144results about "Liquid handling installations" patented technology

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 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.

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.

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 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.

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.

The invention relates to a self-walking lifting aircraft refueling ladder, an aircraft refueling carrier and a refueling method. A refueling ladder bracket composed of a fixed frame, a movable bracket, a hydraulic cylinder, a first limiting block, a second limiting block and a lock pin is arranged, and a platform base of a self-walking platform is correspondingly provided with a pin hole; the movable bracket is driven to ascend and descend through the hydraulic cylinder, the first limiting block and the second limiting block are clamped and fixed, and the lock pin and the pin hole are accurately matched to achieve locking. Compared with the prior art, manual multi-step operation is not needed, through hydraulic cylinder driving and mechanical limiting and locking structure linkage, the separation and hanging processes of the refueling ladder and the refueling carrier are simplified, the locking reliability and stability are improved, the safety risks such as overturning and accidental separation are effectively reduced, and the operation preparation and storage efficiency is improved.

The invention provides a pipeline refueling vehicle. The pipeline refueling vehicle comprises a chassis, a refueling platform, a first hydraulic cylinder, a hand pump and a first pipeline. Wherein the first hydraulic cylinder is arranged on the chassis, connected with the refueling platform and used for lifting the refueling platform; the first pipeline is connected with the first hydraulic cylinder and the hand pump, and the hand pump pumps hydraulic liquid into the first hydraulic cylinder through the first pipeline. By operating the hand pump, hydraulic liquid can be pumped into the first hydraulic cylinder, and the refueling platform is lifted through the first hydraulic cylinder. The hand pump pumps liquid into the first hydraulic cylinder in a mechanical transmission mode and does not depend on a motor, in the process that the refueling platform is used for refueling an airplane, if the pipeline refueling vehicle abnormally flames out and cannot be started, the refueling platform can be rapidly and reliably lifted through the arrangement, and the safety of the refueling platform is improved. The pipeline refueling truck can be rapidly evacuated from the site, the emergency processing capacity of the pipeline refueling truck on the aircraft refueling operation site is improved, and the pipeline refueling truck is convenient to use.

A fuel line terminating in a refuel connector is used to fuel or defuel an aircraft, for example with liquid hydrogen. A supply of nitrogen housed on an aircraft, for example a Nitrogen Generating System, is used in conjunction with a gas line to supply nitrogen into the fuel line, to flush out potentially combustible materials before liquid hydrogen is supplied through the fuel line. The aircraft supply of nitrogen is also used to supply inert gas, via a gas line, to the Ground Support Equipment refuelling or defuelling the aircraft. This can provide redundancy for the Ground Support Equipment's systems, and may allow the aircraft to operate at less well-equipped airports.

The utility model provides a fuel conveying device and a flight system. The fuel conveying device comprises a control device, an oil pump and an oil storage device. Wherein the control device is connected with the oil pump, the oil pump is connected with an aircraft oil tank through a first oil way, and a three-way valve is further arranged on the first oil way; the oil pump is further connected with the oil storage device through a second oil way. The control device is used for controlling the oil pump to rotate forwards and controlling the three-way valve to be powered off, and air in the first oil way and air in the second oil way are exhausted. The control device is used for controlling the oil pump to rotate forwards and controlling the three-way valve to be powered on, and refueling is conducted on the aircraft oil tank from the oil storage device. The control device is further used for controlling the oil pump to rotate reversely and controlling the three-way valve to be powered on, and oil is pumped from the aircraft oil tank to the oil storage device. According to the invention, manual operation is reduced, and the working efficiency is improved.

An apparatus for supplying gas from an aircraft (100, figure 1) to ground equipment (110) comprising a gas supply 318 housed within an aircraft, and at least one gas line 322 in communication between the aircraft gas supply and the ground equipment. The gas used may in this instance comprise liquid hydrogen. A supply of nitrogen 318 housed on an aircraft, for example a Nitrogen Generating System, is used in conjunction with a gas line 322 to supply nitrogen into the fuel line 316, to flush out potentially combustible materials before liquid hydrogen is supplied through the fuel line 316. The aircraft supply of nitrogen 318 is also used to supply inert gas, via a gas line 334, to the Ground Support Equipment (110, figure 1) refuelling or defueling the aircraft 100. This can provide redundancy for the Ground Support Equipment’s systems, and may allow the aircraft (100) to operate at less well-equipped airports. The application comprises a plurality of apparatus and methods relatable to hydrogen / cryogenic refuelling.

The invention relates to a towed aircraft refueling system which comprises a refueling control device, an interlocking device, a hydraulic device and an electric control device. The refueling control device is installed on a pipeline refueling trailer and comprises a ground well hose connector, a ground well hose, a coarse oil filter assembly, an electromagnetic pressure control valve, a rotary connector, a flow control electromagnetic valve, a filter, a flow meter, a safety relief valve, a reel ball valve, a venturi tube, an oil conveying hose and a pressure refueling connecting nozzle which are sequentially connected. The ground well hose connector is used for being connected with a ground well valve on an airport apron so as to introduce aviation oil. The pressure refueling nozzle is used for being connected with an aircraft fuel tank inlet to complete refueling. The interlocking device is used for performing brake interlocking and refueling oil path interlocking control on the refueling control device; the hydraulic device is used for providing hydraulic driving force for a hydraulic execution component on the refueling trailer; the electric control device is used for providing a control circuit for the refueling control device. Compared with the prior art, the invention has the advantages of maneuverability, flexibility, easy operation, energy conservation, economy, safety, environmental protection and the like.

