Abstract: This invention relates to a pressure stabilized inflated air transport vehicle having means for limiting crack propagation in the hull envelope whereby leakage of the gas in the haul due to the crack will not exceed the gas pressure maintaining means.

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 structural panel component, such as an aircraft fuselage shell component, includes a single integral part having longitudinal and crosswise stiffening elements integrally arranged on a skin sheet. This integral component has been formed by a high speed milling chip removal process applied to a solid plate-shaped semi-finished starting material. The skin sheet has areas of differing thicknesses, and the height, thickness, and spacing of the stiffening elements varies as needed, depending on the local loading conditions that will prevail on the finished structural component. The configuration of the component can be optimized to minimize the weight while satisfying all load strength requirements. The manufacturing method is very simple and economical.

Abstract: A novel energy producing flexible material is provided particularly suited for high altitude and stratospheric applications. The flexible energy producing covering includes a flexible solar cell layer, a flexible substrate which preferably matches the shape and size of the airship gore as well and an electrically conductive conduit disposed in a flexible electrically non-conductive adhesive connecting the flexible solar cell substrate to the airship substrate. Preferably two electrically conductive conduits are provided between the substrate layer and the flexible solar cell layer with the electrically conductive conduits being insulated from one another by the non-conductive adhesive. The novel process provided by the invention for joining the airship substrate to the flexible solar cell substrate includes heat, pressure and the selection of substrate materials and in certain applications the use of a vacuum.

Abstract: A coated aerospace aluminum alloy part, such as a lipskin of a nacelle or a leading edge of a wing or tail, is disclosed which part is protected from corrosion due to severe environmental stresses, including high and low temperatures, and rain drop erosion, by a multilayer coating comprising a phosphate bonded metal containing basecoat and a resin based topcoat. A method of coating the part is disclosed.

Abstract: Vertical lift in an aircraft is produced by driving a column of air downwardly, through an annular thrust-flow channel which is formed in the body (fuselage) of the aircraft. The aircraft also has an aerodynamic shape which is capable of developing lift responsive to forward flight. The annular thrust-flow channel is provided with a flow control mechanism which is capable of directing the developed air flow in varying orientations between a substantially vertical (axial) orientation for developing stationary, vertical lift (i.e., hovering) and a vectored (angled) orientation for developing a vertical component for producing lift and a horizontal component for producing forward (or rearward) flight, or flight to either side.

Abstract: A light-weight yet sufficiently dense object made of reasonably rigid material for throwing and catching, having an elongated main body section (12) dividing congruent angled sections (20a & 20b) on either side. Each angled section containing a plurality of angles, and both section being mirror images of each other. The object (15) being of suitable size so as to be thrown and caught easily by an average human.

Abstract: A STOL aircraft has a fuselage 22 vertical 26 and horizontal 27 rear stabilizers and at least one wing made up of a lower primary airfoil 10 and an upper complementary airfoil 11 which, between them, form the inlet 12 and exhaust 14 air ducts. The craft is propelled by one or more cross flow fans 13 contained in a housing(s) 63 (FIG. 7) between the primary 10 and complementary 11 airfoils. The primary 10 and complementary 11 airfoils can be extended and flexed downwardly, by various means.

Abstract: A ducted fan 20 provides lift to a flying vehicle 10. The ducted fan includes direction control vanes (1, 2, 3, 4) for controlling torques applied to the vehicle, and also includes lift negation vanes (305, 306, 307, 308), which control the available lift. The lift negation vanes are oriented with their longitudinal axes parallel to the forward-aft axis (9) of the vehicle in order to reduce drag at high forward velocities. The thrust negation vanes include fixed (305) and movable (305M) portions, with the movable portions rotatable so as to extend into the duct airflow to cause turbulence. The direction control vanes are airfoils arranged for rotation about their quarter-chord axes (410), which reduces the amount of torque required for rotation of the direction-control vanes. This, in turn, allows stepper motors (924a) to be used to drive the vanes. The effects of forward velocity on the ducted fan also creates effects which tend to pitch the vehicle nose-down.

Abstract: The present invention discovers the layup ofi. a multimaterial fully isotropic laminate that exhibits a concomitant stiffness isotropy in extension, shear, bending, and twisting; andii. a multimaterial quasi-homogeneous anisotropic laminate that has identical stiffness anisotropy in extension and bending as well as in shear and twisting.In addition, layups of the multimaterial fully isotropic laminate lead to a substantially new category of the single-material fully isotropic laminate.Although these laminate layups have distinctive applications as load-carrying structures, the approaches and models that generate these layups are closely related.

