233results about "Liquid handling installations" patented technology

A method to load stores on an aircraft, the method may be controlled by one or more controller and may include one or more acts of loading stores onto corresponding lift portions; determining a relative position of the aircraft; positioning the stores relative to the determined position of the aircraft; and securing the stores to corresponding hardpoints (HPs) of the aircraft.

An aircraft servicing system (10) includes a tarmac-servicing system (500). The tarmac-servicing system (500) includes an aircraft-mating element (510) that is mounted and extendible from within an area of a tarmac (502) to couple with an aircraft (504). The tarmac-servicing system (500) supplies primary services to the aircraft (504), such as fuel, air, electrical power, water, coolant, potable water, and gray water. A method of servicing the aircraft (504) includes aligning a primary servicing port (512) of the aircraft (504) over a primary servicing area of a tarmac (502). A tarmac-servicing element (510) is extended out from the tarmac (502) to the aircraft (504). The tarmac-servicing element (510) is aligned and connected to the primary servicing port (512). Primary services are supplied and removed to and from the aircraft (504) in response to the tarmac-servicing element connection with the primary servicing port (512).

An apparatus and method for defueling and aircraft. The apparatus includes a vacuum fuel tank comprising a first vacuum generator, a defueling hose in fluid communication with the vacuum fuel tank, a first defueling fitting attached to the first defueling hose, and a second vacuum generator operatively connected to the first defueling fitting. By providing both a first and a second vacuum generator, the defueling fitting can be attached and detached from an aircraft independent of the suction used to withdraw fuel from an aircraft. According to some embodiments, there may be multiple defueling hoses and additional vacuum generators. Further, some embodiments include a telescoping funnel that can be selectively isolated from the vacuum fuel tank so that the tank can be held at vacuum pressure.

A fuel quality traceable and remote system for monitoring and controlling fuel characteristics during transport from a fuel supply to a supplied device is provided. The system includes one or more subsystems that include at least one sensor monitoring the characteristics of the fuel. The sensor operably sends the data relating to the characteristics to a data register-transmitter which sends the data to a base station that uploads the data to a remote server. The remote server is remotely accessible by a user. The system can also generate warning messages to warn a user when the characteristics are outside a tolerable range. Further, the system can automatically or manually interrupt fuel transport when the characteristics are outside a tolerable range.

The invention provides a refuel control system for controlling refuel of at least one tank (111,112,113, 14,115,116) onanaircraft 100,the refuel control system comprising monitoring apparatus (241, 242, 280, 371, 372, 380, 311, 312, 313, 314, 315, 316, 221) for monitoring data relevant to the refuel process, a control device (330) for receiving said data from the monitoring apparatus, and a refuel valve (130) for controlling flow of fuel to the tank wherein said refuel valve is controllable by the control device such that refuel of the tank can be controlled based on the monitored data. The invention also provides a method of refuelling at least one fuel tank on an aircraft.

A hazardous fluid transfer system is automated for controlling transfer of hazardous fluid within a closed environment thus providing protection to an operator handling the transfer. The hazardous fluid is transferred from a source container to a target container using a processor controlled pump responsive to flow and pressure within a liquid line. A pre-programmed processor receives pressure and flow signals from transducers monitoring the liquid line. The processor actuates a valve within a vapor line between the source and target containers in response to pressure within the target container. The valve is opened for allowing vapor to accumulate within an accumulator during a filling of the target container and closed for causing the accumulator to force vapor stored in the accumulator into the source container, thus transferring the liquid from the source container to the target container while maintaining fluid transfer within the closed environment.

The invention relates to equipment for refueling an aircraft, including a pipe (40) provided with means (42) for connecting onto an intake port (301) of the fuel tank of the aircraft (400) and, at or in the vicinity of the connection means (42), means (501) for determining the value of at least one parameter representative of a flow (E) of fuel passing through the connection means. Said equipment further includes at least one receiver onboard the refueling equipment (1), means (503, 504) for transmitting, to the receiver, a signal (Si(P)) representative of a parameter value predetermined by determination means (501) and an electronic unit capable of receiving, from the receiver, a signal representative of the parameter and of driving at least one flow control and monitoring device in accordance with the signal received from the receiver. The refueling method includes the steps of during a refueling operation, determining the value of at least one parameter representative of the flow (E) at or in the vicinity of the connection means (42), transmitting, to at least one receiver onboard the refueling apparatus, a signal (Si(P)) representative of a parameter value predetermined during the previous step, and automatically driving, in accordance with the signal received by the receiver, a flow control and monitoring device.

