397 results about "Cowling" patented technology

The invention discloses an aircraft fairing and a fairing body composite material integrated forming process, and relates to the technical field of aviation equipment manufacturing. The forming process comprises the following steps: 1) preparing a prepreg; (2) sectional forming; 3) a curing process; (4) demolding and trimming; 5) an assembly process; the whole of the front section, the middle section and the tail section of the fairing is of a long-size U-shaped streamline structure. According to the invention, through molecular collaborative design of fluorination modification-polysiloxane toughening-cyanate ester interpenetration, the key contradiction of a high-performance fairing material is systematically solved; ultrahigh strength and toughness are realized at the same time by utilizing in-situ nano microphase separation; a dense graphite carbon layer is generated through catalysis, so that efficient halogen-free flame retardance is achieved; by means of the partition design of molecular fluorination and surface metallization, the high wave transmission and lightning protection functions are ingeniously unified. And finally, a new generation of aircraft fairing composite material with force bearing, wave transmission, heat resistance, impact resistance and environmental stability is successfully prepared.

The embodiment of the invention discloses a digitalized assembling method of a helicopter fairing, which comprises the following steps of: 1, scanning the surface of the fairing and the surface of a helicopter body structure, and acquiring a three-dimensional contour model of the surface of the fairing and the surface of the helicopter body structure according to scanning data; 2, generating a visual assembly correction scheme by comparing the three-dimensional contour model with a design model imported into a controller; 3, in the fairing assembly process, a visual assembly correction scheme is projected through laser, non-contact hole making and polishing guiding are achieved, and digital assembly of the fairing is implemented; and 4, in the fairing assembling process, dynamic position information of the fairing and all the positioning targets on the aircraft body structure is obtained, the moving track of the fairing in the assembling process is solved, automatic alarming is conducted when the fairing is out of tolerance, and laser projection is frozen. The problems that an existing fairing assembling mode is low in assembling efficiency and precision, and the production efficiency and the assembling requirement of a helicopter are difficult to meet are solved.

The invention discloses a wind turbine fairing optimization design method, which relates to the technical field of fluid machinery and engineering, and comprises the following steps: a basic parameter acquisition and working condition defining step: collecting wind turbine model parameters, and measuring the wind condition of an operation area; the flow guide cover is divided into a windward section, a middle section and a wake flow section; a multi-objective optimization system construction step: determining aerodynamic resistance, structural strength, weight and wake flow influence optimization objectives; an optimization algorithm iteration solving step, wherein an improved non-dominated sorting genetic algorithm is adopted; a simulation verification and parameter correction step: selecting a scheme to perform CFD and finite element simulation; and a physical prototype manufacturing and performance testing step: manufacturing a prototype, and carrying out wind tunnel and field testing. The design efficiency of the air guide sleeve is improved, systematicness is optimized, pneumatic, structure and weight multi-target balance is achieved, cross-model universality is improved, and the problems that traditional design is dependent on experience and unbalanced in performance are solved.

Systems and methods include a tilt device for an aircraft vehicle. The tilt device is configured to rotate a rotor assembly between first and second positions. The tilt device comprises a linear actuator disposed within an aircraft fairing; a sleeve having a slot defined therein; and a piston coupled to the linear actuator configured to translate axially within the sleeve. A method includes actuating the linear actuator to translate the piston, wherein the rotor assembly is coupled to an end of the piston and comprises a motor and one or more rotor blades. The method further includes rotating the piston within the sleeve as the piston translates axially along the sleeve via a pin disposed within a slot defined in the sleeve, wherein the pin extends from the piston and through the slot. The method further includes actuating the motor to operate the one or more rotor blades.

A propulsion assembly having a fairing, a combustion chamber housed in the fairing, an exhaust nozzle delimited by a nozzle wall, a dihydrogen tank, a double-walled supply duct between the tank and the combustion chamber that has an inner wall delimiting an inner volume for the circulation of the dihydrogen and, around it, an outer wall delimiting an outer volume, and a bypass chamber, which is positioned around the nozzle wall and in which is made an upstream orifice for the introduction of the combustion gases and a downstream orifice for the discharge of the combustion gases, and wherein the supply duct has a portion arranged in the bypass chamber.

