297results about "Liquid handling installations" patented technology

The application provides an autonomous refueling vehicle for a hydrogen-electric aircraft, which includes two or more wings. The wings are provided with one or more removable electric propulsion pods. The autonomous refueling vehicle includes a hydrogen refueling module adapted to connect to the propulsion pods and to a hydrogen source. The autonomous refueling vehicle includes also includes a propulsion pod handling device, which is adapted to remove the propulsion pod from the wings and to position the propulsion pods on the hydrogen refueling module such that the propulsion pods are connected to the hydrogen refueling module. The autonomous refueling vehicle is also adapted to autonomously move itself to the hydrogen source to allow the hydrogen refueling module to removably connect to the hydrogen source for refueling of the propulsion pods.

A decision tool models emissions for a sustainable aircraft fuel (SAF) for the lifecycle of the fuel. The decision tool includes a controller module configured to receive data related to at least one fuel pathway for the fuel wherein the fuel pathway considers emissions from initial feedstock production to fuel burn during flight and arrival. The decision tool determines at least one fuel pathway for the fuel used to fuel the aircraft during a flight, models an emission score for the at least one fuel pathway, and then outputs the emission score where a user can purchase the fuel or make other decisions based upon the fuel pathway provided by the decision tool.

An aircraft electrical power supply system includes a fuel cell auxiliary power unit (APU) that supplies auxiliary electrical power to an aircraft, a fuel cell power plant that supplies primary electrical power to the aircraft, and a hydrogen storage unit that supplies hydrogen to the fuel cell APU and the fuel cell power plant.

An aircraft-based fuel quality monitoring and alerting system is disclosed herein. The aircraft-based fuel quality monitoring and alerting system can include a first sensor configured to output a signal associated with contamination of fuel entering an aircraft through a first fuel inlet. The system can further include a processor configured to determine a first contamination level of the fuel based on the signal and an alerting system configured to deliver an alert if the first contamination level is outside a predetermined range.

The present application discloses a method of determining one or more fuel characteristics of an aviation fuel suitable for powering a gas turbine engine of an aircraft, the gas turbine engine having a combustor supplied with fuel from a fuel system, the method comprising: determining a mass of the fuel being supplied to the combustor; determining a corresponding volume of the fuel being supplied to the combustor; and determining one or more fuel characteristics based on the determined mass and volume. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.

The present disclosure provides systems and methods for storing, transporting, and using hydrogen. In some embodiments, the method may comprise (a) storing hydrogen fuel in one or more fuel storage modules; (b) transporting the one or more fuel storage modules to a vehicle fueling site, wherein one or more hydrogen fuel compatible vehicles are located at or near the vehicle fueling site; (c) loading the one or more fuel storage modules into the one or more hydrogen fuel compatible vehicles, wherein the one or more fuel storage modules are configured to be releasably coupled to the one or more hydrogen fuel compatible vehicles; and (d) decoupling the one or more fuel storage modules from the one or more hydrogen fuel compatible vehicles after the one or more fuel storage modules are depleted or partially depleted.

The utility model discloses an airplane pressure refueling joint, including: joint body, pressure stabilizing valve, rubber hose joint, butt joint copper disc, valve subassembly and butt joint handle, joint body and pressure stabilizing valve are connected through fastener and mutually conducted, rubber hose joint is provided on the pressure stabilizing valve, butt joint copper disc is provided on joint body, butt joint handle is provided on the butt joint copper disc, the valve subassembly is provided on the butt joint copper disc, and the butt joint handle is provided on the butt joint copper disc. The filter screen assembly is arranged on the rubber hose connector, the valve assembly is arranged in the connector body and used for controlling opening and closing of the connector body, the butt joint handle is installed on the surface of the connector body, and a bidirectional impurity collecting device is arranged in the rubber hose connector. According to the invention, impurities filtered out of an oil way during refueling can be collected, impurities in an oil tank can be collected during oil pumping of an airplane, unified cleaning is facilitated, and secondary pollution to other aircrafts is avoided.