Abstract: A vertical take-off and landing aircraft has an upwardly-open U-shaped channel extending from a front edge to a rear edge of each of two fixed wings and a thrust providing device, such as a propeller, mounted for tilting at the rear end of the channel. The thrust providing device has an inlet at which low pressure is produced by drawing in air along a path and the thrust providing device is tilted to vary the angle of the air drawing-in path relative to the wing and effect vertical take-off and landing by variably enhancing the lift of the wing.

Abstract: The present invention relates in general to aeronautical engineering and concerns specifically transport vehicles for transportation of liquid and loose cargoes. The invention provides an airborne vehicle capable of carrying a multiton cargo from a limited ground area. The object of the invention is accomplished due to the fact that in the airborne vehicle of the present invention the lifting aerodynamic airfoil system is made of two parts, that is, a stationary part in the form of a ring-shaped fuselage 1, consisting of aerodynamic members 2 and 3 curved spanwise, and a movable part in the form of lifting rotor units 6 arranged along the ring perimeter. A power unit of the vehicle comprises a gas-generator, propulsive units, ramjet ducts, and flywheel members interconnected through a reversible rotary-reciprocating engine-supercharger 22 and a fluid converter.

Abstract: The aircraft incorporates a primary and two control ducted propeller assemblies. The propellers are interconnected for rotation by a single engine. Each propeller assembly is inclined in horizontal flight and has two groups of louvers. When the groups of louvers in a propeller assembly are set to divert air horizontally in opposed directions, reduced vertical thrust is realized. In this manner, pitch and roll may be controlled in vertical flight. Vanes on the control ducts produce differential horizontal thrust to control yaw in the vertical mode. In horizontal flight, all groups of louvers are set to direct the flow aft to produce thrust for high speed forward flight.

Abstract: An airship has a carrier frame with triangular cross-ribs arranged so that an apex faces upwardly and a base faces downwardly, whereby longitudinal beams at the corners of the triangles interconnect the cross-ribs. The carrier frame is enclosed by an envelope including at least three skin segments joined to each other along seams coinciding with the longitudinal frame beams. Each skin segment extends entirely from the bow to the stern and may include several strips. At least two steering air chambers are provided, one near the bow, the other near the stern for trimming purposes. The seams or at least one of the seams, is so constructed that it is readily openable and closable for providing access to the interior of the airship.

Abstract: A high strength panel-like structure having a high strength to weight ratio. The structure comprises two integrally formed panel sections, each panel section comprising an outer sheet portion and inwardly extending ribs that are formed integrally with the related sheet portions, and having inner bonding surfaces spaced from their respective sheet portions. The two panel sections are formed into a unitary structure by bonding the two sections at the bonding surfaces of the ribs. Thus, the bonding area of the panel structure is at the neutral axis of the structure. Desirably inner bonding surfaces of the ribs have a width dimension greater than a width dimension of the ribs.

Abstract: A structurally-embedded electronics assembly is disclosed and includes an outer skin member which is lightly loaded structurally, a primary load-carrying member positioned inboard from the outer skin member, a core member positioned between the primary load-carrying member and the outer skin member, an intermediate skin member positioned between the outer skin member and the core member and an electronics structure positioned between a predetermined two of the members or intermingled with a predetermined number of the members set forth above which are adjacent each other. In another embodiment, a thermally conductive baseplate member is positioned inboard from the primary load-carrying member. In another embodiment, a vibration damping member is positioned inboard from the primary load-carrying member.

Abstract: Fluid friction of a body moving through air or water is reduced by means of a plurality of symmetrical depressions on the surface of the body. The symmetrical depressions are closely spaced but not quite abutting. The symmetrical depressions are sized in proportion to the width of the body. For a cylindrical body, each symmetrical depression is between one fiftieth and one fortieth of the diameter of the body. The symmetrical depressions are shallow, ten to twenty times wider than they are deep. The symmetrical depressions are shaped like sections of truncated cones, or hexagonal prisms, or geodesic domes. The symmetrical depressions cover virtually the entire surface of the body.

Abstract: The invention provides a double-walled, annular balloon which requires less gas to inflate than its volume would indicate. The balloon is formed of double-walled gores joined by continuous overlapping seams, in the longitudinal direction, with intermittent seams in the latitudinal direction, to divide each gore into a serious of connecting inflatable compartments. Each gore is connected to a common plenum which is connected in turn, to a compressed gas container. The gores are inflated at the same time from such common plenum and the balloon, when inflated, can appear as a globe having longitudinal and latitudinal seams therearound with the common plenum contacting the gores at proximate the north pole, thereof. Each gore terminates in a seam proximate the south pole, which seam defines a closed loop which forms an entrance port into such balloon.