The present disclosure relates to a motor vehicle including a frame, a fairing, handlebars, and at least one fairing extension. The fairing and said handlebars are connected to the frame, such that the fairing deflects air about the handlebars at a first deflection angle. The fairing is removably attached to the at least one adjustable wind fairing extension, the fairing extension including at least one planar surface and, in some embodiments, at least one extendible planar surface, a hinge, an aperture, and at least one adjustment pin. The extendible planar surface is adjustable about said hinge along an adjustment plane up to the maximum extension allowed by the at least one adjustment pin. The fairing extension deflects air about the handlebars at a second deflection angle. The extension of the extendible planar surface deflects air about the handlebars at a third deflection angle.

The invention relates to the technical field of heat exchangers, and discloses an aircraft comprehensive heat exchanger which comprises a shell, a longitudinal vortex generator fin set and a micro-channel liquid cooling circulation system, a flow guide cavity for containing cooling liquid is formed in the shell, and the shell and an aircraft belly fairing are integrally installed; the longitudinal vortex generator fin set comprises a plurality of fins of a three-dimensional twisted structure, every two fins symmetrically arranged in the horizontal direction form a fin unit, the fin units are fixed to the face, away from an aircraft belly fairing, of the shell in rows, the twisting angle theta of the fins ranges from 30 degrees to 60 degrees, the ratio of the twisting wavelength to the height of the fins ranges from 0.5 to 2.5, and the width of the fins ranges from 0.5 to 2.5. The micro-channel liquid cooling circulation system is arranged in the shell and comprises a first-stage main channel arranged in the arrangement direction of the fin units, a second-stage branch channel comprises a plurality of rhombic channels penetrating through the first-stage main channel, and a third-stage micro-channel is parallel to the first-stage main channel and penetrates through the second-stage branch channel and can optimize the heat exchange characteristic.

A vehicle cowl structure can include a cowl lower panel extending in a width direction of a vehicle, and a guide panel having an outer end coupled to an inner end of the cowl lower panel in a configuration so that outside air can be introduced into an air conditioning device of the vehicle, wherein the outer end of the guide panel is positioned to be higher than the inner end of the cowl lower panel, such that a gap is defined between the inner end of the cowl lower panel and the outer end of the guide panel.

The invention discloses a fragile front cover of a launch canister, a preparation method and a test system comprising the fragile front cover, the fragile front cover comprises a cover body and a flange part annularly arranged on the periphery of the cover body, at least three radial weakening grooves are formed in the front face of the cover body, an annular weakening groove is formed in the position, close to the edge, of the back face of the cover body, and the section of the annular weakening groove is in a single-slope wedge shape. Comprising a vertical side wall and an inclined side wall, the vertical side wall is vertically connected with the end face of the flange part, an angle a is formed between the inclined side wall and the end face of the flange part, and the inclined side wall extends from the groove bottom of the annular weakening groove to the surface of the cover body and intersects with the vertical side wall to form a directional crack propagation area, so that cracks preferentially extend along the angle a under the impact load effect. Through the design that the integrated polyurethane foaming body is combined with the directional crack propagation area, the actually-measured bursting force peak value is smaller than or equal to 7 kN, and the low-impact requirement of the missile fairing is met. The radial weakening grooves in the front face and the wedge-shaped annular weakening grooves in the back face achieve the synergistic effect, so that the maximum size of the fragments is far smaller than a safety threshold value.

The present application belongs to the technical field of engine detection, and aims to solve the problems of low detection accuracy, high probability of missed detection and low detection applicability. A serpentine robot for aircraft engine detection is provided, which comprises a front vehicle module, a middle vehicle module and a rear vehicle module connected in turn through a bearing composite mechanism; a module attitude adjusting rudder is connected with the bearing composite mechanism, and is used for adjusting the attitude of the front vehicle module, the middle vehicle module or the rear vehicle module; the front vehicle module further comprises a front pulling fork mechanism, a mechanical arm and a visual detection mechanism installed on an integrated seat; the front pulling fork mechanism is used for pulling the engine blades one by one, and cooperates with the visual detection mechanism to detect the blades; the mechanical arm is used for driving the visual detection mechanism to move in multiple directions; and the visual detection mechanism is used for detecting the air duct, the fairing and the blades of the engine. In the present application, the serpentine pipeline robot configuration can adapt to irregular tracks, can freely correct the in-out pose, has wide applicability and high detection accuracy.

