4892results about "Aircraft components testing" patented technology

The different advantageous embodiments may provide an apparatus that may comprise a number of mobile robotic machines, a wireless communications system and a computer system. The number of mobile robotic machines may be capable of moving to a number of locations in a maintenance area and may be capable of performing a number of maintenance operations on a structure in the maintenance area. The wireless communications system may be capable of providing communication with the number of mobile robotic machines within the maintenance area. The computer system may be capable of exchanging information with the number of mobile robotic machines using the wireless communications system.

A method for displaying location specific maintenance history for an object is implemented by operating a camera to locate at least one marker tag with fiducial marker-based tracking functionality on the object to provide a reference to a coordinate system associated with the object. An area of the object surrounding the coordinates defined by marker tag is determined from the coordinate system. A repair history for the determined area is then projected onto the object with the projection referenced to the coordinate system associated with the object.

Systems and methods for monitoring and reporting a quick access recorder (QAR) data in real time. The system includes a QAR for recording fault information, a removable portable hardware component that stores, analyzes and displays the fault information, an onboard data communication network that enables the QAR and the portable hardware component to exchange information, and an air-ground data transmitting device for transmitting the fault information from the vehicle. The removable portable hardware component may be an Electronic Flight Bag (EFB) that hosts a QAR Manager application and communication technologies to manage and report all applications on the EFB.

Apparatus for non-destructive inspection of structural elements or workpieces, in particular those having an airfoil configuration, that moves a scanning sensor across the width (span) of a structural element or workpiece for the purpose of detecting structural damage. In one embodiment, the apparatus simultaneously traverses the length (chord) of the structural element or workpiece. In another embodiment, the apparatus includes a guide rail that encompasses the structural element or workpiece and the scanning sensor travels along the guide rail from a first location at an upper rear region, to the front, of the structural element or workpiece, and then around the leading edge toward the lower rear region. The apparatus includes a processor and a display device to display the processed, sensed, information.

Aircraft maintenance and repair work is facilitated, especially for a commercial aircraft, by a diagnostic system and method, wherein an aircraft component or assembly of components is monitored by at least one sensor which produces and preferably also stores component status information. Respective status information signals are transmitted, preferably in a wireless manner, from a transmitter of the sensor to a receiver of a signal processing unit which provides status information on a display screen. The status information signals are preferably processed and evaluated with reference to rated maintenance and repair reference information to provide instructions as to what needs to be done where and when for a maintenance or repair. The sensor or sensors may operate during flight and the respective stored information is then processed and used on the ground.

There is provided an optical projection system for projecting an image onto an object that is being manufactured and / or inspected. The system includes an image-projecting device, a target-locating device for determining the orientation of the image-projecting device relative to the object, and an image-rendering device for rendering the image that is projected onto the object. The target-locating device advantageously comprises a camera that locates at least one target in mechanical communication with the object to determine the orientation of the image-projecting device relative to the object. The image-rendering device advantageously stores a three-dimensional representation of the object that is converted into a two-dimensional image that is projected upon the object. The image projected upon the object is advantageously used during assembly and / or inspection of the object.

A system (10) and method for monitoring the operational life and / or performance of one or more light-emitting diodes (LEDs) (20) based on sensed parameters are disclosed. The remaining life of each LED may be predicted by counting the clock cycles during which the LED-based light is activated. LED current and / or temperature measurements may be used to control the clock signal and, thus, to compensate the predicted life value. Furthermore, operational characteristics of the LED-based light may be monitored based on LED current and / or voltage measurements. Such characteristics may include performance (e.g., intensity) and failure conditions (e.g., open or short circuits).

A method for managing an airplane fleet is described. The method includes: (i) developing a gold body database for an airplane model for each non-destructive inspection system implemented to detect defects; (ii) inspecting, over a period of time, a plurality of candidate airplanes of the airplane model, using different types of non-destructive inspection systems and the gold body database associated with each of the different types of non-destructive inspection systems, to identify defects present on the plurality of candidate airplanes; (iii) repairing or monitoring defects detected on the plurality of candidate airplanes; (iv) conducting a trend analysis by analyzing collective defect data obtained from inspecting of plurality of candidate airplanes; and (v) maintaining the airplane fleet, which includes plurality of candidate airplanes, by performing predictive analysis using results of trend analysis.

