Aircraft wing |
|
IPC classes for russian patent Aircraft wing (RU 2380277):
 
 Flat drive with foliated structure, flat drive device and lifting plane of aircraft / 2337430
Invention is related to piezoelectric instruments for control of aircraft lifting planes. Flat drive with foliated structure that is symmetrical in relation to middle plane includes flat piezoelectric layer, which has active direction and is connected with one flat passive layer of cloth with rigid haircloth and weft that are oriented in accordance with two directions that form network of cells. Both directions of every cloth layer are same. Active direction of every piezoelectric layer is oriented along single diagonal of cloth layers cells. Flat drive device consists of two drives installed top to tail. Lifting plane of aircraft, for instance, helicopter blade, includes top and bottom surfaces, and also drive device close to back edge.
 Swept-forward wing with swivel part of outer wing panels / 2296082
Each outer panel of proposed wing includes wing extension with sweep-back leading edge, root section with swept-forward leading edge and trailing edge; swivel part of wing outer panel is articulated with this section relative to vertical axis of flying vehicle; it may be turned backward in way of flow so that sweep angle of leading edge may change from initial swept-forward to swept-back magnitudes.
 Aero - or hydrodynamic surface of variable curvature / 2167785
The invention relates to Aero - or hydrodynamic surfaces of variable curvature, which interacts with a counter-thread environment
 Wing variable curvature of the aircraft / 2130858
The invention relates to the field of aviation technology
 Supersonic aircraft / 2051839
The invention relates to aircraft and in particular to aircraft with wings of variable thickness
 Method of controlling airflow boundary layer and device to this end / 2372251
Invention relates to aircraft engine production and aircraft engineering. Device to control airflow boundary layer comprises inner space, boundary layer suction channel and air blow channel arranged in compressor vanes and/or aircraft wings. Aforesaid channels communicate aforesaid space with ambient medium. Boundary layer suction channel represents either a continuous slot or tubular channels that pass along normal to blade and/or wing back surface from higher-pressure zone. Channel to blow air from aforesaid space into airflow lower-pressure zone passes at 5° to 15° to profile back along airflow. Nozzle flat variable rotary shapers can be arranged at air blow channel outlet. This invention covers also the method incorporating above described device.
 Method and system to create potential on over body surface / 2350507
In compliance with proposed method, fluid flows forced from nozzles, holes or slits of, at least, one pipe to on one or more surfaces of body. Note here that fluid flows are injected from nozzles, holes or slits on over one or more body surfaces from the surface front edge thus creating pressure potential on the body surface just between the front and rear edges. Here, note that, at least, one pipe is revolved about its axis. The proposed system, designed to create potential on the body surface using fluid flows forced from nozzles, holes or slits of, at least, one pipe to on one or more surfaces of body to set it moving, to control it or make it manoeuvring, comprises, at least, one pipe with nozzles, holes or slits in its wall. The said pipe is located along the body edge, thus forming its front edge from which the flows passing nearby, at least, one body curved surface reduce pressure on the said surface and produce potential relative to its opposite arbitrary-shape surface. Note here that, at least, one pipe revolves about its axis. It is preferable for the said system to have the surface over which the said flows pass made convex and with one curvature. The pipes can be protected by vertical body arranged between the pipes and parallel to them. The said body can be attached to airship. In this case, the body increased pressure side is furnished with plates hinged to front edge of the said pipes. Note that the plates' motion is damped by shock absorbers.
 Method of change of aerodynamic resistance during motion of transport facility in air medium and device for realization of this method / 2281884
Proposed method consists in change of state of boundary layer of transport facility by smoothly heating of at least 70% of surface of transport facility at permissible temperature gradient of ±20°C to temperature not below 60°C connecting the engine plant of transport facility, air intake or compressor by means of mains with passages adjoining from the inside to external skin of transport facility. According to one version of method, heated mixture of air and combustion products is additionally locally blown out through permeable porous inserts on surfaces of transport facility into air flow around it at definite velocity of this flow. Device proposed for realization of this method includes body of transport facility, engine plant 1 and system for change of state of boundary layer formed by air intake or compressor connected with engine plant of transport facility by hermetic mains 5 provided with passages adjoining from the inside to external skin 9 of transport facility body. According to other versions, mains are also brought to porous inserts 11 of skin 9.
 Aerohydrodynamic latticed-and-slotted system / 2281225
Proposed latticed-and-slotted system contains several working members-wings or blades or vanes which are fastened together and are connected with article by means of coupling components. relative position of working members in space is dictated by their successive forward and upward shifts in way of motion in medium and angle of turn around longitudinal axis, angle of attack beginning with first lower component. Parameters of relative position of each working member may be similar or different from member to member; they may be rigidly fixed by coupling members or may be changed by means of drive in case of considerable change in motion modes: takeoff, landing, acceleration and deceleration; provision is made for mechanically changing the angler of attack relative to medium of motion. Profiles and geometric sizes of each working member are similar or are partially different or different. Working members may be arranged in sections in one row or in modules consisting of two and more sections.
