823 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.

A fairing assembly 10 installed about a heat exchanger, such as a radiator R, to reduce the drag on the vehicle, comprising: a frame installed about the heat exchanger, the frame having a curved contour; a panel mounted in the frame, the panel and fairing assembly defining an air passage for air flow to the heat exchanger; a cover installed in the frame and movable to control air flow through the passage to the heat exchanger; and, moving means for moving the cover over the frame to expose a portion of the opening and allow air to flow into the heat exchanger, the frame and cover thereby reducing the amount of drag on the vehicle while still allowing air flow into the heat exchanger; wherein the panel comprises a first overlapping part and a second overlapping part; and wherein the first overlapping part is moveable from an extended position to a retracted position when the fairing is impacted.

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.

A marine drive is for propelling a marine vessel. The marine drive has a propulsor configured to generate a thrust force in a body of water; a battery that powers the propulsor; and a supporting frame which supports the marine drive relative to marine vessel. The supporting frame has a monolithic body defining a frame interior, and further has a support leg extending downwardly from the monolithic body and a steering arm extending forwardly from monolithic body. A cowling is fixed to the supporting frame via at least one hidden fastener that extends from the frame interior, through the supporting frame, and into engagement with the cowl body, wherein hidden fastener being accessible during installation.

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.

A propulsion assembly is disclosed including a pylon, a turbomachine having an engine and a fan surrounded by a fan casing, a nacelle surrounding the engine and the fan casing, and including a load bearer positioned at the upper part of the nacelle, a forward fan mount between a frontal zone of the fan casing and a frontal zone of the load bearer, a rear pylon mount between the pylon and the load bearer, and a positioning assembly providing positioning between the fan casing and the load bearer. The propulsion assembly is configured to control the separations between the cowls mounted in a moveable manner on the load bearer and a nose cowl.

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 relates to the field of aero-engines, and discloses an anti-icing-surge valve grid device for an aero-engine and an adjusting method. The device comprises a shell, a valve, a fairing, a connecting shell, a piston rod and a connecting base, grids with different numbers and different areas are arranged in the shell in the circumferential direction, and a first anti-icing outlet, an air outlet, an air inlet and a second anti-icing outlet are sequentially formed in the outer wall of the shell; the piston rod is used for driving the valve and the fairing which are connected with the piston rod to move in the shell, so that the elliptical hole in the valve, the curved hole in the fairing and the grids with different areas work cooperatively to form different opening degrees, airflow entering from the air inlet passes through the different opening degrees, and the air flow is formed. Therefore, the flow flowing into the first anti-icing outlet, the second anti-icing outlet and the air outlet is controlled, switching of the anti-icing function and the anti-icing surge function and flow adaptation are achieved, and the energy utilization and reliability guarantee system of an air path system in an aero-engine is optimized.

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 combustion chamber air fairing which comprises a fairing outer cylinder (1) and a guide plate (2), the guide plate (2) is located on the radial inner side of the fairing outer cylinder (1), at least part of the guide plate (2) is a curved surface, a plurality of through holes are formed in the fairing outer cylinder (1), and the combustion chamber air fairing is characterized by further comprising a plurality of partition plates (3) connected to the fairing outer cylinder (1) and the guide plate (2) and further comprising spoilers (4). The problems that uniformity of air flowing into different nozzles from a fairing is poor, a thin-wall structure of the fairing is prone to being damaged during operation, and the mixing effect of air and fuel in a combustion chamber is common are solved, meanwhile, vortex and turbulent flow of the air before the air enters the nozzles are reduced, air flowing is more stable, energy loss in the combustion chamber is reduced, combustion efficiency is improved, and the service life of the combustion chamber is prolonged. The stability and the uniformity of the combustion process are ensured; the invention further discloses a combustion chamber with the combustion chamber air fairing.

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.

