Abstract: A vehicle refueling system includes an aero vehicle and a fuel bladder system. The fuel bladder system includes a fuel bladder, a pickup loop of a predetermined loop size, a reel mechanism to retract at least one side of the pickup loop to reduce the loop size, a snag sensor to sense when the pickup loop has been hooked by the retractable hook, the snag sensor initiating the reel mechanism, a compass to sense the random orientation of the loop, a radio navigation receiver to sense a location of the loop, and a transmitter to transmit the random orientation and the location.

Abstract: A fuel containment area, and method of forming the same are disclosed herein. A fuel containment area is defined in part by a vehicle interior structure, such as an aircraft wing. Portions of the fuel containment area are provided with elastomeric partial bladders or appliques to bridge sections of the vehicle interior structure, to provide additional container integrity, and/or to segregate fuel from certain areas of the vehicle interior, e.g., about electrical components, mechanical leakages, or high temperature areas. The appliques are sealed to the vehicle interior by flexible transition joints to define a continuous, hybrid fuel container.

Abstract: An anti-explosion protection system (10) for flammable vapors comprising a tank (12) for holding a flammable liquid (14) therein. An inflatable air bag (16) is within the tank (12) in a space above the flammable liquid (14). An assemblage (18) is for expanding and contracting the inflatable air bag (16) at the same rate as the flammable liquid (14) exits and enters the tank (12), thereby preventing the flammable vapors from forming within the space above the flammable liquid (14) which could explode and rupture the tank (12). An assembly (20) is for monitoring and visually indicating the movement of the flammable liquid (14) out of and into the tank (12).

Abstract: The invention relates to a device for suspending a helicopter tank, the tank comprising a container which possesses a top wall, a bottom wall, and side walls forming a closed volume which is designed to be placed in a compartment of the helicopter, the compartment having at least one partition adjacent to the top portion of the container. The device comprises at least one fastening made of a material that absorbs energy by plastic deformation, which fastening is fixed firstly to the partition of the compartment and secondly to one of said walls of the container so that in the event of a violent shock it limits the displacement and the acceleration of the container relative to the partition of the compartment by plastic deformation of the fastening.

Abstract: A variable displacement fuel tank for aircraft is provided. The variable displacement fuel tank may be disposed within an upper medial portion (12) of a fuselage (18) of an aircraft (10). In one embodiment, a variable displacement fuel tank (20) includes a fuel bladder (22) adapted to contain fuel and a plurality of panels (30, 34, and 36) coupled to the fuselage (18) and acting on the fuel bladder (22) to restrain and control the shape of the fuel bladder (22). The variable displacement fuel tank (20) also include a power drive system (26) that operates to move the plurality of panels (30, 34, and 36) through a continuum of positions between fully deployed and stowed in order to maintain substantially zero ullage within the fuel bladder (22).

Abstract: An expandable fuel cell (72) for an aircraft (70) has a flexible structure (126) having a perimeter (124) attached to an airframe of the aircraft (70). The flexible structure (126) has an empty position, in which the flexible structure (126) approximately conforms to a moldline (76) of the aircraft (70), and a full position, in which the flexible structure (126) forms a smooth curvilinear protrusion from the moldline (76) of the aircraft (70). A fuel bladder (152) is positioned between the flexible structure (126) and the airframe.

Abstract: The invention discloses a deployable, inflatable conformable fuel tank assembly constructed to be installed at a certain location on an aircraft and to be retained at that certain location throughout the entire flight operation of the aircraft. The fuel tank assembly is constructed to be movable between a first, deployed aerodynamic configuration in which the assembly can hold a supply of liquid fuel, and a second, stowed aerodynamic configuration in which the exterior surface of the assembly conforms to a surface of the aircraft underlying the assembly.

Abstract: A fuel tank has an outlet fuel line with a valve adjacent the tank. The valve is air operated open and spring biased toward closed. A frangible envelope surrounds the fuel tank and is pressurized from the same air line as that to the valve so loss of air pressure in the envelope leads to closing of the valve in case of a crash situation that causes the envelope to rupture.

Abstract: An engine assembly 10 includes an inner housing 12 containing an engine in an outer housing 14 disposed about the inner housing 12 and defining a sealed chamber 16 therebetween. A fuel storage bladder 20 disposed within the chamber 16 in fluid communication with the engine through the inner housing 12. The bladder 20 includes a first wall 24 and a second wall 26 and a peripheral seam for perfecting a peripheral fuel-tight seam interconnecting the first and second walls 24, 26. The walls 24, 26 are flexible for bowing away from each other to contain fuel therebetween and lie against each other upon the application of fluid pressure from a pressure source 18. Each of the walls 24, 26 have an inner surface 28, 30 facing the inner surface of the other of the walls, the inner surfaces 28, 30 having an equal surface area whereby the inner surfaces 28, 30 completely engage each other when the bladder 20 is emptied of fuel.