The invention relates to the field of rocket assembling equipment, and provides a horizontal position adjusting device for a fairing fixture body, which comprises an upper bearing plate, a middle bearing plate and a lower bearing plate which are sequentially arranged from top to bottom, a first lead screw assembly is arranged between the lower bearing plate and the middle bearing plate and comprises a first lead screw and a first lead screw nut, the first lead screw nut is installed on the first lead screw, and a first hand wheel is arranged at one end of the first lead screw. A first vertical bearing assembly is arranged between the lower bearing plate and the middle bearing plate; a second lead screw assembly is arranged between the upper bearing plate and the middle bearing plate and comprises a second lead screw and a second lead screw nut, the second lead screw nut is installed on the second lead screw, and a second hand wheel is arranged at one end of the second lead screw. A second vertical bearing assembly is arranged between the upper bearing plate and the middle bearing plate. By means of the device, accurate translation of the upper bearing plate in the horizontal direction relative to the lower bearing plate can be achieved in a manual mode, and the device is high in bearing capacity, convenient to operate and beneficial to improving the butt joint efficiency of the two half covers.

Variable pitch fan blade (8a) for an unfaired turbomachine fan, the blade (8a) comprising an aerodynamic blade (9) and a base (10), the blade (9) comprising a recess opening simultaneously onto the upper and lower surfaces (14) and a leading edge (15) of the blade (9), the blade (8a) further comprising a measuring device (26) housed in the recess and clipped onto the blade (9), the measuring device (26) comprising a streamlined body (28) whose outer surface (29) is complementary to the outer surface (30) of the blade (9) to ensure aerodynamic continuity, the body (28) carrying at least one measuring instrument (31) configured to measure at least one parameter of an airflow upstream of the blade (9). Figure for the abstract: 2

A cone segment structure of the fairing includes two half-hood structures, the two half-hood structures are both composed of a plurality of bus metal bars and a plurality of loop metal bars that are sequentially connected in an intersected mode, each of the bus metal bars is made in a Von Karman curve shape by adopting a stretch bending mode, the two half-hood structures form a hood with a Von Karman cone segment structure, the hood is covered with a skin, and a top end of the hood is provided with an end cap.

A scroll compressor including a hermetic casing provided with a suction inlet; a compression unit; a drive shaft configured to drive an orbiting scroll of the compression unit in an orbital movement; an electric motor coupled to the drive shaft; an oil sump; a refrigerant guiding device configured to force a main part of a refrigerant, entering the scroll compressor through the suction inlet, to flow downwardly through the electric motor, before reaching the compression unit; and an oil sump fairing arranged between a lower end of the electric motor and a free surface of oil stored in the oil sump, the oil sump fairing being configured to prevent a refrigerant flow, emerging from the lower end of the electric motor, to directly impact the free surface of the oil stored in the oil sump.

An aircraft propulsion unit comprising a motor, a system for supplying fuel to the motor, a fairing inside which the motor and at least part of the fuel supplying system are positioned, and at least one pressure relief device configured to establish communication between the inner and outer zones of the fairing when the pressure in the inner zone is greater than or equal to a given threshold or when a leak is detected. Also an aircraft comprising at least one such propulsion unit.

The utility model relates to the technical field of aircraft, and disclose a kind of movable landing gear fairing, including landing gear and upper fairing, the one end of landing gear is provided with mounting hole, mounting hole is provided with multiple, and pass through upper fairing and enter aircraft, by the mounting hole and aircraft fixed connection, can be fixed by bolt or bolt etc. detachable fixed mode, the upper fairing is fixedly connected with aircraft. By adopting the structure form of one end without connection, the deformation of landing gear can be better absorbed, the inside is filled with foaming material with good compression, effectively supporting fairing, thereby improving stability, solving the problem that fairing is prone to deformation damage, and internal support is insufficient, and stability is poor.

The utility model discloses a double-speed jet flow fan which comprises a fan base, silencing cylinders are connected to the two ends of the fan base, a fairing is arranged in the fan base and fixedly connected with the inner wall of the fan base through a plurality of hollow pipes, a double-speed motor is fixedly connected into the fairing, and an impeller is fixedly connected to the driving shaft end of the double-speed motor. According to the utility model, a power frequency motor in the fan is replaced by the double-speed motor, and a half-power operation mode is adopted, so that the daily ventilation is met, and the energy consumption can be reduced.