The application relates to an aircraft straight-line refueling platform, belonging to the technical field of aircraft refueling, which comprises a ground well pit body, a refueling unit, a lifting body, a folding refueling arm, a movable connecting arm, a well cover body and a lifting mechanism, the refueling unit is arranged in the ground well pit body, the refueling unit is connected with a pre-buried oil pipe below a parking apron, the refueling unit is used for filtering and treating fuel, the lifting body is slidably arranged in the ground well pit body in the vertical direction, the folding refueling arm is arranged on the lifting body, the folding refueling arm is used for being unfolded to the aircraft fueling port for refueling or being folded on the lifting body for storage, one end of the movable connecting arm is connected with the refueling unit, and the other end is connected with the folding refueling arm, and the movable connecting arm is used for conveying fuel. The application has the effect that when fuel is not added, the refueling platform does not additionally occupy the parking apron space, and the possibility of interference between the refueling platform and other equipment of the airport is reduced.

To improve safety during charging of an electric flight vehicle.SOLUTION: An electric flight vehicle 10, which flies by rotating a rotary wing 13 by electric power supplied from a battery 14, comprises output equipment 15 that performs output for calling attention outward from the electric flight vehicle 10 during the charging of the battery 14 from an external power source 20.SELECTED DRAWING: Figure 1

A power system for an engine that can be used in an aircraft, a marine vessel or a land vehicle has a storage tank containing ammonia. An engine supported on the vehicle is configured to operate using hydrogen gas as fuel. A cracking device in or adjacent the engine receives heat from operation of the engine, e.g., from a compressor or a combustion chamber, and also receives ammonia from the storage tank, and it uses the heat from the engine to dissociate the ammonia to produce hydrogen gas. The cracking device supplies the hydrogen gas to the engine, which has a combustor in which combustion of the hydrogen gas takes place. The energy from the combustion drives the engine so as to provide mechanical energy.

This invention provides a pipeline shut-off valve, comprising a valve body and a valve core. An inlet and an outlet are respectively located at both ends of the valve body. A valve seat is provided within the valve cavity. A drive unit is located at the front end of the valve core. The drive unit drives the valve core to move linearly relative to the valve seat, closing or opening the valve port between the inlet and outlet. A diaphragm forms a sealing structure between the valve core and the valve seat. When the drive unit drives the valve core to move, the diaphragm flips to adapt to the relative movement between the two. The diaphragm forming the sealing structure between the valve core and the valve seat ensures a reliable sealing effect during the valve core's movement relative to the valve seat. The diaphragm does not rub against the valve core or valve seat, resulting in no wear. The valve port is opened and closed pneumatically, providing rapid response and ensuring quick pipeline connection and disconnection. The entire drive unit is located inside the pipeline shut-off valve, resulting in a small valve size, which is beneficial for pipeline layout.

In one aspect, a system for charging an aircraft can include a robotic charging device, and a computing system configured to obtain data associated with a transportation itinerary and energy parameter(s) of the aircraft. The data associated with the transportation itinerary can be indicative of an aircraft landing facility at which the aircraft is to be located. The computing system can determine (e.g., select) a robotic charging device from among a plurality of robotic charging devices for charging the aircraft based on the transportation itinerary data and energy parameter(s) of the aircraft; determine charging parameter(s) for the robotic charging device based on the transportation itinerary data; and communicate command instruction(s) for the robotic charging device to charge the aircraft according to the charging parameter(s). The robotic charging device can be configured to automatically connect with a charging area of the aircraft for charging a battery onboard the aircraft.

The invention discloses a foldable universal warning flagpole for an aviation oil pipeline refueling truck, which belongs to the technical field of warning flags for refueling trucks and comprises a support, a support rod, a first elastic part, a fixing rod, a sound production component, an adjusting component and a plurality of warning flags. A fixing rod is installed at the other end of the supporting rod through a first elastic piece, a sound production assembly is installed at the bottom of the fixing rod, an adjusting assembly is installed on the fixing rod, and a plurality of warning flags are arranged on the adjusting assembly and detachably connected with the fixing rod. According to the invention, a sound alarm can be actively sent to the surrounding environment through the sound production assembly, so that a worker can make a quick response after a collision accident; active alarming is achieved by communicating the sound production assembly with the external air source, the method is completely independent of external power supply, the electric spark risk is completely eradicated, the anti-explosion requirement of an aviation fuel oil filling operation scene is met, and the safety of the aviation fuel oil filling process is remarkably improved.