The invention relates to a ground well connector tray, and belongs to the technical field of airport refueling equipment.The ground well connector tray comprises a tray body, the tray body is used for containing a ground well connector, a folding cylinder is movably arranged on the tray body and stretches out and draws back in the vertical direction, and the ground well connector is located in the folding cylinder; a support is arranged on the tray body, a cover plate is hinged to the support, the hinge axis of the cover plate is arranged in the horizontal direction, the cover plate is located above the folding cylinder, a transmission part is arranged on the cover plate, and the transmission part is used for enabling the cover plate to rotate in the direction close to a ground well connector on the tray body. And the folding cylinder is driven to extend upwards. The underground well joint has the advantages that in the running process of an aircraft refueling vehicle, rain, snow and ground silt are not prone to being splashed into a gap of the underground well joint, and the connecting and sealing effect of the underground well joint during aircraft refueling can be guaranteed.

A fuel line, terminating in a refuel connector, is used to fuel / defuel an aircraft, for example with liquid hydrogen. A barrier is disposed around the area where the refuel connector connects to an aircraft fuel port, and is sealed against the aircraft wing with a seal. A gas line runs generally parallel to the aircraft fuel line, and supplies inert gas, for example nitrogen, into the volume defined by the barrier. The inert gas flushes out air present around the refuel connector such that the oxygen concentration in that area is significantly lowered. This prevents ignition of fuel in the event of a fuel leak from the fuel line structure.

A sub-cooler for a sub-cooling cryogenic refueling system is disclosed herein. The sub-cooler includes a first valve to separate flowing cryogenic fuel into a primary flowline and an auxiliary flowline, a second valve to reduce the saturated pressure and temperature of the cryogenic fuel in the auxiliary flowline, a cryogenic heat exchanger to transfer heat from the primary flowline to the auxiliary flowline, a temperature sensor to measure the temperature of the sub-cooled cryogenic fuel in the primary flowline, and a sub-cooler controller to control the effective areas of the primary flowline inlet and the auxiliary flowline inlet at the first valve.

The invention relates to the technical field of static electricity conduction, in particular to a refueling vehicle static electricity conduction mopping adhesive tape alarm device which comprises a mounting shell, a static electricity conduction adhesive tape, a winding unit, a controller, an alarm and an adjusting assembly, the adjusting assembly comprises two adjusting units, two pressure detection units and a plurality of static sensors, the winding unit is started, the static electricity conduction adhesive tape is unwound, and the controller is started to start the alarm. At the moment, the static electricity conducting adhesive tape makes contact with the ground, the static electricity sensor detects the contact condition and the static electricity conducting effect of all parts of the static electricity conducting adhesive tape and the ground, when a certain part is in poor contact, the adjusting unit drives the pressure detecting unit to move to the position above the part, and then the static electricity conducting adhesive tape is pressed through the pressure detecting unit. Meanwhile, the pressing pressure is detected, the situation that the static electricity conducting adhesive tape is seriously abraded due to the fact that the pressing pressure is too large is avoided, and therefore the static electricity conducting adhesive tape makes full contact with the ground, and the risk of fire explosion is reduced.

The invention relates to the field of aircraft maintenance, in particular to an intelligent aviation kerosene and bactericide mixed filling device which comprises a shell and an oil conveying pipeline, the oil conveying pipeline penetrates through the shell, and a fuel oil input connector and a fuel oil output connector are arranged at the two ends of the oil conveying pipeline correspondingly; the bactericide distribution bin is communicated with one end of the bactericide conveying pipeline, the other end of the bactericide conveying pipeline is inserted into the oil conveying pipeline and connected with a three-stage impeller with holes, the three-stage impeller with the holes and the oil conveying pipeline are coaxially arranged, and a fuel oil flow sensor is embedded in the oil conveying pipeline and used for detecting the oil amount in the oil conveying pipeline. An electromagnetic valve and an electromagnetic diaphragm metering pump are installed on the bactericide conveying pipeline, a controller is installed in the shell, the controller is electrically connected with the fuel flow sensor, the electromagnetic valve and the electromagnetic diaphragm metering pump, in the refueling process, kerosene and a bactericide can be intelligently controlled to be mixed, and the mixing effect is guaranteed.

