Hollow soft wing with air intake at tip and shaped slot on upper surface |
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IPC classes for russian patent Hollow soft wing with air intake at tip and shaped slot on upper surface (RU 2389644):
       
 Aircraft wing / 2380277
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.
 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
 Air supercharger for flying vehicles with soft gas-filled wings / 2305652
Proposed device has cylindrical load-bearing body with air intake wells located inside it, bars for securing the body to paramotor and adapter pipe unions of air ducts which are connected with elastic gas lines. Provision is made for air-locking gills.
 Para-glider vehicle / 2282567
Proposed para-glider vehicle has foldable framework covered with casing made from air-tight cloth and additional casing. Pilot is connected with vehicle by means of rope secured to it at top of casing. Besides that, vehicle is provided with rope screen which may be pulled in any direction, thus changing pilot CG relative to vehicle center and making it possible to select required direction of gliding.
Aircraft wing / 2380277
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.
 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
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FIELD: transport. SUBSTANCE: invention relates to aircraft engineering. Hollow soft wing with air intake at tip comprises lower surface, upper surface and ribs. Upper surface is furnished with pockets that forms tapered duct to allow airflow to flow through upper slot on wing upper surface. EFFECT: improved aerodynamics. 9 dwg
The technical field to which the invention relates. Transportation; ballooning, aviation, aerospace; aircraft heavier than air. The level of technology Soft wing formation which is caused by excess pressure in the inner cavity, resulting from the inhibition of the flow in the air intake at the toe profile, and the tension of the sling system, the crew intake reduces the aerodynamic performance of the profile. In addition, the hollow profile design makes the equipment wing mechanization, and attempts to increase the curvature of the profile at take-off and landing modes manipulations with sling system lead to breaks in the surfaces of the wing. Controls boundary layer and profile curvature soft wing can improve its aerodynamic quality, and its load-bearing properties at take-off and landing modes, thereby making the aircraft with soft wing is less sensitive to weather conditions, increasing the range of its operating speed and reducing the required area of its bearing surface. Previously, attempts were made to control boundary layer on the upper part of the hollow wing through cracks in its surface, but it did not bring significant improvement in load-bearing characteristics of the wing, while plain is in and utagau its design. The closest technical solution to the proposed and adopted for the prototype wing is described by United States Patent No. 4191349 from 4 March 1980. The prototype is a soft hollow wing with the air intake in the toe, including the bottom surface, the top surface of the rib and having at least one slit in its upper surface, and the opening of the crack is directed toward the trailing edge of the wing, thus, to guide emerging from the fissure flow along the surface of the wing. The disadvantage of this technical solution is that before you crack missing a narrowing channel, so that the air coming out of the cracks, not accelerated and additional zone of reduced pressure on the upper surface of the wing is not voznikaem, hole slots directed toward the rear edge of the wing, violates the smoothness of the contour profile, forming a "step". In the aerodynamic performance of the wing above design was not higher than that of the wing that does not have cracks on their surface. Not increased and the range of acceptable angles of attack of the wing. As a consequence, the wings above-described construction is not currently used. Disclosure of inventions The invention is aimed at improving the aerodynamic profile of the hollow soft to the conference had been with the air intake. The invention is a hollow soft wing with the air intake to wear, characterized in that its cavity is made pockets (see item 1, figure 1, 2, 3)forming at least one tapered channel output through the slit in the upper surface of the wing. Narrowing the channel in the cavity of the wing forms a kind of second toe, and an ambient air flow creates additional pagsasalaysay power, thus improving the aerodynamic performance of the profile. In addition, the conversion of the excess pressure inside the hollow wing in thin high speed jet, midwayusa on its upper surface, leads to the formation on this surface an additional zone of reduced pressure, pushing the disruption of the flow from the upper surface of the wing at high angles of attack. The latter allows you to: - rotate the rear part of the profile relative to the front, thereby increasing the curvature of the profile (see figure 3) without the formation of folds on the lower surface of the wing, using the pockets together with the separation of the ribs on the front and rear supporting each his pocket; to change the installation angle of the wing as a whole or increase the curvature of the wing at pulling it back with the formation of folds on the lower surface, using these pockets without separation of the ribs. The implementation of the invention For OC the NCI received effect consider the shape of the profiles, derived from the original NACA 4415, and the distribution of pressure on them when Re=2196294 and an angle of attack of 10 degrees. Gradation of pressure on all the figures the same. The shape and the pressure distribution on the source profile is shown in figure 4. Profile shape with the inlet and the pressure distribution on it is shown in figure 5. Profile shape with pockets forming shaped slit, and the pressure distribution on it is shown in Fig.6. Profile shape with pockets, forming a profiled slot, rejecting the rear part of the profile at an angle of 20 degrees relative to the front part, and the pressure distribution on the profile shown in Fig.7. Numerical aerodynamic calculation (program used FlowVision ver.2.3) shows the following main features profiles on a given mode:
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