Combined anti-ice system

FIELD: aviation.

SUBSTANCE: combined anti-ice system consists of a thermal device located under skin of wing leading edge, and movable flap. The flap is installed at a distance of 1-2 maximum thicknesses of profile from the leading edge. The flap turns by an angle of 20°. Flap surface and surface of the wing in front of the flap are coated with superhydrophobic coating, preventing the formation of barrier ice.

EFFECT: ensuring of flight safety by anti-icing protection of airfoil surfaces.

1 dwg

 

The invention relates to aircraft and is intended for de-icing the aerodynamic surfaces of aircraft (LA).

Currently known electro-mechanical, pneumatic, thermal and other systems protect bearing surfaces from LA icing.

Closest to the technical essence of the famous is thermal system based on the heating protected from freezing surface LA by using electric heating elements. This system is presented in detail in the book (Tenishev R. H. and other "Anti-icing devices in aircraft, PM, engineering, 1967, pp. 43-77). Described in this work, the system de-icing consists of electric heating elements located under the wing. Heat to the outside of the casing is transmitted by conduction.

The use of such a system prevents icing of the heated surface LA. Drops of water falling on a heated surface, not freezing, spread under the influence of the air flow in the form of a liquid film. Getting on the unheated surface of the film freezes in the form of a barrier of ice. The presence of a barrier of ice causes distortion of the contour of the streamlined surface LA and the change in aerodynamic characteristics, leading to overenunciated.

The property to form on the surface LA ice barrier is a fundamental lack of thermal anti-icing system.

In recent years, for de-icing developed physico-chemical methods to reduce adhesion and to prevent or slow down the transition of supercooled droplets of water-air flow in the solid state with the subsequent removal from the surface under the action of the air stream. Developed on the basis of these new methods superhydrophobic coating (see, for example, L. B. Boskovic, ... A. B. Miller, Y. F. Potapov and other "Anti-icing properties of superhydrophobic coatings on aluminum and stainless steel. Izvestiya an. Ser. chemical, 2013, No. 2) allow you to create quite economical de-icing system. Presented in the cited work study showed that superhydrophobic coatings contribute to the collapse of the liquid film formed during operation of thermal system, droplets, easy Slovenia air flow. This property superhydrophobic coatings are encouraged to use when creating a de-icing systems.

The task and the technical result of the invention is the creation of a combined anti-icing systems that do not allow education on aerodynamic surfaces Barinov the ice and, thus, ensuring the safety of aircraft flight.

The solution of the problem and the technical result is achieved by the fact that in the combined anti-icing system containing thermal anti-icing device located under the skin of the leading edge of the wing, on the wing surface at a distance l=(1-2)bmax, the maximum profile thickness from the front edge has a retractable into the wing faceplate with angle up to 20° with a surface and the surface of the wing in front of scutellum covered with a superhydrophobic coating.

The drawing shows a schematic diagram of the proposed system.

Combined anti-icing system contains heat protivoobledinitelnoy device 3 located under the skin of the leading edge 2 of the wing 1 retractable into the wing flap 4, the surface of which, as part of the 5 wing surface caused superhydrophobic coating. Cluster 4 is located at a distance l=(1-2)bmax, where bmax is the maximum thickness of the profile from the leading edge of the wing, and in the closed state is part of the wing surface.

When the flow around a wing LA 1 supercooled air flow to prevent icing of the leading edge 2 is included thermal protivoobledinitelnoy device 3 and is opened to the angle α of the flap 4. Crystallizing pen is it the edge of the ice melt, and the formed film of water under the influence of air flow on superhydrophobic non-wetted parts 5 wing surface in the direction of the flap 4, breaking under the action of surface tension forces on the drops. From the surface of the flap 4, is installed at an angle of 10÷20°, drops blown off in the air flow, not falling on the surface of the wing 1 and, thereby, eliminating the icing surface.

Thus, a combined anti-icing system prevents formation of ice barrier and ensuring the safety of aircraft flight.

Combined anti-icing system containing thermal anti-icing device located under the skin of the wing leading edge, wherein on the surface of the wing at a distance l=(1-2)bmax maximum profile thickness from the front edge has a retractable into the wing faceplate with angle up to 20° with a surface and the surface of the wing in front of scutellum covered with a superhydrophobic coating.



 

Same patents:

FIELD: electricity.

SUBSTANCE: electric impulse de-icing device is related to impulse devices and may be used for mechanic de-icing of metal coating of vehicles such as planes, helicopters, aerofoil boats and vessels. It comprises electromagnetic induction coils, a control pulse distributer and an ice detector. The electromagnetic induction coils are coupled through thyristors in parallel to a storage capacitor connected to a charger. The control pulse distributer comprises in-series clock generator, a pulse counter and a decoder. The clock generator is frequency controlled; it includes the master clock, a three-digit binary counter, a multiplexor, and three comparators. The decoder outputs are connected through pulse amplifiers to control electrodes of the thyristors. The ice detector output is coupled to the controlled input of the clock generator. The device ensures partial load modes of force impact during pulse treatment of the de-iced coating.

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2 cl, 2 dwg

FIELD: transport.

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FIELD: transport.

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The invention relates to methods, systems and devices (structures) for heating the ice and snow and to change the adhesion strength of ice at the contact between the ice and the selected objects
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FIELD: transport.

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Collapsible airfoil // 2492412

FIELD: weapons and ammunition.

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4 dwg

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4 cl, 7 dwg

FIELD: aeronautical engineering.

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3 dwg

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Collapsible airfoil // 2492412

FIELD: weapons and ammunition.

SUBSTANCE: collapsible airfoil comprises a base and a hingedly connected rotary blade, a pusher and a screw converter of pusher progressive motion into rotary motion of the blade. The screw converter comprises two cylinders with helical surfaces and an interacting working element. Cylinders are arranged coaxially in series. One of cylinders is connected to the base, and the other one - with the blade, besides, the second cylinder has helical surfaces of another direction, in comparison to the helical surfaces of the first cylinder. The working element is made in the form of a threaded stem placed in inner cavities of cylinders with the possibility of progressive and rotary movements. The working element with one end is rigidly connected to the pusher sliding inside the first cylinder, and with the other end it is introduced into the second cylinder. Helical grooves made along the surface generator of the threaded stem in its middle part change their direction from one to another, which responds to helical surfaces of cylinders.

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4 dwg

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EFFECT: higher safety and combat efficiency, better relationship between lift and drag.

3 dwg

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