Large-sized aerodynamic model

FIELD: aircraft engineering.

SUBSTANCE: invention relates to large-size aircraft aerodynamic models design, employed for testing in wind tunnels. Device consists of interconnected fuselage cores, wing with moving high-lift system, moving empennage with framing fixed on them, longitudinal elements and flat shaped elements, repeating skin inner contour. At that, wing and fins central part cores are connected with fuselage core by means of fasteners, allowing, if necessary, to change wing and fins position relative to fuselage. Besides, fuselage core comprises fasteners for model mounting on wind-tunnel balance, and wing and fins cores are made so, that their weights correspond to analyzed aircraft weights and its centering characteristics. Due to fasteners assembled aerodynamic model or its separate elements can be hinged installed on wind-tunnel balance supporting device supports in wind tunnel working part.

EFFECT: technical result consists in possibility of creating of aerodynamic model prefabricated structure having external surface geometrically similar to analyzed future aircraft and equipped with high-lift system controlled components.

7 cl, 11 dwg

 



 

Same patents:

FIELD: aircraft engineering.

SUBSTANCE: blade comprises regular part of constant weight and geometrical shape and various replaceable end elements. Adapter pins, minor part of the spar, joint point and connector are arranged at blade regular part. Blade root regular part comprises the following elements. Leading multiple section strap, spar of preset stiffness and weight, top and bottom skin, filler of leading part, filler of trailing part, counter flutter weights, end rib with micro switch, electric conductors, connector and weights provoking the flutter. Replaceable end elements represent a structure composed of top and bottom skin, fastening holes for connection with said adapter pins, LEDs, electric conductors, connector, counter flutter weight and light filler. Proposed method consists in the following. Firs, blade root regular part is made with obligatory precise measurement of extending parts, say, adapter pins and spar end part. Results of measurements are used in making of seats in multiple replaceable end elements differing in weight, side, shape and centering. Now, regular parts are assembled with the help of split screw joint.

EFFECT: various aerodynamic characteristics obtained on the basis of one blade, higher reliability, accelerated testing.

10 cl, 14 dwg

FIELD: aircraft engineering.

SUBSTANCE: invention relates to analysis of aircraft aeroelasticity in wind tunnel. In making of aircraft models at NC tools, preliminary and verification calculations of the frame mathematical model. Obtained results are used to produce the frame from steel of aluminium alloy by high-speed honing at NC tool with allowance for similarity of mass-inertia and stiffness characteristics of structural frame with that natural frame of aircraft. Bottom shaping surface of the model is machine together with structural frame at NC tool. To produce outer lines of the model shaping surface, fused material with low modulus of elasticity is sprayed on premade frame. Final shaping of the model upper airfoil is performed at high-speed low-moment honing at NC tool with the help of complete mathematical model.

EFFECT: high precision of geometrical similarity of the model airfoil and of mass-inertia and stiffness characteristics reproduction.

5 dwg

FIELD: measurement equipment.

SUBSTANCE: model comprises a power core and a cover, representing when assembled a single dismountable structure of a closed aerodynamic shape. The cover is made from a single unit of a low-modular material, such as foam plastic of alternating thickness along swing and chord of the bearing surface, divided into sections. Thicknesses of sections gradually decrease in direction from the local sites of contact of the sections with the model core towards transition zones, at the same time the angles of section face bevel make not more than 45-50. Local sites are located in the central part of each section, and transition zones between sections are formed as a result of reduction of thickness of the single material block. The proposed method for manufacturing of the aerodynamic model includes milling of the core and the cover in CNC machines and also iteration finishing of stiffness characteristics of the assembled model. The cover is made by shaping or method of quick prototyping from a single block of a low-modular material. On its inner surface they create sections with local sites of contact with the core with slanted surfaces of section faces and transition zones of the sections. From outside and inside the cover is reinforced with cloth of unidirectional composite, and its transition zones are reinforced additionally.

EFFECT: simplified design of an aerodynamic model, simplified method of its manufacturing.

4 cl, 4 dwg

FIELD: power engineering.

SUBSTANCE: wind-powered engine mockup for adjustment of a wind-powered engine for specified wind conditions comprises a rotor with blades. Blades are fixed with locating elements in locating holes of a ring fixed by means of brackets on the axis of rotor rotation. Locating elements are made as quick-detachable for variation of a number of rotor blades and angle of their inclination to the axis of rotor rotation. The start of the rotor blades matches the inner diameter of the ring. The external diameter of the ring complies with such deviation of the rotor blades, when the distance from the central axis to the end of the rotor blade is maximum. Rotor blades with stator blades of the wind-powered engine mockup are directed towards each other.

EFFECT: increased efficiency of power generation, by means of preliminary setting of a wind-powered engine for specified wind conditions and tryout of different versions of its structural design on a mockup.

