4 results about "Aircraft fuel system" patented technology

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.

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.

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.

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.