622 results about "Cowling" patented technology

An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft comprises a fuselage extending between the forward end of the aircraft and the aft end of the aircraft; a wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; an unducted turbofan engine including an unducted fan defining a fan diameter; and a pylon fairing that connects the unducted turbofan engine to the wing assembly, the pylon fairing defining a leading edge and including a first inflection point along the leading edge, the first inflection point defining a first radius of curvature that is less than 5 times the fan diameter and greater than 0.1 times the fan diameter.

The invention belongs to the technical field of engine nacelle part production, and particularly relates to an intelligent welding system and method for an engine nacelle combined type air inlet fairing. An inner spoiler moving groove and an outer spoiler moving groove are machined in the air inlet duct casting blank borne by the air inlet duct positioning assembly through the inner cutting assembly and the outer cutting assembly correspondingly, and the air inlet duct casting blank is formed into an air inlet duct component; a first clamping feeding assembly, a second clamping feeding assembly, a third clamping feeding assembly and a fourth clamping feeding assembly are used for feeding an inner reinforcing part, a heating part, a noise reduction and sound absorption part preassembled with a spoiler assembly and an annular cover plate into a cavity of the air inlet channel component, and the fed parts are welded and fixed into the cavity of the air inlet channel component through a welding assembly; in this way, intelligent welding and assembling operation of the combined air inlet fairing can be achieved, and the combined air inlet fairing has the advantages of being high in structural strength, good in noise reduction and sound absorption effect and capable of achieving automatic deicing of the lip and air inlet distortion control.

The invention belongs to the technical field of engine nacelles, and particularly relates to an engine nacelle fairing with an inner supporting framework system.The engine nacelle fairing is reasonable in design and is mainly composed of a rectifying outer cover, a first inner supporting framework, a second inner supporting framework, an arc-shaped air guide pipe and an annular cover plate; a plurality of sets of first positioning protrusions and second positioning protrusions corresponding to the first positioning protrusions are installed in an annular cavity of the rectification outer cover, and the first inner supporting frameworks or the second inner supporting frameworks are connected in an inserted mode through the first positioning protrusions and the second positioning protrusions corresponding to the first positioning protrusions. The first inner supporting framework, the second inner supporting framework and the arc-shaped air guide pipe can be pre-assembled into an inner supporting framework system, the annular cover plate is used for sealing the annular cavity of the rectification outer cover, in this way, the overall compressive strength of the engine nacelle fairing can be greatly improved, and meanwhile heat generated by working of an engine can be used for achieving freezing prevention of the fairing.

The invention belongs to the technical field of overall aerodynamic design of helicopters, and particularly relates to an infrared suppressor fairing of a helicopter and an air heat optimization design method of the infrared suppressor fairing. The fairing comprises a fairing body, a shutter air inlet, a square protective net air inlet, a second-stage exhaust pipe and a first-stage mixed exhaust pipe. The front of the fairing body is regarded as a half ellipse which is laterally cut along a long axis; a shutter air inlet is formed in the front portion of the fairing body, and the plane of a shutter is crescent A square protective net air inlet is formed in front of the top of the fairing body; an oval second-stage exhaust pipe is arranged behind the top of the fairing body so that high-temperature exhaust can be further cooled by means of downwash airflow of the rotor wings. A first-stage mixed exhaust pipe is sleeved in the second-stage exhaust pipe; and the primary mixing exhaust pipe is connected with an outlet of the transmitter. According to the method, the problem that the pneumatic performance and the thermal performance are difficult to consider in a traditional design method is solved, comprehensive optimization of the pneumatic performance and the thermal performance of the fairing is achieved, and a pneumatic design scheme of the infrared suppressor fairing is formed.

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.

A firewall system isolating a fire zone of an engine (2) from a hanger (1) located in a non-fire zone, comprising: a vertical firewall (3) arranged at a front end of a frame of the hanger, on which a support structure (13) is arranged for mounting the hanger and a fairing of the engine; and a bottom firewall (7) which is provided so as to extend rearward from the vertical firewall, is provided so as to cover the suspended frame from below, has a bottom plate (71), a left side plate (72), and a right side plate (73), and has an isolated space formed by the vertical firewall, the bottom firewall, and the suspended frame. Fireproof sealing isolation of an aircraft engine can be achieved, meanwhile, arrangement of multiple systems such as fuel oil, hydraulic pressure, an air source, fire prevention, power and EWIS is achieved, influences between the systems are avoided, and structural weight reduction can be achieved.