1 cl, 3 dwg

FIELD: test equipment.

SUBSTANCE: invention refers to aerodynamics and can be used at investigations of characteristics of aerodynamic models (AM) of transport vehicles. The method consists in the fact that on the leading edge of the object, for example of a wing, there arranged is a collar that is made from photopolymer using quick prototyping method. Besides, as per mathematical wing model there created are internal outlines of mathematical model of collar - ice simulator; then, as per the specified frame sections simulating ice formation there created are external outlines of collar - ice simulator in the form of double curved surface. Then, mathematical model of ice simulator is divided into parts; for each part there created is mathematical model of connection element - lock representing shaped elements of pin-slot type, as well as mathematical model of support elements of jig system, the dimensions of which define the geometry of ice simulator in the space on the jig plate. Based on the created mathematical models of ice simulator parts, locks and support elements there made on a stereolithograph are separate parts of ice simulator and support components, which are oriented vertically in the stereolithograph. Ice simulator is assembled by means of the jig plate on which ice simulator parts are installed in turn on support elements of the jig system; at that, liquid photopolymer is pre-applied to locks, parts are connected and photopolymerisation of liquid photopolymer in locks is performed by means of UV lamp. Ice simulator removed from the jig is cleaned from photopolymer residues.

EFFECT: improving the manufacturing accuracy of ice simulator and shortening its manufacturing period.

11 dwg

FIELD: physics.

SUBSTANCE: model has a force core piece and one detachable cover. The core piece is in form of part of a profile which includes the entire top surface, e.g., a wing, as well as the bottom surface of the nose of the wing. At points where the cover of the bottom part of the wing profile is located in the material of the force core piece, having not less than 70-85% total wing stiffness, there is a depression which forms between the core piece and the cover, an inner free space with volume of not less than 5-10% of the entire inner volume bounded by the exterior outline of the model, in which there are inverted L shaped drainage pipes, sensors for measuring distribution of pressure on the surface of the model, as well as a drive and additional weights needed to achieve mass-inertial similarity of the model. The method of making said model is characterised by wide use of numerically controlled machine tools for rapid high-precision and cheap manufacturing of the core piece and the cover. High accuracy of simulation is provided owing to use of iterative perfection of the stiffness of the core piece by measuring the contribution of wing stiffness into total stiffness of the model and correcting the mathematical model of the core piece.

EFFECT: simple design, high rapidness of the process of making high-quality elastic-like aerodynamic models.

16 cl, 12 dwg

FIELD: physics.

SUBSTANCE: invention relates to aerodynamics and can be used in making an aerodynamic model (ADM) of a vehicle, e.g., airplanes, rockets, motorcars, railway transport etc. The objective of the invention is to speed up the process of making a highly drained model and improving the quality of an experiment for viewing its streamline motion. The aerodynamic aircraft model made from photopolymer material with a drainage system for outlet of dyes, has a fuselage nose and tail section with engine pods, a tail fin and a half wing. The model is made from a water-resistant photopolymer material and is fitted with a device for pumping liquid for imitating engine operation, connected by a flexible cable to an external drive, wherein channels for feeding dyes have a transition part with a variable diameter and calibrated nozzles for outlet of dyes.

EFFECT: possibility of washing channels inside the model, cutting the duration of making the model and possibility of conducting tests on the aerodynamic model made from photopolymer material in a hydrodynamic tunnel.

6 cl, 3 dwg

FIELD: aircraft engineering.

SUBSTANCE: proposed method consists in producing skins from polymer composite material, nose plate, spar, tail section filler, tip, end rib, nose extension, gluing all elements into closed-shape single structure, and applying polymer coat onto outer surface. Multilayer skins have reinforcements in spar attachment area made by increasing the number of layers. Note here that in making polymer composite material, binder weight does not exceed that of fiberglass while spar is made from materials suitable for milling. Then, plate is secured on spar rear wall. Besides, holes of preset diameter, quantity and location are made in tail section filler. Then, check sections are marked on vane outer surface to represent lines located at definite distance from the center of rotation.

EFFECT: increased margin of safety, faster fabrication.

6 cl, 4 dwg

FIELD: machine building.

SUBSTANCE: linear actuator consists of case and of reducer motor for drive of spindle with thread. A nut transferring a pusher is installed on the spindle with thread. The spindle with thread is connected to a reducer motor by means of a chain gear. A shaft of the reducer motor and the spindle with thread are parallel and directed to opposite sides. Also, the reducer motor is eccentrically set to ensure tension of chain drive.

EFFECT: increased accuracy of positioning and repeatability of linear actuator.

9 cl, 3 dwg

FIELD: physics.