The invention provides an aviation oil filling system and an aviation oil filling device. The aviation oil filling system comprises a pair of oil barrels and an oil pumping system, the oil pumping system comprises a pair of oil pump assemblies, a filter separator, a flow meter, a rubber pipe reel and an oil filling gun, and the pair of oil pump assemblies are inserted into the pair of oil barrels respectively and make contact with oil in the oil barrels. The pair of oil pump assemblies is sequentially communicated with the filter separator, the flow meter, the rubber pipe reel and the oil gun to form an oil filling loop. Wherein during refueling, one oil pump assembly in the pair of oil pump assemblies is in a working state, and the other oil pump assembly is in an idle state. By arranging the pair of oil barrels, the capacity of the aviation oil filling system is increased, the aviation oil supply volume is improved, and meanwhile by arranging the pair of oil pump assemblies to work in turn, the oil supply efficiency can be improved.

A decision-making tool models emissions of sustainable aircraft fuel (SAF) over a life cycle of the fuel. The decision tool includes a controller module configured to receive data relating to at least one fuel pathway of fuel, where the fuel pathway considers emissions from initial feedstock production to fuel combustion during flight and arrival. The decision tool determines at least one fuel pathway for fueling the aircraft during flight, models an emissions score for the at least one fuel pathway, and then outputs the emissions score where a user may purchase fuel or make other decisions based on the fuel pathway provided by the decision tool.

The invention relates to the technical field of aircraft ground refueling, and discloses an aircraft pressure refueling device which comprises a quick-change connector, a connector body assembly and an adjustable pressure reducing valve. The adjustable pressure reducing valve comprises a valve body, an elastic piston assembly and an adjusting switch, the valve body is arranged between the quick-change connector and the connector body assembly, an inlet used for being communicated with the quick-change connector and an outlet used for being communicated with the connector body assembly are formed in the valve body, and a throttling opening used for being communicated with the inlet and the outlet is formed in the valve body. The elastic piston assembly is arranged at the throttling opening of the valve body, the adjusting switch is arranged on the valve body and connected with the elastic piston assembly, and the adjusting switch is used for driving the elastic piston assembly to increase or decrease the opening degree of the throttling opening. The problem of how to adjust the oil outlet pressure can be solved.

An airport installation including a plurality of types of aircraft in which each aircraft of one type includes a tank containing dihydrogen at a saturation pressure in a first range different from the other first ranges, for each type of aircraft a storage tank at a saturation pressure in a second range associated with the type of aircraft, and for each storage tank pumps or other devices fill from the storage tank the tank of the aircraft of the type for which the first range corresponds to the storage tank.

The invention relates to an aircraft linear refueling platform, and belongs to the technical field of aircraft refueling, the aircraft linear refueling platform comprises a ground well pit body, a refueling unit, a lifting body, a folding refueling arm, a movable connecting arm, a well lid body and a lifting mechanism, the refueling unit is arranged in the ground well pit body, and the refueling unit is connected with a pre-buried oil pipe below an airport apron; the refueling unit is used for filtering fuel oil, the lifting body is slidably arranged in a ground well pit body in the vertical direction, the folding refueling arm is arranged on the lifting body, and the folding refueling arm is used for being unfolded to an aircraft refueling port for refueling or folded on the lifting body for storage. One end of the movable connecting arm is connected with the refueling unit, the other end of the movable connecting arm is connected with the folding refueling arm, and the movable connecting arm is used for conveying fuel oil. The refueling platform has the advantages that when refueling is not conducted, the refueling platform does not occupy the space of the airport additionally, and the possibility that the refueling platform interferes with other equipment of the airport is reduced.

