Wing aircraft |
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IPC classes for russian patent Wing aircraft (RU 2222472):
                     
 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
 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.
 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.
 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.
 Hollow soft wing with air intake at tip and shaped slot on upper surface / 2389644
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.
 Aircraft flexible control surface / 2408498
Flexible elastoplastic control surface (1; 11, 14) is, in fact, flat in span direction (9) ram airflow direction (6) and comprises actuators (3) acting on control surface (1; 11, 14) at various points of force application spaced apart in crosswise direction with respect to ram airflow direction (6). Actuators (3) are configured so that, when activated, they deflect aforesaid pints (2) to allow elastic deformation without jogs on control surface (1; 11, 14) in directions of span (9) and ram airflow (6).
 Rotary element to increase lift, particularly, deflecting wing tip with high aerodynamic characteristic / 2414386
Invention relates to aircraft engineering. Wing deflecting tip features profile of aircraft wing. Wing 10 comprises torsion 10a has first side with first skin 11 and second, opposite, side with second skin, and torsion box edge facing deflecting tip 20 with front skin that is a continuation of first skin 11. Wing deflecting tip 20 comprises main case 21 that allows transition from first side to second side, and first transition part 20a facing the first side, and second transition part 20b that faces second side. Said wing deflecting tip 20 can be set by retention mechanism 23 and drive that coupled said tip with torsion box 10a between first, IN, position and second, OUT, position. First transition parts 20a of the tip can slide on over wing front surface. Wing deflecting tip can be mounted between first and second positions at preset angle to wing torsion box 10a, and wing profile may be widened around imaginary rotational axis 30.
 Strengthened panel / 2469907
Panel comprises a composite lining, multiple stringers attached to the lining, and actuation mechanisms of force application. Each mechanism is arranged between neighbouring pairs of stringers and is arranged as capable of applying a local force to the lining, causing bending of lining between stringers to form a group of several folds in the lining. The method to bend a panel includes application of a compressing load to the panel in the plane of lining and a local force to the lining between neighbouring pairs of stringers with the help of actuation mechanisms, when the load exceeds a preset threshold.
 Maneuvering aircraft / 2503584
Invention relates to aircraft engineering, particularly, to maneuvering aircraft and their control systems. Maneuvering aircraft comprises fuselage, swept wing, front wing-root extensions, control components and undercarriage. Said front wing-root extensions are arranged in fuselage head-to-tail joint and equipped with controlled rotary airfoils. Wing-root extension controlled surface turn axes are perpendicular or angularly to aircraft wing surface.
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The invention relates to the field of aviation. Wing (1) attached affecting its lifting force parts (20, 21) wings that can be moved from aerodynamically inefficient transport position in aerodynamically efficient working position, and Vice versa, from the working position to the transport position. Parts (20, 21) of the wing is placed in its working position on the upper surface (3) and/or on the lower surface (4) wings (1), at least one part (20, 21) of the wing on each wing is on the top and/or bottom surface of the wings (1) in its working position, at least in the greater part of the width of the wing (1) between its front edge (24) and rear edge (23). Part (20) wings, installed in its working position, increase the lifting force of the wings (1) and change, in particular increase, the angle of attack (2) wings (1). The invention is aimed at improving aerodynamic qualities. 30 C.p. f-crystals, 23 ill.
The invention relates to a wing of the aircraft, in particular to the wings with a cross-section and angle of attack, suitable for flying with great speed, and the wings have the parts that affect their lifting force which is transferred from aerodynamically defectedrecords position.
According to the Bernoulli law of gases, the flow rate of which increases, reduce its pressure. Aircraft with wings use this physical principle. Fig. 1 shows in sectional view a conventional wing 1 with a given angle of attack 2. The upper surface 3 of the wing 1 is concave outward. Passing on the wing 1 air flow 5 must pass through the upper surface 3 a larger (longer) path in comparison with the bottom surface 4 of the wing 1. Formed on the upper surface 3 of the wing 1 as a consequence, the negative pressure (uplift force in the direction of arrow 7 in Fig. 1) in horizontal flight equalizes the weight of the plane and supports it in the air.