Abstract: A fuel tank for aircraft includes a rigid securement for securing the tank to the aircraft, a skin connected to the securement, and a liner inside the skin. The skin includes an elastic fiber and a tensile fiber embedded in a flexible matrix. In one embodiment, the elastic fiber and the tensile fiber are wound in layers within the flexible matrix, and the elastic fiber is wrapped spirally about the tensile fiber. The elastic fiber is preferably an elastomeric fiber such as an elastic, segmented polyurethane fiber. The tensile fiber is preferably an aramid polymer fiber such as an aromatic polycarbonamide fiber. The flexible matrix may be formed of natural rubber or neoprene rubber. When the tank is filled, the elastic fiber lengthens until the tensile fiber resists further stretching. The elastic fiber tends to contract as the tank is emptied, substantially reducing the storage space required by the tank. The tank is nestable when empty, but is nonetheless substantially ready to receive fuel.

Abstract: A coated fabric comprising a fabric substrate and a coating thereupon, said coating comprising a plurality of layers wherein at least one of the layers comprises a polyester polyurethane having a Shore A hardness of at least 90 durometer, or a linear polyurethane elastomer formed from a polyol; a diisocyanate compound; a first extender component having a molecular weight of below about 500; and a second extender component; wherein the diisocyanate compound is initially reacted with the first extender component in a molar ratio of above 2:1 to form a modified diisocyanate component having a functionality of about 2 prior to reaction with the other components to provide relatively low temperature processing properties to the composition. Preferably, different layers of these polyurethanes are included.

Abstract: An inflatable external fuel tank is disclosed for carrying fuel under an aircraft wing, the tank having a predetermined displacement when full and being collapsible to a lesser displacement when empty. The tank skin is comprised of a flexible thermoplastic material. A keel structure is located inside the tank and defines the diameter and longitudinal length of the tank.

Abstract: The high cost of fabrication of a turbojet propulsion system 12 for a missile having an engine 18, mounted within a casing 14, including an inlet 20 to a compressor 22 and an exhaust gas outlet 24 is avoided in a structure having a propulsion system 12 with an inlet 26, 28; 37 located forward of the engine 18 for directing free stream air to the inlet 20 of the compressor 22, an outlet 30, 33; 38, 40 located aft of the engine 18 for directing exhaust gas into the free stream air, an engine starter 42 aft of the engine outlet 24, and a fuel storing bladder 46 forward of the engine 18.

Abstract: Containers with low permeability to hydrocarbon vapors, and in particular to fuel vapors, having at least one surface coated with a p-xylylene polymer and/or its derivatives. The containers find use in the fuel industry and, in particular, in the automobile industry for the production of fuel tanks for cars, commercial vehicles, and motorcycles.

Abstract: The two-liquid propulsive system for an artificial satellite is characterized in that the components of the propellant are unequally distributed in at least two pairs of tanks (12, 16) and (14, 18) which are associated in such a way as to provide additional fuel in a first pair of tanks and additional oxidizer in a second pair of tanks, and in that the different pairs of tanks are suitable for being used in succession during predetermined time periods so that the exhaustion of a first propellant component in one tank (14 or 16) indicate that the residual normal lifetime of the satellite is at best approximately equal to said predetermined time period, and that after exhaustion of the second propellant component in the tank (16 or 14), the two tanks (12 and 18) each containing an excess quantity of one of the propellant components are associated in order to extract the satellite.

Abstract: A spacecraft propulsion system which integrates the function of the apogee kick motor (AKM) and reaction control system (RCS) is disclosed. In accordance with this invention, a pump-fed AKM is employed which results in lightweight main tanks and pressurization systems. The RCS thrusters are operated by small bellows tanks which are intermittently pressurized by a gas pressurization system to provide high pressure for operation of the RCS thrusters. The system according to this invention enables use of lighter weight main propellant tanks since they do not have to withstand high internal pressures and also enables realization of the numerous advantages of a pump-fed AKM. Several embodiments describe various methods for cycling the bellows tanks.

Abstract: A container having flexible walls. One or more layers of a high-strength load-carrying member are provided, with the member including meandering, aromatic, polyamide cords, with a cover material having a relatively slight adhesion to the cord. Where several layers of load-carrying members are provided, the meandering cords are angularly shifted so that the cords of one layer cross the cords of another layer.

Abstract: A lightweight pillow tank (10) is disclosed which includes upper and lower sections (12, 14) which are secured together along a seam (22) of predetermined width (24). A sleeve extends along a mid line of the width about the entire perimeter to the seam. Suitable holes or slits (32, 36) are formed through the outer material and the sleeve to permit a rope (34) to be threaded through portions of the sleeve to form tie-down points for the tank.

