832results about "Aircraft maintainance" patented technology

A maintenance station for an unmanned aerial vehicle includes a housing having at least one opening for the entry and exit of the unmanned aerial vehicle, at least one platform movable through the opening from the outside to the inside of the housing, at least one robotic arm positioned inside the housing and including a maintenance arm having a holder and / or a filling tube for changing the battery for maintenance of the unmanned aerial vehicle, and at least three adjustment elements that can move toward a common point on the platform to adjust the position of the unmanned aerial vehicle.

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.

An aircraft with a folding wing tip arrangement having a wing tip device mounted at a joint at the end of a fixed wing. It is desirable to transfer power and / or data into a folding wing tip, which presents challenges such as repeated exposure to potentially harsh environmental conditions, with movement, and / or with changes in tensional loads. A wiring harness includes a plurality of conductors and is arranged to transmit electrical power and / or data to the wing tip device. A length of the harness is received in a protective sleeve, and the sleeve extends over a length of the wiring harness spanning the joint, the sleeve being removable from the wiring harness.

The invention provides an aero-engine blade maintenance method and system, a robot and a medium, the method is applied to a micro maintenance robot, and the method comprises the steps that when the rotating speed of an aero-engine is not lower than the preset rotating speed, a magnetic-gas composite driving module is used for obtaining a first moving path according to an edge intelligent center system; moving to a blade detection position of the aero-engine blade corresponding to the first moving path; when the moving stop position of the micro maintenance robot is the blade detection position, the bionic reversible adsorption layer in the adsorption state is adsorbed to the blade detection position; detecting first leaf detection data of a leaf detection area corresponding to the leaf detection position by using a multispectral sensing module, and obtaining a repair strategy based on the first leaf detection data; and a repair module is utilized to perform repair operation on the to-be-repaired blade area in the blade detection area according to the repair strategy. In this way, the detection function and the repair function are integrated, and the purposes of rapid detection and minimally invasive repair are achieved.

There are provided systems and methods for prognostic analytics of an asset. For example, there is provided a processor-implemented method for severity prediction for aircraft components. The method includes accessing time series flight-by-flight data relating to a component of an aircraft, the time series flight-by-flight data comprising performance data; determining, by a prediction model, an estimated degree of distress for the component based on the time series flight-by-flight data; determining a flight-by-flight severity prediction for the component based on the estimated degree of distress; and providing a preemptive recommendation for the component based on determined the flight-by-flight severity prediction.

The utility model discloses an aircraft wheel maintenance bracket which comprises a lower shell, an upper shell is fixedly connected to the outer wall of the upper side of the lower shell, a bearing frame is arranged in the upper shell in a sliding mode, a first two-way screw rod is rotatably arranged between the inner walls of the two sides of the bearing frame, and two symmetrically-distributed first moving blocks are arranged on the rod wall of the first two-way screw rod in a threaded and sleeved mode. Compared with the prior art, the airplane wheel maintenance bracket has the advantages that the universal wheels can extend out of the lower shell to support the lower shell to move when the airplane wheel maintenance bracket needs to be moved through the arranged moving assembly, and when the airplane wheel is maintained, the universal wheels can be retracted into the lower shell, so that the lower shell integrally touches the ground, the contact area between the lower shell and the ground is large, and the service life of the airplane wheel maintenance bracket is prolonged. The stability is improved; through the arranged lifting assembly, the bearing frame can ascend and descend, when the airplane wheel is disassembled, the bearing frame ascends, the airplane wheel is supported by the supporting plate, and in this way, the airplane wheel can be easily separated from the wheel shaft.

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.

A method for aircraft maintenance scheduling includes using a scheduling environment as a reinforcement learning (RL) environment to simulate an operational concept, train an RL agent, and generate aircraft maintenance decisions and explanations; providing a decomposed reward Deep Q-Network (drDQN) algorithm, wherein the drDQN algorithm includes a first Deep Q-Network (DQN) and a second DQN; using the first DQN to maximize a mission accomplishment objective; using the second DQN to minimize a maintenance cost objective; providing a trained drDQN agent; using the trained drDQN agent to obtain the aircraft maintenance decisions and corresponding mission accomplishment and maintenance cost rewards; using a scheduling module to arrange aircraft maintenance activities; and using an explainable module to get reasons to detail why the decisions are made and present tradeoffs between the decisions and non-selected alternatives.

