Abstract: A drogue assembly (10) for in flight refueling includes a circumferenal array of triangular support arms which carry a drogue parachute (29) which extends circumferentially around their shorter sides. Each support arm is pivoted and mounted on a pivot pin (19) at its apex for pivotal movement in a radial direction. At least alternate ones of the support arms carry leaf springs which extend into pockets (51) formed in the drogue parachute (29). The leaf springs act on the drogue parachute (29) in opposition to air pressure loading on it in flight so that it tends to increase the chord angle of the drogue parachute (29) from the leading edge. Hence the effective area of the drogue parachute in flight is varied automatically above a certain predetermined minimum which depends on the dimensions of the trailing edge so it is reduced as air speed is increased and vice versa.

Abstract: A drogue assembly comprises a circumferential array of triangular support arms. Each support arm is pivoted and mounted on a pivot pin at its apex for swinging movement in a radial direction. Each juxtaposed pair of support arms is joined together by a net which is joined to each of those support arms at spaced intervals therealong. The support arms carry a drogue parachute which extends circumferentially around their shortest sides.

Abstract: A mid-air transshipment system wherein a cargo carrying, pallet/airfoil is towed by a supply plane. The pallet is roofed by a bi-wing mounted on shock absorbers within its cavity. It trails a cable and a drogue which is speared by the probe of a pursuing aircraft. In coordination with is supply plane the receiving aircraft maneuvers the pallet towards a wing pylon or an internal cargo bay. The attachment method includes winching the pallet up against the aircraft's deployed landing gear. Once secured, zippered seams in the pallet's walls allow the aircraft to disencumber itself of unessential pallet elements.

Abstract: An aerial refueling system includes a pod assembly which is removably mounted for translation on an elongated pylon secured to the underside of an aircraft fuselage, whereby the pod assembly is moved relatively forward on the fuselage for stowage and relatively aftward on the fuselage for refueling operations. The pod assembly includes a pivotable, telescoping boom having control surfaces by which to aerodynamically position the boom's free end relative to the pod assembly. A coupling preferably establishes fluid communication between the boom and a fuel tank within the aircraft fuselage only when the pod assembly assumes the relatively-aftward refueling position on the pylon. A ram-air turbine on the forward end of the pod assembly provides all necessary power for the pod assembly, with wireless remote operation of all pod assembly functions preferably used to minimize the extent of alterations when installing the aerial refueling system on the aircraft.

Abstract: An apparatus attached to a fuel hose and deployed rearwardly of a tanker craft, the apparatus for inflight refueling of an aircraft and includes a fuel valve for controlling the flow of fuel through the valve, a coupler attached to the fuel valve for receiving and locking onto the probe of a receiving aircraft and for conveying fuel through the coupler and to the probe of the receiving aircraft, and a plurality of struts attached to the coupler, the struts configured and arranged to compress inwardly when acted upon by sufficient compressive forces and to expand outwardly against aerodynamic forces when located in the airstream, the struts forming a bell shaped target for guiding the probe of the receiving aircraft into the coupler.

Abstract: A pre-conditioned air connection ring designed to adapt the PCA connection port of an Airbus aircraft to the configuration which is standard in the industry. The connection ring includes a plurality of projections and slots which allow a standard pre-conditioned air adapter chute to be fitted onto an Airbus PCA connection port.

Abstract: An apparatus and method for aerial refueling of an unmanned aerial vehicle (UAV) wherein a laser receiver/transmitter on a target device towed by a host aircraft projects a reticle pattern aft of the host aircraft and a laser receiver/transmitter on a probe of the UAV is activated as the UAV is moved within the projected reticle pattern. Thereafter, a rangefinder guides the UAV towards the host aircraft until the laser transmitter/receiver of the UAV is aligned and boresighted with the laser transmitter/receiver of the host aircraft at which time the mode of the laser transmitter/receiver of the UAV alternates between a rangefinder mode and a modulation data link mode to transmit vital information concerning the UAV to the host aircraft. The probe on the UAV continues to move toward the drogue until the probe establishes contact within a receptacle structure of the drogue and is coupled thereto.