An improved fluid transfer accuracy, information collection, and overall management. A system may utilize a pump to transfer fluid from a source to a target vessel, a meter for measuring an amount of fluid transferred, a density meter to detect actual fluid density, and a control unit to determine actual fluid transfer amount based on density. As an example, a fluid flow meter can be coupled with a flow conduit to determine fluid volume, along with the density meter to detect real-time density of transferred fluid. During a fluid transfer event, such as aircraft refueling, LPG fueling, or other refined fuels or valuable liquids, fluid volume can be converted to fluid weight in real-time based on actual density. The real-time fluid weight can be used to determine if a target fluid weight has been reached, and fluid flow can be shut off at the appropriate time.

The invention belongs to the field of unmanned aerial vehicle refueling, and particularly relates to an unmanned aerial vehicle refueling system and method. In order to reduce the occupied space of the refueling system and ensure that mixed fuel oil is evenly mixed, the unmanned aerial vehicle refueling system comprises a lubricating oil container, a refueling butt joint mechanism and an aviation kerosene container communicated with the refueling butt joint mechanism through a main pipeline, and a metering pumping mechanism is arranged on the main pipeline. The lubricating oil container is located above the main pipeline and communicated with the main pipeline through an auxiliary pipeline, and a flow valve is arranged on the auxiliary pipeline. The communicating position of the auxiliary pipeline and the main pipeline is located on the downstream of the metering pumping mechanism, and a pipeline stirrer is arranged on the portion, located between the communicating position of the auxiliary pipeline and the main pipeline and the refueling butt joint mechanism, of the main pipeline. The invention further correspondingly provides an unmanned aerial vehicle refueling method. In the invention, the gravity and the kinetic energy of the oil are reasonably utilized, so that only one metering pumping mechanism is utilized for refueling, the occupied space is reduced, and the oil is mixed twice to ensure uniform mixing.

Disclosed is a method of determining an operating condition of a valve of an aircraft system. The method includes obtaining a first time period associated with actuating the valve, and a second time period associated with actuating the valve. The method includes providing an indication of an altered operating condition associated with actuation of the valve based on the first and second time periods.

The unmanned aerial vehicle refueling system comprises a first to seventh oil circuit, an oil outlet ball valve, a pump inlet pressure gauge, an electric pump, a pump outlet pressure gauge, a filter separator, a flow meter, an electromagnetic valve one, a manual refueling ball valve, a reel, a first joint, an electromagnetic valve three, a flow regulating valve, an automatic exhaust valve, an electromagnetic valve two, a pair of clamping ball valves, a hand pump, a sediment ball valve, a filling ball valve, a liquid level control valve and a tank body.

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 ground refueling management system of the present disclosure utilizes various components already existing in an aircraft ground refueling vehicle to characterize and track, in real time, events of an aircraft refueling operation. The components include a fuel meter, a fuel delivery deadman sensor, a fuel nozzle sensor and a ground refueling vehicle brake sensor. Data from these components in combination with data provided by a mobile computing device that is integral to the refueling operation provide the data points to determine the amount of time elapsed for each event of the refueling operation. Knowledge of each event of the refueling operation provides the opportunity for identifying where time spent can be reduced.

The application provides a kind of override architecture of cut-off valve and its installation method and operation method, even if the control solenoid fails and is invalid, it can make the gas path normally on-off, the fuel path normally on-off, so as to normally supply oil to fuel tank or stop. The override architecture of cut-off valve comprises: a manual override device, which is arranged away from the control solenoid and the cut-off valve in the original machine pressure pipeline; a transmission assembly, the input end of which is connected to the manual override device, and the output end of which is connected to the original machine pressure pipeline, which can transmit the movement of the manual override device to the original machine pressure pipeline; an elastic sealing assembly in the pipe, which is connected to the output end of the transmission assembly, and blocks the gas inlet of the original machine pressure pipeline to form a normally closed sealing structure, when the manual override device works, the gas path is conducted, and the fuel path is conducted, when the manual override device stops working, the gas path is disconnected, and the fuel path is disconnected.

The invention discloses a ground oil transportation system for interacting with an aircraft, relates to the technical field of aviation oil transportation, and can solve the problems that an existing oil pipe cannot be unlocked and released under huge traction force, and leakage is easily caused. The embodiment of the invention discloses a ground oil transportation system for interacting with an airplane, which comprises an oil pipe for transporting oil to the airplane, and a storage module, a guide tensioning module and a clutch module which are arranged on a chassis, and the oil pipe is wound on the storage module through the guide tensioning module; one end of the storage module is rotationally connected to the base plate, the other end of the storage module is connected with the guiding and tensioning module, and the clutch module is meshed with the end, close to the guiding and tensioning module, of the storage module in the circumferential direction; under the condition that the oil pipe is pulled to cause deformation of the guide tensioning module, the oil pipe drives the end, connected with the guide tensioning module, of the storage module to move in the axial direction through the guide tensioning module and enables the storage module to be subjected to diameter shrinkage deformation, the storage module is disengaged from the engagement and disengagement module, and the storage module can freely release the oil pipe.