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 invention belongs to the technical field of aircraft maintenance, and particularly discloses aircraft maintenance belly skin dismounting and mounting equipment which comprises supporting levers arranged in pairs and moving wheels on the lower portions of the supporting levers, the two supporting levers are connected together through a plurality of bidirectional hydraulic rods, the bidirectional hydraulic rods are fixed to a middle lever, and telescopic hydraulic cylinders are arranged on the lower wall of the middle lever in an array mode. The lower end of the telescopic hydraulic cylinder is provided with a vacuum suction cup, supporting rods are arranged on the upper wall of the supporting lever in an array mode, the upper ends of the supporting rods are connected together through a transverse lever, lifting assemblies are arranged on the supporting lever and the transverse lever, self-matching adjusting assemblies are arranged on the lifting assemblies, and an automatic contour adapting assembly is arranged between every two opposite self-matching adjusting assemblies. The connecting blocks are sequentially connected through the curable connecting assemblies to form a chain-shaped structure, the chain-shaped structure is automatically attached to the surface of the airplane belly skin according to the shape of the airplane belly skin, fixing of the positions of the connecting blocks is automatically completed, and deformation of the airplane belly skin in the hoisting process is avoided.

Embodiments of the disclosure provide for model-based generation of corrective actions for remediating an abnormal event. Some embodiments cause rendering of a graphical user interface (GUI) via a computing device, where the GUI comprises a ranking of a plurality of corrective actions associated with at least one abnormal event. In some embodiments, the ranking of the plurality of corrective actions is obtained from a model that establishes mappings between the at least one predefined abnormal event and historical data. Some embodiments receive, from the computing device, feedback data via the GUI, the feedback data indicating a successfulness of resolution associated with implementing at least one of the plurality of corrective actions. Some embodiments update the model to improve a scoring of the at least one predefined abnormal event based at least in part on the feedback data.

The invention discloses an engine accessory on-condition maintenance decision-making method considering inherent characteristics and repair characteristics, and belongs to the field of turbine engine maintenance, and the method comprises the following steps: classifying turboshaft engine accessories based on the inherent characteristics to obtain classified accessories, the classified accessories comprise a repairable accessory and an unrepairable accessory; performing fault damage analysis on the classified accessories to obtain an external field maintenance decision; determining factory return maintenance accessories based on the external field maintenance decision; and analyzing the factory return maintenance accessory based on the repair characteristics to determine a maintenance decision of the accessory in the overhaul. The method can be used for guiding the maintenance decision of accessories of the turboshaft engine in external field use and factory return overhaul stages, scientifically determining the maintenance mode and the disassembly depth, improving the reliability and maintainability of the engine, reducing the maintenance cost and improving the guarantee capability of the engine.

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 digital twinning monitoring method for the full-life health state of a service aircraft structure belongs to the related technical field of digital twinning, and comprises the following steps: firstly, designing a health state data acquisition scheme to obtain health state data in a real flight state; secondly, performing screening extraction and optimization treatment on the health state data, and constructing a flight data-mechanical response data health state data set of a service aircraft structure; thirdly, establishing a flight data-mechanical response data-life monitoring digital twinborn model, and realizing high-precision prediction of the fatigue residual life of a service aircraft structure; and finally, making an inspection and maintenance task intelligent planning scheme, and dividing inspection and maintenance grades based on the fatigue residual life and the fatigue reliability coefficient. According to the method, fatigue residual life prediction and inspection and maintenance task intelligent planning of the service aircraft structure can be realized, a service aircraft structure full-life health state digital twin monitoring process is formed, and full-life health state monitoring and management can be conveniently carried out for the service aircraft.

Aspects of the disclosure are directed towards path generation. A method includes a computing system registering a first coordinate system of a target object with a second coordinate system of a robot. The computing system can generate a trajectory over the surface of the target object based on the registration. The computing system can generate a robot job file based at least in part on the generated trajectory. The computing system can transmit the robot job file to a robot controller.

An apparatus for servicing internal components of an aircraft engine includes a flexible hollow tube; a latching mechanism connected to or incorporated with the flexible hollow tube; and a servicing device to be inserted through the flexible hollow tube. The servicing device is freely moveable through the flexible hollow tube and decoupled from the latching mechanism. The flexible hollow tube is shaped and configured so as to enable proximate positioning of the flexible hollow tube with respect to a rotatable component of an aircraft engine allowing attachment of the flexible hollow tube to the rotatable component via the latching mechanism after the flexible hollow tube is inserted through an entry port of the aircraft engine.