Abstract: A method and apparatus for generating visual information for an operator in a first aircraft and a pilot in a second aircraft regarding the second aircraft's position relative to a first aircraft. A 3-D camera system (72) generates a real time 3-D video image of the second aircraft. A selecting device (82) provides selection of a stored geometric model based on the second aircraft type. A display monitor (83) displays the generated real time 3-D video image and the selected geometric model. A matching device (84) matches the displayed geometric model to the displayed real time 3-D video image. A processor (84) determines the position of the second aircraft relative to stored zone information according to the matched geometric model and generates control signals according to the determined second aircraft position. Director lights (88) mounted on the outside of the first aircraft display position information visible to the pilot of the second aircraft according to the generated control signals.

Abstract: A refueling tank has a telescopic refueling probe formed by a plurality of telescoping tubes which are actuable for extension and retraction from an existing pylon mounted jettisonable external fuel tank on the wing of an aircraft. The telescopic drive action is achieved by a drive mechanism including a motor and a jack screw mechanism which operates to extend and retract the telescoping tubes slidably mounted, one on the other. The probe when fully retracted is completely enclosed within the associated fuel tank assembly resulting in no additional drag or lift on the aircraft and keeping the probe concealed.

Abstract: An improvement in an airplane mounted aerial refueling boom wherein the boom assembly mounting permits motion about three axes. A first pivot attached to the fuselage of the airplane provides for radial or azimuth motion of the boom about a vertical or yaw axis of rotation essentially normal to the air stream. The second axis of motion, the pitch axis, is located below the airplane fuselage and perpendicular to the yaw axis so that the pitch axis rotates with any yaw motion of the boom and allows vertical displacement of the boom. Vertical and yaw displacement takes place in a conventional fashion. The third axis of motion, the roll axis, is located in-plane with and perpendicular to the pitch axis. This roll axis is coincident with the longitudinal centerline of the boom structural tube and a helical rotary actuator that produces a commanded roll motion as a function of pitch and yaw motion of the boom assembly.

Abstract: A refueling system mounted to an aircraft fuselage for transferring fuel from a tanker aircraft to a receiver aircraft. The refueling system including a pylon extending from the fuselage at a position aft of the main wing and having a refueling pod mounted thereto at an outboard location. A refueling hose is disposed within and extendable from the refueling pod and functions to transfer fuel from the refueling pod to the receiver aircraft. A means for transferring fuel from a fuel source, located within the aircraft, to the refueling hose is also provided. The pylon and refueling pod are configured so as to channel the refueling hose in a preferred direction to maximize safety during refueling. The channeling of the refueling hose is accomplished by mounting the refueling pod at an angle to the pylon, mounting the refueling pod at an angle to a horizontal plane, mounting the pylon at angle to the fuselage, or a combination of these mounting arrangements.

Abstract: A refueling cart, for refueling large aircraft at a major airport having pressurized fuel hydrants at loading/unloading aprons, includes auxiliary facilities on the refueling cart that are usually powered by compressed air that is obtained from compressed-air bottles carried on the cart. To avoid the labor and annoyance of checking and refilling the bottles of compressed air, a small air compressor is carried on the refueling cart and is powered by a fluid motor that is in turn powered by the flowing pressurized fuel. A variable orifice is placed in the path of the fuel flowing from a hydrant to the airplane. The pressure generated across the variable orifice by the flowing fuel pushes a small amount of fuel in a path that bypasses the orifice. That bypass path includes the fluid motor, and the bypassing fuel at the pressure difference generated by the orifice drives the fluid motor. The flow of fuel to the airplane is not constant but varies as the planes tank(s) are filled.

Abstract: A self-contained fueling module (10) provides the exact amount of hydrazine necessary to fuel a satellite (50) prior to launch. The fueling module (10) includes a propellant tank (14), a vacuum tank (12) and a pressurant tank (16). The propellant tank, filled with hydrazine, is shipped to the launch site where it is installed in the fueling module. Prior to launch, the fueling module is connected to the satellite and the hydrazine is driven with Helium pressurant into the satellite fuel tank. The Helium also pressurizes the satellite fuel tank to flight pressure. Any remaining fuel is evacuated from the connections (45) and fuel transfer lines (42) with the vacuum tank. Personnel do not have to wear self-contained atmospheric pressurized environment (SCAPE) suits because there is no risk of hydrazine exposure.

