on each of two sides of the secondary feature, such that pressure is transferred to the pressure augmentation strip during co-curing/co-bonding, and co-curing/co-bonding the composite part and the secondary feature. When the area between the composite part and the secondary feature is fairly large, the method can comprise the further steps of positioning a sine wave spring between the pressure augmentation strip and the secondary feature, injecting a structural paste adhesive into the voids around the sine wave spring, and curing the structural paste.

Abstract: An aircraft advertising system comprises an aircraft. The aircraft is generally very long with respect to its width and height. A support beam is provided. The support beam has a coupling end and a free end. The coupling end has a pivot pin. In this manner the collapse of the beam is allowed for take off and landing of the aircraft. Also provided is a sign of a durable fabric material. The sign is adapted to display indicia. The sign has a top edge, a bottom edge, a front edge, a rear edge and a pair of faces on either side. The top edge is coupled to the bottom portion of the body of the aircraft. The front edge is coupled to the support beam.

Abstract: A high-altitude airship has a non-rigid hull. On launch, the airship is partially inflated with a lifting gas. The partially inflated hull is less susceptible to buffeting and turbulence from lower atmosphere air currents during ascent. A ballast rotates the airship into a flight attitude (e.g., near horizontal) upon reaching a desired altitude. A low-powered propulsion system may be included to propel the airship at the desired altitude. Upon completion of its mission, the airship may be deflated and returned using aerodynamic deceleration such as a parachute, a parafoil and a ballute.

Abstract: An airship (1) comprising gas envelope means for providing in use a hull (2) with a generally longitudinally extending longitudinal axis (20) and solar cell array means (3) arranged in use to be mounted on the outside of the hull (2). The solar array means (3) are arranged in use to extend around only a part of the circumference of the hull (2) and are turned about the longitudinal hull axis (20) to control the amount of incident solar radiation collected by the solar cell array means (3).

Abstract: The invention concerns a launch vehicle comprising a shroud (1a, 5a) supporting auxiliary propellers (2, 3) applying in operation excess flow of stresses to the shroud (1a, 5a), said device comprising means for coupling the payload (4) with the launch vehicle shroud. The invention is characterized in that the coupling means are designed to ensure a mechanical coupling between the payload (4) and the shroud along the direction of the launch vehicle longitudinal axis (X), and to cause them to be disengaged along radial and tangential directions. The invention is useful for neutralizing the effects on the payload of excess stresses applied on the launch vehicle shroud by the auxiliary propellers (2, 3).

Abstract: A support assembly is provided for selectively supporting an aircraft engine cowling on an aircraft, the latch assembly including a cowling support mounted to the cowling, an aircraft support mounted to the aircraft frame; and a latching member. The latching member is moveable between a first position, in which it substantially fixes the cowling support to the aircraft support, and a second position, in which it permits the cowling support to move relative to the aircraft support. The support assembly also variably mounts the engine cowling to the aircraft mount such the support assembly substantially isolates the first support mount from a transfer of cowling weight from the second support mount in an ‘open’ condition, and permits a transfer of cowling weight from the second support mount to the first support mount in a ‘closed’ condition.

Abstract: A passenger airplane container system comprises a pod. The pod has a hollow generally cylindrical configuration. The pod further has a horizontal divider. The horizontal divider separates the pod into a passenger area and a baggage area. An airplane is provided. The airplane has a central pod receiving region with a closure device. The closure device is movable between an open orientation and a closed orientation. The open orientation so allows for the movement of a pod into the receiving region. The closed orientation securely encompasses the pod. In this manner the pod is securely contained for takeoff and flight and landing.

Abstract: A stratospheric airship capable of substantially and smoothly varying the volume of a buoyant gas is provided so as to allow the airship to stably ascend into the stratosphere and keep a station therein. A stratospheric airship includes a gas envelope defined by a ship hull, the gas envelope being divided by a diaphragm into a buoyant gas compartment containing a buoyant gas and an air compartment containing air, the stratospheric airship being allowed to ascend by varying the volume ratio between the buoyant gas and the air, wherein the periphery of the diaphragm is coupled to the ship hull generally at the midpoint along the vertical dimension thereof, and a central portion of the diaphragm is coupled to a suspension chord whose upper and lower ends are coupled respectively to the upper and lower surfaces of the ship hull. The sloshing phenomenon of the diaphragm is suppressed, whereby the change in the shape thereof is balanced, and thus there is no asymmetric distribution of the buoyant gas.