The disclosed embodiments relate to methods and systems for monitoring sub-systems of an aircraft to detect an abnormal condition, and for identifying one or more sources that are causing the abnormal condition. In response to detecting a trigger event during flight of the aircraft, data for a plurality of relevant parameters is measured and stored in a parameter file. The parameter file is transmitted from the aircraft over a wireless communication link, and relayed to a ground support network. At the ground support network, the measured data for the plurality of the relevant parameters is then used to identify the one or more sources that are causing the abnormal condition.

The disclosed embodiments relate to methods and systems for requesting and retrieving aircraft data during flight of an aircraft. This aircraft data can be used to perform additional monitoring of aircraft sub-systems to detect an abnormal condition, and / or to identify one or more sources that are causing the abnormal condition. In one embodiment, aircraft data for one or more relevant parameters can be requested from the ground, measured on-board the aircraft, and stored in a data file that is then communicated back to personnel on the ground. The real-time aircraft data for one or more relevant parameters can then be analyzed to identify the one or more sources that are causing the abnormal condition.

A system for automated fault analysis and execution of post-flight or pre-flight tests for an aircraft is provided. The system includes a maintenance test client system onboard the aircraft, and a ground-based maintenance test server system that is remote from the aircraft. The maintenance test client system is configured to collect fault data for the aircraft, and to wirelessly transmit the fault data to the ground-based maintenance test server system after the aircraft has landed. The ground-based maintenance test server system is configured to receive the fault data, to generate a test checklist that is influenced by the fault data, and to transmit the test checklist to the maintenance test client system. The maintenance test client system wirelessly receives the test checklist, and initiates execution of at least one test specified in the test checklist.

A system and method provides overall security, service, and maintenance management for airlines. The system intends to reinforce national security by installing safeguard on-board computer system on every commercial airplane, maximize customer confidence and satisfaction by providing scalable security / service management, communicate with FAA, FBI, or CIA systems by using new telecommunication technology, and Interact with Apollo, Saber and other airline legacy systems by providing individualized interfaces. The system also helps flight attendants to have better passenger services, and helps mechanics to have better aircraft maintenance.

A system (10) and method for monitoring the operational life and / or performance of one or more light-emitting diodes (LEDs) (20) based on sensed parameters are disclosed. The remaining life of each LED may be predicted by counting the clock cycles during which the LED-based light is activated. LED current and / or temperature measurements may be used to control the clock signal and, thus, to compensate the predicted life value. Furthermore, operational characteristics of the LED-based light may be monitored based on LED current and / or voltage measurements. Such characteristics may include performance (e.g., intensity) and failure conditions (e.g., open or short circuits).

The present invention resides in a system, method and an article of manufacture for transmitting maintenance and diagnostic data from an aircraft. The system has an aircraft, a cellular infrastructures and a data reception unit. The aircraft has an avionics system and a communications unit. The avionics system has a plurality of line replaceable units, and the communications unit is connected to each line replaceable, unit. The cellular infrastructure is in communication with said communications unit after the aircraft has landed. The communication is initiated automatically upon the landing of the aircraft. The data reception unit is connected to the cellular infrastructure.

The invention discloses a method for measuring positioning points based on a laser tracker in a docking process of airplane parts. The method provided by the invention comprises the following steps of 1, establishing a model of transformation between an airplane global coordinate system and a laser tracker measure coordinate system according to common observation points, 2, acquiring current calculating positions of positioning measure points of airplane parts according to a process joint sphere centre position, and 3, controlling and driving a laser tracker to search current accurate positions of the positioning measure points of the airplane parts from the current calculating positions according to a cross helical search method and to carry out automatic measure. The method provided by the invention has the advantages that 1, an advanced laser measure technology is adopted so that the airplane assembling measure precision is improved; and 2, a measure process does not need artificial light introduction and full automatic search measure of a docking assembling process is realized according to an algorithm so that working efficiency and measure precision are greatly improved and working strength of workers is reduced.

