1158results about "Aircraft maintainance" patented technology

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.

An Automatic Service Station Facility (ASSF) for replenishing various motivational energy sources onboard different types of AUV, Drones, and Remotely Controlled (RC) or robotic vehicles is disclosed herein. In one embodiment, the automatic service station facility includes a rack, replaceable fuel tanks, a service module, and an electronic computer control system. The replaceable fuel tanks are stocked on the rack and substantially filled with various fluids which are utile as motivational energy sources within fuel-operated vehicles. The service module is mounted on the rack, and the electronic computer control system is connected in electrical communication with the service module. In this configuration, the service module is controllably operable to receive a depleted replaceable fuel tank from a fuel-operated vehicle and also selectively deliver one of the filled replaceable fuel tanks onboard the vehicle. In another embodiment, the service station facility may also stock replaceable batteries for selective delivery onboard battery-operated vehicles. In another embodiment, the ASSF is self-propelled, remotely controlled, and solar powered, being able to move long distances to remote locations which may be hazardous to humans, such as disaster zones or battle fields, where the ASSF can service AUV, Drones, and Remotely Controlled (RC) or robotic vehicles needed for the particular applications. Alternatively, the solar powered ASSF can be made to move continuously and service vehicles continuously for long duration operations like herding cattle for example.

A fast line maintenance repair process for damaged composite structures includes the application of a pre-cured patch that uses a quick curing paste adhesive to bond the patch to the structure. The adhesive is cured at relatively low elevated temperatures provided by a chemical heat pack. The low temperature cure eliminates the need to dry out the part and permits the application of the repair in a hazardous environment. In a typical commercial airline application, airline maintenance personnel can install the repair at the flight gate. The repair is intended to restore the structure to a desired load capability in approximately one hour. The repair can be removed if need be with less overall damage than would occur upon removal of typical mechanically fastened repairs. All or some of the repair materials and tools can be provided in a portable kit.

A modularized robot includes a robot platform configured to convey mobility and connectivity to external components to the modularized robot, a robot workhead configured to convey the ability to perform an operational task to the modularized robot, and a robot adapter attached to either the robot platform or the robot workhead and configured to mechanically link the robot platform to the robot workhead. Moreover, a swarm of modularized robots and a robot system include such modularized robots.

Disclosed is a field repairable airfoil structure such as a wing or a rotor blade and a method for repair and removal of erosion or impact damage to elastomeric coatings on surfaces such as the leading edge of the airfoil using special hand sandable coatings and preformed molded boots, preformed sheets or tapes with an optional topcoat applied thereto having higher sand erosion resistance.

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 low-profile, automated guided vehicle (AGV) performs surface treatments over large areas of a structure having limited access, such as an aircraft underbelly. The AGV includes a movable gantry provided with automated robot. The robot has interchangeable end effectors for carrying out the surface treatments. Travel of the AGV relative to structure is controlled by a ground guidance system.

In a first aspect, there is a method of making a rotor blade, including designing at least one of an upper skin, a lower skin, a support network, and components therefor; and forming at least one of the upper skin, the lower skin, a support network, and components therefor using an additive manufacturing process. In a second aspect, there is an airfoil member having a root end, a tip end, a leading edge, and a trailing edge, the airfoil member including an upper skin; a lower skin; and a support network having a plurality of interconnected support members in a lattice arrangement and/or a reticulated arrangement, the support network being configured to provide tailored characteristics of the airfoil member. Also provided are methods and systems for repairing an airfoil member.

A maintenance system is provided for an environmental conditioning element of an environmental control system of a vehicle. The maintenance system includes a data acquisition module configured to determine an ambient temperature, an altitude of the vehicle, and a measured ECS compressor temperature; a fouling module coupled to receive the ambient temperature, the altitude, and the measured ECS compressor temperature from the data acquisition module and configured to generate a fouling condition of the environmental conditioning element based on at least the ambient temperature, the altitude, and the measured ECS compressor temperature; and a reporting module coupled to receive the fouling condition from the fouling module and configured to generate a report for a user that includes the fouling condition.

Structural analysis automation allows the implementation of more detailed or accurate analysis methodology that reflects the actual behavior of the damaged or repaired structure and consequently improves the resulting damage disposition for example by Increasing the allowable damages and structural repairs applicability, increasing the allowable damage limits causing the reduction of unnecessary installation of structural repairs, optimizing repairs and increasing fly-by periods and inspection intervals.

A method of repairing a composite material is provided in which a frustum-shaped portion of a composite material is removed, and the composite material and a repair material are bonded with each other while evacuating. The repair method includes step S2 of removing a damaged part 11 from the front side so as to pass through in the thickness direction while leaving a support wall protruding inward in the radial direction from the periphery of the top face of the frustum-shaped portion; step S3 of sealing the back side by placing a sealing plate, which is inserted from the front side into a through hole formed by the removing step, on the support wall; step S5 of placing the repair material through an adhesive on the composite material where the frustum-shaped portion has been removed; and step S6 of evacuating in a state in which the front side is sealed.

A method and apparatus for identifying a condition of assembly of an aircraft. A current state of assembly of the aircraft is identified. Parts present in the aircraft for the current state of assembly of the aircraft are identified. The parts present in the aircraft for the current state of assembly of the aircraft are displayed in a graphical user interface on a display device.

Disclosed is a field repairable coated airfoil such as a wing or a rotor blade having a leading edge protected by a spray applied or prefabricated variable thickness, multilayer coating system composed a primer or adhesive layer, a basecoat layer and a topcoat where the coating is continuously tapering having a thicker cross section at the leading edge and a thinner cross section at the trailing edge of the airfoil.

Aided preventive diagnostics of an aircraft system, comprising a plurality of subsystems at least one of which comprises a subsystem configured for monitoring and notifying a detected event, using critical event charts. After receiving a message notifying the occurrence of said detected event, a minimal diagnostic set relative to said at least one detected event, comprising a plurality of elements each represented by a node of said critical event chart is created, each element of said minimal diagnostic set being determined according to at least one logical implication relation of said critical event chart with a node representing said at least one received notification message. At least some of the elements of said minimal diagnostic set are then ranked, said ranked elements forming part of said diagnostic report.

A method and apparatus may be present for moving a wing. A plurality of lifting assemblies may be attached to a first plurality of channels in a ring associated with the wing of an aircraft. A plurality of base assemblies may be attached to a plurality of fittings with a second plurality of channels associated with a fuselage of the aircraft. The plurality of lifting assemblies may be moved away from the plurality of base assemblies using a plurality of biasing systems such that the ring may move away from the fuselage.

A method for reworking an electrically conductive layer of a composite skin is disclosed in which a patch replaces the altered section of the electrically conductive layer. The method is performed by removing a portion of the electrically conductive layer to reveal the underlying composite skin. A patch is formed, having an electrically conductive section coupled to an adhesive having a low dielectric breakdown strength, and is then introduced over the underlying composite skin such that the adhesive layer covers the underlying composite skin and overlaps an unremoved portion of the electrically conductive layer. The patch is applied such that the electrically conductive section within the patch covers the adhesive layer and overlaps the unremoved section of the electrically conductive layer. The adhesive layer preferably has a low dielectric breakdown strength, so that electricity from lightning which strikes the composite skin may be conducted through the adhesive.