Abstract: An aerial refueling system for refueling aircraft in flight from a tanker airplane, via a fuel supply hose and drogue system comprising an elongated boom having inboard and outboard end portions, and having pivotal support structure at the inboard end portion to accommodate pivoting of the boom between retracted position adjacent the airplane fuselage and extended position in which the boom projects away from the fuselage; the boom having a guide to guide endwise extension and retraction of the hose and drogue to and from aircraft refueling deployed position; and hose and drogue control structure carried by the aircraft fuselage for effecting storage, and hose and drogue endwise extension and retraction via the guide.

Abstract: A high altitude launch platform, used to launch a payload into earth orbit, is part of a payload launch system having a payload launching rocket with an engine carried by the high altitude launch platform. A first amount of fuel, substantially less than the capacity of the fuel tanks, is provided to the fuel tanks of the engines for the launch platform while the launch platform is on the ground. The launch platform is flown to a first altitude and the fuel tanks are provided with a second amount of fuel while the high altitude launch platform is at the first altitude. The addition of the second amount of fuel is sufficient to allow the payload to be launched into orbit.

Abstract: An enhanced hose for use in fuel transfer and the like. Embedded within the hose's body are fiber-optic fibers in which light is transmitted. At predefined locations on the hose, selected portions of said fiber-optic fibers are exposed and structured to permit light to escape. Structuring of the fiber-optic fibers to permit light to escape is done by: terminating the fiber at that point, removing the cladding on the fiber at that point, or by creating a radical bend in the fiber. The intensity of the light escaping from the fiber-optic fibers is easily controllable by adjustment of the light source's intensity which feeds the light into the fiber-optic fibers. Additionally, compensation is made so that elongation of the hose does not break the fibers. Since no electrical current is being used, the enhanced hose is particularly useful for illuminating the exterior of a hose which is conveying explosive materials such as fuel.

Abstract: A visual guidance system and method includes a subsystem which both locates the aircraft and mating structures thereof and also determines their motion and their rate of change of motion. The locating subsystem has an electrical output which feeds the location and motion data to a guidance system computer which utilizes software which combines the data with other data in a database containing the dimensional size and configuration of the aircraft and mating structures. The combined data is converted to a suitable form and fed to the computer monitor which displays the aircraft and mating structures thereof in real time during the refueling operation. The computer and computer monitor are provided with image controls which allow the operator to select the perspective viewing angle as well as the image contrast and color in order to enhance the visual cues provided by the image and facilitate the refueling operation.

Abstract: The invention relates to a system for the flight refueling of at least one first aircraft provided with an intermediate fuel intake means connected to at least one fuel tank, by a second aircraft equipped with an intermediate fuel supply means connected to at least one fuel supply tank and which can be connected to the intermediate fuel intake means so as to permit, with the aid of at least one fuel pump, the transfer of fuel contained in the tank(s) of the second aircraft to the tank(s) of the first aircraft. This system includes at least one camera positioned below the aircraft, at least one multimode display to display at least one image from a camera and symbology information such as fuel data information used during the refueling operation.

Abstract: The variable speed drogue for use with an inflight aerial refueling system includes a refueling coupling for receiving a refueling probe. A plurality of trailing edge support arms are pivotally mounted to the trailing edge portion of the refueling coupling, projecting rearwardly, and a plurality of leading edge support arms are pivotally connected to the refueling coupling forward and outward of the trailing edge support arms. A drogue canopy is connected between the trailing ends of the leading and trailing edge support arms, presenting a projected area, to provide drag. A plurality of cord linkages are secured at one end to the leading edge of the drogue canopy, and are connected at their other end to a rear cord ring mounted to the trailing edge portion of the refueling coupling member.

