1103results about "Aircraft maintainance" patented technology

The invention relates to a mobile structure for dispatching and accommodating drones, comprising a landing platform, a lifting unit for adjusting the height of the landing platform, and a storage unit. The lifting unit allows lifting and lowering of the landing platform up to a height from which a drone can take off and land (take-off height), and to a height in which the landing platform can transfer a drone to a storage level of the storage unit or receive the drone from a storage level (storage level height).

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.

The invention provides an aircraft landing gear dismounting and mounting device, belongs to the technical field of aviation equipment, and solves the problem that in the prior art, landing gear dismounting and mounting equipment is difficult to meet the requirements for efficient, accurate and flexible dismounting and mounting in the modern aviation maintenance field. Comprising a frame, a moving frame is arranged on the inner side of the frame, and the moving frame is driven by a first driving device; a moving plate is arranged on the frame and is driven by a second driving device; an arc-shaped guide rail is arranged on the movable plate, a supporting frame is arranged on the arc-shaped guide rail, a lifting device and a fixing device are arranged on the supporting frame, and a clamp is arranged on the top of the lifting device. According to the undercarriage disassembling and assembling device, through cooperative operation of the first driving device, the second driving device and the lifting device, all-directional flexible adjustment of the tool on the X axis, the Y axis and the Z axis is achieved. Due to the design of the arc-shaped guide rail, the supporting frame can flexibly rotate within a certain angle range, and the adaptability and flexibility of the device are further enhanced.

The invention discloses airplane wheel disassembly and assembly auxiliary equipment for civil aircraft maintenance, and relates to the technical field of tire maintenance devices.The airplane wheel disassembly and assembly auxiliary equipment comprises a traction frame body, a protruding part is inwards formed in the middle of the traction frame body, a first hydraulic jack is arranged on the protruding part, and a supporting frame is arranged at the output end of the first hydraulic jack; vertical supporting plates are arranged on the two sides of the supporting frame, combination plates are arranged on the vertical supporting plates on the two sides, transverse plates are arranged on the combination plates, supporting rods are symmetrically arranged on the transverse plates on the two sides respectively, and arc-shaped plates are arranged on the upper end faces of the supporting rods on the two sides. According to the lifting function of the airplane tire dismounting device, the airplane tire can be lifted upwards in the dismounting process, so that the gravity of the airplane tire cannot act on a fixing bolt, a user can conveniently take down the airplane tire, meanwhile, the airplane tire is rotated through cooperation of a groove-shaped structure, and therefore a worker can conveniently and rapidly maintain the state of the airplane tire.

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.

The utility model relates to the field of aircraft coating repairing technology research, in particular to an in-situ automatic repairing device for an aircraft local coating. Comprising a mobile operation platform, a 3D camera which is arranged on the mobile operation platform and is used for collecting 2D images and 3D point cloud data of the surface of an airplane, a repairing module which is arranged on the mobile operation platform and is used for coating cleaning or paint spraying, and an upper computer which is used for controlling the mobile operation platform, the 3D camera and the repairing module. Compared with the device in the prior art, the device can automatically inspect, identify and position the damaged area of the coating on the surface of the airplane, and in-situ automatic identification and repair of the damaged special-shaped bent coating on different parts of the surface of the airplane are realized.

The present disclosure relates to a multi-tiered computing environment for balancing compute resources in support of robot operations. In an example, a robot is tasked with performing an operation associated with an airplane having an airplane model. To do so, the robot may need another operation that is computationally complex to be performed. An on-premises server can execute a process that corresponds to this computationally-complex operation based on sensor data of the robot and can output the resulting data to the robot. Next, the robot can use the resulting data to execute another process corresponding to its operation and can indicate performance of this operation to the on-premises network. The on-premises network can send the indication about the operation performance to a top-tier server that is also associated with the airplane model.

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.

Apparatus and computer-implemented methods for determining one or more properties associated with at least one shroud gap of a turbine are described. An example method includes obtaining a plurality of image frames of a shroud gap of a turbine, wherein the turbine is in a different orientation in each of the image frames; and a first reference image of the first shield gap in a first orientation. Image frames in which an orientation of the shroud gap matches the first orientation may be identified based on the first reference image for each of the plurality of shroud gaps. Image processing may be performed on the identified image frame to identify a first region of the image frame associated with the shield gap. The identified regions of the image frame may be combined to obtain a gap mask. A gap mask may be applied to each identified image frame to identify a second region, and image processing may be performed on the second region to determine one or more properties associated with at least one shield gap.

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.

The invention discloses an aircraft reinforcement learning predictive maintenance decision-making method under residual life uncertainty. The method comprises the following steps: generating a training set and a test set according to flight mission sequence data; respectively constructing a first value distribution reinforcement learning model and a second value distribution reinforcement learning model; selecting a flight task sequence from the training set, inputting the flight task sequence into the first value distribution reinforcement learning model, and generating an aircraft maintenance decision; based on a second value distribution reinforcement learning model, calculating a long-term income corresponding to the aircraft maintenance decision; updating network parameters of the first value distribution reinforcement learning model according to the long-term income and the second value distribution reinforcement learning model; and after the updated first value distribution reinforcement learning model is trained, predicting the aircraft maintenance decision through the trained first value distribution reinforcement learning model, so that the reliability of the determined aircraft maintenance decision can be improved.

The utility model discloses an aircraft landing gear installation assistive device, which relates to the technical field of aircraft maintenance equipment, and comprises a movable base, the right part of the top end of the movable base is fixedly connected with a fixed box, the left part of the bottom end of the movable base is fixedly connected with a support frame, and the top end of the fixed box is fixedly connected with a lifting mechanism. A clamping mechanism is fixedly connected to the left end of the lifting mechanism, a bearing mechanism is fixedly connected to an inner cavity of the supporting frame, and the lifting mechanism comprises a first motor and a mounting plate. According to the auxiliary installation tool for the aircraft landing gear, by starting the telescopic cylinder, the telescopic cylinder drives the bearing plate to rise upwards, the bearing plate slides on the outer wall of the second guide rod, the bearing plate is limited and guided through the second guide rod, the bearing plate is more stable in the moving process, the bottom of the aircraft landing gear is borne through the bearing plate, and the installation efficiency of the aircraft landing gear is improved. And the downward gravity borne by the clamping mechanism is reduced, so that clamping is more stable, and the bearing effect is achieved.

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.

Aspects of the disclosure are directed towards artificial intelligence-based modeling of target objects, such as aircraft parts. In an example, a system initially trains a machine learning (ML) model based on synthetic images generated based on multi-dimensional representation of target objects. The same system or a different system subsequently further trains the ML model based on actual images generated by cameras positioned by robots relative to target objects. The ML model can be used to process an image generated by a camera positioned by a robot relative to a target object based on a multi-dimensional representation of the target object. The output of the ML model can indicate, for a detected target, position data, a target type, and / or a visual inspection property. This output can then be used to update the multi-dimensional representation, which is then used to perform robotics operations on the target object.

An onboard hydraulic system for an aircraft is disclosed having a motor-pump unit including an electric motor and a hydraulic pump driven by the motor, a hydraulic consumer supplied with pressurized hydraulic fluid from the motor-pump unit, a fluid reservoir, a pressure sensor for sensing pressure of the pressurized hydraulic fluid, a control unit for controlling the motor-pump unit, and a pressure setting mechanism for adapting a pressure setting of the motor-pump unit for ground service or maintenance or specific flight conditions.