16 results about "Aircraft fuel system" patented technology

The present application belongs to the field of aircraft fuel system, and relates to a kind of integrated design light weight fuel transfer system and method of seaplane. Including Ⅰ, Ⅱ, Ⅲ, Ⅳ, Ⅴ, Ⅵ oil tank on the wing of the aircraft, pressure refueling connector, pressure refueling control valve, oil level controller, pressure refueling control panel, oil pump, low oil level signal. One oil pump integrates the flow of oil transfer system and the flow of emergency oil discharge system two working states, maximally reduces the number of pump;Pressure refueling pipeline, oil transfer pipeline, emergency oil discharge pipeline are integrated designed, reduce the number of pipeline;Thirdly, the low oil level signal of oil tank and the low oil level signal of oil quantity measuring system are shared designed during oil transfer and emergency oil discharge, the on-off control of oil transfer system and the on-off control of pressure refueling are shared designed, the on and off of oil transfer are controlled by pressure refueling control valve, reduce the setting of oil transfer cut-off valve.

An aircraft fuel system includes a first integrated boost stage having a boost pump configured to receive a fuel flow from a fuel tank via a boost supply line, at least one generator collocated with and operatively connected to the boost pump for driving the boost pump, and a tap fluidly connecting the boost pump and the at least one generator for selectively delivering an amount of the fuel flow to the at least one generator. The fuel system further includes a gearbox operatively connected to the at least one generator, and a main stage downstream of the boost stage and operatively connected to the gearbox. The main stage includes a main pump configured to receive the fuel flow from the boost pump along a main supply line, and a filter disposed along the main supply line upstream of the main pump for filtering the fuel flow.

This invention belongs to the field of testing technology, specifically relating to a dynamic shear test device and method for a flexible connection assembly of an aircraft fuel system. The test device includes a reciprocating assembly, a clamping assembly, and a loading assembly. A second push block in the reciprocating assembly is connected to a first locking block in the clamping assembly. The loading assembly is located on one side of the clamping assembly. The reciprocating assembly applies a shear load to the flexible connection assembly. The clamping assembly is responsible for clamping and fixing the test tube. The loading assembly injects pressure into the test tube. By connecting two test tubes using the flexible connection assembly, and controlling the pressurization module in the loading assembly to pressurize the test tube and the electric cylinder in the reciprocating assembly to apply thrust to the test tube, the internal working pressure and external shear load of the flexible connection assembly are tested. This provides standard equipment and methods for conducting life testing research on flexible connection assemblies, and also provides a reference for the selection of flexible connection assemblies.

The invention relates to a fuel tank suitable for a ground simulation test of an aircraft fuel system and a fixing frame of the fuel tank, the fuel tank comprises four groups of fuel tank test pieces with the same structure and capacity as the fuel tank on an aircraft, and the fuel tank comprises a first fuselage fuel tank test piece, a second fuselage fuel tank test piece and two groups of left and right flank fuel tank test pieces, the four groups of fuel tank test pieces and the test equipment are connected through a test pipeline and a communication line; the fixing frame is of a truss structure, a first fuselage fuel tank test piece installation area and a second fuselage fuel tank test piece installation area are arranged in the truss structure, left and right side wing fuel tank test piece installation areas are symmetrically arranged on the two sides of the truss structure, and connecting flanges fixedly assembled with the test bed outer frame are arranged at the front end and the rear end of the truss structure. And the fixed frame is driven by the test bed outer frame to realize pitching and overturning actions. According to the method, the test cost is reduced, the verification period is shortened, the performance parameters in the limit state can be obtained, and the reliability of the test conclusion is ensured.

The present application belongs to the field of aircraft fuel system processing, and relates to a cutting device for polyurethane foam shaping and a use method thereof. The cutting device is used for cutting polyurethane foam by using the shape of a nichrome wire model at high temperature. The nichrome wire model with different shapes is placed in a main body, is lifted to slide along a sliding groove at the top of the main body to one side of the main body, and is rotated to be horizontally placed by a motor. A motor is arranged at the lower part of the side of the main body, and an operation table parallel to the nichrome wire model is fixed above the output shaft of the motor. The polyurethane foam is placed on the operation table, and is controlled to move upwards until the polyurethane foam is attached to the nichrome wire model, so that the cutting of the polyurethane foam is completed. The cutting device uses the nichrome wire model to replace a cutter, can realize one-piece shaping, has a smooth cutting surface, and can prevent the generation of excess scraps by using the electric heating mode, so as to avoid the hidden danger of excess substances. The cutting efficiency and cutting quality of the cutting device are greatly improved, and great convenience is brought to the later inspection.

