Abstract: A variable volume fluid storage tank or reservoir and related fluid transfer system are provided for storing and transferring volatile or hazardous fluids, particularly such as fuel in an aircraft fuel supply system. Each fluid storage tank comprises a tank body in combination with a movable base wall defining a variable volume internal chamber for receiving and storing fluid. Each storage tank further includes a dispense port for dispensing the fluid, e.g., to a manifold or the like for supply to one or more aircraft engines, with the base wall moving relative to the tank body during fluid dispensing to substantially preclude any residual air or vapor space within the storage tank. A fluid level sensor unit mounted outside the tank chamber tracks displacement of the base wall to provide an indication of the fluid volume remaining within the storage tank.

Abstract: A system for emergency aircraft control uses at least one engine and lateral fuel transfer that allows a pilot to regain control over an aircraft under emergency conditions. Where aircraft propulsion is available only through engines on one side of the aircraft, lateral fuel transfer provides means by which the center of gravity of the aircraft can be moved over to the wing associated with the operating engine, thus inducing a moment that balances the moment from the remaining engine, allowing the pilot to regain control over the aircraft. By implementing the present invention in flight control programming associated with a flight control computer (FCC), control of the aircraft under emergency conditions can be linked to the yoke or autopilot knob of the aircraft. Additionally, the center of gravity of the aircraft can be shifted in order to effect maneuvers and turns by spacing such center of gravity either closer to or farther away from the propelling engine or engines.

Abstract: A method of loading propellant into a spacecraft that comprises storing and transferring propellant in a portable propellant loading tank, temperature conditioning and helium saturating the propellant in the propellant loading tank, transferring the loading tank to a launch site, coupling the loading tank to the propellant storage tank, and pressurizing the portable propellant loading tank to transfer the propellant to the propellant storage tank in the spacecraft. The method may further comprise weighing the propellant loading tank during propellant transfer, venting the propellant storage tank in the spacecraft to a receiver tank, and weighing the receiver tank during propellant transfer. The amount of propellant transferred to the propellant storage tank is equal to the difference between the measured weights of the respective loading and storage tanks.

Abstract: Fuel supply system for multijet airplanes using cryogenic fuel with one tank or one tank group for each engine or for all engines on one side of the longitudinal central plane of the airplane, and, if desired, with an additional, common tank or an additional, common tank group for all engines. A transfer line with shut-off valve leads from each tank/tank group associated with a defined engine or with the engines of one side of the airplane to at least one other tank/tank group and/or, if desired, to the tank/tank group common to all engines. If desired, at least one transfer line leads from the common tank/tank group to at least one other tank/tank group.

Abstract: A system, a portable propellant loading tank and loading method for bipropellant spacecraft servicing to load propellant into a spacecraft. The spacecraft has a propellant storage tank with a propellant input and a vent output. The system comprises a portable propellant loading tank for storing and transferring propellant that is couplable to the propellant input of the propellant storage tank in the spacecraft. The propellant loading tank is a stainless steel tank that is electropolished on its interior surface. A portable weighing system having a plurality of load cells provides output signals indicative of the weight of the propellant loading tank. A load cell readout device is coupled to the portable weighing system for providing an output indicative of the weight of the propellant storage tank. A receiver tank is coupled to the vent output of the propellant storage tank in the spacecraft.

Abstract: The present invention relates to a distributed fuel system, wherein a plurality of fuel tanks used for storing fuel are distributed in different locations.The fuel tanks are connected to each other via a manifold which permits fuel to flow therein. The distributed fuel system includes a plurality of control components interposed at predetermined points of the manifold to permit or restrict the flow of the fuel contained in the manifold in response to control signals. A method for distributing the fuel between the fuel tanks to achieve predetermined levels in each of the fuel tanks comprises the steps of determining the status and condition of the fuel system. The functions to be performed are then selected. Based on the system status and the functions to be performed, the configuration of the control elements is selected to perform the functions to be performed.

