581results about "Aircraft maintainance" patented technology

An insertion tool is provided. The tool includes a flexible section comprising a plurality of rigidizable links, an end effector actuator, and an end effector coupled to the flexible section. A flexible is shaft inserted through the flexible section, wherein torque is transferred from the end effector actuator to the distal end via the flexible shaft to cause a rotation of the end effector. A tool may include a tool-less disconnect interface between the end effector and the flexible shaft.

The invention discloses an unmanned aerial vehicle load engine state identification method based on deep learning, and the method comprises the following steps: S1, collecting the multi-mode operation data of an unmanned aerial vehicle load engine, and completing the standardization preprocessing; s2, inputting the spatial data into a spatial pyramid pooling network, and extracting a multi-scale spatial feature matrix; s3, inputting the spatial features into a masking auto-encoder, performing feature masking, encoding and reconstruction, and generating reconstruction features and error information; s4, fusing the original features, the reconstructed features and the non-spatial data, inputting a discrimination network, and outputting a health label and a risk score; and S5, according to an identification result, a flight control system or a maintenance platform is linked to realize alarm and scheduling. According to the method, intelligent identification and abnormal risk early warning of the state of the load engine of the unmanned aerial vehicle are realized by fusing multi-scale spatial feature extraction and a covering self-encoding reconstruction mechanism.

The invention relates to the technical field of aircraft maintenance, and particularly discloses a guide supporting structure for replacing large components of an aircraft. The longitudinal supporting seat can be movably arranged on the vehicle body in the horizontal direction; the linkage operation adjusting mechanism is arranged on the side wall of the longitudinal supporting seat and is used for providing two independent transmission powers with variable speeds for the longitudinal supporting seat; the lifting mechanism can be movably arranged on the longitudinal supporting seat in a sleeving mode in a lifting mode, the lifting mechanism is further provided with a rotatable retainer, the retainer is used for fixing an aircraft landing gear in a disassembly and assembly state, and lifting power of the lifting mechanism and rotating power of the retainer both come from the longitudinal supporting seat. According to the invention, multi-degree-of-freedom adjustment in a limited space is realized, and meanwhile, a guide supporting structure with high positioning precision and operation convenience is taken into account, so that the safety and efficiency of replacement operation of large components of an aircraft are improved.

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.

A brake in combination with a slider for holding an aircraft workpiece in position for maintenance. The combination has a slider which circumscribes and moves on a support bar and a brake configured to lock the slider in place on the support bar. The brake has a brake pad internal to the slider and at least partially congruent with the support bar. The brake pad is engageable and disengageable from the support bar by respective insertion and retraction of a key pin extending outwardly from the wall of the slider. The key pin and the brake pad are connected by a driver pin, so that insertion of the key pin towards the support bar urges the driver pin towards the support bar and the brake pad into locking contact with the support bar. A method of locking an aircraft workpiece in position for maintenance is also disclosed. The method comprises the steps of: providing a stand having X, Y, Z adjustability of a fixture for holding the aircraft workpiece moving a slider to a predetermined position on a spreader, locking the slider the in the predetermined maintenance position with a brake and joining an aircraft workpiece to the fixture.

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.

Systems and methods are provided for offline voice control in aircraft management. A computing system can include a processor and a non-transitory computer-readable storage device storing computer-executable instructions. The instructions can be operable to cause the processor to perform operations comprising receiving an audio input; converting the audio input to a textual message; analyzing the textual message with a natural language processing technique to identify an intent; generating a structured command based on the identified intent; and transmitting the structured command to a user device.

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 an airplane wheel maintenance production line which comprises a decomposition area used for disassembling an airplane wheel assembly, and disassembled parts at least comprise a tire, an inner half hub and an outer half hub; the cleaning area is adjacent to the decomposition area and is used for cleaning at least part of the parts; the inspection area is adjacent to the cleaning area and is used for inspecting at least part of the parts; the assembling area is adjacent to the inspection area and is used for assembling the inspected parts and / or new parts to form a new airplane wheel assembly; the decomposition area, the cleaning area, the inspection area and the assembly area are connected through a conveying belt. By means of the production line, the labor intensity can be reduced in the airplane wheel maintenance process, the working efficiency is improved, and the phenomena that parts slide down and are damaged, and personnel are injured during carrying are avoided.

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.

A drive shaft has a central tubular portion formed of a polymer composite with imbedded fibers. It extends between a first end and a second end. The central tubular portion has an outer peripheral surface. There is at least one ring on the outer peripheral surface of the central tubular portion. A method of repairing a composite material tube includes the steps of (a) identifying a damaged area on a composite tube, and (b) placing a patch on a surface of the tube and over the damaged area.

To provide an effective, efficient, and accurate system and method for allowing accurate retrieval of a record indicating an arbitrary issue.SOLUTION: In a system 100, an input device 108 selects one or more seed records 116 regarding one or more maintenance issues of one or more vehicles. Further, a user interface 104 outputs one or more first electronic signals that include the one or more seed records 116. A records database 110 includes maintenance records 112 for the one or more vehicles. A similarity engine control unit 102 communicates with the user interface 104 and the records database 110. The similarity engine control unit 102 receives the one or more first electronic signals including the one or more seed records 116, searches the maintenance records 112 within the records database 110, and finds one or more first return records 118 including a subset of the maintenance records 112 that are similar to the one or more seed records 116.SELECTED DRAWING: Figure 1

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.

A mobile charging system for electric vehicles may include a fluid management system. The fluid management system may be configured to be fluidly coupled to the electric vehicle. The fluid management system may be configured to provide heating or cooling to a vehicle battery system during charging of the vehicle battery system of the electric vehicle.

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 application provides an aircraft conduit field maintenance cabin, which comprises a cabin body, a plurality of conduit maintenance devices, a conduit storage bin, an outdoor power supply and a generator, the plurality of conduit maintenance devices, the conduit storage bin, the outdoor power supply and the generator are distributed in the cabin body, the outdoor power supply is used for providing power for the plurality of conduit maintenance devices, and the generator is used for charging the outdoor power supply; a plurality of slide rail devices are further arranged in the cabin body, the slide rail devices are used for carrying the conduit maintenance devices, so that the carried conduit maintenance devices can be pulled out to the outside of the cabin body. The application further provides a maintenance vehicle, which comprises the cabin body as described above. By adopting the technical scheme, the aircraft conduit field maintenance cabin and the maintenance vehicle can be carried by a light off-road chassis, can be suitable for wild environments such as mountain roads, muddy roads and gravel roads, can pass through the roads with limited width and height in cities, and can still open the cabin door for maintenance operation in narrow lanes.

The invention provides a composite material structure layer damage repairing method which comprises the following steps that S1, a punching area is determined on the outer surface of a composite material structure layer, and the punching area comprises the whole damage part; punching the punching area and penetrating the punching area to the inner surface of the composite material structure layer to form a punched hole; s2, the position with the height h away from the inner surface is selected as an inclined grinding datum plane, the outer surface, located around the penetrating hole, of the composite material structure layer is subjected to grinding and inclined cutting, an inclined cutting plane located on the outer side of the penetrating hole is obtained, and the bottom of the inclined cutting plane is located on the inclined grinding datum plane; s3, a back plate made of the same material as the composite material structure layer is attached to the inner surface of the composite material structure layer and covers the through hole; s4, a filling body made of the same material as the composite material structure layer is embedded, bonded and fixed in the through hole, the inner side face of the filling body abuts against the backboard, and the outer side face of the filling body is located on the inclined grinding datum plane; and S5, a repairing layer is laid on the inclined cutting face, and a covering layer is laid on the repairing layer.