Abstract: The present invention describes a dual suspension catenary system which includes aspects of both an internal catenary system and an external catenary system. The dual suspension catenary system of the present invention retains and expands upon the advantages of the internal and external catenary systems, such as larger payload suspension and envelope integrity while decreasing the disadvantages (e.g., envelope breach and aesthetics).

Abstract: A method for the exact setting down or taking up of cargo from aircraft is disclosed. When setting down persons or cargo from aircraft which has not landed, the problem arises of an exact setting down not being possible, or only with great difficulty, in particular under adverse weather conditions. The invention provides a method whereby exact and even “spot-on” setting down or taking up of a load is made possible, even if the ambient conditions do not allow the aircraft to be kept steady. With the spatial framework of ropes biased by the aircraft, the position of the load in space is clearly fixed. The load can thus be exactly lowered down to the ground or taken up from the ground, without it being necessary for the aircraft to be still. Here, the aircraft itself is located at an appropriately selected distance above the load. The invention can also be applied to transportation by airships to construction sites, to catastrophe regions, etc.

Abstract: The invention is an attachment fitting for use on the flexible wall of a structure. In detail, the fitting includes a slot in the wall of the structure. A first flexible member is included having a center portion folded over its self forming a loop extending through the slot from a first side of the wall and out from the second side, and outer fan shaped portions on each end of the center portion bonded to the first side of the wall of the structure adjacent to the slot. The first flexible member further includes a plurality unidirectional reinforcing filaments in a matrix material with the filaments being parallel to each other in the center portion and fanning out from each other in each of the outer portions. A second flexible member having a periphery extending about the slot and the outer portions of the first flexible member is bonded thereto and to the first side of the flexible wall of the structure.

Abstract: The invention concerns a fastening arrangement between the hose-like neck (11) of a sonde balloon (10) and the closing piece or valve piece (13) of the balloon. The closing piece or valve piece (13) can be fitted inside the hose-like neck (11) of the sonde balloon (10) as gas-tight. The fastening arrangement comprises a fastening ring (12), which can be fitted onto the free mouth part of the neck (11) of the sonde balloon. Hereupon, the outer end (11a) of the mouth part of the neck (11) can be folded outside and over the fastening ring (12) onto the neck part (11) placed on the cylinder part (13b) of the closing or valve piece (13), the neck (11) thereby becoming two-fold. The inner diameter (D.sub.1) of the fastening ring (12) has been dimensioned smaller than the diameter (D.sub.2) of the cylinder part (13b) of the closing or valve piece (13).

Abstract: A non-rigid airship is provided which includes a gas envelope having propulsion units mounted on either side thereof. Thrust emanating from the propulsion units is deflectable to control at least the vertical positioning of the airship. Horizontal positioning of the airship may be controlled by varying the relative thrust of the propulsion units. A method is also provided for controlling the flight path of an airship. The method includes providing propulsion units on opposite sides of the airship and deflecting the thrust of the propulsion units to control vertical placement of the airship. Horizontal placement of the airship may be carried out by varying the relative thrust of the propulsion units.

Abstract: An airship is described that shows a central rigid frame, extending the length of the airship, about which are arranged at least three equally spaced gas envelopes containing a lifting gas. Propulsion units are located at each end of the central frame and are controllably moved in different directions to control the airship. Also included on the airship is a hot air envelope above the lifting gas envelopes and provided with pivoting masts to increase and decrease the size of the hot air envelope.

Abstract: A rescue balloon for rescuing individuals from high places such as towers and building includes an enclosed envelope for holding heated air under substantially greater than atmospheric pressure with a burner contained within the enclosed envelope for burning a combustible gas to generate sufficient heated air under pressure in the envelope to provide lift to the balloon. A rescue compartment is carried by the envelope for accommodating rescued individuals and a tether is provided for guiding the balloon as necessary to effect rescues. The balloon includes a porous blast shield positioned within the envelope to prevent direct contact between the envelope and the flame of the burner. The blast shield comprises an upright cylinder supported and secured in fixed relation within the envelope by a plurality of catenaries attached to the blast shield and to the inner walls of the envelope around its perimeter. The burn super-pressurizes the heated air within the envelope.