The present application belongs to the technical field of aircraft fuel system, and relates to an automatic device for jet cleaning of an aircraft fuel system and a use method thereof. The present application adopts a form of a stepping motor matched with a rudder to realize rotation of a three-degree-of-freedom mechanism, achieve accurate positioning in space, adopt program setting of a fixed jet route, drive and control a three-degree-of-freedom steering mechanism to perform omnidirectional jet cleaning according to a specified route, can effectively remove excess materials in the fuel tank, simultaneously increase a fuel cooling system device, realize real-time monitoring of fuel temperature by a built-in temperature sensor, and automatically realize a fuel cooling function, provide suitable temperature fuel for the jet device, avoid the influence of high temperature on each system in the fuel tank, and realize automatic and intelligent cleaning. The automatic cleaning device has a simple operation process, complete cleaning effect, improved cleaning efficiency, reduced production cost, and improved economic benefit of the company.

The invention relates to the field of aircraft fuel oil, in particular to a fault analysis method for a multivariable complex system, which comprises the following steps of: 1, reading all test variable data of a ground simulation test of an aircraft fuel oil system; step 2, inputting fault variables in all test variable data of the ground simulation test of the aircraft fuel system, and determining a correlation coefficient threshold; step 3, performing correlation analysis on each fault variable; according to the method, aircraft fuel system ground simulation test data serves as a sample, aircraft fuel system ground simulation system fault and correlation analysis is achieved around fault variable data, correlation coefficients among fault variables are obtained through calculation, and fault detection is emphasized on strong correlation fault variables.

The invention belongs to the technical field of aircraft refrigerating systems, and particularly relates to an airborne auto-cascade refrigerating system control method and system. The cold source temperature T1 at the fuel supply position of the aircraft fuel system and the heat sink temperature T2 at the liquid return position of the airborne equipment needing temperature control are collected, and when T2-T1 is larger than T02, the airborne auto-cascade refrigeration system operates in an auto-cascade mode; and when T2-T1 is greater than or equal to T01 and less than or equal to T02, acquiring gravity overload or attitude change data of the aircraft, acquiring the temperature T3 and the pressure P3 at the inlet of the gas-liquid separator, constructing an agent model representing the mapping relation of the two-phase inlet state, the gravity condition and the separation efficiency of the gas-liquid separator, and calculating the gas-liquid separation efficiency of the gas-liquid separator through the agent model. The separation efficiency is compared with a preset separation efficiency threshold value, and the airborne auto-cascade refrigeration system is controlled to operate according to an auto-cascade mode or a single-stage compression mode according to a comparison result; when T2-T1 is smaller than T01, the airborne auto-cascade refrigeration system operates in a single-stage compression mode, T01 is the lower threshold value of the difference value between the heat sink temperature T2 and the cold source temperature T1, and T02 is the upper threshold value of the difference value between the heat sink temperature T2 and the cold source temperature T1. According to the invention, efficient and reliable operation of the airborne refrigeration cycle system can be realized in a complex dynamic environment and a wide temperature range working condition.

This invention belongs to the field of target drone fuel systems, specifically relating to a high-stability supersonic target drone fuel system and its fuel sequence management method. The system includes a fuselage fuel tank, a first solenoid valve, a second solenoid valve, a pressurized fuel tank, a fuel pump, an overflow valve, an engine pump, a monitoring module, and a control module. The fuselage fuel tank comprises three sets of fuel tanks arranged sequentially. The first set of fuel tanks is located in the forward section of the target drone fuselage, while the second and third sets are respectively located in the fuel tanks in the middle of the target drone fuselage, positioned before and after the theoretical center of mass of the target drone. This invention places the first set of fuel tanks in the forward section of the fuselage. The fuel system prioritizes consuming fuel from the first set of tanks to adjust for the forward shift of the center of mass after booster separation, ensuring that the stability of the target drone after booster separation remains within a controllable range. Furthermore, because the first set of fuel tanks is positioned forward of the center of mass, only a small space in the forward section is required to complete the overall center of mass adjustment.

A fuel tank system is disclosed. The fuel tank system includes a fuel tank and a detection system associated with the fuel tank. The detection system includes a source device emitting light into the fuel tank and an analysis device. The analysis device includes a collection device capturing scattered light resulting from the emitted light interacting with fuel in the fuel tank and providing an optical signal corresponding to the captured scattered light. The analysis device includes an optical detection device converting the optical signal to an electronic signal representative of properties of the captured scattered light and a computing device. In one or more embodiments, the computing device generates, based on the electronic signal, data including an indication of: a presence or absence of one or more contaminants in the fuel tank, a type of the one or more contaminants, and location information of the fuel and contaminants.

The invention belongs to the technical field of aircraft fuel system design, and discloses an adsorption tank, a ventilation system for a methanol fuel aircraft and the aircraft. The adsorption tank comprises: a carbon tank housing for accommodating an adsorbent; the desorption nozzle assembly is a U-shaped shell with an opening in the upper surface and is communicated with the lower end of the carbon tank shell; the atmosphere mouthpiece is connected with the upper end of the carbon tank shell; the adsorption mouthpiece is connected with the middle part of the lower end of the carbon tank shell and is surrounded by the desorption mouthpiece assembly; filter plates and porous metal plates are arranged at the upper end and the lower end in the carbon tank shell from inside to outside; an adsorbent is filled between the filter plates at the upper and lower ends; a spring is arranged between the porous metal plate at the upper end and the upper panel of the carbon tank and is used for pressing the adsorbent; the carbon tank is provided with a middle filter plate for dividing the adsorbent filling area into an upper subarea and a lower subarea; the upper partition is filled with zeolite molecular sieves, and the lower partition is filled with carbon powder.

