79results about "Aircraft cleaning" patented technology

A processor-implemented method for post-wash recovery prediction for aircraft components includes accessing wash event data associated with a component of an aircraft; averaging the data and determining outlying events; filtering the data to remove outlying events; performing feature engineering to determine a plurality of features; providing, as inputs to an analytic model, the plurality of features and the filtered data; predicting, by the analytic model, a post-wash recovery; and providing a washing recommendation based on the post-wash recovery to selectively cause the component to be washed.

The intelligent take-off and landing platform comprises a storage box, the top face of the storage box is slidably connected with a cover plate assembly, the inner bottom face of the storage box is fixedly connected with a lifting column, the top face of the lifting column is fixedly connected with a parking platform, the unmanned aerial vehicle is placed in the center of the top face of the parking platform, and the outer wall of the lifting column is slidably connected with a storage unit. A cleaning unit is slidably connected to the side wall of the lifting column and comprises a power assembly fixedly connected to the bottom face of the storage box, a support is slidably connected to the outer wall of the power assembly, a cleaning assembly is fixedly connected to the top face of the support, and a first sealing plate is fixedly connected to the side, close to the unmanned aerial vehicle, of the support and rotationally connected with the cleaning assembly. The surface of the unmanned aerial vehicle can be simply cleaned through the effect of the cleaning assembly, so that it is ensured that the surface of the unmanned aerial vehicle is kept clean when the unmanned aerial vehicle needs to be used next time, the damage condition caused by dust attachment is reduced, and the working efficiency of the unmanned aerial vehicle is improved.

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.

A method for performance analysis of an aircraft engine component includes accessing data of an aircraft engine component, the data including a performance signal; detecting a signature of the performance signal; performing a first analysis by an analytical model, based on the data and the performance signature, to determine performance metrics of the aircraft engine component; converting a first performance metric to a second performance metric based on a derivative, the derivative being derived from at least two of the determined performance metrics; determining an analytic for the aircraft engine component based on at least one of the derived derivative or the determined performance metrics; selectively providing a washing recommendation for the aircraft engine component based on the determined analytic; and selectively causing the aircraft engine component to be washed based on the washing recommendation.

A cleaning system (20) for a gas turbine engine (100) includes a foam supply unit (26) for generating cleaning foam (194) that is injected into the gas turbine engine (100), and an air blower (180) that is operably coupled to a core flowpath (121) of the gas turbine engine (100), the air blower (180) being configured to draw a flow of air (182) through the core flowpath (121) at a flow rate that induces rotation of the gas turbine engine (100) at a target rotational speed.

The invention relates to the technical field of snow blowing vehicles, and discloses a snow blowing vehicle snow blowing nozzle with a hard-shell snow removing function, which comprises a connecting pipe, the left side of the connecting pipe is communicated with a corrugated pipe, the left side of the corrugated pipe is communicated with a necking pipe, and the left side of the necking pipe is communicated with a snow blowing pipe; the outer side of the connecting pipe and the outer side of the necking pipe are fixedly connected with the same telescopic mechanism, a shell breaking mechanism with the two ends extending to the front side and the rear side of the snow blowing pipe respectively is arranged in the snow blowing pipe, and an air inducing mechanism which is located on the outer side of the shell breaking mechanism and can be in linkage with the shell breaking mechanism is further arranged in the snow blowing pipe. The snow blowing pipe is further provided with a turbulent flow mechanism located above the air inducing mechanism, and the front face of the snow blowing pipe is provided with a transmission device fixedly connected with the turbulent flow mechanism. According to the snow blowing nozzle of the snow blowing vehicle with the hard-shell snow removing function, the problems that an existing snow blowing vehicle is low in snow removing efficiency and has potential safety hazards when being used in the scene that much snow is accumulated on the surface of an airplane are solved.

An aircraft structure dynamic loading testing device, including a nozzle, an attachment mechanism with a first portion attached to the nozzle such that a nozzle force direction is constrained at a set orientation and a second portion for attaching to the aircraft structure and configured to be constrained at a given orientation with respect to the aircraft structure, and a length of conduit. In use, fluid is supplied along the length of conduit to the nozzle and ejected from the nozzle such that the nozzle exerts a dynamic force on the aircraft structure in the direction of the nozzle force direction. A dynamic loading testing device, a kit of parts and methods of dynamic load testing of a structure are disclosed.