Abstract: A lighter-than-air aircraft includes a rigid platform having cargo and passenger compartments and gas bags attached to the platform for holding a gas having a density less than air, thus imparting lift to the platform. The bags are arranged in pairs, there being a pair of spaced apart upper bags along the upper surface of the platform and a pair of spaced apart lower bags along the lower surface. While the bags cover portions of the upper and lower surfaces, both surfaces remain exposed along the longitudinal centerline of the platform, and here the platform is provided with vertical ducts and bays. The ducts house motors and propellers which drive air through the ducts and thus impart a vertically directed force to the platform. The bays hold containers which are lowered from and raised into the bays with a crane that moves along tracks extended along the upper surface of the platform.

Abstract: A rescue balloon for rescuing individuals from high places such as towers and buildings includes an enclosed envelope for holding heated air under substantially greater than atmospheric pressure with a burner contained within the enclosed envelope for burning a combustible gas to generate sufficient heated air under pressure in the envelope to provide lift to the balloon. A rescue compartment is carried by the envelope for accommodating rescued individuals and a tether is provided for guiding the balloon as necessary to effect rescues. The balloon includes a porous blast shield positioned within the envelope to prevent direct contact between the envelope and the flame of the burner. The blast shield comprises an upright cylinder supported and secured in fixed relation within the envelope by a plurality of catenaries attached to the blast shield and to the inner walls of the envelope around its perimeter. The burn super-pressurizes the heated air within the envelope.

Abstract: A process and an apparatus for hooking of a band of a flexible material, intended to be subjected to tensile forces, to a fixation piece, for hooking onto the fixation piece of an envelope of which the end portion is divided along a given length, into a plurality of bands of equal width, the process comprising longitudinally folding one extremity of the band upon itself, at least one time, in such a manner as to form at least one hem (14, 15), transversely gathering the hem in accordian fashion in such a manner as to form a flange presenting a fan-shaped configuration, using a fixation piece provided with a groove of a wedge-shape conjugate to the shape of the flange, the groove having a longitudinal extremity opening toward its apex, and arranging the flange within the groove, the band extending through the open extremity of the groove in such a manner as to create a self-locking of the flange when the band is placed in tension.

Abstract: A suspension cable for connecting together the carriage support ropes and the envelope load cords of a hot air balloon in the area of the burner assembly. The suspension cable comprises a non-electrically conductive material having a destruct point sufficiently high to avoid damage from the accidental exposure to the flame of the burner and a tensil strength sufficient to support the balloon carriage. The suspension cable is braided and the non-conductive material comprises an aramid fiber core. The suspension cable includes a non-electrically conductive sheath surrounding the core which will destruct if accidentally exposed to the flame of the burner in order to give an indication that the suspension cable should be inspected.

Abstract: A device for coupling a flexible envelope (1) to an external element including a ballonet (3) with two fasteners (4, 5) located in such a manner as to define the upper and lower poles of said ballonet, one of the fasteners (5) being linked by coupling members (2, 16) fitted to position the ballonet with respect to the envelope (1) in such a manner as to create a contact surface Z1 between said ballonet and the envelope (1), the second fastener (4) being linked to the external element by link means (8-15) including drive means to set the ballonet (3) in rotation; this device makes it possible to transmit large point forces or torques between an external element and an envelope, especially a space-balloon envelope.

Abstract: An airborne missile launcher is provided which is of modular construction to carry a variety of different missiles. A main body section has top attachment points, whereby it is carried by an aircraft, and sub-rail hangers at its underside to receive alternative missile-carrying sub-rails each of which sub-rails has one or more longitudinal tracks for carrying one or more types of missile. The sub-rail may be mounted in telescopically sliding relationship with the main body section. To complete the launcher body, forward and aft body sections are attached to the main body section, each of the forward and aft body sections being selected from a number of different such sections to suit different types of missile. For certain missile types, the forward and aft sections may be simply a plastics fairing; for certain other missile types, the forward and aft section may house a missile umbilical retraction mechanism and other operative means.

Abstract: A gondola for a hot air balloon utilizes a rigid carriage with external and internal walls forming an enclosure with a central opening sized for accommodation of crew members. A platform extends across and closes a bottom of the central opening. The external and internal walls are spaced and form an internal and integral reservoir for the carriage for storage of fuel for powering the hot air balloon. In one embodiment, a crew module accompanies the carriage, and the carriage is arranged for jetisoning in emergencies.

Abstract: An airship 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 spherical balloon is rotatably 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. The yoke arms carry engines which propel the airship in a forward direction transverse to the axle, and means are provided for rotating the balloon about the axle so that the balloon front surface moves upward relative to the centre of the balloon and provides lift due to the Magnus effect.