 Method of forming lift force and device for realization of this method / 2260545
Proposed method includes reduction of pressure in closed space above lifting surface at presence of atmospheric pressure under it; lift force is created due to difference between said pressures; closed space is formed by closing the upper open portion of chamber by flat jet of liquid. Provision may be also made for evacuation of air from closed space by means of vacuum pump. Device for creating the lift force has at least one body with lift force and at least one unit for forming the closed space at reduction of pressure above respective surface. Each body is made in form of chamber which is open at the top and bottom forming the lifting surface. Each unit for forming the closed space is made in form of slotted nozzle connected with liquid supply unit and located in upper portion of respective chamber for creating the lift force closing the upper open part of chamber for forming closed space inside it. Chambers may be located one above another so that their lifting surfaces are parallel or lie in one plane. At least one chamber may have lifting surface located at angle relative to horizontal plane. Chamber may be rectangular in section parallel to lifting surface; slotted nozzle mounted on its side surface may form rectangular or round lift force when slotted nozzle is round in shape and is located in chamber concentrically relative to its section for creating diverging circular lift force. Each chamber may have inlet hole of intake passage opposite slotted nozzle; said passage is connected with reservoir connected in its turn with liquid supply unit.
 Helicopter / 2246426
Proposed helicopter has fuselage with main rotor, tail and end booms and steering rotor; tail boom narrows from rear compartment of fuselage towards end boom; external outlines of cross-sections of end boom have shape of aerodynamic profile forming moment of force counter-acting to reaction torque of main rotor under action of velocity head of air during horizontal flight. Secured on side of tail boom is profiled deflector with aerodynamic outer surface; nose of this deflector is located at level of separation of induction flow of air created by rotation of main rotor from lateral surface of tail boom; inner surface of deflector embraces lower part of lateral surface of tail boom forming air passage narrowing under tail boom with longitudinal slit for discharge of reaction jet of air in way opposite to motion of main rotor above tail boom. Deflector is secured on tail boom at distance equal to 0.65-0.85 of radius of rotation of main rotor blade.
 Aircraft with passenger emergency modules / 2172277
The invention relates to Aeronautics and concerns create aircraft with emergency means of salvation and the means of increasing the lifting force
 Aero(hydro)dynamic device / 2163207
The invention relates to the automotive, shipbuilding and aircraft construction, with regard to the creation of devices that improve Aero(hydro)dynamic quality of land, water and air vehicles
 The way to ensure shock-free supersonic motion of the aircraft in the atmosphere and aircraft / 2107010
The invention relates to aviation, space technology and can be used to create new types of aircraft designed for flight at supersonic speeds at the surface of the Earth, and the height of up to 150 km
 The way the boundary layer laminar < / span > wing and device for its implementation (options) / 2086473
Helicopter / 2246426
Proposed helicopter has fuselage with main rotor, tail and end booms and steering rotor; tail boom narrows from rear compartment of fuselage towards end boom; external outlines of cross-sections of end boom have shape of aerodynamic profile forming moment of force counter-acting to reaction torque of main rotor under action of velocity head of air during horizontal flight. Secured on side of tail boom is profiled deflector with aerodynamic outer surface; nose of this deflector is located at level of separation of induction flow of air created by rotation of main rotor from lateral surface of tail boom; inner surface of deflector embraces lower part of lateral surface of tail boom forming air passage narrowing under tail boom with longitudinal slit for discharge of reaction jet of air in way opposite to motion of main rotor above tail boom. Deflector is secured on tail boom at distance equal to 0.65-0.85 of radius of rotation of main rotor blade.
Method of forming lift force and device for realization of this method / 2260545
Proposed method includes reduction of pressure in closed space above lifting surface at presence of atmospheric pressure under it; lift force is created due to difference between said pressures; closed space is formed by closing the upper open portion of chamber by flat jet of liquid. Provision may be also made for evacuation of air from closed space by means of vacuum pump. Device for creating the lift force has at least one body with lift force and at least one unit for forming the closed space at reduction of pressure above respective surface. Each body is made in form of chamber which is open at the top and bottom forming the lifting surface. Each unit for forming the closed space is made in form of slotted nozzle connected with liquid supply unit and located in upper portion of respective chamber for creating the lift force closing the upper open part of chamber for forming closed space inside it. Chambers may be located one above another so that their lifting surfaces are parallel or lie in one plane. At least one chamber may have lifting surface located at angle relative to horizontal plane. Chamber may be rectangular in section parallel to lifting surface; slotted nozzle mounted on its side surface may form rectangular or round lift force when slotted nozzle is round in shape and is located in chamber concentrically relative to its section for creating diverging circular lift force. Each chamber may have inlet hole of intake passage opposite slotted nozzle; said passage is connected with reservoir connected in its turn with liquid supply unit.