To increase efficiency of the task of detecting and addressing FOD.SOLUTION: In one embodiment, systems and methods include using an inspection system to remove or seal foreign object debris. An inspection system comprises: a borescope, in which multiple optical fibers are disposed; a mounting system; an articulation system; and a controller, which comprises a display; where a proximal end of the borescope is coupled to the mounting system, the mounting system is configured to secure the inspection system to an external surface, the mounting system is coupled to the articulation system, the articulation system is configured to actuate the borescope, and the articulation system is communicatively coupled to the controller.SELECTED DRAWING: Figure 1

The application discloses a shipborne aero-engine cleaning equipment in the technical field of engine cleaning equipment, which comprises a water tank, a box body, a pipe coiler assembly, an output assembly and a control assembly, wherein the box body is internally provided with a sealed chamber, the output assembly, the control assembly and the pipe coiler assembly are all installed in the sealed chamber, and the gap between the through hole and the water pipe is sealed through a sealing assembly, so that the water pipe can freely leave the sealed chamber while the sealing effect of the sealed chamber is guaranteed, the output assembly, the control assembly and the pipe coiler assembly are isolated from the external environment, the corrosion of the output assembly, the control assembly and the pipe coiler assembly by the high-salt-mist environment at sea is reduced, the aging of various devices is effectively alleviated, and the service life of the overall equipment in the high-salt-mist environment at sea is increased.

An unmanned ground-based hygiene maintenance vehicle, UGV, includes a housing with a base plate, top plate and housing side wall substantially perpendicular to the base plate. Arranged in the housing is at least one wheel drive coupled to at least one wheel in a recess in the base plate. The UGV includes sensors for sensing the environment of the UGV, and a controller for autonomous location and navigation of the UGV based on sensing parameters of the sensors. The UGV includes an articulated robot arm on the top plate of the housing and to support a hygiene maintenance tool. The UGV includes at least one load-receiving element coupled to the housing side wall and extending outwards from the housing side wall, wherein the load-receiving element includes a load support surface for supporting a hygiene maintenance tool supply module with respect to a vertical direction extending transverse to the base plate.

The invention belongs to the field of aircraft cleaning, and relates to a cleaning device and method for a watertight compartment of an amphibious aircraft. And the track is fixed on a keel beam of a watertight compartment of an airplane through adhesive. The programmable trolley is installed in the track, and a plurality of motors are arranged in the programmable trolley. Wherein one motor rotates forwards or reversely under a control instruction of a built-in control module of the programmable control trolley to drive a wheel shaft of the programmable control trolley to rotate forwards or backwards, so that the trolley is driven to move forwards or backwards. The other two motors rotate by a fixed angle under the control instruction of the control module arranged in the trolley to drive the two mechanical arms to rotate within a certain angle range, and the telescopic hose sequentially passes through the programmable control trolley and the mechanical arms and is connected to the spray heads at the ends of the mechanical arms. Manual cleaning work does not need to be carried out in the watertight compartment for a long time, the maintenance cost is saved, and the suffocation risk of personnel is reduced; the method can be used as a measure for cleaning the watertight compartment after leakage during the offshore taxiing / test flight period of the amphibious aircraft.

The invention relates to the technical field of unmanned aerial vehicle nests, and provides a photovoltaic power station inspection unmanned aerial vehicle nest structure which comprises a bottom plate, limiting holes are formed in the outer surface of the bottom plate, and the whole nest structure is fixed by installing the bottom plate on a new energy vehicle; a photovoltaic energy charging assembly is fixedly connected to the top of the nest shell, an entering unit is arranged on the outer surface of the nest shell, a charging unit is arranged on the inner wall of the nest shell, and a rear disassembly plate is fixedly connected to the side, away from the entering unit, of the nest shell. The entering unit can remove dust and impurities on the surface of the unmanned aerial vehicle, then the unmanned aerial vehicle enters the charging unit to be charged, and the photovoltaic energy charging assembly can absorb solar energy to supplement energy to the whole structure.

To provide a system and method for disinfecting an interior of an aircraft.SOLUTION: An aircraft includes an interior and an environmental system configured to circulate air through the interior. The aircraft also includes at least one disinfectant dispenser configured to dispense a disinfectant in the air circulated through the interior. In one example, a disclosed method for disinfecting the interior of the aircraft includes steps of: (1) circulating air through the interior of the aircraft; (2) dispensing the disinfectant in the air circulated through the interior; and (3) removing the disinfectant from the interior when a predetermined situation is reached.SELECTED DRAWING: Figure 4

The utility model discloses a multi-rod cleaning device based on aircraft propeller wing driving, which is characterized in that a plurality of guide rods are fixed on the peripheral side of a fixed disc, and at least one cleaning component penetrates through the guide rods; the center of the fixing disc is rotationally connected with a rotating rod, threads are formed in the outer wall of the rotating rod, the rotating rod is rotationally connected with a driving block through the threads, one end of the transmission part is hinged to the cleaning assembly, the other end of the transmission part is hinged to the driving block, and the cleaning assembly comprises a cleaning block. A guide channel used for being matched with the guide rod is formed in the cleaning block, a cleaning channel is formed in the cleaning block, at least one cleaning brush assembly is installed in the cleaning channel, and at least one water outlet hole is formed in the inner wall of the cleaning channel. A pit is formed in the center of the fixing disc, a rotating motor is fixed to the pit, and an output shaft of the rotating motor is fixedly connected with a rotating rod. The propeller cleaning device is simple in structure and capable of automatically cleaning the propeller.