As a result of change of velocity, angle of attack 2 and/or aerodynamically effective upper surface of the wings can affect the characteristics in flight. The lift force generated on the wing of the plane, directly proportional to the area of the main surface which is a air flow, and is proportional to the square of the velocity of the air flow on this wing. In addition, the lifting force is approximately proportional to the angle of attack of the wing, while he remains within about 14 degrees. Angles larger values lead to the so-called "Cabrera the relationship of the lifting force and drag. But since this ratio depends on various factors, namely the weight of the aircraft or the air flow rate passing over aerodynamically efficient aircraft parts, then trying to rush the lift force and drag to existing conditions and consequently applications. Made to work at subsonic speeds transport aircraft is the ratio of the force of the lift/drag about 20, and the airframe has a ratio of 30 or more. In the range of supersonic speeds attained the ratio of lifting force and reverse thrust is reduced to less than 10.
To satisfy aerodynamic and economic requirements of a flight with a low and high speed, high or low gruzoperevozki, optimization of range and fuel consumption, as well as the use of a runway large or small length, the aircraft with the wings should change their aerodynamic characteristics of lifting force.
According to the prior art has proposed measures to change the lifting force of the wings of the aircraft and their adaptation to different situations. One suggestion is to use inflatable wings or inflatable parts of the wings.
ΓΌ the wing deflection (bending) of the outer shell of the wing. Both possibilities are generally suitable only for low-speed light aircraft with wings. Another, anyway associated with high costs and therefore expensive possibility is the use of rotary wing. In Fig. 2 shows the most widespread at present, the technique of modifying the lifting force of the wing, namely the use landing flaps (sliding panels) 10. These landing flaps 10 demonstrate the effect of the fact that they extend the back and sometimes the front part of the wing 1 down. Consequently extends also creates a lifting force profile on the upper surface 3 of the wing 1. This increases the lifting force. But as on the bottom surface 4 of the wing 1 in constant angle of attack 2 is created in the cavity 12, in-flight encounter strong turbulence 13, which lead to the famous "shaking" of the aircraft with the extended flaps 10, for example, when landing. Such landing flaps 10 are usually built into the wings and, if necessary, come to them, but, as described in the patent DE 2353245 WITH, can also be accommodated in the fuselage of the plane and from there to move to its operating position near the edges of the wings (front and rear edges). But as in this, as in all drugface remain unchanged, this form changes the lifting force has narrow limits. For technical reasons and for reasons of stability takeoff and landing configuration increases the surface may not exceed a certain value, and the necessary cross section of the wing may not be less than a certain value and the angle of attack cannot be changed. Cross-section and length of the wing must have a certain minimum size. For efficiency reasons, but also due to the desired universality of their characteristics, have been developed aircraft types that are adapted to a relatively narrow applications. Attempts to expand the versatility of the potential areas of application known to the present time (aircraft with vertical takeoff and landing aircraft with short takeoff and landing, the convertiplane, aircraft with rotating wings) macoeconomic, as they are very expensive, and does not satisfy achieved up to the present time aerodynamic properties. Patent US 4890803 And shows and describes wing aircraft of the above type, which has on the upper surface passing essentially throughout the length of the section. The height of this section on the upper poverhnostnom in Fig.4 US patent 4890803 And embodiment, the flaps can be moved in the longitudinal direction of the wing, to push it into the receiving cavity in the lower part of the fuselage of the aircraft and again it slides out of the cavity. This creates the opportunity to turn the flap on an axis located on the territory of the rear edge of the wing to change its effective size (length) to change the lifting force, therefore, the aerodynamic properties of the wing. The basis of the invention lies in the task of creating the wings of the aircraft of the above type, aerodynamically efficient profile and angle of attack which you can modify. In accordance with the invention this task is solved by the characteristics of paragraph 1 of the claims. Preferred and has the advantage of embodiments of the invention are subject of the dependent claims. Using the invention can be modified and adjusted in accordance with different requirements aerodynamically effective profile, and if desired, the angle of attack of the aircraft using at least one part of