The utility model relates to the technical field of aircraft maintenance, concretely is a kind of aircraft fuel system refueling pressure monitoring and emergency cut-off device, including support column, still including the pressure blocking component being set on the upper end of support column, the locking cap being set in the lower end of support column, the utility model is installed on the gravity refueling port of aircraft No. 1 tank, pressure display and control terminal are installed at ground convenient observation position, not only can real-time display the pressure in aircraft tank, but also can emergency cut-off ground refueling equipment when aircraft refueling system failure, improve the security of aircraft refueling process, the device can also meet the aircraft fuel tank tightness test use simultaneously.

The invention belongs to the professional technical field of aircraft fuel systems, and particularly relates to an aircraft fuel tank pressure refueling oil spill test system and method, and the method comprises the steps: refueling an aircraft fuel tank until the pressure at an aircraft refueling joint reaches a set value; collecting pressure and mass data in the aircraft fuel tank at different moments, calculating the oil spill rate in the aircraft fuel tank, and storing the data of different oil spill rates and pressure at different moments in the calculation result; setting a time target value tfinal, judging whether the test end time is not greater than the time target value tfinal or not, and if yes, repeatedly collecting, calculating and storing pressure and quality data; if not, stopping aircraft fuel tank pressure refueling, and ending the test. A high-precision weighing measurement system is adopted, the oil spill rate is dynamically calculated in real time, meanwhile, the pressure at each measurement point of the oil tank is monitored in a distributed mode, the method has the remarkable advantages of being good in accuracy and high in automation degree, and the oil spill capacity of the aircraft oil tank and changes of the oil tank pressure are truly reflected.

This utility model belongs to the field of aviation safety, specifically an explosion-proof enclosure for aircraft fuel system signal acquisition. It includes a main body for the explosion-proof enclosure, an assembly chamber within the main body, a load-bearing block mounted in the assembly chamber, an assembly frame hinged to the load-bearing block, a traction groove and a telescopic cavity within the assembly frame, and a locking mechanism mounted on the traction groove and telescopic cavity. The locking mechanism includes a push rod, which is assembled with the traction groove and telescopic cavity. The push rod is also equipped with a push plate, which is assembled with the traction groove. A connecting plate is also assembled on the push rod, which is assembled with the telescopic cavity. A telescopic spring is also mounted on the push rod. The main body of the explosion-proof enclosure is equipped with a traction mechanism, which includes a vertical block and a support block. The aforementioned explosion-proof enclosure for aircraft fuel system signal acquisition solves the problem of poor stability of the assembly frame, which leads to easy shaking and increased assembly difficulty, through the cooperation of the push rod and push plate.

The invention discloses a multi-degree-of-freedom simulation experiment platform for an aircraft fuel system. The multi-degree-of-freedom simulation experiment platform comprises a pump valve system simulation module, an acceleration adjustment module and a posture adjustment module, the pump valve system simulation module is used for simulating an aircraft fuel system, the acceleration adjustment module is used for changing the acceleration of the pump valve system simulation module, and the attitude adjustment module is used for changing the movement direction of the pump valve system simulation module; the acceleration adjusting module comprises a rotating arm, and the pump valve system simulation module is arranged at the outer end of the rotating arm. When the rotating arm is driven by the power mechanism to rotate at variable speed, the outer end of the rotating arm generates rotating acceleration, and the acceleration magnitude order of the aircraft is simulated through the rotating acceleration of the outer end of the rotating arm. In the invention, the rotating arm drives the pump valve system simulation module to generate rotating acceleration, the actual great acceleration magnitude order of the aircraft is simulated, the working condition difference with the actual aircraft is reduced, and the experimental error is reduced.

The invention discloses a mechanical oil transportation cut-off control valve for an aircraft fuel system, and belongs to the field of aircraft fuel systems, the mechanical oil transportation cut-off control valve comprises a shell, a floater control assembly and an oil transportation control assembly, the floater control assembly and the oil transportation control assembly are mounted in the shell, a valve seat is further arranged in the shell, the valve seat and the shell jointly define an oil transportation cavity, and a floater oil duct and a piston oil duct are arranged on the valve seat. The floater oil duct and the piston oil duct are both communicated with the oil conveying cavity; the floater control assembly comprises a floater valve, a floater support and a floater element, one side of the floater support is rotationally connected with the valve seat, the other side of the floater support is fixedly connected with the floater element, one end of the floater valve extends into the floater oil duct, and the other end of the floater valve penetrates through the floater oil duct to extend out and is connected with the floater support; the oil conveying control assembly comprises a piston and an oil conveying pipe, one end of the piston extends into the piston oil duct, the other end of the piston penetrates through the piston oil duct and extends out to be connected with the floater support, and the piston oil duct is connected with the oil conveying pipe, so that emergency operation of an oil conveying passage can be cut off in advance.