297results about "Aircraft maintainance" patented technology

The invention relates to an aircraft fuel system fault isolation and maintenance decision-making method based on a knowledge graph, and the method comprises the steps: employing an equipment tree analysis method to disassemble an aircraft fuel system into a plurality of maintenance units of different levels, and obtaining system knowledge data; obtaining fault knowledge data and maintenance knowledge data of each maintenance unit; constructing a fault isolation and maintenance knowledge graph according to the obtained system knowledge, fault knowledge and maintenance knowledge; and obtaining a to-be-matched fault early warning result output by the fault early warning system, searching a matched entity in the fault isolation and maintenance knowledge graph, and outputting a corresponding fault isolation and maintenance decision. According to the invention, accurate fault isolation suggestions and maintenance decisions can be quickly generated according to fault information, the maintenance work efficiency can be greatly improved, and accurate maintenance of equipment is realized.

The present disclosure provides techniques for deep reinforcement learning to achieve full-cycle automation in airplane component failure prognostics. Flight data is preprocessed to identify parameters representing operational characteristics of an airplane component. A reinforcement learning framework is formulated based on the preprocessed flight, comprising defining a state representation as an input to a policy model, determining an action of sending an alert or not based on the state representation, modeling one or more system behaviors in response to the action using the preprocessed flight data, calculating a reward of the action under the state representation using a predefined reward structure, collecting training data by simulating an airplane component prognostic procedure. The policy model is trained using a learning and optimization algorithm with the training data to increase an expected discounted cumulative reward by choosing an action under the state representation.

A folding wingtip aircraft includes a wing that includes a primary portion and a wingtip. The folding wingtip aircraft includes a folding wingtip system configured to rotate the wingtip relative to the primary portion. The folding wingtip aircraft also includes a flight control computer. The flight control computer is configured to, in response to a first determination that a wingtip position of the wingtip is not in a folded position when a second determination indicates that a last completed command by the folding wingtip system was a fold command, set error codes for the folding wingtip system. The flight control computer is also configured to change a setting to indicate that the folding wingtip aircraft is grounded based on the error codes.

A method for repairing a zone of a metal structural aircraft part having a protection defect in the vicinity of an orifice for receiving a fastener. There is a step of positioning an isolation element on the zone around the orifice, a step of applying a coat of paint to the zone, covering the isolation element, and a step of inserting a metal fastener into an orifice of the isolation element, prior to or following the step of applying the coat of paint. The metal of the fastener is in contact with the isolation element, itself in contact with the metal forming the aircraft structure.

The utility model discloses a multi-degree-of-freedom adjustable undercarriage disassembling and assembling device which comprises a movable base, a lifting mechanism, a fine adjustment mechanism, a support adjusting mechanism, a control cabinet and four axle supports. According to the multi-degree-of-freedom adjustment undercarriage dismounting and mounting device, horizontal movement is achieved through the movable base, lifting movement is achieved through the lifting mechanism, angle adjustment is achieved through the fine adjustment mechanism, and therefore three-dimensional movement of an undercarriage in the mounting process and accurate alignment with a standard mounting angle are achieved, and the problem that manual angle adjustment is difficult is solved; the disassembly and assembly processes of the undercarriage are more efficient and convenient; the support adjusting mechanism is used for adjusting the distance between the four axle supports, so that the four axle supports can be suitable for most undercarriages of common models, and the operation cost of airlines and maintenance factories is greatly reduced.

An example method performed by a computing system for determining a maintenance interval for a subject aircraft configuration comprises obtaining sensor data reported by an electronic system of a population of the subject aircraft configuration. The method further comprises obtaining a failure mode definition that identifies a set of failure modes involving a component of the subject aircraft configuration. The method further comprises implementing a first predictive model to determine a first lifetime-probability distribution of a failure mode involving the component based on the sensor data. The method further comprises implementing a second predictive model that differs from the first predictive model to determine a second lifetime-probability distribution of a failure mode involving the component based on the sensor data. The method further comprises determining a maintenance interval for the component based on the first lifetime-probability distribution and the second lifetime-probability distribution.

Tracking a maintenance compliance window of opportunity is provided. The method comprises receiving an alert in response to an aircraft system exceeding an operational threshold or failing to transmit a report. A lead time countdown to a compliance deadline is started in prescribed units. Elapsed and remaining units, out of a total number of allotted units in the lead time, are calculated based on reports from sources defining an operating cycle of the aircraft system. The countdown is displayed in a user interface as a normalized sliding scale of elapsed percentage of total number of allotted units in the lead time. The remaining units out the total number of allotted units are also displayed in the user interface. The countdown is ceased in response to the first of: resolution of the alert or the countdown reaching the compliance deadline, wherein the lead time has completely elapsed.