Abstract: A high altitude, high pressure balloon comprised of a number of gores. The gores are made from a material and have a size, that are the results of an analysis of the anticipated stresses to which the balloon will be subjected. In particular, the gores are made from nylon and have dimensions that have been determined to result in stable creep characteristics. An alternate embodiment of the balloon uses multiple spheres.

Abstract: An all-wing aircraft is disclosed that has novel foreplane and depending aftplane, a center wing section and outer wing panel flying surfaces which cooperate aerodynamically to eliminate the need for conventional fuselage and tail structures. The foreplanes are strategically located to create a positive pitching moment which is sufficient to significantly reduce elevator forces and to balance the negative pitching moment induced by the outer wing panels and the downwardly extending aftplane units that provide static and dynamic pitch and yaw stability. At the same time, the foreplane structures serve as an unobstructed means to mount engines forward on the airframe to established a forward empty center of gravity. Additionally the aftplane structure serves as a means to mount main landing gears, elevators, ruddervators and to provide structural means for interconnecting outboard wing sections of the airplane.

Abstract: The invention relates to improvements in hot air balloons and the like. An insulation of carbonaceous fibers is provided on the interior of the balloon's envelope and/or the skirt, nozzle or scoop which is light weight and provides flame and scortch protection.

Abstract: A lighter-than-air type vehicle comprising a frame-work and a series of inflatable lift bags secured to said framework. The lift bags inwardly contain heating elements and a gas, such as hydrogen or helium, in intimate contact with the heater elements. A source of power is coupled to the heater elements is such that the supply of electrical current, for example, to said elements can be varied as to increase or decrease the degree of inflation of the respective lift bags. Propulsion structure is affixed to the framework and preferably comprises a pair of oppositely revolving propellers which are independently controlled. A shroud and interior plate-like vanes surround the propellers and are constructed and powered to vary the air stream, as to direction, coming from the propeller area.

Abstract: An improved means for convection cooling the skin surfaces of an atmospheric flight craft such as are subject to air friction-induced overheating when the craft operates at high speed, featuring employment of multiple layered, spaced apart skin members separated and relatively braced by web and post members. Fresh coolant fluid is simultaneously flushed against and contiguously covers a multiplicity of relatively small patches of the inside surface of the outer skin member to be protected, and the spent coolant from each patch is separately removed therefrom and returned to the craft's refrigeration facility. The web and post members also act to direct the pattern of coolant flow so as to provide a much improved heat transfer coefficient than can be attained by other coolant path configurations when an equal pressure drop is applied.

Abstract: A VTOL aircraft having a fuselage with fixed ring wings on either side thereof. Each ring wing has a rearwardly extending nacelle associated with it. Each nacelle has a ring tail empennage at its after end and a propulsor fan in its nose operating in the bore of its associated ring wing. The propulsor fans provide propulsion thrust for conventional flight in which the flow created over the lifitng surfaces due to forward velocity of the aircraft generates lift for flight. The propulsor fans operate to induce a flow over the lifting surfaces to generate lift for VTOL flight without a requirement for forward velocity by the aircraft. Aerodynamic control means such as spoilers are provided in the ring wings and empennages for pitch, roll, and yaw control in conventional flight.

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: A hot air balloon envelope (11) of the type having a downwardly-directed bottom opening (12) and characterized by being formed of a multiplicity of elongate gores (26) joined along adjacent sides, each of the gores being formed of a multiplicity of joined-together individual fabric panels (30). The improvement comprises at least one observation window (40) positioned in the upper hemisphere of the envelope in substitution for an envelope panel and having a size and transparency sufficient to permit an occupant of a balloon carriage (20) suspended from the envelope to look upwardly through the bottom opening and the observation window to view large objects, such as other balloons in the vicinity above the balloon envelope and not otherwise visible from the balloon carriage.

Abstract: A VTOL/STOL aircraft of simple design and construction. The aircraft has a central semi-venturi shaped airfoil surface defining a channel integral to the fuselage, a canard system and a horizontal stabilizer system at the respective ends of the channel, and a propulsion unit for accelerating airflow through the channel to achieve stable and easily maneuverable flight.