A method and apparatus for defueling an aircraft. The apparatus includes a defueling fitting comprising one or more structural connectors, which may include one or more suction cups. The one or more structural members are attached to a mount. The mount may be of any shape, including generally straight, angled, polygonal, or circular. An actuator assembly is attached to the mount for opening an aircraft defueling valve. The first and second suction cups are operatively connected to a vacuum source to connect the defueling fitting to an aircraft body, with the actuator assembly positioned at the aircraft defueling valve. The defueling fitting facilitates safe and convenient defueling of certain aircraft that have recessed or covered fuel drain valves. For example, the Boeing C-17 has fuel drain valves that are recessed behind doors, heretofore presenting a great obstacle to appropriate defueling. The defueling fitting described herein may be used in small and tight spaces, even when other conventional defueling fittings are not helpful.

A fuel tank system is disclosed that includes a fuel tank and a first fluid flow path between a gas space in the fuel tank and outside of the fuel system. A gas separation membrane is disposed with a first side in communication with the first fluid flow path and a second side in communication with a second fluid flow path. A fluid control device is in communication with the second fluid flow path and is configured to provide fluid flow from the second fluid flow path to a liquid space in the fuel tank or to outside of the fuel system. A prime mover is disposed in communication with the second fluid flow path, and is configured to move fluid on the second fluid flow path from the second side of the separation membrane to the fuel tank liquid space or to outside of the fuel system.

A fire suppression drone comprises a main body, a plurality of propellers provided on an outer circumference of the main body and driven by a driving motor, a pump provided in the main body and connected to a water feeding vehicle through a water feeding hose, at least one water jet nozzle provided on the outer circumference of the main body to jet water supplied by the pump, a camera provided on the outer circumference of the main body, and a controller connected with the driving motor, the pump, and the camera and connected with a remote controller to be wirelessly communicable with the remote controller, wherein the remote controller includes a monitor, the monitor capable of display, in real-time, an image captured by the camera.

This invention discloses a distributed parking system for drones comprising a network of parking pads for drones distributed over a geographic area, each of which comprising a parking surface of one or more parking spots on which a drone can land and park securely, a power refill module that replenish the power source of a parked drone, a control module that controls functions of the parking pad, and a communication module through which the control module is connected to a communication network; and a master controller that controls functions of the parking pads and communicates commands to and receives reports from the parking pads through the communication network.

An aircraft fueling system (890) includes an underground fuel supply (904). A fuel pump (906) is coupled to the underground fuel supply 904 and is used to supply fuel to an aircraft (902). A fuel probe (908) is coupled to the fuel pump (906) and is extendible to an aircraft fueling port (926). A fuel probe connection sensor (938) generates a connection signal. A controller (924) is coupled to the fuel pump (906) and the fuel probe connection sensor (938) and adjusts the supply of the fuel (904) to the aircraft (902) in response to the connection signal.

A multiply-redundant system that protects fueling of rockets, aircraft and other vehicles using Liquefied Natural Gas (LNG) along with an oxidizer such as Liquefied Oxygen. One or more sensors in combination with one or more optional microswitches combine to detect any leaks, fire or explosion hazards quickly locking out further fueling. For different levels of safety, different combinations of sensors can be used.

The present invention provides a tank vent device for venting gas from a tank 10 comprising a gas inlet 107 for receiving gas from a vent outlet of the tank, a gas outlet 109 for discharging the gas received, and a pressure valve 70 connecting the gas inlet and gas outlet, wherein the pressure valve is connected to a control pressure input 108 and is controllable by control pressure supplied at the control pressure input, whereby, in use, the pressure valve is controlled by the control pressure to open and close so as to regulate the flow of gas between the gas inlet and the gas outlet. The present invention also provides a vent tank 10, methods of venting gas from a tank including a method including the steps of connecting a tank vent device to a tank and supplying gas at a lower pressure than the pressure of the tank to the tank vent device and a method of refuelling an aircraft.

The invention relates to box type multifunctional aircraft refueling equipment, which is characterized by comprising an openable box, and two sets of oil transportation refueling mechanisms which are arranged in the same box, consist of metering devices and a pipeline valve system for realizing oil transportation and comprise a four-channel gravity fueling mechanism and a two-channel concealed telescopic fueling mechanism. By the box type multifunctional aircraft refueling equipment, normal aircraft refueling operation is realized in a four-channel gravity fueling mode and a two-channel pressure fueling mode, so that the fueling radius is greatly enlarged, and after the fueling is finished, an oil transportation pipeline can be shrunk, and the occupied space of the whole equipment is reduced; and moreover, the box type multifunctional aircraft refueling equipment contributes to keeping the operating site neat and standardizing the requirements of environment friendliness.

A method and apparatus for defueling an aircraft. The apparatus includes a defueling fitting comprising one or more structural connectors, which may include one or more suction cups. The suction cups are disposed in a mount. The suction cups may be raised from a surface in the mount and arranged in a non-circular pattern to facilitate connection to contoured surfaces. An actuator assembly may be attached to the mount for opening an aircraft defueling valve. The suction cups may be operatively connected to a vacuum source to connect the defueling fitting to an aircraft body, with the actuator assembly positioned at the aircraft defueling valve. The defueling fitting facilitates safe and convenient defueling of aircraft, even aircraft with significantly contoured surfaces.