The utility model relates to the technical field of aircraft repair dock, and particularly provide a kind of nose dock compatible multiple models, including right side lifting general platform, left side lifting general platform and radar platform, first windscreen platform, second windscreen platform, third windscreen platform and fourth windscreen platform, right side lifting general platform and left side lifting general platform all include a layer of platform, second floor and third floor;Radar platform includes radar platform support and radar platform board, and first windscreen platform is fixedly arranged on radar platform board;Second windscreen platform and third windscreen platform are translationally connected on the layer of platform of right side lifting general platform and left side lifting general platform, and fourth windscreen platform is translationally connected on third windscreen platform.The utility model can adjust the overall height of nose dock according to the height of different model aircraft, and according to windscreen position, different windscreen platform is used to maintain windscreen, and material can be conveniently transported into or out of aircraft.

The application discloses a lifting steering device and a screwing detection device for aircraft maintenance applied by the lifting steering device, and belongs to the technical field of aircraft maintenance. The lifting steering device comprises a base, a threaded cavity is arranged on the base, a threaded block is arranged in the threaded cavity, the threaded block is installed at the lower end of a lifting rod, and the threaded block is engaged with the inner wall of the threaded cavity through threads. The upper end of the lifting rod is provided with a first driving wheel, a second driving wheel is arranged above the first driving wheel, and a gap is kept between the second driving wheel and the first driving wheel. The screwing detection device comprises a main shaft, a conversion box is installed on the main shaft, a second driving reduction motor is installed on the conversion box, the second driving reduction motor is connected with a first bevel gear in a power manner, and a second bevel gear is installed on one side of the first bevel gear. By controlling the forward and reverse rotation of each motor, the lifting, screwing and clamping operations of the working end in the equipment can be realized, so that the working end of the device reaches the construction area which is difficult to reach to perform detection and operation.

The utility model discloses a fuel oil enclosed switch performance test device, which belongs to the technical field of aviation repair, and comprises a left clamp, a right clamp, an inflatable gland, pull rods, a rubber pad and the like, the left clamp and the right clamp form an openable annular structure for clamping a fuel oil enclosed switch, the openable annular structure is fixedly provided with four pull rods, one side of the inflatable gland is provided with an oil inlet nozzle, and the other side of the inflatable gland is provided with an oil outlet nozzle. A groove is formed in the other side, four through holes are formed in the circumference, a rubber pad is installed in the groove, a pull rod penetrates through the inflation gland and then is matched with a butterfly nut, and the fuel oil sealing switch is tightly pressed on the inflation gland. According to the utility model, the problem of poor sealing of the original tool and the enclosed switch is solved.

The universal maintenance dock comprises a maintenance assembly and an aisle assembly, the maintenance assembly comprises a first supporting frame and a maintenance platform, the first supporting frame is provided with a first lifting mechanism, a plurality of first trundles are arranged at the bottom of the first supporting frame, and the maintenance platform is arranged at the top end of the first lifting mechanism; the aisle assembly comprises a second supporting frame and an aisle platform, a second lifting mechanism and a third lifting mechanism are arranged at the two ends of the second supporting frame respectively, a plurality of second trundles are arranged at the bottom of the second supporting frame, and the top end of the second lifting mechanism is rotationally connected to one end of the aisle platform; the top end of the third lifting mechanism is hinged to the other end of the aisle platform, the ends, close to each other, of the aisle platform and the maintenance platform are hinged to each other, and the aisle platform can be adjusted in a telescopic mode in the length direction. According to the universal maintenance dock, airplanes of different models can be maintained, and the practicability is better.

A roller arrangement for a moveable control surface of an aircraft component includes a roller, a fitting, and an adapter sleeve. The roller component has a shaft and a wheel coupled to a roller end of the shaft, wherein the wheel is configured to rotate about a major longitudinal axis of the shaft. The fitting is couplable to the moveable control surface, and it includes a support opening defined therein. The support opening is shaped, sized, and configured to accommodate passage of the wheel therethrough. The adapter sleeve includes an interior passageway defined therein, wherein the interior passageway is shaped, sized, and configured to removably receive and couple with the shaft of the roller component. The adapter sleeve is removably secured to the fitting, to inhibit lateral movement of the adapter sleeve relative to the fitting.