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 invention relates to the technical field of aviation maintenance equipment, in particular to an aircraft tire full-automatic disassembly and assembly mechanical arm device which comprises a base, a four-degree-of-freedom lifting platform, an inclined frame, a control module, a laser radar sensor, a pressure monitoring module, a limiting frame, a hydraulic jack, an undercarriage, a tool rotating disc, a guide rail, a sliding block base, a redundant mechanical arm and a camera. + / -0.05 mm high-precision positioning is realized through laser radar point cloud matching, and safe and efficient equipment operation is ensured in combination with millimeter-wave radar anti-collision early warning; and the four-degree-of-freedom lifting platform and the redundant mechanical arm are cooperatively operated, so that accurate disassembly and assembly of the aircraft tires are completed. The working efficiency can be remarkably improved, manual intervention is reduced, and the operation safety and the positioning precision are guaranteed.

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 belongs to the technical field of aircraft avionics systems, and particularly relates to an aircraft separation surface electric connector mounting hole positioning device. Comprising a guide rail base, a mounting hole positioning sliding block, a driving connecting assembly and a knob adjusting assembly. Wherein four mounting hole positioning sliding blocks are arranged on a rail of the guide rail base, and mounting holes in the mounting hole positioning sliding blocks are used for clamping the mounting position of the structure separation surface connector; the knob adjusting assemblies are arranged on the guide rail base; the driving connecting assembly comprises four driving connecting pieces, one end of each driving connecting piece is connected with one mounting hole positioning sliding block, and the other end of each driving connecting piece is connected with the knob adjusting assembly; and the knob adjusting assembly rotates, and the mounting hole positioning slide block is driven to move on the guide rail base by driving the connecting piece, so that the positioning of the mounting hole of the separated surface electric connector is realized. The positioning device is used for accurately positioning the mounting hole of the aircraft separation surface electric connector, the positioning process is simplified, the positioning accuracy and efficiency are remarkably improved, scrapping and damage caused by drilling of the aircraft wire harness electric connector are avoided, and the positioning device has high use value and economic benefits.

The invention discloses airplane brake assembly quick disassembly equipment with a self-stabilizing function, and relates to the technical field of quick disassembly equipment. Comprising a jacking mechanism, a control system and a base, a supporting frame is arranged on the upper side of the base, the jacking mechanism is arranged on the lower side of the base, a rotating motor is installed on the supporting frame, a rotating frame is installed on an output shaft of the rotating motor, a descending oil cylinder is installed on the rotating frame, a clamping plate is arranged on a telescopic rod of the descending oil cylinder, and multiple sets of clamping balls are installed on the clamping plate. Walking wheels are arranged on the jacking mechanism, a fixing cylinder is arranged on the base, a lifting cylinder and a rotating shaft are sequentially installed in the fixing cylinder, a transverse clamping cylinder is installed above the rotating shaft, two sets of inclined clamping cylinders are rotationally installed on the transverse clamping cylinder, and through a buffer spring and magnetorheological fluid, it is ensured that the airplane wheels and the brake assembly are placed stably; the purpose of automatically stabilizing the airplane wheel and the brake assembly is achieved, and the airplane wheel and the brake assembly are prevented from shaking and toppling over.

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.

The invention provides an aircraft wing skin repairing method. The skin includes an underlying fabric. The repairing method comprises the following steps: cutting a to-be-treated area skin of the aircraft wing skin to form a repairing notch; determining a to-be-repaired area according to the repairing notch; preparing a repairing skin corresponding to the to-be-repaired area; the repairing skin is fixed to the to-be-repaired area; the contact surface of the repairing skin and the cut aircraft wing skin is polished, so that a gradient groove is formed in the contact surface; and filling the gradient groove with a filler which is homogeneous with the aircraft wing skin based on a wet process so as to complete the repair of the aircraft wing skin. According to the repairing method provided by the invention, the airplane wing skin is connected in an inclined gradient lap joint manner, so that the connecting strength of the repairing skin and the airplane wing skin is improved, and the firmness and reliability of the repaired airplane wing skin are improved.

The present disclosure provides repair systems, repair components, and methods for repairing composite structure systems using a set number of prefabricated repair components including a repair component and various shims which are fabricated to repair multiple composite members in a composite structure system.

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.