Protective shield against impacts of ice on aircraft
FIELD: aircraft engineering.
SUBSTANCE: invention relates to aircraft engineering, particularly to a self-recovering shield protection against impacts of ice on an aircraft (AC), in particular, an AC with propeller engines. Protective shield against impacts of ice on an aircraft structures comprises layers of a composite material (CM) having microcapsules containing a recovering agent. Herewith the CM also contains microcapsules containing particles of a catalyst. Under action of the catalyst particles the recovering agent becomes a polymerized recovering agent, where the recovering agent is dicyclopentadiene. Herewith the catalyst particles are particles of tungsten hexachloride and diethylaluminium chloride (WCl6-Et2AlCl).
EFFECT: provided is higher flight safety due to the use of a self-recovering material, which recovers the protective material in flight.
14 cl, 7 dwg
FIELD: machine building.
SUBSTANCE: invention relates to a sealing element of lifting surface installed between two components of control surface of an aircraft for the purpose of closing a slot between them able of being adjusted by width. The sealing element comprises an attachment section for the connection with the first component, the first and the second booms running from the attachment section and distanced from each other so that to let the second component in-between. The sealing element also comprises the first stiffening element made with the possibility of partial limiting the relative movement of the first and second booms. The first stiffening element is solid and comprises the first stiffening lever and the second stiffening lever. The first stiffening lever is set inside or near the first boom and the second stiffening lever is set inside or near the second boom so that the relative movement of the first and second booms is partially limited by the first stiffening element. When manufacturing the sealing element a mould for it shall be provided so that to correspond to the outer contour of the sealing element having the attachment section and the first and the second booms running from the attachment section. One stiffening element is to be provided inside the mould. Sealing material is introduced into the mould for partial filling of space around the stiffening element. Then the sealing material is hardened and the sealing element is taken out of the mould.
EFFECT: improved seal.
10 cl, 13 dwg
SUBSTANCE: invention relates to aircraft engineering, particularly, to undercarriage module protective panel. Said protective panel is mounted with the help of deformable parts on the support connected with aircraft airframe. Protective panel outer surface comprises composite material. Deformable parts interact with several stringers fitted at the frames. Extent of deformation of deformable parts is adapted to elongation at outer surface fracture to make several deformable parts deformed before fracture of said outer surface.
EFFECT: decreased weight of protective panel and higher impact strength.
14 cl, 4 dwg
SUBSTANCE: aerodynamic body incorporates control appliance to adjust its position relative to aircraft main wing. Adjustment of its position at lateral end E1, E2 makes a variable clearance between said aerodynamic body and another aerodynamic body or said main wing. Device 1 to close the slot with skin part 20 extending along slot G to close aerodynamic body in span direction SW1, SW2 on its end so that skin part 20 telescopes relative to aerodynamic body in span direction SW1, SW2. Aircraft wing first version covers aircraft with main wing and multiple aerodynamic bodies A1, A2 arranged side by side and across wing depth direction S1. Aircraft wing second version covers aircraft with main wing and body A1, A2 controlled by control device and arranged across wing depth direction S1 nearby fuselage or main wing.
EFFECT: higher aerodynamic efficiency owing to sealed slot between structural parts.
21 cl, 18 dwg
SUBSTANCE: invention relates to aircraft engineering, namely, to aircraft air intake assembly. Proposed assembly comprises approach air intake 20 with approach air inlet 36, secondary air inlet 26, displacing flap 30, secondary air inlet channel 28, air duct 38 and check valve 40 arranged in secondary air inlet channel 28. Said flap 30 can displace to first and second positions to stop secondary air inlet 26 in first position and to partially open said inlet 26 in second position and to enter airflow in some zones directed to approach air intake 39. Secondary air intake 28 and approach air intake channel 22 can be communicated with air duct 38.
EFFECT: optimised operation in cruising flight.
15 cl, 13 dwg
SUBSTANCE: transonic and supersonic wing with laminar flow comprises hybrid flat split flap connected with the wing and including flat flap deflected downward at the first angle, and split flap deflected at the second angle larger than the first one. Said wing may comprise buildup extending ahead of the wing inner spread, skewed wing tip, reverse fairing on joint between buildup or fuselage and wing leading edge, inner leading edge flap extending through at least 15% of wing span, and hybrid flat split flap arranged at training edge.
EFFECT: decreased positive pressure gradient at flap top surface training edge.
17 cl, 3 dwg
FIELD: process engineering.