A composite structure and methods are presented. A method of performing a composite repair is presented. A fiber mixture is forced through a composite structure and into a void of the composite structure, the fiber mixture comprising an adhesive and a plurality of electromagnetically steerable fibers. An electromagnetic field is applied to the fiber mixture within the void of the composite structure. The adhesive of the fiber mixture is cured to form the composite repair with structural capabilities.

The utility model discloses an aircraft landing gear state comprehensive simulation device, which belongs to the field of simulation devices, and comprises a device main body, a first adapter cable and a second adapter cable, the first adapter cable and the second adapter cable are connected with the device main body, a display is embedded in the middle of one side surface of the device main body, a switch and socket assembly is arranged around the display, and the first adapter cable and the second adapter cable are connected with the device main body. The switch and socket assembly specifically comprises a first quick-release cable socket embedded in the edge position of one side above the display, a second quick-release cable socket is embedded in one side of the first quick-release cable socket, and a power switch is embedded in the side, away from the first quick-release cable socket, of the second quick-release cable socket. A power socket is embedded in the side, away from the second quick-release cable socket, of the power switch, and a self-checking key switch is embedded in one side of the displayer. According to the utility model, automatic protection and visual display of the airplane state when the airplane state logic is disordered are realized, and normal airplane performance is ensured.

The present application relates to the technical field of aircraft body structure repair, in particular to a method for improving the adhesion of composite material bonding repair metal structure, comprising the following steps: determining the damage range by visual inspection and non-destructive testing method; then using artificial polishing method to pretreat the surface of the damaged part; preparing composite patch material, adhesive and related auxiliary materials; laying the patch according to the design requirements; packaging the vacuum bag, installing the heating unit and curing; post-processing the patch; checking the composite patch; according to the gap size and area size of different regions, cutting the appropriate size of glass fiber fabric; marking the installation position of the patch by using the red pencil line method; mixing the glue; cutting a layer of glass cloth, the size of which is larger than the total size of the required filling size, and the glass cloth is treated by dipping in glue. The present application can effectively control the thickness of the glue layer, increase the controllability of the repair process, improve the tensile shear strength after bonding, effectively improve the actual repair effect, and meet the actual use requirements.

The utility model discloses an aircraft bleed air auxiliary test device, and relates to the technical field of aviation aircraft valve test and maintenance, the aircraft bleed air auxiliary test device comprises a test cabin and a test bench, the middle part of the upper surface of the test bench is provided with an aircraft valve through a tool module, and two ends of the aircraft valve are respectively provided with an air inlet adapter and an air outlet adapter; a first valve connector is arranged at the other end of the aircraft valve, and a second valve connector is further arranged at the position, close to the middle, of the aircraft valve. According to the design, the rapid clamping and replacing efficiency of the aircraft valve can be improved, various valves are connected in series / in parallel, different valves can be opened and closed according to different testing requirements, switching of testing pipelines is achieved, the testing efficiency is improved, the testing cost is reduced, and the testing efficiency is improved. The multi-purpose machine is achieved, full-intelligent data collection is adopted, all parameters such as pressure and flow can be fed back to an external operation computer in real time, and real-time checking is facilitated.

A repair method comprises arranging a thermoplastic patch (40) on a thermoplastic aircraft component (38), each including a thermoplastic matrix with fibres, arranging a metal plate (58B) against the patch (40) and the aircraft component (38), and consolidating the patch (40) and the aircraft component (38) by concurrently induction heating the patch (40), the aircraft component (38) and the metal plate (58B). Preferably, the induction heating involves generating eddy currents to excite the fibres in the thermoplastic patch (40), the fibres in the thermoplastic aircraft component (38). Meanwhile, the heated metal plate (58B) heats the patch (40) and aircraft component (38) by conduction. A second metal plate (58A) may be provided on an opposite side to the first. Preferably, the patch (40), aircraft component (38) and the metal plate(s) (58A, 58B) are provided in a vacuum bag (70) used to apply pressure during consolidation.