The utility model discloses an aviation cleaning device which comprises a cleaning box, a gun head, a spraying module and an adsorption module, the cleaning box is provided with a cleaning liquid cavity, a first access port and a second access port, the gun head is detachably connected to the cleaning box, the spraying module is provided with a first spraying head and a second spraying head, and the first spraying head and the second spraying head are different in caliber. The gun head is detached from the cleaning box and connected with the first access port and the second access port, then the first spray head or the second spray head is detached to be cleaned and connected with the gun head according to requirements, cleaning liquid can be sprayed through the first spray head or the second spray head, aviation equipment is cleaned, and the adsorption module is arranged in the cleaning box and can adsorb grease and impurities. According to the aviation equipment cleaning device, the first spraying head or the second spraying head can be arranged for spraying during cleaning work, so that spraying of spraying liquid with different flow speeds and spraying diameters is achieved, and the aviation equipment cleaning device adapts to cleaning of the aviation equipment in different space ranges.

This invention provides an automatic cleaning method and system for the hangar door side of polar shipborne helicopters. This invention belongs to the technical field of aviation ground support equipment and ship auxiliary machinery. The cleaning method includes: acquiring helicopter images, extracting key features of the fuselage, identifying the aircraft type and calculating the initial pose based on the PnP algorithm, and converting the preset cleaning path to the coordinate system of the cleaning device; generating a propeller cleaning sub-path, employing a master-slave control strategy to control two robotic arms to synchronously flush and clean the upper and lower surfaces of the propeller blades, and maintaining the balance of jet impact force through pressure closed-loop feedback; establishing a ship swaying dynamics model to estimate and predict the ship's motion state in real time, and combining the real-time feedback deviation vector obtained from laser ranging and visual acquisition to generate a corrected speed command; identifying the surface state category through temporal filtering and texture analysis, and adaptively adjusting according to the identification results.

The present invention is entitled "Disinfection System." A disinfection system includes a plurality of ultraviolet (UV) lamps and a control unit including one or more processors. The UV lamps are installed at various locations within the interior compartment of a vehicle. The UV lamps are configured to receive power from a power source on the vehicle and to emit UV light into the interior compartment during vehicle operation. The control unit is operatively connected to the UV lamps and is configured to modify the power supplied to one or more of the UV lamps located in the public area of ​​the interior compartment based on the occupancy of the public area.

Disclosed herein is a surface preparation and livery printing system and a method of preparing a surface and printing a livery. The method includes preparing (205) a surface of an aircraft part in a first processing booth to form a prepared surface of the aircraft part. The method also includes transporting the aircraft part to a second processing booth being adjacent to the first processing booth upon completion of preparing the surface. The method further includes applying (210) a livery to the prepared surface of the aircraft part in a second processing booth and upon completion of applying the livery, transporting the aircraft part to a third processing booth being adjacent to the second processing booth. The method still further includes applying (215) a clearcoat over at least the livery applied to the prepared surface of the aircraft part in a third processing booth.

In one embodiment, systems and methods include using an inspection system to remove or seal foreign object debris. An inspection system comprises a borescope; wherein a plurality of optical fibers is disposed within the borescope; a mounting system; an articulation system; and a controller, wherein the controller comprises a display; wherein a proximal end of the borescope is coupled to the mounting system, wherein the mounting system is configured to secure the inspection system to an external surface, wherein the mounting system is coupled to the articulation system, wherein the articulation system is configured to actuate the borescope, wherein the articulation system is communicatively coupled to the controller.

A control apparatus, which controls a drive motor that drives a rotor installed in an electrical aircraft, instructs the drive motor to selectively operate in at least two motor-control modes. The at least two motor-control modes include a flying motor-control mode for causing the electrical aircraft to fly, and a cleaning motor-control mode for cleaning the rotor. The control apparatus controls, in the cleaning motor-control mode, the drive motor such that a rotational frequency of the drive motor is lower than a predetermined human-audible frequency range.