SUBSTANCE: proposed method consists in making model components including fuselage integrated with wings, front horizontal and tail units, as well as parts with boundary layer drain channels. Parts with engine duct inner passages are moulded from carbon fiber-reinforced plastic, injection mould being divided into top and bottom parts. Note here that mould bottom part accommodates parts with boundary layer drain channels and parts with engine duct inner passages for fuselage with wings or metal plate for attachment of tail unit to airframe. Produced top and bottom halves hardened, they are jointed together on building block till complete hardening with the help of epoxy resin. Airframe is assembled on said building block. Said airframe comprises not profiled core with brackets, aforesaid top and bottom halves. Replaceable nose cone is fitted on core. Front and tail units and intake and outlet nozzles are screwed to fuselage.

EFFECT: reduced time of producing aerodynamic model.

3 dwg

FIELD: experimental aerodynamics, possible use for researching characteristics of aircrafts.

SUBSTANCE: device contains holder, holder cowl, flow meter nozzle, positioned on output portion of through channel. Flow meter nozzle, positioned in output portion of through channel contains throttle, made in form of cylinder with a half of rotation ellipsoid connected to it. Throttle is held on component of mechanism for measuring attack and sliding angles, not connected to aerodynamic weights, on the cowl of holder, on which device is held on aerodynamic weights. Held on the throttle are heads of full and static pressures with receiving apertures in vertical plane before the throttle, and also receiver of braking temperature and receivers of static pressure, mounted at output from flow meter nozzle. Heads of full and static pressures and receivers of static pressure are connected to appropriate measuring devices by means of draining pipes.

EFFECT: decreased internal resistance of aerodynamic model and, respectively, increased precision when measuring external resistance of aircraft model at hyper-sound flow speeds.

3 dwg

FIELD: engines and pumps.

SUBSTANCE: two-stage jet engine simulator consists of a cylindrical housing accommodating a cylindrical ring cowling simulating the intake flow separation into external and internal stages. The housing head outlines are identical to those of engine nacelle and air intake. The ring cowling front end face accommodates the engine spinner. The housing and ring cowling tail end faces are covered with inclined separation screens arranged with a gap between them. The engine simulator is furnished with two accumulating devices arranged one into another. The outer accumulating device top end face is jointed to the housing, while the inner accumulating device top end faces is linked to the ring cowling. Note here that both lower end faces of the aforesaid devices are covered by detachable covers. The housing head part has a window to allow shooting, the spinner and ring cowling being coated with a dull paint. The invention allows estimating the total amount of foreign objects getting in the jet engine on running on the strip and recording the points where sand particles collide with the simulator inner surface.

EFFECT: engine higher efficiency.

5 cl, 8 dwg

FIELD: physics.

SUBSTANCE: model is installed on weighers of a supersonic wind tunnel, and is equipped with a system of supplying the working medium in form of a jet stream. The model is in form of a central casing and two gondolas, installed symmetrically on pylons at a certain distance from it and displaced relative the casing along the longitudinal axis at a position, excluding interference effects of streams on the casing, flowing from the nozzle of the gondola. Supply of jet streams of the working medium to the gondolas is done through the central casing. Power characteristics of the model are measured using a weight method, successively with supply of jet streams of the working medium to the gondolas, i.e. with and without thrust. The model is installed on weighers in a supersonic wind tunnel, jet streams of the working medium are let in and the power characteristics are measured while an external stream blows the model. The difference between these weight measurements is determined, and then this difference is compared with the value of thrust, determined from the results of pneumometric measurements.

EFFECT: increased accuracy and authenticity of aerodynamic tests.

2 cl, 1 dwg

FIELD: transportation.

SUBSTANCE: aerodynamic model comprises detachable head, stern and intermediate modules. Contours of modules imitate contours of aircraft body sections on a reduced scale, which are defined by conventional division of the latter in parts limited by shape and location of its lower or upper surfaces of the same type. At the same time external contours of modules are shaped by combination of surfaces of simple geometric figures.

EFFECT: suitability for tests on existing test bench equipment, low manufacturing cost, provision of tested models appearance versions expansion, high manufacturability.

25 cl, 2 dwg

FIELD: physics.

SUBSTANCE: proposed method consists in making model components including fuselage integrated with wings, front horizontal and tail units, as well as parts with boundary layer drain channels. Parts with engine duct inner passages are moulded from carbon fiber-reinforced plastic, injection mould being divided into top and bottom parts. Note here that mould bottom part accommodates parts with boundary layer drain channels and parts with engine duct inner passages for fuselage with wings or metal plate for attachment of tail unit to airframe. Produced top and bottom halves hardened, they are jointed together on building block till complete hardening with the help of epoxy resin. Airframe is assembled on said building block. Said airframe comprises not profiled core with brackets, aforesaid top and bottom halves. Replaceable nose cone is fitted on core. Front and tail units and intake and outlet nozzles are screwed to fuselage.