The present application provides a safety detection method and system for a refueling vehicle. Among them, the safety detection method for a refueling vehicle includes: obtaining an automatic driving instruction for the refueling vehicle; wherein, the automatic driving instruction includes an automatic driving path and the parking position of the aircraft to be refueled; in response to the automatic driving instruction, detecting whether a plurality of vehicle interlock devices in the interlock mechanism are in a safe state; if at least one of the plurality of vehicle interlock devices is not in a safe state, controlling the refueling vehicle to brake; if all of the plurality of vehicle interlock devices are in a safe state, releasing the brake on the refueling vehicle and controlling the refueling vehicle to travel along the automatic driving path to the parking position of the aircraft to be refueled or drive away from the parking position of the aircraft to be refueled.

The invention relates to the technical field of aviation, and discloses a multifunctional power-assisted refueling ladder which comprises an AGV chassis body, a push-pull frame is installed on the top of the right side of the AGV chassis body, and a control handle is installed on the push-pull frame; a lifting guide rail is installed on the top of the AGV chassis body, a lifting block is slidably arranged in the lifting guide rail, a lifting platform is installed on the right side of the lifting block, a lifting main machine is installed on the top of the lifting platform, a mechanical arm is installed on the lifting main machine, a hanging buckle is installed at one end of the mechanical arm, and an oil gun is clamped in the hanging buckle. An oil pipe is arranged at the bottom end of the oil gun, and an oil pipe guide wheel is installed on the back face of the AGV chassis body. According to the multifunctional power-assisted refueling ladder, through cooperation of the AGV chassis body and the lifting platform and cooperation of the mechanical arm and the hanging buckle on the lifting platform, automatic lifting and butt joint of the refueling gun are achieved, meanwhile, a control handle and an anti-skid step are arranged, manual operation and maintenance are facilitated, and an oil pipe does not need to be dragged manually.

The invention relates to the technical field of emergency flameout systems, in particular to an airplane refueling vehicle emergency flameout system which comprises a vehicle engine, a generator, a platform anti-collision switch, an engine flameout module, a first relay, a vehicle power source, an alarm and a second relay. The two ends of a normally open contact of the second relay are connected with the signal sending end and the signal input end of the engine flameout module in series respectively, and the engine flameout module is in communication connection with the vehicle engine. And the vehicle power supply, the normally closed contact of the first relay and the alarm are sequentially connected in series. By arranging the generator, the first relay and the alarm, a driver can be reminded through the alarm when the generator is abnormal and the engine flameout module cannot work; and meanwhile, under the condition that the anti-collision switch of the platform is not reset after being closed, equipment operation is stopped emergently, and the vehicle is prevented from being started again.

The present invention relates to a lifting type refueling system, which is mainly composed of a spring support unit, a height-adjustable refueling pipeline, a rotatable joint, a movable arm with an internal self-locking mechanism, a rotatable docking refueling joint, and a lifting unit including a counterweight. The present invention completes the lifting function of the pipeline part by using a lifting unit, ensuring that the system can be completely stored inside the ground well when not in use, does not occupy ground space, and occupies a small space in the ground well, with good storage performance. Through the spring support structure and the lifting pipeline, the system achieves the purpose of refueling devices at different positions and heights, and is particularly suitable for aircraft fuel tanks to be refueled or emptied. In addition, under the condition of meeting the operating height, the overall structural design of this system is more centralized, thereby achieving the purpose of reducing the storage space.

The invention belongs to the technical field of offshore refueling, and discloses an offshore inverted tank refueling system which comprises a first hose, an aviation oil pump, a filter separator, a flow meter, an automatic regulating valve and a second hose which are sequentially connected, and the filter separator is provided with a first communication port, a second communication port, a third communication port, a fourth communication port and a fifth communication port. The first communicating port is communicated with an aviation oil pump, the second communicating port is communicated with a flowmeter, the third communicating port is used for being connected with an oil discharging pipe and used for releasing residual oil to an external device, the fourth communicating port is communicated with a first oil port of an oil return tank through an exhaust valve, and the fifth communicating port is communicated with a first pipeline between the aviation oil pump and a first hose. A second oil port of the oil return tank communicates with the first pipeline, the connecting position is located on the upstream of the connecting position of the fifth communicating port and the first pipeline, and the oil return tank is further provided with an oil discharging port used for releasing residual oil. The offshore tank reversing refueling system is relatively simple in structure, relatively small in supply mode limitation, relatively good in compatibility and relatively high in working safety.