Abstract: An elongated, rigid boom for the in-flight refueling of rotary wing aircraft in which a forward end of the boom is adapted for attachment to the fuselage of a rotary wing tanker aircraft and is of sufficient length to extend rearwardly of the tanker aircraft for the rear end of the boom to be clear of the tanker aircraft rotor path. The forward end of a funnel refueling drogue configured to receive the fueling probe of an aircraft to be refueled is swivelly attached to the rear end of the rigid boom and a fuel line supported by the boom extends from a connection into the tanker aircraft refueling tanks to a female refueling aircraft probe connection in the drogue.

Abstract: An in-flight hose-and-drogue refueling system has the capability of steering the drogue using four thrusters which are energized by pressurized air. The system measures the drogue's 3-dimensional position relative to either the refueling aircraft or the probe on the receiver aircraft. A control system utilizes the measurements of the drogue's 3-dimensional position to activate the thrusters so as to either minimize the excursions of the drogue due to turbulence, thus enabling easier hook-up, or alternatively, to track the receiver's probe and automatically guide and contact the drogue to the probe.

Abstract: A servo controlled system is provided for electrically coupling the motions and applied forces of pilot and co-pilot control sticks. Servo-coupling between the two control sticks is accomplished by detecting the position of the control sticks of respective controllers and/or detecting torque exerted on the control sticks. The position and torques signals are processed and employed in a feedback loop for each control stick to generate a feedback signal to motors to which the control sticks are mechanically coupled. The motors act on the control stick to simulate the feel of traditional mechanical controllers, and to cause the controllers to track each other's movements.

Abstract: A docking target (10) includes three concentric circles (C1, C2, C3) each comprising a plurality of different color light emitting diodes (D1, D2, D3) spaced about the circumference of each circle (C1, C2, C3). During vehicle approach, each circle appears initially as a light spot, then a continuous ring of light and finally a plurality of independent light points at defined distances of the vehicle (14) from the station (12) so that the operator can determine distance of the vehicle (14) to the target (10). The light emitting diodes (D1, D2, D3) on each circle, when visible, provide attitude information of the vehicle (14) with respect to the station (12) by the intensities of the light emitting diodes (D1, D2, D3) and the geometric shape produced thereby so that the operator can adjust the attitude of the vehicle (14) with respect to the station (12).

Abstract: The variable speed drogue for use with an inflight aerial refueling system includes a refueling coupling for receiving a refueling probe. A plurality of trailing edge support arms are pivotally mounted to the trailing edge portion of the refueling coupling, projecting rearwardly, a plurality of pivot linkage members are pivotally connected to the trailing edge portion of the refueling coupling, and a plurality of leading edge support arms are pivotally connected to the pivot linkages. A mechanism is also provided for uniformly and symmetrically longitudinally changing the pivot points of the leading edge support arms to change the projected area of the drogue canopy.

Abstract: A mat for protecting the surfaces of equipment from scratching, denting, and chemical action during servicing, particularly well suit for the surfaces of an aircraft during a refueling operation. The mat closely conforms to the surface shape of the aircraft wing and does and cannot be readily moved or damage during use. The mat preferably includes one or more depressions for containing spills fuel and/or accommodating tools and other servicing items and equipment.

Abstract: A vehicle propulsion system for accelerating a vehicle along a desired travel path in the atmosphere, space, or aerospace includes a trail laying device for laying a trail of fuel along at least part of the desired travel path at high altitude. The vehicle itself has one or more inlets arranged to ingest fuel from the trail into a combustion chamber where the fuel is ignited and burnt to provide thrust before being expelled via an exhaust. The trail of fuel is laid in a similar manner to a condensation trail of a jet aircraft, but with suitable propellant additives for providing the desired fuel mixture to the trailing vehicle. The vehicle includes an auxiliary propulsion system for propelling the vehicle when outside the fuel trail.