Abstract: Rapidly assembled expendable fuel tanks which provide an auxiliary source of fuel supply for aircraft and which include flexible fuel storage bladders which are housed within sectionalized tanks or pods which are designed to be manually assembled and disassembled within minutes in the field utilizing interchangeable components designed to permit maximum efficiency in ordinance supply and material handling so that a plurality of tanks may be packaged, shipped and stored with a considerable savings in space being achieved with respect to conventional rigidly constructed expendable fuel tanks. In addition, universal mounting tank ejecting strongbacks enable a variety of tank sizes and configurations to be utilized with a variety of tactical aircraft thereby standardizing assembly and mounting procedures for the auxiliary fuel tanks used with such aircraft.

Abstract: A turbojet aircraft has a fuselage pod in which all fuel is stored for engines also linked to the pod. The pod and engines can be jettisoned in flight to improve aircraft performance in the event of a forced landing. The pod carries a plurality of fuel tanks, each having a collapsible bladder formed of a layer of elastomeric material and a layer of stainless steel mesh.

Abstract: A fuel tank adapted for mounting on the exterior of an aircraft comprising a flexible fuel chamber and a plurality of flexible inflatable tubular ribs attached to the walls of the fuel chamber, with means for introducing and removing liquid from the fuel chamber and with means for inflating and deflating the inflatable ribs.

Abstract: A free drop container for liquids and especially potable liquids such as water. The container includes a molded impact resistant shell having a generally spherical shape. A port in the shell defines a hole through the shell wall, with the hole having a first diameter extending from the exterior partially through the shell wall and a second smaller diameter extending through the rest of the shell wall to the interior thereof such that the two diameters define a seat in the shell wall. A screw-in cap is removably fitted to close the first diameter hole preferably by cooperative threading with the circumferential surface of the first diameter hole. A pour spout is sized to slidably fit the second diameter hole, and can extend out from the shell for pouring when the cap is removed. A plug is removably fitted in the pour spout, and a resilient impact-resistant lining is provided that does not crack or break on impact and covers the interior of the shell for contact with potable liquids inside the shell.

Abstract: A fuel holding apparatus and method utilizes a plurality of capillaries which actually confine the fuel. The fuel holding method and apparatus can be used in vehicles and high performance aircraft to reduce the likelihood of an explosive ignition of the fuel in a crash situation.

Abstract: A main storage tank (2) is pressurized by engine bleed air. A supply tank (12) communicates with tank (2) and with an engine feed line (50). A fluid impermeable expandable wall (34) separates tank (12) into isolator chamber (38) and pressure chamber (40). A surface tension screen (44) covers inlet (42) into isolator chamber (38) to allow liquid fuel to enter chamber (38) and prevent gas from entering chamber (38). During operation of the flight vehicle, a fuel pump withdraws fuel from chamber (38). Pressure chamber (40) is vented to ambient air when the flight vehicle is under no power or is operating under g forces greater than zero, to allow wall (34) to expand and contract to compensate for changes in temperature and pressure. Chamber (40) is pressurized by engine bleed air when the vehicle is operating under zero or negative g forces.

Abstract: A turbojet aircraft has a fuselage pod in which all fuel is stored for engines also linked to the pod. The pod and engines can be jettisoned in flight to improve aircraft performance in the event of a forced landing.

Abstract: A collapsible liquid container apparatus, particularly for use with helicopters for carrying and storing fuel, has a bladder-like tank having closable ports to admit and discharge fuel. The apparatus has a frame to support the tank, and a harness cooperating with the tank and the frame to suspend the tank from the frame. Preferably, the frame has three legs and the tank is suspended between the three legs, and is restrained against excessive lateral movement relative to the frame. The harness includes a plurality of flexible tension links which extend from peripherally spaced locations on the tank. The locations are within a generally horizontal plane positioned approximately mid-way between uppermost and lowermost portions of the tank when filled to permit an upper portion of the tank to collapse inside a lower portion of the tank as the tank empties.

Abstract: An oilproof rubberized fabric is described, comprising a woven fabric as a strength member and having coated thereon an oilproof synthetic rubber, wherein simplicity of construction and ease of fabrication and symmetry of structure and physical properties on both sides of the woven fabric are attained by means of a resin having an oil-barrier property and an adhesive property applied so as to fill up interstices in the woven fabric.