Abstract: The invention concerns a steered aerostatic balloon and in particular the creation of balloons of large volumes, which are free (airships, space balloons) or captive (material loading or unloading balloons). This balloon has an outer envelope (1) containing air, an interpolar connector (11) connecting the lower pole (2) and the upper pole (3) of this envelope, a grid of longitudinal reinforcements (8) connected to the poles (2) and (3), a grid of circumferential reinforcements (8) connected to the poles (2) and (3), a grid of circumferential reinforcements (7), at least one inside envelope (12) within the first envelope and containing helium, this latter envelope during inflation coming to rest against the outer envelope and being provided with poles fixed on the interpolar connector (11), and lastly air intake means and air evacuation means to and from the outer envelope.

Abstract: By controlling the flow of the air over an airfoil, a lifting force can be achieved even in the absence of forward motion by the aircraft. The air flowing over the airfoil is forced into a chamber by a propulsion unit and the air entrapped in the chamber can be recirculated to a forward portion of the airfoil lifting surface, thereby increasing the lifting force of the airfoil. The lifting body has side members associated with the airfoil to channel the air over the airfoil. Outlets from the chamber are provided to direct the flow of air in any lateral direction for assistance with directed motion or for assistance with aircraft stability. Additionally, outlets in the bottom of the aircraft can assist in the vertical force exerted on the aircraft by forced air escaping therefrom.

Abstract: A one-piece load line pocket (30) is disclosed for a hot air balloon (10). The load line pocket comprises an elongate fabric tape having a pair of opposing, longitudinally extending shoulders (31, 32). One of the pair of shoulders is adapted to be placed in overlapping relation, respectively, with an adjacent balloon envelope gore (24) and stitched thereto. The gores (24) are secured together in closely adjacent relation to each other but free of any direct interconnection therebetween. The tape also has a longitudinally extending, tubular pocket (34) intermediate to and integrally formed with the pair of shoulders (31, 32) for freely enclosing a load line (18) which extends from the top to the bottom of the balloon envelope (11) for supporting a balloon carriage (16).

Abstract: A wingless aircraft having a power channel with two parallel ducts afixed to the top of the fuselage. A jet engine or other drive mechanism is positioned within each duct. No air flow is permitted between any part of the lower surface of the power channel and the fuselage. Each duct contains a number of variable-pitch airfoils that are independently adjustable. This independence of adjustment between variable-pitch airfoils within a single duct and the ability to adjust the variable-pitch airfoils in one duct as a group independently of those in another duct provides horizontal stability and compensates for undesired yawing. The lift is controlled to somewhat by adjustment of the variable-pitch airfoils and the angle of attack, and to an even greater extent in cooperation with adjustable auxiliary wing panels mounted above openings in the upper surface of each duct above one of the variable-pitch airfoils. The auxiliary wing panels nest in openings above the airfoils when not in use.

Abstract: The invention concerns a spheroid container flattened at either pole. The structure is made from gores assembled along their edges. Meridional mono-directional reinforcements are fixed at intervals to the connecting lines of the gores. The gores are made of a material with a low elastic modulus and a high capacity for plastic elongation and the meridional reinforcements from a material with a high elastic modulus. An overpressure inside the structure causes it to take on the shape of a lobed spheroid, flattened at either pole. Application for closed balloons and pressurized containers.

Abstract: A stress control mechanism for a space balloon is comprised of an axial tie member extending from the upper pole of a load carrying space balloon envelope, the tie member passing from the upper pole of the space balloon envelope through the balloon to an aperture located in a slideable member attached to the lower pole of the space balloon, a stopping member positioned at a pre-selected point on the axial tie member as a member for stopping the slideable member and thereby permitting the space balloon to assume a pre-selected shape upon inflation of the space balloon.

Abstract: A balloon envelope is disclosed which has the ability to minimize and isolate destructive tears, and which comprises a latticework of interconnected vertical and lateral reinforcing tapes which form open areas therebetween, and with a fabric panel overlying and covering each open area. The fabric panels are sewn to the surrounding tapes in a manner such that there is no direct interconnection between adjacent fabric panels. The envelope is fabricated by a procedure wherein the vertical gores, which are each composed of a vertical array of the fabric panels, are initially formed by sewing adjacent side edges of adjacent panels to intermediate laterally directed tapes, and then sewing a vertical tape component along each side of the resulting array of panels. The vertical side edges of the thus formed gores are then sewn together to form a sphere-like configuration.