each wing, movable along the wing from the fuselage and/or installed on the wing tanks. At least one part of the wing (on each wing) in accordance with the invention may consist of several parts, in which the proposed part of the wing may also consist of only one element, covering the entire perimeter of the fixed wing on the same area throughout its length or speaking for him. According to the invention, the wings have several aerodynamically efficient parts, either separately, or together are used to modify the profile and, if necessary, the angle of attack, in which they are installed. Preferably the wing, attached to the upper surface of the wings, in their working position to increase the lifting force of the wings. Additional parts of the wings, attached to the bottom surface, in its working position serve to increase stability, improve the aerodynamic properties and, above all, together with parts of the wings, attached to the top surface, to change, in particular, increasing the angle of attack of the wings. You might also consider the possibility of moving the retractable wing independently from the other parts of the wing in order that they can be used not only for bilateral and synchronous) change the lifting force and, if necessary, the angle of attack of the wings, but when driving with one hand - with steering wheel - for management purposes. Achieved according to the invention the change in the aerodynamic properties cralonin the flaps or other means for changing the aerodynamic properties of the wings. With the invention of the available part of the wings, which, in particular, are suitable for flight at high speeds cross-section and is suitable for flight at high speeds, the angle of attack. When the aircraft is in flight at high speeds the wing according to the invention are in the transport position in which they are placed, for example, inside the fuselage of the aircraft or in containers provided on the wings. To fly with a low speed of the wing according to the invention is moved from the fuselage of the aircraft or tanks on the bearing surfaces in its operating position, in particular to move along the bearing surfaces in its operating position, and alter the shape of the wing, and thus its carrying power. When in working position to the parts of the wing aerodynamically effective profile determined by the profile of the wings and the profile of the wing. According to the invention of the wings in their aerodynamically efficient position can change the profile of the wings at a constant angle of attack of the wings. Additionally, parts of the wings, in particular, on the lower surface of the wings, can change the angle of attack of the wings. Part of the wings according to the invention or (when brevipinna plot or act for the front or rear edge and/or at the end of the wing. For compact accommodation provided by the invention, parts of the wings in the pushed position (transport position) they can be stacked on each other is provided in the fuselage of receiving cavities and/or installed in the wing tanks or telescopically pushed into each other. According to the invention of the wing can move to its operating position, changing aerodynamically effective profile and/or the angle of attack of the wings, fuselage and/or installed on the wing tanks. There is also the opportunity to bring part of the wings into position with a time offset from the fuselage and installed on the bearing surface of the tanks. Of course, that part of the wings according to the invention does not exclude that equipped their wings are also known in the prior art devices, such as landing flaps. Provided according to the invention of the wing can be used instead of or together with well-known established on the wings of devices to control and/or balance of the aircraft. Provided according to the invention of the wing can be one piece or may consist of several parts, which are each movable fromThe connection parts of the wings with wings can be carried out regardless of whether there are on each wing, one piece or two, or more parts, for example, by digemid each other with geometric closure retaining means (a pair of groove-rib). It is an advantage when provided according to the invention of the wings in the transport position, its face end surface form a part of the outer skin of the fuselage of the aircraft or the side wall of the container in which it is installed. Provided that at least one part of the wing according to the invention can extend beyond the existing wing, at least in one direction. So, part of the wing may extend beyond the wing forward, backward or at the end of the wing, facing away from the fuselage. While the preferred part of the wings that protrude behind the wing on its forward edge and/or on its rear edge. Provided according to the invention of the wing can be made on their surfaces facing the wings of the aircraft, so that they adhere to them over the entire surface or partially. While it is preferable that at least one part of the wing close to the wing ahead for the SNO invention of the wing consist of several