A locking system to secure a trans cowl to a frame of a thrust reverser on an engine of an aircraft. The locking system includes an arm that is connected to the trans cowl with the arm having a receptacle. A lock includes a body and a pin with the pin movable relative to the body and with the lock positionable between a locked position and an unlocked position. In the locked position, the pin is in an extended position relative to the body that extends into the receptacle to secure the trans cowl in a stowed position. In the unlocked position, the pin is in a retracted position relative to the body that is away from the arm to enable the trans cowl to move to a deployed position.

The utility model relates to the technical field of propellers, and discloses a bearingless rotor hub and a flexible beam propeller, the bearingless rotor hub comprises a hub upper pressing plate arranged on the upper surface of a hub central assembly, a bolt arranged on the upper surface of the hub upper pressing plate, a nut in threaded connection with the outer surface of the bolt, and a flexible beam arranged on the outer surface of the nut. A positioning assembly is arranged on the inner wall of the hub center assembly, in order to make the lifting force on the two sides of the hub of the aircraft more uniform, the aircraft adopts a bearingless rotor system, a bearingless rotor hub and a flexible beam propeller, the load transmission efficiency is high, the hub is simple in structure, light in weight and low in manufacturing cost, and the bearingless rotor hub is small in resistance and high in reliability. Compared with an integrated paddle and a split paddle, a fairing does not need to be additionally arranged, the flight efficiency is high, the overall appearance is attractive, and compared with a fixed pitch propeller clamp mechanism in the prior art, the lifting force of the two sides of the bearingless propeller hub of the aircraft is more uniform through the structure of the bearingless propeller hub and the flexible beam paddle.

The utility model relates to a follow-up hatch cover, a nacelle and a tilt rotor aircraft, belongs to the technical field of aircrafts, and solves the problems that the appearance of a rotor shaft fairing in the prior art has a bulge, and interference exists between the rotor shaft fairing and the nacelle. The device comprises a hatch cover unit, a hinge unit, a sliding rail unit and a sliding unit, the hinge unit and the sliding unit are arranged at the two ends of the hatch cover unit respectively, the sliding rail unit is arranged on a power cabin, the hinge unit is used for connecting the hatch cover unit with a rotor shaft cabin, and the sliding rail unit is used for connecting the hatch cover unit with the rotor shaft cabin. The sliding unit is used for enabling the hatch cover unit to slide along the sliding rail unit. The cabin cover unit can slide along the sliding rail unit along with rotation of the rotor shaft cabin, and when the aircraft takes off and lands vertically, the cabin cover unit moves towards the power cabin and exposes the sunken part, so that the rotor shaft fairing can be inserted into the sunken part, and interference between the rotor shaft fairing and the power cabin is avoided.

A refuse vehicle includes a chassis, a cab coupled to the chassis, a body coupled to the chassis, the body including a refuse compartment configured to store refuse, a lift assembly configured to transfer refuse from a refuse container into the refuse compartment, a cowl coupled to at least one of the body or the cab and extending above the cab, and a heat exchanger positioned at least partially within the cowl such that the heat exchanger extends above the cab.

An electronic device may be provided with peripheral conductive housing structures, a rear wall, and a vent that includes a conductive cowling. The device may include an antenna having an antenna arm coupled to a positive antenna feed terminal and having a parasitic element. The parasitic element may be formed from a conductive trace that is layered onto the rear wall, that is indirectly fed by the antenna arm, and that overlaps a portion of the conductive cowling. The parasitic element may be shorted to a conductive bracket on the rear wall or may be separated from the bracket by a gap. If desired, the conductive cowling may form some or all of a parasitic element for the antenna. The conductive cowling may be indirectly fed by the conductive trace and / or may include an extension that is indirectly fed by the antenna arm.

The invention discloses a composite material fairing, a combined die and a forming method. The fairing comprises a connecting support, a supporting core material, a suction surface shell, a pressure surface shell, a left wing type surface shell, a right wing type surface shell and an empennage. The supporting core materials are arranged on the two sides of the connecting support, the suction surface shell covers the tops of the supporting core materials and the top of the connecting support, and the pressure surface shell covers the bottoms of the supporting core materials and the bottom of the connecting support. The leftmost side of the supporting core material is covered with the left wing profile shell, the rightmost side of the supporting core material is covered with the right wing profile shell, and the rear end of the connecting support is covered with the tail wing. The suction surface shell, the pressure surface shell, the left wing type surface shell, the right wing type surface shell and the empennage are all carbon fiber reinforced resin matrix composite material structural parts. The manufacturing method is applied to the field of fairing manufacturing, high forming precision is achieved, light-weight treatment of the fairing can be achieved, and the manufacturing process is relatively simple.