The invention provides an intelligent simulation training bomb for ground attack of an unmanned aerial vehicle. The training bomb comprises a bomb body, a thrust reverser, a fairing, a mounting frame, a smoke tank and a control module. Wherein a gas cabin is arranged in the bomb body, and the thrust reverser is composed of an electromagnetic valve and a multi-way pipe. The mounting frame integrates a fuming tank, a control module and a motion sensing module, and the control module calculates the falling speed, the grounding time and the position coordinates in real time based on data of all sensors of the motion sensing module so as to control the electromagnetic valve to be opened, so that compressed gas in the gas cabin is ejected from a reverse thrust gas opening in the circumferential direction of the fairing through the multi-way pipe; in combination with deformation buffering of the fairing made of an elastic material, nondestructive recovery of the training bomb is achieved, and repeated use is facilitated. And meanwhile, the fuming tank is controlled to trigger and release tracing smoke, so that an impact point is marked, and parameters such as latitude and longitude during landing are sent to a ground guide training system to serve as an evaluation basis of throwing precision.

A combustor for a gas turbine engine includes a ceramic matrix composite (CMC) dome structure, a CMC outer liner, a CMC inner liner, and a cowl structure, that are connected together via at least one outer connection and at least one inner connection. An outer seal member is arranged to seal an outer gap between an outer liner connecting flange and an outer dome connecting flange, and an inner seal member is arranged to seal an inner gap between an inner liner connecting flange and an inner dome connecting flange.

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.

The utility model relates to a horizontal fairing and a horizontal compressor, the fairing comprises a fairing body, the bottom of the fairing body extends outwards to form a bottom edge, one end of the bottom edge far away from the fairing body is bent towards one side of the top of the fairing body to form a side turnup, and the side turnup is bent towards the other side of the top of the fairing body. The end, away from the bottom edge, of the side turnup is bent towards the side away from the cover body to form a top turnup, and the angle theta between the top turnup and the central axis of the cover body is larger than or equal to 70 degrees and smaller than or equal to 135 degrees. Compared with the prior art, the oil outlet quantity and the oil content of a system of the horizontal compressor are reduced, so that the cold force and the energy efficiency of the compressor are improved.

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.

An electric propulsor is provided. The electric propulsor includes a core cowl and an outer cowl. A first air flowpath is defined radially outward of the outer cowl and a second air flowpath is defined between the core cowl and the outer cowl. The electric propulsor also includes one or more electric machines, a fan rotatably drivable by at least one electric machine, and a booster having a plurality of airfoils disposed at least in part in the second air flowpath, the booster being rotatably drivable by at least one electric machine for compressing air flowing along the second air flowpath. The electric propulsor further includes a heat exchanger disposed within the second air flowpath downstream of the booster, the heat exchanger being in thermal communication with at least one of the one or more electric machines and / or a gearbox mechanically coupled with the fan.

The invention discloses a fuselage structure of a patrol flight unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicle design, the fuselage structure comprises a front fuselage, a middle fuselage, a rear fuselage, a middle fuselage fairing, a nose fairing and an external joint, the front fuselage is a short and thick long circular section large-diameter fuselage, and the middle fuselage and the rear fuselage adopt slender standard straight tube type small-diameter fuselages; the axis of the middle fuselage is an aircraft reference line; the front end of the front fuselage is wrapped by the fuselage fairing, a transition area is arranged between the front fuselage and the middle fuselage, the transition area is wrapped by the middle fuselage fairing, and the external connector is installed on the lower portion of the middle fuselage and used for catapult launching. The unmanned aerial vehicle is reliable, efficient, low in cost and capable of being applied to small and medium-sized unmanned aerial vehicles.

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.

A nacelle for an aircraft propulsion unit includes an air intake cowl, and an intermediate section including fixed and removable hoods defining an access space between front ends of the hoods and an outer rear end of the air intake cowl. The intermediate section includes an annular row of mutually spaced connecting parts which rigidly connect the outer rear end of the air intake cowl to the front ends of the hoods so as to transmit longitudinal forces, and an intermediate cowl extending between the air intake cowl and the hoods, around the connecting parts, thereby closing the access space and creating aerodynamic continuity with the air intake cowl and the hoods. The intermediate cowl is formed from at least one strip which is held in place by tangential clamping of the circumferential ends of the strip.

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.