Abstract: The towed glider flight control system of the invention has a towing frame interconnecting and pivotally connected at each end to the towed glider and the towing aircraft. Sensors measuring the angular relationships between the towing frame and the towed glider and the rage of change in these relationships and sensors measuring flight conditions of the glider and towing aircraft are connected to the input of a computer of which the output connects to the glider aerodynamic control surface. The computer determines differences between sensor sensed parameter values existing when a selected spatial geometric relationship exists between the glider and towing aircraft and sensor parameter values received by the computer from the sensors and from these differences the computer calculates motions required of the glider aerodynamic flight path control surfaces to establish a glider flight which establish and maintain the selected spatial geometric relationship of the glider and towing aircraft.

Abstract: A process and apparatus are provided for estimating the movement of a moving object relative to a reference object. A symbol is formed on the moving object, the symbol having a rectilinear contour with at least two parallel straight lines. The symbol is observed from the reference object and the movement is determined by means of successive projections along two axes having a relative rotary movement with respect to the recorded image of the symbol. The rotary motion is preferably at such a rate that it does not interfere with obtaining images of the straight lines.

Abstract: An aerial refueling system includes a reel mounted for rotation about a central axis for winding and unwinding a hose. A sheave is provided to receive the hose as it leaves the reel and to change the direction of the hose so that it trails axially of the reel. The sheave is mounted on a non-rotating carriage which is supported by the reel and moves axially along the reel as the reel rotates.

Abstract: A method and apparatus for in-flight refueling of unmanned aircraft includes a manned tanker aircraft having a refueling probe mounted thereon. The probe is extendable for increased visual reference. A drogue mounted on the distal end of a flexible refueling hose is trailed from the unmanned aircraft. The refueling hose is stored on a reel assembly mounted on the fuel tank of unmanned aircarft. The reel assembly is remotely actuated from the manned tanker to pay out the refueling hose. A homing system transmits signals from the manned aircraft guiding the drogue to the probe. Upon insertion of the probe into the drogue, automatic coupling occurs and the unmanned aircraft is refueled.

Abstract: A deployment arangement comprises an inner tube 10 pivoted to ground at `P` and carrying an outer tube 12 for telescoping movement. The inner end of the outer tube 12 carries a collar assembly 14 which is pivotally connected to a drive or radius arm 18 which is pivoted to ground at `Q`. The radius arm 18 carries a drive plate 50 which defines a cam track in which a cam follower runs. The mechanism is driven by a ram 20. On actuation of the ram 20, the consequent rotation of a drive plate relative to the collar assembly 14 initially executes a programmed rotation of the outer tube 12 about its longitudinal axis and then locks the outer tube against rotation. Thereafter, the outer tube 12 extends telescopically relative to the inner tube and the inner tube pivots about `P`.

Abstract: A fuel delivery system for refuelling airplanes comprising a delivery station mounted on an airplane refuelling tank-vehicle and movable from a rest position wherein it is completely received within a suitable, practically inaccessible housing formed on the tank to an operative position wherein it is completely outside the housing and perfectly accessible to the operator who is carrying out the refuelling, operation; the supporting frame of the system, which is of a simple and solid construction is controlled to move from the one position to the other preferably through hydraulic mechanical means.

Abstract: A pod assembly for attachment to an aircraft including a pod housing and a fairing housing mounted on the pod housing. A bulkhead divides the pod housing into first and second compartments. The first compartment is for containing radiating electronic apparatus, such as an electronic countermeasures system. The second compartment and the fairing housing are for containing aerial refueling equipment, such as a hose-and-drogue system and power generating apparatus for the provision of power to the electronics and refueling equipment contained therein. Air from the first compartment is used for cooling the first compartment and ventilating the second compartment.

Abstract: A robotic connector or interface includes a roughly conical male member in which the conical side may be concave. The male member includes a radial indexing pin, and a central bore in which polarized electrical connectors are located. A mating female member includes a cavity with a fundus and movable peripheral lips adapted for grasping the base of the male member when engaged for drawing the male member into full mating relation with the cavity. A tapered slot in the side of the female member guides the index pin to impart rotational forces so that mating can take place even if the approach is skewed. The electrical connectors are mounted on a separately indexed, spring loaded connector plate at the fundus of the cavity. A motor-driven linkage operates the peripheral lip members.