SUBSTANCE: invention relates to composites used in aircraft engineering, particularly, to reinforced strap from composite designed to be secured to aircraft wing top surface. It comprises core of composite and at least one glass layer to cover at least one inner side of said core and at least one top glass layer that covers core outer side, said glass layers completely covering the core outer surface. Proposed method comprises the stages that follow. First bottom glass layer is arranged in the mould to cover mould bottom. Extending edges of bottom glass layer extend from both sides of the mould sidewalls. Strap is placed in the mould. Note here that core outer side is coated with at least one glass layer preliminary and afterwards. First bottom glass layer edges are bent off to said strap so that said glass layer abuts on strap outer edges. The mould is closed by cover to anneal the strap in the mould in drying chamber for gall layer polymerisation. Strap coated with glass layer is extracted.
EFFECT: higher durability of strap used as transition strap between aircraft wing and fuselage.
8 cl, 8 dwg
SUBSTANCE: invention relates to aircraft engineering, particularly, to reduction of aerodynamic noise produced by aircraft undercarriage in takeoff and landing. Aircraft undercarriage extended in landing and/or takeoff comprises two end covers and buckle. Two end covers are designed to close every end of undercarriage hollow axle, say, articulated axle of undercarriage two links. Crossbar can enter said hollow axle to connected end covers so that they are retained thrusted against ends of this axle.
EFFECT: reduced noise at takeoff an landing.
9 cl, 1 dwg
SUBSTANCE: invention relates to use of filler-containing polyurethane lacquers as wear-resistant coatings and also to a visible wearing zone of structural parts of an airplane that mechanically rub each other during operation, particularly in the area of landing flaps of an airplane during contact with spoilers. The landing flap of an airplane in the area of contact with spoilers is coated with a wear- and yellowing-resistant coating. The coating consists of hardened lacquer containing a polyurethane matrix based on aliphatic components, and wear-resistance enhancing filler materials embedded into the polyurethane matrix. The filler materials are selected from a group of filler materials with Moh's hardness of at least 7 and grain size 0.1 mcm <d50<30 mcm and mixtures of said filler materials with filler materials having Moh's hardness of at most 2 and grain size 3 mcm <d50<50 mcm. The solid filler materials are ceramic filler materials and soft filler materials are plastic filler materials. Use of lacquer which contains a polyurethane matrix based on aliphatic components and wear-resistance enhancing filler materials embedded in the polyurethane matrix as wear- and yellowing-resistant coating for landing flaps (2, 2') of an airplane in the area of contact with spoilers (4), is also suitable for the wearing zone of cargo doors or the wearing zone of two structural parts of an airplane that mechanically rub each other during operation.
EFFECT: achieving wear-resistance of landing flaps mechanically or optically.
16 cl, 8 dwg
SUBSTANCE: invention relates to aviation technology and can be used in the construction of radome. Plane caisson radome contains two spar and connecting them with each rib frame construction. Spars and ribs in the form of multiple frames. Ribs are connected to the frame spars on spar racks. Achieved by improving the technological and performance of a radome antenna plane, due to expansion usable space in the caisson fairing.
EFFECT: improved technology and performance of a radome antenna plane, due to expansion usable space in the caisson fairing.
SUBSTANCE: invention relates to aircraft engineering. Aircraft 10 comprises fuselage 12, two wings 14, 16 whereto engine nacelles are attached, each being secured by central fairing 18, 20 to fuselage on its both sides. Said central fairing comprises two opposed surfaces jointed to wing upper and lower surfaces arranged along fuselage. One of said surfaces has local deformation of shape geometry to create aero dynamical lateral disturbances of airflow from central fairing to wing to control airflow over wing surface.
EFFECT: perfected aircraft design.
14 cl, 21 dwg
SUBSTANCE: invention relates to aircraft engineering. Aircraft comprises tail unit with total area is larger than 30% of the main wing area but smaller than 90%.
EFFECT: higher antispin properties.
SUBSTANCE: invention relates to aircraft engineering. Proposed device comprises flap main element (5) to be extended and retracted relative the main wing and extending element (6A-1). Said element features smooth outline and is arranged nearby end part in direction of flap main element positive pressure surface to extend from the flap main element (5). Said wing comprises the main wing and lift increase device. Noise decrease device comprises the detachable main element to be jointed with end part in direction of the flap main element span and detached from said end part in direction of the main element span, and the extending element.
EFFECT: increased lift, decreased noise at the same weight.
6 cl, 40 dwg
SUBSTANCE: invention relates to aircraft engineering. Control surface 3 comprises two power drives 15, main closing rib 9 arranged at one end of said surface 3. Main closing rib 9 is coupled with the main torsion bar 8. Said main torsion bar 8 is integrated with leverage 14. Note here that said two power drives 15 operate to influence the turn of control surface 3 in aircraft flight. Control surface 3 comprises also secondary torsion bar 11. Said secondary torsion bar 11 is aligned with said primary torsion bar 8 and fitted therein. Secondary torsion bar 11 is integrated with leverage 14 and secondary closing rib 28 of control surface 3.
EFFECT: lower bending forces at articulated parts, higher stiffness, lower driving forces, decreased weight.