Abstract: A propellant immobilizing system and method in which propellant motion in the propellant storage tanks (22) is reduced or eliminated during velocity change maneuvers to reduce disturbance torques acting upon the spacecraft (10) and improving the spacecraft attitude pointing performance. The thrusters (14, 16, 18 or 20) are fired to produce a small impulse in the direction of the desired Velocity change to begin motion of the propellant within the fuel tank in the opposite direction. After the fuel has moved within the tank to a location in which the propellant center of mass is aligned with the propellant tank (22) center of curvature in the direction of the desired velocity change, thrusters (14, 16, 18 or 20) are again fired to produce a force in the direction of the current velocity of the propellant center of mass to stop the propellant center of mass relative to the propellant tank (22).

Abstract: In a tank 10 for cryogenic liquid to be used in a low-gravity environment (e.g., on a space vehicle), a liquid transfer apparatus 15 (which comprises an elongate array of fins 32 and a sponge structure formed from panels 31) functions to transfer cryogenic liquid from the interior of the tank 10 to a bowl structure 20 defining a reservoir region adjacent an outlet of the tank 10. A perforated plate 22 disposed between the sponge structure and the outlet of the tank 10 causes cryogenic liquid to pass through the outlet into an outlet line 40 in a regular and generally unbroken flow. To prevent any substantial amount of heat transfer into the reservoir region of the tank 10, the bowl structure 20 is separated from the inner surface of the tank 10 by a capillary distance in order to provide a thermally insulating space therebetween.

Abstract: A spacecraft includes a pair of pressurized propellant tanks. The pressure may be provided from a common pressurant tank. Each propellant tank has a propellant output port. A manifold includes a first branch coupled between a common juncture and the output port of the first tank, and a second branch between the juncture and the output port of the second tank. At least the second tank is associated with a heater. A controllable valve, such as a normally open pyrovalve, is coupled in the second branch. In order to fully utilize the propellant in the tanks, the second tank is differentially heated relative to the first when the tanks are nearly empty, to create a tendency toward a pressure difference, which drives propellant from the second tank to the first. When all or most of the propellant is transferred, the valve is operated to close off the second branch of the manifold, to isolate the now-empty tank.

Abstract: A system for storing liquid under pressure is adapted to contain any of various quantities of liquid determined in advance with approximately the same filling ratio in an environment in which the temperature varies. It comprises a main storage tank adapted to contain at least the largest of these quantities of liquid in such a way as to leave a residual volume of pressurized gas and a reserve gas storage capacity mechanically independent of the main storage tank and in permanent communication with the residual volume of pressurized gas via a liquid non-return device. The reserve capacity is chosen so that the quantity of liquid actually introduced into the system divided by the sum of the volumes of the main storage tank and reserve capacity is at least approximately equal to the filling ratio.

Abstract: The balance of a spin-balanced spacecraft may be dynamically adjusted by moving a liquid between or among containers spaced about the spin axis. The transfer of liquid is accomplished by controllable heaters associated with each container, for heating that container from which liquid is to be transferred to increase the pressure and drive out liquid. A spacecraft for accomplishing this method includes a balance sensing arrangements such as a gyroscope and logic for determining which container or containers are to be emptied and for controlling the heaters. Weight is minimized by accomplishing the transfer of liquid among fuel containers by way of manifolds which also supply fuel to thrusters.

Abstract: A flying saucer is remotely controlled and includes a plurality of angularly spaced apart guide flaps and motors all of which are operated independently of each other. Each of the motors has a fuel tank associated therewith and the fuel tanks can be interconnected with each other to share fuel or can be connected with a main fuel tank to receive fuel therefrom.

Abstract: Parallel transfer pumps (92, 94) operate to transfer fuel from auxiliary tanks (52, 60, 66) to the main tank (10). A pressure sensor (106) in the pump discharge line in combination with tank level rate mechanisms (86, 88, 90) sequences pumps (92, 92) and transfer valves (100, 102) if required, and confirms successful transfer or alarms when unsuccessful.