Abstract: A vehicle for the exploration of the atmosphere comprising an infra-red and olar montgolfier (hot-air balloon) capable of being piloted reversibly. The vehicle comprises a gas-tight envelope in which the upper part of the envelope is either transparent to or slightly absorbent of infra-red radiation, the outer face of the upper part of the envelope is slightly emissive in the infra-red region of radiation and the inner face of the upper part absorbs infra-red radiation so that ascending forces which act on the montgolfier are only obtained as a result of the heating of the gas contained in the envelope which is produced by the absorption of infra-red radiation.

Abstract: A construction of the external skin of the hull of a metal-clad airship utilizing sections of hull plating of different thickness to connect the sheets or gores of the plating of the main portion of the hull to the base skin of structural members, such as external longerons and internal frame members.

Abstract: A non-rigid aerodynamic balloon having integral stabilizing tail fins is provided. The balloon is most useful in tethered applications, such as for advertising. The balloon is formed from a plurality of flexible skin-like gores which are joined together with a plurality of longitudinal seams running lengthwise of a main body of the balloon. Each gore is a continuous piece of flexible skin-like material which forms a portion of the body and a side wall of one of the stabilizing fins. The longitudinal seams join adjacent gores along outer edges of the stabilizing fins so that seams are not required to join the stabilizing fins to the main body of the balloon.

Abstract: Lighter-than-air apparatus includes a thin, pliable air-tight outer envelope disposed in overlying relationship over a light-weight, coarse-opening inner frame of a spherelike shape. The envelope includes a sealable opening therein, so that the envelope can be at least partially evacuated to render the apparatus lighter than air. A vacuum pump is provided and is connected in fluid communication with the opening for controlling the quantity of air contained in the envelope to determine the amount of lifting energy. In one form of the invention, an outer frame is disposed within the envelope and surrounding the inner frame, and the outer frame is composed of a stiff, rigid open-mesh material with the openings in the inner frame being smaller in size than the opening in the outer frame.

Abstract: A substantially permanently buoyant balloon suitable for use as a toy or in advertising, for example, is provided which includes an envelope containing a lighter than air gas such as helium, which envelope is made from attached panels of a nonelastomeric polymer sheet material carrying a continuous metal layer on at least one side thereof. The metal layer can either be a thin metal film contiguously bonded to the polymer, or can be metal which is vapor deposited over the surface of the polymer. The balloon itself is constructed so that the ratio of its volume taken to the two-thirds power divided by its surface area is in the range of from about 0.21 to about 0.01, and the weight of the envelope can range from about 2.6 .times. 10.sup.-4 gm/cm.sup.2 to about 1.7 .times. 10.sup.-2 gm/cm.sup.2. The envelope is preferably manufactured in two dimensional "lay-flat" form in any desired two dimensional shape unlike conventional balloon envelopes which are inherently three dimensional surfaces.

Abstract: Strong, lightweight structural shapes or structures adapted for anistropic load bearing useful as structural beams or stiffeners for other structures, e.g., aircraft and which prevent or have improved resistance to forces tending to peel apart the structures, i.e., incipient peel. The shapes are fabricated from plicated laminates of strips or sheets of resinous, filament reinforced, composite materials having high strength and low weight. Fabrication of the shapes is carried out in such manner that upon curing of the resin the resultant stiffener shapes are capable of distributing loading forces so as to reduce localization of stresses.

Abstract: Strong, lightweight structural shapes or structures adapted for anistropic load bearing useful as structural beams or stiffeners for other structures, e.g., aircraft and which prevent or have improved resistance to forces tending to peel apart the structures, i.e., incipient peel. The shapes are fabricated from plicated laminates of strips or sheets of resinous, filament reinforced, composite materials having high strength and low weight. Fabrication of the shapes is carried out in such manner that upon curing of the resin the resultant stiffener shapes are capable of distributing loading forces so as to reduce localization of stresses.

Abstract: An improved lighter-than-air article is provided. The improvement is a covering which consists essentially of a triaxial fabric having a gas impermeable polymeric film firmly adhered to one surface and a heat-sealable polymeric film firmly adhered to the other surface.

Abstract: A method of finishing cloth-covered aircraft wings and fuselage. The cloth, cotton or polyester cloth of the type made from monofilaments of the condensation product of ethylene glycol with terephthalic acid or dimethyl phthalate is, after application thereof onto the airframe, coated with a layer of latex and dried, then coated with a second, or intermediate, layer of different coating and dried, and then coated with a decorative coating material. The use of latex as a first coat on the cloth results in substantial savings in labor and time and results in a coated fabric of superior flexibility integrity and durability.