This invention relates to a maintenance and testing device for an aircraft air conditioning system. An engine testing module emits sound waves, which are detected by a piping testing module. The collected signals are analyzed and processed in the main controller to obtain a diagnostic result regarding whether the air conditioning system is damaged. It can accurately determine the physical health status of the air conditioning system and accurately identify any physical damage, with high accuracy and a simple testing method. Simultaneously, it detects temperature parameters at the engine, piping, and cockpit to determine the air conditioning system's operational health index. By detecting the air composition in the cockpit during air conditioning operation, it can detect the cockpit safety index. It can effectively analyze the air conditioning's operating efficiency and the cockpit safety index, ensuring that aircraft that pass the inspection will not pose a danger during missions.

A portable sediment discharge ground supporting device is suitable for carrying out sediment discharge maintenance operation on an auxiliary fuel tank of an airplane and comprises a rod-shaped ejector rod, a plurality of supporting rods and a plurality of supporting rods, the shape of the cross section of the ejector rod is matched with the shape of a sediment discharge valve of the auxiliary fuel tank, and the supporting rods are arranged on the supporting rods. A space for accommodating fuel oil deposits is formed in the oil collecting part; the auxiliary fuel tank is provided with an oil collecting part and an oil collecting part, the flow guiding part is formed into a long and thin pipeline, one end of the flow guiding part is connected to the oil collecting part in a fluid communication mode, and the clamping part is connected with the auxiliary fuel tank in a mechanical matching mode. By means of the portable sediment discharging ground supporting equipment, a ground operator can complete auxiliary sediment discharging maintenance operation of the fuel tank under the condition that long-term handheld operation is not needed, and therefore the operation efficiency can be effectively improved.

This invention provides a helicopter concealed folding maintenance ladder, comprising: a folding assembly (3), a telescopic assembly (4), a fixing assembly (5), a telescopic assembly wire lock (6), a folding assembly wire lock (7), and a conformal stringer (8); the fixing assembly (5) is fixed inside the tail beam, one end of the telescopic assembly (4) passes through the fixing assembly (5), and the other end is connected to the inner side of the folding assembly (3) via a single / double ear connector (9), and a conformal stringer (8) is provided on the outer side of the folding assembly (3); the folding assembly (3) and the telescopic assembly (4) can be opened and closed by folding / unfolding and extending / retracting, for use by maintenance personnel; the telescopic assembly wire lock (6) is used to lock and unlock the telescopic assembly (4) after it has been extended or retracted, and the folding assembly wire lock (7) is used to lock and unlock the folding assembly (3) after it has been folded and unfolded. It can be concealed inside the tail beam and has a folding function.

The invention relates to a propeller blade for an aircraft propeller, comprising a wing section (10) and a propeller blade root (20) connected thereto, as well as a method for repairing such a propeller blade. The wing section (10) can have a foam and / or honeycomb core (11, 12, 13) with a sheath (14) made of a fiber-reinforced polymer material. The propeller blade root (20) can be made of a metallic material and comprise a shaft (21) extending into and connected to the wing section (10), at least one outer bearing ring (23), and an adjustment pin (22). It is preferred that the bearing ring (23) has a running surface consisting of a layer (26) of a steel material welded or remelted onto the bearing ring (23), which has a yield strength Rp0.2 of over 750 N / mm² and a tensile strength Rm of over 1,000 N / mm².The bearing ring (23) with the running surface can have a core Vickers hardness HV10 of over 430.

The invention relates to a system and method for aircraft structure repair plan design. According to the technical scheme, the aircraft structure damage can be automatically recognized to determine the damage information, and the damage information comprises the geometric parameters, the position and the type of the damage. And based on the damage information, generating a repair scheme by referring to the digitally processed structure repair manual and structure repair rule base, and projecting the repair scheme to the skin surface.

The application relates to the technical field of pressure switch repairing, and discloses an aircraft generator pressure switch assembly repairing method, which comprises the following steps: drilling off the pin; removing the switch assembly and a first sealing ring; removing a clamping ring and a first gasket; sequentially removing a sealing bushing, a piston, a spring and a second gasket, and removing a second sealing ring on the sealing bushing; welding a new micro switch with a wire, and fixing the micro switch to a mounting joint; using a packaging glue and a catalyst mixture to package the mounting joint, and curing the mounting joint according to selected conditions; sequentially mounting the second gasket, the spring, the piston and the sealing bushing to a pressure switch shell; mounting the first gasket and the clamping ring; mounting the first sealing ring to the switch assembly, and fastening the switch assembly to the shell; testing and adjusting the opening pressure and the closing pressure on a test bench; drilling a hole at a position deviated from an original pin hole, and mounting a new pin, and thus the repairing of the pressure switch is completed. The pressure switch with faults can be repaired instead of being replaced, so that the problem of the pressure switch fault is solved at a low cost.