Abstract: A bank of comparators is utilized to control a logic circuit which indicates proper system operation when measured hydraulic real motor control pressures are within normal limits for the current airspeed after hose deployment. Also, before such deployment, simulated test signals are applied to the comparators to ensure proper operation of the comparators and logic circuitry.

Abstract: A passive type forward/aft indicator for mounting on an aircraft refueling tanker. The indicator providing the appearance of an ascending liquid thermometer for guiding an aircraft to be refueled. The indicator providing proper longitudinal positioning underneath the tanker. The indicator can be used equally well for space docking and other types of rendezvous missions.

Abstract: An aerospike is adapted to be attached to the front nose of an aerodynamically asymmetric space vehicle system, such as the external tank and orbiter of the space shuttle. The aerospike basically comprises a tapered elongated portion having a first end which is adapted to be attached to the nose of the space vehicle, and a second free end terminating in a substantially rounded disc-like tip member. Use of the spike reduces aerodynamic heating and drag during ascent of the space vehicle into its orbital position, provides an attachment point for tether operations and for propellant recovery, and permits transportion of an external tank into its orbit.

Abstract: An advanced fuel receptacle lighting system for aerial refueling of receiver aircraft during night time operations. The receptacle lighting system mounted on a tanker aircraft for enhancing a boom operator's visual view of a fuel receptacle area on the receiver aircraft without blinding or distracting the receiver pilot.

Abstract: An improvement in an aircraft refueling boom wherein the boom support attachment provides two axes of motion. The first axis, attached to the fuselage, provides for lateral motion of the boom about a longitudinal or roll axis of rotation essentially parallel to the air stream. The second axis of motion, the pitch axis, is located below and perpendicular to the roll axis so that the pitch axis rolls with any roll motion of the boom and provides for vertical displacement of the boom. The resultant boom nozzle motion is such that vertical displacement occurs in a conventional fashion while lateral displacement takes place in an arc or rolling motion rather than a yawing motion.

Abstract: A modular nozzle system for refueling aircraft fuel tanks includes a nozzle valve linkage mechanism which permits the valve body to have a shorter length than previous designs. The nozzle may include a mechanical fuse for releasing the connection between the nozzle body and a fuel tank upon the application of predetermined forces. The nozzle may also include a swivel joint which facilitates positioning the nozzle for connection to a fuel tank. The nozzle may also include a quick disconnect assembly which facilitates connection of the nozzle to various hose end connection. The system also may comprise an assembly fixture for assembling the mechanical fuse and a test fixture for testing the release force of the mechanical fuse.

Abstract: The telescoping member of an aerial refueling probe is hydraulically actuated for extension/retraction by pressurized fuel. The force for extending the probe is the result of fuel pressure against a check valve in the end of the telescoping member. The force for retraction is the result of fuel pressure in a retraction chamber between the telescoping member and the inner fixed member of the probe wherein the separating force generated therein retracts the telescoping member. A housing is provided to isolate the probe from the environment and to reduce the frictional forces that resist the telescoping motion. A system for locking the telescoping member in its retracted position and in its extended position is also provided. The telescoping member and the housing may be composite graphite/epoxy.

Abstract: The hose reel comprises a supply hose having an inlet end and an outlet end, and a drum mounted for rotation about a central axis and having an outer surface for receiving the supply hose. The inlet end is connected to the drum and a sheave is provided for wrapping the supply hose around the drum outer surface as it rotates. The sheave is moved axially along the drum as it rotates.

Abstract: A method and apparatus are disclosed for remotely connecting, disconnecting and reconnecting a flexible communication member between two spaced apart bodies which are in predetermined relative positions to one another within given tolerances, and more particularly, to the connecting of an electrical connector to a carried spacecraft from an orbiter while providing for a minimum transfer of energy therebetween. A remote actuation of an electrical connector between two bodies is accomplished by driving an extendable member carrying a detachable connector from one of the bodies into mating contact with a fixed connector on the other body. A locking means associated with the other body retains the detachable connector in such mating contact while the extendable member is withdrawn. A flexible cable is first secured between said one of the bodies and the detachable connector.