10 cl, 7 dwg
SUBSTANCE: invention relates to aircraft structural components and airfoils, particularly, to airfoils design for compact aircraft stabilisation in the plane of trajectory and for control in ballistic flight. Compact aircraft comprises fuselage, airfoils and tail plane. Airfoils are mounted at fuselage at the center of gravity to turn about aircraft lengthwise axis. Said airfoils represent two wings secured to turn assembly and arranged in symmetry about aircraft lengthwise axis in different planes.
EFFECT: higher aircraft efficiency, use of airfoils for flight control.
SUBSTANCE: invention relates to aircraft engineering, particularly, to assembling aircraft components, namely to attachment of tail unit to fuselage. On fitting tail unit front shutter in gap between fuselage and tail unit end face, tail unit is set to 0° relative to fuselage to remove panels from end face and to set shutter into said gap. Beforehand, shutter mounts are secured on outer shutter. Rod keys are fitted via through holes and turned through 90° to fit in mount part-through slot to strain the shutter to operating sizes. Thereafter, tail unit detachable panels are mounted along strained shutter to remove rod keys. Proposed appliance comprises mounts and rod keys with articulated spherical surfaces. Note here that said mounts have cruciform openings with one through cutout and one part-through cutout. Rod keys are composed of threaded rods on one end and, on opposite end, of plates with flanges shaped to match through cutouts and spherical surfaces of mounts.
EFFECT: ruled out mechanical damages.
2 cl, 5 dwg
SUBSTANCE: invention relates to launching site equipment. Proposed method consists in creating closed water curtain adjoining carrier rocket aft section and to combustion product jet formed by incident jets pre-directed to carrier rocket axis at an angle. Incident flows of separate jets fall nearby said aft section with partial overlap. Proposed device comprises annular water duct arranged on launch pad, axially symmetric about rocket axis, with water feed branch pipes and channels to feed water on curtain made on water duct top face surface. Sleeve with through hole is secured in every aforesaid channel. Nozzle is secured on every said sleeve that deflect from vertical.
EFFECT: higher efficiency.
5 cl, 3 dwg
SUBSTANCE: body stabilisation apparatus has a dynamic resistance element mounted on the edge of the body on a post, the axis of which is directed on the axis of stabilisation of the body. The dynamic resistance element is in form of a brake flap. The flap is mounted at the end of the post in the region of its geometric centre and is hinged with possibility of turning freely about the axis perpendicular the axis of the post.
EFFECT: simple design of the apparatus and reduced size and weight.
2 cl, 2 dwg
SUBSTANCE: invention relates to aircraft engineering. Proposed method consists in that aircraft aerodynamic surface is made symmetrically convertible in the form of tandem duck by arranging additional v-like tail unit at aircraft nose. Gliding is distinguished by intermittent variation of flight direction, back-and-forth, in conditions of pendulum parametric resonance with periodically lowered suspension point along stable flat zigzag trajectory made up of wave-like glide-path sections. Under ground effect, aircraft vertical landing if performed with critical angles of attack of aircraft aerodynamic surfaces.
EFFECT: shorter landing ground run.
4 cl, 4 dwg
FIELD: aircraft engineering.
SUBSTANCE: proposed invention relates to aircraft engineering and can be used in analysing aeroelasticity on dynamically similar models of aircraft in altitude tunnels. Proposed model comprises primary set that simulates stiffness characteristics of structure and consists of plate, spars and ribs, and forming surface acting as the structure outer aerodynamic surface. Primary set plate is made from high-modulus polymer composite material and represents variable-thickness compartments with stepped and stepless surfaces. Spars and ribs also have stepped and stepless surfaces arranged on one side of aforesaid plate and jointed thereto along their stepless surfaces. Aforesaid forming surface consists of two parts, top and bottom, and is made from material with elasticity factor 10 times lower than that of primary set material.
EFFECT: higher accuracy of geometrical similarity and representation of mass-inertial and stiffness characteristics.
FIELD: transport, aviation.
SUBSTANCE: proposed aerodynamic surface represents a solid non-flat outer wing with aerodynamic twist. The aerodynamic surface elongation λ varies within 0<λ<5.5 wherein the said elongation λ is equal to relation between the square of aerodynamic surface span L and aerodynamic surface area S.
EFFECT: improved aerodynamic characteristics due to optimised lifting force factor and drag.
SUBSTANCE: invention relates to sealing compositions, in particular, for sealing punctured vehicle tyre, and inflatable product. Composition for sealing punctured type includes one liquid carrier, one or more viscosity-regulating and slurrying agents, one or more filling agents and sealants and sodium polyacrylate. Composition can contain inhibitor of corrosion.
EFFECT: invention makes it possible to improve quality of sealing in the process of punctured tyre repair, accelerate time of repair without impairing the environment.
25 cl, 3 ex