Abstract: The pocket structure for a foldable wing of an aircraft, especially a high erformance aircraft, is constructed at least partially of flexible material forming a completely closed volume with an inward fold for receiving a wing portion. The fold divides the closed volume into two portions which are interconnected outside the reach of the fold to form an auxiliary fuel tank for the aircraft. The pocket structure has sealing lips extending along both of its outwardly facing side walls. The sealing lips are constructed as two bellows which are filled with a gas under pressure. Thus, the lips perform two functions. First, the lips seal a zone below the wing from a zone on top of the wing to maintain the pressure difference. Second, the lips strengthen and protect the outwardly facing side walls of the wing pocket structure forming an auxiliary fuel tank. The pocket also performs two functions, namely, the wing receiving function and the tank function.

Abstract: An improved surge dampening baffle adapted to be secured inside of collapsible liquid storage tank (pillow tank) is disclosed. The improved baffle comprises several plies of a suitable fabric. The improved baffle is flexible and collapsible; yet readily repairs and retains its shape after a distortion so as to substantially always provide alternatively disposed hollow truncated and tapered convolutions which are instantaneously available to dampen a developing surge of a liquid stored in the pillow tank.

Abstract: Disclosed is a fabrication technique for, and the structure of, a flexible self-sealing fuel tank having a preactivated sealant constructed by laying-up over an innerliner, positioned on a form, prefabricated panels having a self-sealant member stitched into a rubber-coated outer wrap.

Abstract: A flexible, fabric-reinforced, complex-shaped container comprises a fabric reinforcement material and at least one facing layer of a polymeric or elastomeric material, said fabric comprised of yarns capable of changing their effective lengths upon being shaped to a complex mold configuration and thereafter maintained in that shaped condition by curing of the composite material. The method of the invention comprises applying a differential pressure to the fabric reinforced composite in a concave mold having the desired complex configuration to move the composite into the mold cavities as the effective length of the yarns change to conform to the mold and thereafter curing of the composite so as to set the composite to the mold shape.

Abstract: Disclosed is a fabrication technique for, and the structure of, a flexible self-sealing fuel tank having a preactivated sealant constructed by laying-up over an innerliner, positioned on a form, prefabricated panels having a self-sealant member stitched into a rubber-coated outer wrap.

Abstract: A collapsible fuel tank for aircraft, the tank having rigid top and bottom elements and foldable rigid side walls containing therein a non-vented fluid-impervious elastomeric bladder. When fluid is pumped into the bladder, it distends to deploy the top, bottom, and side walls whereby a box-like structure whose rigid walls protect the bladder is erected. The withdrawal of fluid from the bladder causes it to contract such that the walls are folded and the tank thereby collapsed into a space-saving volume. The tank can be mounted on the outside surface of an aircraft and the contraction of the tank as fuel is expended effects a reduction of the aircraft frontal area to reduce drag.

Abstract: A coated fabric having a cured, synthetic elastomeric compound bonded thereto in a fashion to control the final weight and other physical and chemical properties thereof. The method comprehends the exposure of a fabric to an elastomer during its pot life to allow it to penetrate the fabric under "blotting" conditions and then quickly curing the elastomeric compound.

Abstract: An expandable fuel storage tank for aircraft has a resilient exterior wall panel in the form of a leaf spring anchored at both ends to a surface region of the aircraft, one anchorage being in the form of a simple hinge and the other incorporating a translatory device so that when the wall panel becomes bowed outwards due to the fuel storage tank being filled with fuel the ends of the panel can move relatively toward one another. The panel is formed as a spring such that when fuel is removed from the fuel storage tank, the panel tends to flatten to resume a position in general continuity with the surface region of the aircraft.

Abstract: An externally located crashworthy self-sealing fuel tank for use in combination with military aircraft is provided. The tank, having a cross-sectional shape with a substantially flat top and a shallow catenary extending below the flat top, is suspended within a hammock which is connected to the underside of the aircraft. This installation eliminates the normal surrounding structure which would tend to tumble incoming projectiles and increase the severity of tank wounds, minimizes the damaging effect of hydraulic ram upon the aircraft structure and minimizes hazards of explosions or fires by eliminating voids or cavities adjacent to the fuel tank.

Abstract: A container capable of passing the temperature requirements of U.S. Defense Department Specification MIL-T-25783 B and C (ASG) Tank, Fuel Aircraft and Missile Non-Self Sealing High Temperature Removable consisting of an inner layer of polyurethane elastomer of 2 to 30 mils adhered to at least one ply of nitrile rubber coated polyester fabric, said ply of nitrile rubber being adhered to an inner side of a barrier layer of a polyamide epoxy resin mixture and a nitrile rubber compounded with phenolic resin being used as a tie coat between the barrier and the polyester fabric.

Abstract: A method of building an elastomeric fabric container by building an innerliner on a building form, applying a solvent solution of fluorocarbon elastomer over the innerliner and laying up fabric over the cement coat while the cement is sufficiently fluid to strike through the fabric to give at least one layer of fabric covered with at least one coat of fluorocarbon elastomer and curing the elastomer to give a finished container.