An aircraft wireless data communication system includes an aircraft computer / server in communication with a plurality of aircraft systems. Access to the aircraft systems via the computer / server is available in real-time via wireless communication with a ground-based computer system. The ground-based computer system includes a computer that can be accessed from one or more networks of computers. Each authorized computer user on an airline, manufacturer, or supplier network has remote real-time access to the aircraft computer / server. Properly authorized remote users can: perform comparisons between the aircraft actual configuration identity and an aircraft authorized configuration identity; perform system diagnostic testing; view system status and parameters; collaborate with users from local and remote organizations using real-time aircraft data; and upload and download software and data to and from aircraft systems.

An apparatus is provided for analysis of a repair for a structure by identifying component parts of the structure that have common material properties and geometric constraints, and based thereon determining a generic repair component for the component parts that also have the common material properties and the geometric constraints. A set of loads are extracted from a loads model of the undamaged structure and redistributed in a loads redistribution model at a damaged or defective portion of the component part. The set of redistributed loads indicate loading incurred by the generic repair component under an external load. The apparatus then uses the redistributed loads to perform an analysis to determine a margin of safety of the generic repair component and, in instances in which the margin of safety is positive, outputs the material properties and geometric constraints of the generic repair component to a fabrication system for production thereof.

A system, apparatus and method provide a means for testing operation of vehicle brake system. More particularly, a brake actuator is automatically commanded to engage a brake disk stack while the vehicle is in a benign state. An engagement force applied to the brake-disk stack by the actuator then is determined, and the engagement force is compared to a first threshold value. If the engagement force is within a predetermined range of the first threshold value, it is concluded that the brake system is operating normally, otherwise it is concluded that the brake system is operating abnormally.

The present invention enables the processing head to locate itself precisely on the surface of the structure being processed, and to then reposition itself correctly for the next laser spot. Further, the present invention will complete processing a laser peened area, the area including a multiplicity of spots arranged in a specific pattern, and correctly laser peen each spot in the area under control of a controller including control linkages with the laser.The invention further provides an automated laser peening processing head encompassing spatial position sensing and locating means, as well as programmed spatial positioning, application of overlay materials, verification of proper overlay condition and positioning, and notification of the laser to pulse the surface of the structure.

The invention is a multiple degree-of-freedom test stand for unmanned air vehicles, and is particularly useful for small or micro unmanned air vehicles. The stand is gravity balanced using springs such that no weight of any part of the stand becomes a burden to the tested vehicle when it flies while constrained to the stand. A joint and a plurality of members are used to enable multiple degrees of freedom.

A method for inspecting assembly of components in a structure includes acquiring a visual representation of at least a portion of the structure, and saving an electronic file of the visual representation on a computer readable medium. A three-dimensional design of the structure, which contains information on a proper position of the components within the structure, is accessed. The visual representation is compared with the three-dimensional design using a computer, and a feedback indicating a result of the comparison is generated.

The invention provides a microminiature rotorcraft experiment platform and an application thereof. The microminiature rotorcraft experiment platform comprises an experiment platform base, a globe joint bearing, a microminiature rotorcraft, a six-dimensional force sensor, onboard circuit hardware and an upper computer, wherein the six-dimensional force sensor is connected between the experiment platform base and a stator of the globe joint bearing; and the microminiature rotorcraft is provided with the onboard circuit hardware. The experiment platform is the microminiature rotorcraft experiment platform with wide application range, the use range of the traditional rotorcraft experiment platform or three degree of freedom experimental device with a single function can be greatly expanded, the experimental requirement of the rotorcraft can be furthest satisfied. The microminiature rotorcraft experiment platform disclosed by the invention can be used for replacing the traditional practical flight test and has the advantages of simple mechanical structure and strong popularity and is easy to realize.