The invention relates to an aircraft ground support unit (1) (GSU) for supplying a specific service according to a specific set of service parameters to an aircraft (2) on the ground and consuming a specific service energy for supplying the specific service as a whole in a given available service duration, the GSU comprising: a rechargeable energy storage unit (3) (RESU) which, when fully charged, is configured for autonomously delivering the specific service energy required for supplying the specific service in the given available service duration, an energy sensor (4) configured for measuring an instantaneous state of energy parameters of the RESU, a control unit (5) configured for, • identifying the aircraft (2), preferably including an aircraft type and an airline, • identifying in the database the specific set of service parameters of the specific service to the thus identified aircraft, • establishing a specific service energy budget estimate corresponding to the specific set of service parameters in various ways, • determining an instantaneous charge level of the RESU based on the instantaneous state of the energy variables, • comparing the specific service energy budget estimate with the instantaneous charge level of the RESU, and for • generating an output signal representative of a capacity of the RESU to deliver the specific service energy budget estimate as a function of the instantaneous charge level of the RESU.

An auxiliary power unit (10) includes an air inlet housing (26); a compressor (12; 56) arranged to receive air from the air inlet housing (26); and a spray nozzle positioned within the air inlet housing (26) oriented to spray a cleaning fluid directly at the compressor (12; 56), the spray nozzle having a connection for connecting to a source of cleaning fluid.

The application discloses an aero-engine ground cleaning device and method, and belongs to the technical field of aero-engine cleaning. The device comprises a solution storage system, a pipeline system and a control system arranged in the device body. The solution storage system comprises a cleaning liquid tank and a clean water tank. A temperature control assembly is arranged in the solution storage system, which controls the temperature in the cleaning liquid tank and the clean water tank. The clean water tank and the cleaning liquid tank are connected with the pipeline system, which controls the automatic switching and flow regulation of the clean water tank and the cleaning liquid tank. The control system is connected with the temperature control assembly and the pipeline system, and controls the cleaning temperature and the cleaning speed. The cleaning liquid tank and the clean water tank are switched to sequentially and finely clean the aero-engine with the cleaning liquid and the clean water, and the temperature of the cleaning liquid and the clean water is controlled. The cleaning parameters are set according to the type of the aero-engine.

To provide autonomous or semi-autonomous mobile UV sanitizing equipment that can consistently and efficiently sanitize structures and areas while moving.SOLUTION: An ultraviolet (UV) light sanitizing cart includes a UV light array, a body, actuators, and a control unit. The UV light array includes UV lamps configured to emit UV light to sanitize a surface of a component. The body includes a mobile base and multiple interconnected rigid members supported by the base. The UV lamps are mounted on at least one of the rigid members. The actuators are mechanically connected to the body. One or more of the actuators are configured to move the rigid members relative to the base. The control unit is configured to generate control signals for controlling the actuators to move the UV light array along a sanitizing path that follows a contour of the surface.SELECTED DRAWING: Figure 1

A portable sanitizing system and method include a wand assembly including a sanitizing head having an ultraviolet (UV) lamp. A container includes an internal chamber. The wand assembly is coupled to the container. One or more component modules are configured to be removably secured within the internal chamber.

A treatment system for a gas turbine engine includes a detergent supply containing a detergent, the detergent comprising a corrosion-resistance additive (e.g., Gadolinium doped ceria particles, a foam generating assembly operably coupled to the detergent supply, the foam generating assembly being configured to generate a foam using the detergent, and a foam supply line fluidly coupling the foam generating assembly to a cleaning port of the gas turbine engine to supply the foam into the gas turbine engine.

A wash system (300A, 300B, 300C) for washing a gas turbine engine (10) having a compressor section (22, 24), a combustion section (26), and a turbine section (28, 30) includes a detergent reservoir (365) for storing a wash fluid (372), a foam wash module (315) in fluid communication with the detergent reservoir (365) for generating a flow of foamed wash fluid (376), a particulate reservoir (370) for storing solid particulates (380), and at least one supply line (378) fluidly coupled to the foam wash module (315) and the particulate reservoir (370) for supplying a mixture of the foamed wash fluid (376) and the solid particulates (380) to the gas turbine engine (10).

A maintenance tool (5) for aircraft equipment comprising a plurality of bladed stages, the aircraft equipment comprising an inner circumferential surface, the maintenance tool (5) comprising: a frame (6), a support member (7) configured to support the aircraft equipment, the support member (7) being mounted to rotate about a principal axis (Z) relative to the frame (6), the frame (6) comprising a cleaning system (8) having at least one cleaning nozzle (9) configured to project a cleaning fluid onto the inner circumferential surface of the aircraft equipment. (See abstract figure: Figure 4)