Abstract: A true mass fuel gaging system for aircraft utilizing multiplexing of tank unit measurements in or adjacent a fuel tank for improved accuracy and fault isolation. The system provides dual equipment channels for redundancy throughout all data processing portions of the system and also uses extensive built-in testing (BIT) routines so that upon detection of a fault an alternative channel can be switched into use. Detected fault locations are displayed in the cockpit with the fuel quantity displays. The system also provides displays of center of gravity measurements derived from fuel mass and location.

Abstract: A redundant rocket engine for high reliability that incorporates a single thrust chamber and its attendent hydrogen and oxygen injectors and provides a pair of independent but indentical engine systems that provide the fuel feed and cooling systems where one system remains in a standby condition until a malfunction occurs while the other system remains operative. The independent systems are comprised of all of the movable parts.

Abstract: A true mass fuel gaging system for aircraft utilizing multiplexing of tank unit measurements in or adjacent a fuel tank for improved accuracy and fault isolation. The system provides dual equipment channels for redundancy throughout all data processing portions of the system and also uses extensive built-in testing (BIT) routines so that upon detection of a fault an alternative channel can be switched into use. Detected fault locations are displayed in the cockpit with the fuel quantity displays. The system also provides displays of center of gravity measurements derived from fuel mass and location.

Abstract: A novel propellant resupply system for, and method of recharging the propellant tanks of, the attitude control system (ACS) of a spacecraft or the like are described, comprising first and second propellant conduits respectively interconnecting the outlets of the fuel and oxidizer pump inducers of the primary propulsion system with the fuel and oxidizer tanks for the ACS thruster engines, and controller valves within each propellant conduit for controllably diverting fuel and oxidizer under pressure from the fuel and oxidizer pumps to the thruster fuel and oxidizer tanks during operation of the primary propulsion system engines.

Abstract: A multi-engine helicopter fuel supply balance system effects automatic trfer of fuel from a larger tank to a smaller tank in response to low fuel level in the smaller tank when in automatic mode, and effects a transfer of a predetermined quantity of fuel between selected tanks by timed operation of a constant delivery pump when in manual mode.

Abstract: By employing in-line gas turbine power plants in the nose and tail of a low profile highly streamlined aircraft, twin engine reliability is obtained with only a single engine frontal area combined with the employment of strakes rather than pipes for the nose engine exhaust, excellent fuel economy is obtained. While a nose mounted turboprop serves as the main power supply, a tail mounted turbojet with only a small fraction of the turboprop horsepower provides a supplementary power source during take-off or optionally to enhance cruise performance. Should the turboprop fail in flight the turbojet is capable of taking over at a reduced cruising speed. A fuel system common to both engines offers additional safety features and an improved method for effecting proper trim with either or both engines operative.

Abstract: An oil replenishment system provides a remote reserve oil tank and the plumbing necessary to fill the main oil tank or tanks of engines, especially aircraft engines during flight. This system includes apparatus to determine the quantity of oil pumped to any one engine so that a quantity gauge is not required on the engine. A selector valve located on the reserve tank which may be remotely controlled directs replenishment oil to the selected engine tank. The system is designed to be powered from the existing on board hydraulic power system.

Abstract: The method of purging entrained air or vapor from fuel stored in two or more tanks in an aircraft, and more particularly in multi-engine aircraft during crossfeed fuel delivery when the aircraft is climbing to altitude, which method consists of reversing the fuel booster pump, or pumps, in the temporarily unused tank, or tanks, while all fuel is withdrawn from one tank to supply the engines, whereby the fuel agitation produced by the reversed pump or pumps effectively frees the entrained air or vapor from the fuel to escape to atmosphere through the fuel tank vent system.

Abstract: A vehicle fuel system comprising a plurality of tanks, each tank having a feed and a return conduit extending into a lower portion thereof, the several feed conduits joined to form one supply conduit feeding fuel to a supply pump and using means, unused fuel being returned via a return conduit which branches off to the several return conduits.