Some embodiments of the present invention may include a caddy for securely storing aircraft pre-flight fuel testing equipment, including a handle, a first compartment configured to securely hold a fuel testing jar, and a second compartment configured to securely hold a fuel cap, wherein the first and second compartment openings are oriented toward the top of the caddy. Aspects of the present invention may also include a method of pre-flight fuel testing of an aircraft, including the steps of removing a fuel cap from the aircraft fuel tank and stowing the fuel cap from the aircraft fuel tank in a preflight fuel testing caddy, and removing a fuel testing jar from the preflight fuel testing caddy for fuel testing.

A gimbal joint includes a first clevis having a first arm defining a slot. The gimbal joint also includes a second clevis having a second arm. The second arm has a curved surface that engages the first arm and allows for relative rotational motion between the first and second clevises. The gimbal joint also includes a pin coupled with the second arm. The pin is slidably received within the slot of the first arm to allow for relative translational motion between the first and second clevises.

The utility model relates to an aircraft refueling vehicle oil temperature sensing and adjusting device, which belongs to the technical field of temperature sensing and adjusting devices, and comprises a mounting guide rail, clamping structures are arranged at two ends of the mounting guide rail, temperature sensing controllers are mounted on the lower surfaces of the two ends of the mounting guide rail, and an electric winder is designed at one end of the mounting guide rail. The outer side of the electric winder is sleeved with shading cloth, stretching structures are installed in the two sides of the installation guide rail, the outer sides of the stretching structures are sleeved with connecting sleeves, the connecting sleeves are fixedly connected with the shading cloth, and cooling flow guide pipes are rotationally installed in the stretching structures.

Provide a system. 【Solution means】 Means for receiving visual data acquired by an unmanned aircraft, Means for analyzing the acquired visual data to detect the existence of illegal acts or waste, Means for notifying in real time information regarding detected illegal acts or waste, Means for providing an interface that enables residents to monitor problems and participate in countermeasure actions, Means for receiving complaints from residents, Means for analyzing the complaints and determining the priority of problems, Means for automating the provision of information to residents, Means for automatically generating and sending countermeasure plans to locations with problems, A system including the above.

1. A support device 20 for supporting a fluid circulation duct C, said support device comprising: a link 22 for supporting the duct by means of two end portions 22a of the link separated from one another in the longitudinal direction, which in cross section adopt a curved shape to support a portion Ca of the duct, the two end portions 22a being connected together by two intermediate portions of the link, each intermediate portion connecting one end 22a1, 22a2 of the two end portions 22a; two links 24, 26 for fastening the support device to an outer structure; and connection elements 28a-28d between the support link 22 and the fastening links 24, 26, each connection element having a fastening link and an intermediate portion of the support link passing through the fastening link and allowing sliding of the fastening link and the support link through the connection element.

The present application discloses a method of determining one or more fuel characteristics of an aviation fuel suitable for powering a gas turbine engine of an aircraft, the method comprising: determining a mass of a fuel being loaded, or which has been loaded, onto the aircraft; determining a corresponding volume of the fuel; determining one or more fuel characteristics of the fuel based on the determined mass and volume. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.

A modular power generation device for supplying electricity to aircraft on ground, comprising: a power unit 1 configured to generate electricity using alternative fuels, said power unit 1 further comprising: - A power generation module 2; - An interface configured to connect with an aircraft as defined by predetermined standards; - An interface configured for interaction with human operators of the device; - Safety systems for the operation of the device; - An interface with a fuel unit 8 for the exchangeable supply of fuel; and - An interface with said fuel unit 8 for the monitoring, command, and control of said fuel unit 8.

Mobile refueling system for refueling a vehicle, in particular an aircraft, from a stationary tank, characterized in that the refueling system comprises a forklift truck (10) driven by a drive mechanism and a module trolley (28) coupled to the forklift truck (10), on which a refueling module (26) is arranged, which has a first connection for connecting to a stationary connection of a stationary tank and a second connection for connecting to a refueling connection of the vehicle.