EFFECT: reduced time of producing aerodynamic model.

3 dwg

FIELD: machine building.

SUBSTANCE: linear actuator consists of case and of reducer motor for drive of spindle with thread. A nut transferring a pusher is installed on the spindle with thread. The spindle with thread is connected to a reducer motor by means of a chain gear. A shaft of the reducer motor and the spindle with thread are parallel and directed to opposite sides. Also, the reducer motor is eccentrically set to ensure tension of chain drive.

EFFECT: increased accuracy of positioning and repeatability of linear actuator.

9 cl, 3 dwg

FIELD: aircraft engineering.

SUBSTANCE: proposed method consists in producing skins from polymer composite material, nose plate, spar, tail section filler, tip, end rib, nose extension, gluing all elements into closed-shape single structure, and applying polymer coat onto outer surface. Multilayer skins have reinforcements in spar attachment area made by increasing the number of layers. Note here that in making polymer composite material, binder weight does not exceed that of fiberglass while spar is made from materials suitable for milling. Then, plate is secured on spar rear wall. Besides, holes of preset diameter, quantity and location are made in tail section filler. Then, check sections are marked on vane outer surface to represent lines located at definite distance from the center of rotation.

EFFECT: increased margin of safety, faster fabrication.

6 cl, 4 dwg

FIELD: physics.

SUBSTANCE: invention relates to aerodynamics and can be used in making an aerodynamic model (ADM) of a vehicle, e.g., airplanes, rockets, motorcars, railway transport etc. The objective of the invention is to speed up the process of making a highly drained model and improving the quality of an experiment for viewing its streamline motion. The aerodynamic aircraft model made from photopolymer material with a drainage system for outlet of dyes, has a fuselage nose and tail section with engine pods, a tail fin and a half wing. The model is made from a water-resistant photopolymer material and is fitted with a device for pumping liquid for imitating engine operation, connected by a flexible cable to an external drive, wherein channels for feeding dyes have a transition part with a variable diameter and calibrated nozzles for outlet of dyes.

EFFECT: possibility of washing channels inside the model, cutting the duration of making the model and possibility of conducting tests on the aerodynamic model made from photopolymer material in a hydrodynamic tunnel.

6 cl, 3 dwg

FIELD: physics.

SUBSTANCE: model has a force core piece and one detachable cover. The core piece is in form of part of a profile which includes the entire top surface, e.g., a wing, as well as the bottom surface of the nose of the wing. At points where the cover of the bottom part of the wing profile is located in the material of the force core piece, having not less than 70-85% total wing stiffness, there is a depression which forms between the core piece and the cover, an inner free space with volume of not less than 5-10% of the entire inner volume bounded by the exterior outline of the model, in which there are inverted L shaped drainage pipes, sensors for measuring distribution of pressure on the surface of the model, as well as a drive and additional weights needed to achieve mass-inertial similarity of the model. The method of making said model is characterised by wide use of numerically controlled machine tools for rapid high-precision and cheap manufacturing of the core piece and the cover. High accuracy of simulation is provided owing to use of iterative perfection of the stiffness of the core piece by measuring the contribution of wing stiffness into total stiffness of the model and correcting the mathematical model of the core piece.

EFFECT: simple design, high rapidness of the process of making high-quality elastic-like aerodynamic models.

16 cl, 12 dwg

FIELD: test equipment.

SUBSTANCE: invention refers to aerodynamics and can be used at investigations of characteristics of aerodynamic models (AM) of transport vehicles. The method consists in the fact that on the leading edge of the object, for example of a wing, there arranged is a collar that is made from photopolymer using quick prototyping method. Besides, as per mathematical wing model there created are internal outlines of mathematical model of collar - ice simulator; then, as per the specified frame sections simulating ice formation there created are external outlines of collar - ice simulator in the form of double curved surface. Then, mathematical model of ice simulator is divided into parts; for each part there created is mathematical model of connection element - lock representing shaped elements of pin-slot type, as well as mathematical model of support elements of jig system, the dimensions of which define the geometry of ice simulator in the space on the jig plate. Based on the created mathematical models of ice simulator parts, locks and support elements there made on a stereolithograph are separate parts of ice simulator and support components, which are oriented vertically in the stereolithograph. Ice simulator is assembled by means of the jig plate on which ice simulator parts are installed in turn on support elements of the jig system; at that, liquid photopolymer is pre-applied to locks, parts are connected and photopolymerisation of liquid photopolymer in locks is performed by means of UV lamp. Ice simulator removed from the jig is cleaned from photopolymer residues.

EFFECT: improving the manufacturing accuracy of ice simulator and shortening its manufacturing period.

11 dwg

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