|
FIELD: aircraft engineering. SUBSTANCE: invention relates to aircraft engineering, particularly to light airplanes. Proposed wing comprises spars, stringers and skin, and has back step-cutout arranged on upper surface that features slightly curved bottom and extends along wing span. Wing upper surface support panels designed to regulate the depth of aforesaid step-cutout and pivoted to vary their position with the help of springs. The latter are rigidly coupled with the recess bottom and regulation panel lower surface. EFFECT: higher lifting properties. 5 dwg
The invention relates to aircraft, light aircraft, and specifically to the design of an airplane wing. It is known the aircraft wing profile NACA 23012 for creating a lifting force required for flight of aircraft [1]. The disadvantage of this wing is a disruption of the flow with its upper surface due to the interaction of the positive pressure gradient and boundary layer with increasing angle of attack over the angle of attack of the beginning of the breakdown, crash this lifting force, the reduction of the lift coefficient and aerodynamic quality [1]. Known profile of a wing having a top surface opposite the step-cut with a slightly curved bottom of the recess, extended along the span of the wing, which ensures the prevention of flow separation at high angles of attack, the increment of lifting force at certain angles of attack when the appropriate configuration steps [2]. The results of the study of such a wing profile with steps a depth of 50% and 33% of the thickness profile and the wing profile without cut show that the maximum values of the coefficients of the lifting forceuaall profiles are approximately equal. While the profile with 33% step-stall phenomenon tightened to α=40°. Profile with a step of 50% of the width and 50% depth provides a large increment of lifting power to turn the ski at all angles of attack compared to the profile of the neck disruptive phenomena that begin with α=25° (figa). The disadvantage of the wing has a profile NACA 23012 with a step is having a positive effect increment lifting force or only in the subcritical angles of attack (the configuration steps 50% of the chord and 33% depth) or delaying stall at high angles of attack, i.e. an increase in the lifting force at supercritical angles of attack for the base profile (configuration steps 50% of the chord and 33% depth). The objective of the invention is to improve the aerodynamic characteristics of a wing of small aspect ratio is close to rectangular for light aircraft. To achieve this task, the proposed technical solution is the use of aerodynamic principle of regulating the depth of a step profile, using extended the wingspan of the sections in the form of panels. On the upper surface of the wing sets out the management section of the profile depth, the hinge is placed at a distance of 25% from the rear edge and along the wing span. The control is performed by elastic elements (springs), rigidly connected to a bottom of the recess and the bottom surface of the panel control. On figa depicts a panel depth of cut on figb shows the profile of the wing, having on the upper surface of the step-cut (FR what type), on FIGU - General view of the proposed wing. On figa shows the dependence of the lift force Withuafrom the angle of attack α, figb shows the value of the glide To the angle of attack α. The proposed design of the wing contains: spar (1), stringers (2), a casing (3), the panel depth of cut (4)attached with axial hinge (5)to the casing (3), in the region of the rear edge of cutout and lying on the springs (6)which is mounted in the bottom of the excavation. The device operates as follows: when increasing the angle of attack below the critical panel is in the lowest position (50%) and held so by the influence of the elastic force of the spring. When the critical angle of attack due to the reduction of static pressure panel is set to 33%, the depth of the spring is stretched, the panel is in equilibrium due to the equality of the forces of elasticity of the springs and lift forces. By reducing the depth of the step breakdown of the thread is pulled at high angles of attack (figa). Boundary layer breaks down at an angle of attack, significantly greater than the baseline profile. With decreasing angle of attack of the panel returns to its original position, corresponding to 50% of the depth due to compression springs. Advantages of the claimed invention has been proven through studies in wind tunnels small / min net is her 10-80 m/s (figb). The phenomenon of failure on the prototype occurs when the angle of attack α=20°. In this case the gap flow begins in the immediate vicinity of the leading edge. Wing with adjustable ensures the prevention of relapse at α=38° at a greater distance from the leading edge. Values of aerodynamic quality in contrast to prototype get more increment at all angles of attack up to critical. The application of the proposed wing will reduce the length of required runway, due to the increase in lifting force, to increase the maximum angle of attack, to improve the characteristics of the output when the critical angle of attack, which ultimately contributes to the safety of the flight. References 1. Aerodynamics of aircraft and hydraulics systems. Ed. it has M.I., M: WIA, 1994 2. Express Information, 1989, No. 17, p.19-21 (prototype). The wing of the plane containing the spars, stringers, the casing and having on the upper surface of the reverse step-neckline with slightly curved bottom of the recess, extended along the wing span, characterized in that on the upper surface of the wing panels are installed to regulate the depth of the step-cut, pinned with one hand on the axial hinges with the possibility of changing its position by means of springs, which are rigidly connected with the bottom of the recess and the bottom on top of the spine panel control the depth of a step-cut.
|