The invention discloses a performance test platform and method for a multi-rotor unmanned aerial vehicle. The test platform comprises a base, a stand column, a top frame, a performance test instrument and a calculation processing center; the bottom of the stand column is connected to the base through a ball-head universal bearing, and the top of the stand column is connected to the top frame through a ball-head universal bearing; the top frame is hung on an external rigid body through an elastic inhaul cable; a rack of the multi-rotor unmanned aerial vehicle is provided with a sleeving ring arranged on the stand column in a sleeving mode; the performance test instrument comprises an on-vehicle test instrument body which is arranged on the multi-rotor unmanned aerial vehicle and used for testing flight attitude information and work condition information of the multi-rotor unmanned aerial vehicle and a ground test instrument body which is arranged on the test platform and used for testing external response information of the multi-rotor unmanned aerial vehicle; the calculation processing center comprises a data collecting unit and a data analyzing unit. The test platform is simple in structure, good in flexibility and capable of accurately testing multiple performance indexes of the aerial vehicle.

A system for use in monitoring, measuring, computing and displaying the volumes of internal gas within a telescopic aircraft landing gear strut. Pressure sensors and temperature sensors and motion sensors are mounted in relation to each of the landing gear struts to monitor, measure and record the impact movement and rates of internal landing gear strut fluids; experienced by landing gear struts, as the aircraft landing gear initially come into contact with the ground. The computer of this system measures the compression experienced by each landing gear strut and determines if the landing gear strut is improperly serviced with either excess or deficient volumes of nitrogen gas. Additional features include automating the inspections required to aircraft landing gear, prior to flight, during flight and during landing events.

The invention relates to a device and method for automatic test and fault diagnosis of a plane audio integrated system, which are used for maintaining the plane audio integrated system of Airbus series and Boeing series. The method comprises the steps of: operating test software by an industrial personal computer to provide a man-machine interaction environment, and carrying out analysis, computation and statistic treatment on acquired data so as to further complete fault diagnosis; compiling a fault diagnosis program according to all circuit diagrams and test point information of the audio integrated system, provided by a CMM (Capability Maturity Model for Software) manual, and clearing up injected data information on faults, excitation, response and the like to form a fault record in a fault dictionary; in the fault diagnosis program, providing the positions of testing points in need of manual measurement and corresponding test information; testing the testing points in need of manual measurement by detection personnel to confirm a fault area, and displaying corresponding diagnosis results. The device and method provided by the invention can commonly meet the requirement of the automatic test for two types of audio integrated systems including the AMU (Audio Management Unit) of Airbus series planes and the REU (Remote Electronic unit) of the Boeing series planes, and are favorable for reducing the labor intensity of maintenance personnel and improving maintenance efficiency.

A method for ensuring the operation and integrity of a three-dimensional integrated logistical system that includes a plurality of drones and a plurality of service stations; each of the plurality of drones having a plurality of environmental sensors and a plurality of internal sensors. The plurality of drones is routed to a destination location through a fleet management software that monitors the plurality of drones and the plurality of service stations. The fleet management software is able to detect operational issues amongst the plurality of drones and if necessary reroute the plurality of drones to the plurality of service stations in order to resolve said operational issues. A robotic service unit in each of the plurality of service stations is able to autonomously service the plurality of drones in addition to equipping the plurality of drones with a designated payload.

Systems and methods for monitoring and reporting a quick access recorder (QAR) data in real time. The system includes a QAR for recording fault information, a removable portable hardware component that stores, analyzes and displays the fault information, an onboard data communication network that enables the QAR and the portable hardware component to exchange information, and an air-ground data transmitting device for transmitting the fault information from the vehicle. The removable portable hardware component may be an Electronic Flight Bag (EFB) that hosts a QAR Manager application and communication technologies to manage and report all applications on the EFB.

Aircraft maintenance and repair work is facilitated, especially for a commercial aircraft, by a diagnostic system and method, wherein an aircraft component or assembly of components is monitored by at least one sensor which produces and preferably also stores component status information. Respective status information signals are transmitted, preferably in a wireless manner, from a transmitter of the sensor to a receiver of a signal processing unit which provides status information on a display screen. The status information signals are preferably processed and evaluated with reference to rated maintenance and repair reference information to provide instructions as to what needs to be done where and when for a maintenance or repair. The sensor or sensors may operate during flight and the respective stored information is then processed and used on the ground.