Abstract: A nozzle for an aerial refueling boom is disclosed in which the locking latches on the nozzle housing are operated by a solenoid which allows the latches to be moved to an unlocked position by the operator in the aerial refueling tanker. The nozzle embodies an inlet fitting at its forward end which is adapted to be fixed to the boom. A nondestructive detent arrangement releasably couples the nozzle housing to the inlet fitting so that if the housing is deflected at an excessive angle, it will break away from the fitting and thus the boom without damaging the boom.

Abstract: A system for transferring fluid between two marine tankers, including a first articulated loading arm mounted on the first tanker and a second loading arm or other suitable receiver mounted on the second tanker. The first loading arm is guided into operating contact with the second arm or receiver by laser tracking and ranging equipment, and by a computer which computes the location of the end of the first loading arm relative to the second arm or receiver. After the first loading arm and the receiver are connected together, the computer calculates the position of the outboard end of the first loading arm, compares this position to a set of safe operating boundaries, and provides a warning signal whenever the end of the arm moves outside any of these safe boundaries. When the end of the first arm moves outside a critical boundary the computer provides a disconnect signal which shuts down the loading operation and disconnects the first loading arm from the second arm or receiver.

Abstract: An improved aerial refueling system, suitable for operation under nighttime or other limited visibility conditions, is described, and comprises a tanker aircraft with refueling boom depending rearwardly thereof, a receiver aircraft having a fuel receptacle for interconnection with the boom, means disposed on the tanker for illuminating the receiver aircraft with infrared light during hookup and refueling, infrared sensitive viewing means and an optical imaging device on the tanker through which the boom operator may view the boom and receiver aircraft to guide the boom into position for connection with the receiver aircraft.

Abstract: An aerial refuel floodlight capable of being mounted on the leading edge of a vertical stabilizer in a receiver aircraft utilized for in flight refueling. The aerial refuel floodlight is of a projectile-shape having a lamp mounted therein. Surrounding the lamp is a cone-shaped reflecting element terminating in a hemispherically-shaped reflecting element which directs light emanating from said lamp through an off-axis lens mounted adjacent thereto. A scoop-shaped reflector situated adjacent the lens and in the upper part of the fixture directs the magnified light onto the fuselage of the receiver aircraft adjacent to and including the refuel receptacle.

Abstract: A pressure fueling adapter for aircraft has spring loaded primary and secondary nested poppets for controlling fluid flow therethrough, the primary poppet operable by engagement with the position lever of a fuel nozzle and the secondary poppet responsive to pressure differentials to allow inlet fluid flow and check back flow. A cam interengagement mechanism may be manually actuated to connect the primary and secondary poppets for simultaneous movement by the position lever of the fuel nozzle to defeat the secondary poppet check, for defueling purposes.

Abstract: An apparatus is disclosed for refueling an aircraft primarily fron a ship at sea, the ship being subject to changes in vertical and horizontal position due to pitch, roll, and heave, and combinations thereof. The apparatus comprises a first beam having a first end pivotally attached to the ship and extending upward therefrom. A second beam is pivotally attached at its first end to the second end of the first beam and extends substantially in a horizontal direction therefrom and preferably is supported by an air spring mounted between the first and second beams. A positioning device, preferably in the form of a hydraulic actuating cylinder, is coupled to both the first beam and the ship and is adapted to adjust the angular position of the first beam with respect to the ship in response to a first control signal.

Abstract: A ground-based aircraft refueling system uses existing air-to-air refueling technology. A fixed facility design attaches a moveable air-to-air type refueling boom and probe to an overhead track mounted on the ceiling of a TAB VEE aircraft shelter. Movement of the boom and probe is controlled from a remote control room protected from hazardous chemical and biological environments. In a second embodiment, a moveable facility design mounts on the top of a tank truck a first boom attached at a right angle to an air-to-air type refueling second boom and probe. The booms and probe are remotely controlled from the truck cab, which is protected from hostile chemical and biological environments. A third embodiment adds to the moveable facility design a second tank and nozzle outlet for spraying decontaminate.