The invention provides a vertical power module heat dissipation device and method and an aircraft, and belongs to the technical field of aircrafts, and the heat dissipation device comprises a heat exchanger fairing and a heat exchanger; the heat exchanger fairing is in a streamline shape with two sharp ends and a wide middle, the two ends of the heat exchanger fairing are fixedly arranged on the power arm body, and heat exchanger heat dissipation openings are formed in the top of the heat exchanger fairing and located below the forward-rotating propeller and the reverse-rotating propeller. Driving motor modules of the forward-rotating propellers and the reverse-rotating propellers are located in the heat exchanger fairing, and heat exchanger heat dissipation channels are formed between the inner side wall of the heat exchanger fairing and the two sides of the top of the power arm body; the heat exchanger is arranged in the heat exchanger fairing, and cooling fins of the heat exchanger are arranged at heat dissipation openings of the heat exchanger. And a hot liquid inlet and a cold liquid outlet of the heat exchanger are respectively connected with a cooling liquid outlet pipe and a cooling liquid inlet pipe of the driving motor module. The problem that in the prior art, a heat dissipation structure is arranged outside a power arm, and flight resistance is caused to cruise flight of an aircraft can be solved.

Locking system for a thrust reverser of an aircraft. A locking system for securing a translating cowl to a frame of a thrust reverser on an engine of an aircraft. The locking system includes an arm connected to the translating cowl, wherein the arm has a receiving portion. A lock includes a body and a pin, wherein the pin is movable relative to the body, and wherein the lock is positionable between a locked position and an unlocked position. In the locked position, the pin is in an extended position relative to the body, the pin extending into the receiving portion to secure the translating cowl in a stowed position. In the unlocked position, the pin is in a retracted position relative to the body, away from the arm, to enable movement of the translating cowl to a deployed position.

An acoustic blanket absorbs acoustic energy and reduces noise in a launch vehicle. The acoustic blanket may be overlaid on a wall of a payload fairing of the launch vehicle. Materials and construction of the acoustic blanket allow for a relatively thin and light sound barrier. The acoustic blanket may comprise vertically-lapped polyester that is overlaid with a lightweight melamine foam. This combination of materials creates an acoustic impedance mismatch between layers that leads to absorption of acoustic energy across a relatively broad range of frequency bands. The acoustic blanket has a particular heat seal pattern that helps absorb noise while allowing the acoustic blanket to be relatively soft and flexible, which is useful for attaching the acoustic blanket to a curved wall of a fairing or other launch vehicle shapes. The acoustic blanket utilizes micro-perforations on multiple sides to allow for movement of air / venting while maintaining the bulk materials inside.

An assembly (1) of variable-pitch blades for an unfaired aircraft turbomachine, the assembly comprising a rotor (3) movable about a radial axis (X) of the turbomachine, a stator (4) fixed about said radial axis (X), and at least one lightning arrester (5). The lightning arrester (5) comprises a pin (6), at least one face of said pin (6) being in contact by friction with the rotor (3), a screw (7) radially extending from said pin (6), and a means (8) for connecting the pin (6) and the screw (7), said means (8) comprising a spring interposed between the pin (6) and the screw (7). Figure for the abbreviation: Fig 1

The application relates to the technical field of aircraft fairing, and discloses an electric heating assembly and an air inlet fairing applying the electric heating assembly, the electric heating assembly is applied to ice prevention and deicing of the air inlet fairing, and the electric heating assembly comprises a first heating piece and a second heating piece; the first heating piece is arranged from a near tip to a peripheral wall of the air inlet fairing, a first electrode of the first heating piece and the tip of the fairing form a first temperature zone, a second temperature zone is formed between the first electrode and a second electrode, and a first difference value between an average temperature of the second temperature zone and an average temperature of the first temperature zone is obvious to meet the requirement of a higher temperature of the tip; the first temperature zone is arranged to realize directional heating of the tip area, the ice prevention and deicing capacity of the tip area is obviously improved, and the problem of insufficient heating of the tip and easy icing in the prior art is solved.