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.

A marine drive may include a frame configured to support the marine drive with respect to the marine vessel, a cowling enclosing a portion of the frame in a cowling interior, a steering arm configured such that movement of the steering arm causes rotation of the marine drive with respect to the steering axis, and a flexible rigging connector extending from the cowling interior to a location in the marine vessel. The flexible rigging connector may extend through a guide passage in the steering arm. Additionally or alternatively, the steering arm may include a base member and a mounting member selectively movable relative to the base member to adjust the length of the steering arm.

A gas turbine engine includes a fan assembly, a turbomachine defining in part a working gas flowpath, the gas turbine engine defining a bypass passage over the turbomachine, a core cowl, and a heat exchanger assembly including a heat exchanger and a heat exchanger cowl defining a cooling air flowpath extending between a flowpath inlet in airflow communication with the bypass passage to receive a cooling airflow from the bypass passage and a flowpath outlet in airflow communication with the bypass passage to exhaust the cooling airflow back to the bypass passage, the heat exchanger positioned within the cooling air flowpath, the cooling air flowpath comprising a diffusion section located between the flowpath inlet and the heat exchanger.

This document describes a system that can be attached to the outer skin of a vehicle, such as an aircraft. A disclosed version of the system comprises an antenna component, a support frame, brackets, and an aerodynamic fairing. The antenna component is connected to the support frame, which has a plurality of clevis mounting features. Each support fitting can be coupled between one of the clevis mounting features and the outer skin of the vehicle. The fairing consists of an upper and a lower part. The upper part has a defined opening. The lower part is configured and arranged to connect to the outer skin of the vehicle. The opening is shaped and dimensioned to accommodate at least a portion of the support frame that is connected to the upper part of the fairing.

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.

Systems and methods are disclosed for providing a deployable fairing system to a tractor trailer. The deployable fairing system includes an actuator used to extend the deployable fairing from an unextended configuration to an extended configuration to occupy a portion of a gap area that exists between a tractor and an attached trailer. The deployable fairing includes deployable upper and / or lower horizontal assemblies that are pivotally coupled to a frame attached to the tractor / cab, and two side panels that are pivotally coupled to one or both of the upper and lower horizontal assemblies. The deployable upper and lower horizontal assemblies and the two side panels fold in on one another along multiple hinged axes in the unextended configuration, and extend rearward from the top and sides of the tractor in the extended configuration to cover a portion of the gap. The fairing may advantageously flair from front to the rear.

The invention relates to the technical field of aircraft fairing assembly and disassembly, in particular to a suspension device for aircraft fairing assembly and disassembly, which comprises a bearing base and further comprises a vertical groove body arranged on the upper side of the bearing base, the lower end of the vertical groove body is fixedly connected with a driven shaft penetrating through the bearing base, and the bottom end of the driven shaft is fixedly connected with a driven gear in a clamping manner; a driving shaft penetrates through the bearing base, and the bottom end of the driving shaft is fixedly connected with a driving gear in a clamped mode. According to the suspension device, the aircraft fairing can be rapidly suspended to different directions and different height positions, the automation degree is high, the stability of the suspension process is high, the working safety is ensured, the aircraft fairing with different lengths and different thicknesses can be positioned on the suspension device, the application range is relatively large, and the suspension device is suitable for popularization and application. And the number of the balancing weights can be adjusted according to the weight of the aircraft fairing, the balancing weights can be conveniently and rapidly placed, the operation difficulty is low, and the stability in the suspension process is further ensured.