A propulsion system for an aircraft includes a propulsor rotor, a powerplant, a nacelle and a lockout system. The powerplant is coupled to and configured to drive rotation of the propulsor rotor. An electrical system for the powerplant is configured to receive electrical power from an electrical power source. The nacelle includes an access structure configured to move between a first position and a second position. The access structure at least partially covers the electrical system when in the first position. The access structure is arranged in the first position for propulsion system operation. The access structure is operable to be arranged in the second position for propulsion system maintenance and / or propulsion system inspection. The lockout system is configured to automatically trigger an operation to cut off the electrical power to the electrical system from the electrical power source when the access structure moves away from the first position.

The utility model relates to a cable take-up and pay-off device for a ground well, which comprises an aircraft plug mounting bracket, a cable guide device, a branching frame and a cable tray, the aircraft plug mounting bracket is used for bearing an aircraft plug, and the cable guide device comprises a left guide wheel, a right guide wheel and a front guide wheel. Rotating shafts of the left guide wheel and the right guide wheel are vertically arranged and are rotationally mounted on two sides of the front end of the upper part of the aircraft plug mounting bracket respectively; a rotating shaft of the front guide wheel is horizontally arranged and perpendicular to the two sides of the frame structure, and the front guide wheel is rotationally installed below the left guide wheel and the right guide wheel. The branching frame is of a plate-shaped structure and is used for isolating cables in respective areas in a zoning manner; the cable tray is arranged in the ground well and used for bearing the cable and preventing the cable from directly making contact with the ground. The cable take-up and pay-off device can achieve convenient take-up and pay-off of the cable, and the cable is not prone to being clamped and knotted in the take-up and pay-off process.

The utility model provides wide -bodied aircraft air inlet channel overhauls work platform, including platform base, the head one end of platform base is fixed with the parallel arrangement's outer extension pole, the top of platform base is fixed with the stand, is installed with the inclined arrangement's cat ladder structure between stand and platform base, the inner side wall of stand is slidably installed with the lifting column through a plurality of guide wheels, is provided with the ladder pole between lifting column, the top of lifting column is fixed with the top platform, is fixed with the top frame between top platform and lifting column, is installed with the lifting adjusting device between top platform and platform base. This work platform can be used for aircraft air inlet channel overhauls, can conveniently integral removal to the position of need overhauls, and conveniently carries out the platform height's adjustment according to the overhauls height, to enhance the adaptability of use, has effectively improved the overhauls efficiency, has reduced the overhauls operation intensity.

The invention relates to the technical field of aero-engine maintenance, and discloses a maintenance method for reducing the failure rate of aluminum element content exceeding of lubricating oil of an accessory casing of an aero-engine so as to reduce the failure rate of aluminum element content exceeding of the lubricating oil of the accessory casing of the aero-engine. Comprising the following steps: 1) according to an easy-to-wear area of an aluminum bushing of an accessory casing to be maintained, determining a corresponding area of the aluminum bushing to be strengthened as a laser shock strengthening area, and setting machining allowance; (2) determining a deformation control area and machining allowance of the aluminum bushing to be strengthened; (3) carrying out laser shock peening pretreatment on the aluminum bushing to be subjected to peening processing; and 4) performing laser shock peening on the laser shock peening area of the aluminum bushing to be subjected to peening processing, so that the abrasion loss in the peening area of the aluminum bushing can be reduced by 52%, the spectral aluminum element content of lubricating oil of the accessory casing is reduced by 38.5%, and meanwhile, deformation and laser burn of the aluminum bushing caused by laser shock peening are avoided.

This invention relates to a rapid repair patch and a rapid repair method for repairing external damage. To improve the rapid repair of localized and mechanically unrelated damage (28) in an aircraft component (26), a rapid repair patch (36) is proposed. The rapid repair patch (36) has a layer structure (38) comprising a plastic foil (40) and an adhesive layer (48) on which a lightning protection layer (42) is applied, the adhesive layer being disposed at least on the plastic foil (40). The rapid repair patch (36) can be adhered to the damaged part (28), thereby placing the lightning protection layer (42) in electrical contact with the lightning protection layer of the component (26). The rapid repair patch (36) may have a QR code or RFID tag for storing or retrieving information about the rapid repair patch (36) or the rapid repair performed by means of the rapid repair patch (36).