The invention relates to a heat dissipation air duct of a liquid cooling radiator of a piston engine, which not only meets the low resistance requirement of the aerodynamic configuration of an aircraft, but also meets the heat dissipation power requirement of the engine. Comprising an external fairing and an internal heat dissipation air channel, the external fairing is matched with the appearance of a machine body and completely wraps the internal heat dissipation air channel, the internal heat dissipation air channel is divided into a front cold air inlet area, a middle radiator area and a rear hot air flow guide area, and the front cold air inlet area is connected with the external fairing; a radiator is fixed in the middle radiator area, the rear hot air flow guide area and the outer fairing are of an integrated structure, an air guiding opening is formed in the front portion of the outer fairing, an engine air inlet is formed in the left side of the middle of the outer fairing, and an engine exhaust opening is formed in the right side of the middle of the outer The heat dissipation air channel is provided with the independent internal heat dissipation air channel and the external fairing, so that the heat dissipation efficiency can be ensured, and the external pneumatic appearance can be ensured to be smooth.

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.

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 turbojet power logistics unmanned aerial vehicle based on a fixed wing structure and a control method. The unmanned aerial vehicle comprises a carbon tube fuselage, cork wood wings, a full-motion horizontal empennage, double vertical empennages, a nose fairing, a storage bin, a turbojet engine, an undercarriage, a flight control system and an emergency parachute. According to the turbojet power logistics unmanned aerial vehicle based on the fixed wing structure and the control method, the fixed wing structure and the turbojet engine are organically combined, short-distance take-off within 50 meters can be achieved, compared with a traditional propeller type fixed wing unmanned aerial vehicle, the take-off distance is shortened by 40% or above, the cruising speed can reach 80 km / h-120 km / h, the unmanned aerial vehicle can be matched with a standard material box of 200 mm * 200 mm * 400 mm, and the unmanned aerial vehicle is suitable for large-scale popularization and application. The flight control system supports two modes of manual remote control and automatic driving, and is equipped with an emergency parachute, so that safe parachute recovery of the unmanned aerial vehicle in an emergency state is realized, and the problem that a traditional unmanned aerial vehicle has obvious limitation when meeting emergency material delivery requirements is effectively solved.

Aerodynamic underbody structures, assemblies with the same, and methods of manufacturing, integrating, and using the same. To improve the aerodynamic performance of a vehicle, e.g., a truck, such as a tractor-trailer, one or more aerodynamic underbody structures are integrated thereon. The aerodynamic underbody structures can each include an elongated panel (22) that attaches to a mounting structure (18) that attaches to a vehicle underbody, thereby allowing each elongated panel to extend downward into a flow path beneath the vehicle. The elongated panels may extend substantially in parallel, being spaced inward from outer chassis structures, wheels, and / or fairings, or can be angled relative to each other. The configurations and implementations of the aerodynamic components described herein can improve aerodynamic performance of vehicles.

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.

The purpose of this invention is to reduce the fuel consumption of heavy trucks by maximizing laminar flow alongside trailer walls. Fins extending from the bottom edge of the trailer side rail form a barrier between regions of high and low pressure, separating the turbulent air of the vehicle undercarriage and the more stable airflow above. Overlapping plastic forms with a flat surface are angled downward and outward and installed along the length of the vehicle. Through a tube fitted with a pipe, a fin is clamped to bars that span the gap between trailer crossmembers. Configured for comprehensive coverage fore to aft with limited lateral extent, this creates a streamlined aerodynamic profile. Its preservation of laminar flow is useful in insolation and increases the effectiveness of other fairings.

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 relates to the technical field of aerospace equipment, in particular to a fairing closing method and device and a fairing. The method comprises the steps that when the target distance of a steering wheel does not reach a preset distance, the target distance of the steering wheel is adjusted to be the preset distance so that the circle center of a first rectification half cover and / or a second rectification half cover can coincide with the circle center of the bottom of a satellite; when the gear shaper on the rectification half cover is not aligned with the gear shaper hole in the satellite, the rectification half cover is controlled to rotate in situ, so that the gear shaper on the rectification half cover is aligned with the gear shaper hole in the satellite; when the first rectification half cover and the second rectification half cover are not aligned, the height of a steering wheel in the first rectification half cover and / or the second rectification half cover is adjusted, so that the first rectification half cover and the second rectification half cover are aligned; and when the first rectification half cover and the second rectification half cover meet preset conditions, the first rectification half cover and the second rectification half cover are closed. According to the method, the operation complexity is reduced, and the fairing closing convenience is improved.

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.

1. Name of this design product: Vehicle fairing. 2. Purpose of this design: As a fairing for a vehicle. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: a 3D model.