parts, they can be movable independently from each other, so that they can be moved from transport in the active position. When this part of the wing can be made so that, for example, of the wing to the upper surface of the wings separated in the longitudinal direction and each have a segment relating to the front edges of the wings, and have each piece belonging to the rear edges of the wings. Preferably, when multiple parts of the wings were connected to each other, which is particularly preferably, for example, when provided part of the wings relating to the upper surface and the lower surface of the wings. In this case, preferably, if the parts of the wings are connected at their front edge and/or trailing edge. This is especially important when parts of the wings are the wings on their front edges and/or trailing edges and attached to the wings, not on the entire surface. The invention solves the above problem by moving one item or several, preferably installed telescopically elements of the transport position in the wind working position, in which may be simultaneously modified cross-section CR, which covers a segment or all of the fixed wing, or acts for him, and made so that in the working position creates a modified cross-section and/or the angle of attack, or may consist of multiple profiles, which together form the necessary public profile and a new angle of attack of the wing in flight configuration with a low speed. The solution according to the invention enables the creation of economically simple design (you can save on the flaps and ailerons), with a mechanical hand and easy from the point of view of statics does not cause doubts (in any phase of the fixed wing is the backbone of moving parts), and allows the simultaneous change of the profile of the wing and/or the angle of attack, and to create control pulses via asynchronous motion of moving parts in the active position. Other details and characteristics, and advantages of the invention ensue from the following description of examples of implementation of the invention using the drawings on which is shown: Fig. 3 is a cross section of a wing containing a portion of the upper surface and the lower surface, Fig. 4 is a front view of an airplane with two pushed in each wing by wing, Fig.5 is a plane with a wing made of three parts, Fig.6 is a plane with fully extended parts of the wing, Fig. 7 is a schematic view of an airplane with two wings and two parts of the wings, which are made on the upper surface of the wings, Fig. 8 is a plane with two on top is pushed into each other by parts of the wing in the transport position, Fig.9 is a plane extended in each wing only one part of the wing, Fig.10 and 11 is a plane with two wings, and part of the wings belong to the upper surface and lower surface and is not extended or partially extended or fully extended, Fig. 12-14 is another variation of the execution is not extended or partially extended parts of the wings,Fig. 15 is an embodiment of an airplane with a wing that can be put in position on the upper surface and the lower surface of the wings, Fig. 16 - the plane of Fig.15, and part of the wings belonging to the lower surface of the wings, advanced, Fig. 17 - variant execution (schematic) with tanks on the wings to install parts of the wings, Fig. 18-22 - cross-section of the wings with the related parts in the different versions of the Fig.23 is another embodiment of. In Fig. 3 in the example shown, how in line is 1. Due to pull-out (or rotation) is shown in Fig.3 two aerodynamically efficient parts 20 and 21 of the wing from the fuselage of the aircraft is changed aerodynamically effective cross-section of the wing 1. There is a big aerodynamically useful bulge (upper) surface 22 of the wing and thus the optimal flow for the low-speed wing profile, which is aerodynamically efficient is composed of parts 20, 21 of the wing and the wing 1. In Fig.3 as an example it is shown that two aerodynamically efficient parts 20 and 21 of the wing in its extended condition cover wing 1 to select the length and protruding beyond the rear edge 23 of the wing. Parts 20 and 21 of the wing according to the invention can take part length or the entire length of the wing 1, or to act for him in the side. In addition, parts 20 and 21 of the wing (or only one of them) can pass from the front edge 24 of the wing 1 to its rear edge 23 (see Fig.3), but also parts 20 and 21 (or only one) ends at some distance from the front edge 24 and/or the rear edge 23 of the wing 1 (they are above it or do not reach the front or rear edge). Parts 20 and 21 of the wing produces more lift than the wing 1. Parts 20, 21 of the wing in the example on fumarii wing profile. As a result of this increased angle 2 attack of the wing 1. These aerodynamic characteristics allow flight with (extremely) low speed with great stability, transport large payloads or use of (very) short runways. After lowering the movable parts 20, 21 of the wings are aerodynamically effective only relatively short and its cross-section and angle of attack designed for high speeds (main) wing 1. Thanks created so small frontal resistance to the same plane are possible high speed with a large range and great fuel efficiency. According to the Bernoulli law for flying in the range of low velocities, the optimal cross-sectional shape of the wing is a teardrop shape. But this applies only to flight speeds in the subsonic range. When approaching or exceeding the sound barrier this form becomes an obstacle, as are formed when approaching the sound barrier of a shock wave with a large amplitude create a strong drag. When the sound speed these shock waves form approx is but 50 degrees. According to the area rule Richard Travis Withcomb aerodynamic resistance of the aircraft at speeds of sound barrier depends on the distribution of the total cross-sectional area along the aircraft. To reduce this drag on the sound barrier and above it attempts to perform a frontal side, opposite the oncoming air flow, as small as possible. For this reason, high-speed airplanes have wings with a narrow front edges of the wing-shaped blades, the fuselage of a large elongation and a small cross-section of the wing. To avoid deflecting the ends of the wings in the shock wave generated when approaching the sound barrier and reaching the cone ago, these aircraft often have a strongly distinctive arrow-shaped wings (for example, Mac Donnell Douglas F15). As known landing flaps aerodynamic properties of the wings can be changed only to a limited extent, these structural characteristics have implications in the fact that the payload is small, the range of small and takeoff and landing speed is high. In the range of low velocities and/or when a large useful be used. In the range of low velocities described configuration of the wings suboptimal. The aircraft used for flight at subsonic speeds, and for flight at supersonic speed (for example, the Rockwell b-1B or Concord), currently represent compromises efficiency in the range subsonic speeds, and the range of supersonic speeds. The invention solves this problem. Fig. 4 shows schematically and in front of the aircraft fuselage 30 and two wings 1, and the receiving cavity 40 and 41 for parts of the wings is shown in its transport position, that is in inoperative position. Fig. 5 shows the plane of Fig.4, with parts 20 and 21 of the wings depicted in the receiving cavities 40 and 41. Fig. 6 shows the plane of Fig.4 and 5, and part 20 of the wings on the upper surface 3 of the wing 1 and part 21 of the wings on the lower surface of the wing 1 is advanced into position. Fig.5 and 6 show that each of the parts 20 and 21 of the wings in this example consists of several parts, which in the transport position in the receiving cavities 40 and 41 is pushed telescopically into each other. In the form shown in Fig. 6 the working position of the individual parts parts 20 and 21 of the wings divorced for the execution of parts 20 and 21 of the wings reach (not shown) of the ends of the wings 1, or may extend beyond them. Fig. 7-9 show an embodiment in which the fuselage 30 aircraft with two wings there are only two receiving cavity 40 to 20 parts of the wings. These parts 20 of the wings may be derived from it is shown in Fig.7-8 transport position (inoperative position) in its operating position according to Fig. 9, and Fig.9 shows that the part 20 of the wings may be nominated only in part. Fig.7-9 also show that the outer ends of the parts of the wings or their details form part of the cladding (cladding) of the fuselage 30 aircraft. It is shown also for other embodiments according to Fig.4-16 and 10-17. This version of the runtime to create an advantage in that the parts 21 of the wings, is pushed into its transport position, remains smooth and streamlined outer shape of the fuselage 30. Fig. 10 shows parts 20 and 21 can also be nominated only partially, and is shown in Fig.10 position related to the upper surface 3 of the wing 1 of part 20 of the wings partially extended, and related to the lower surface 4 of the wing 1 is not extended. Fig. 11 shows that it is possible to completely pull the parts 20 and 21. Fig.12-14 show an embodiment of the aircraft with the fuselage of the part 20 of the wings is shown in Fig.12 in its transport position, that is, in the receiving cavity 40, and Fig. 12 also shows that the outer end surface 27 of the same part 25 part 20 of the wings, which takes care of the second part 26 of the telescopic lower, in the transport position according to Fig.12 each form with a covering of the fuselage 30 plane shutter flush for receiving cavities 40. Fig.15 and 16 show an example run of the aircraft fuselage 30 and two wings 1, with wings 1 includes parts 20 and 21 of the wings. Part 20 of the wings in the position of Fig.15 partially extended, part 21 related to the lower surface 4 of the wing 1, is in its transport position inside the fuselage 30 aircraft. Fig.16 shows the plane according to Fig.15 with fully extended portions 20 and 21 of the wings, which can consist of each of the three digemid each other (for example, digemid telescopically into each other) parts 25, 26 and 28. Fig. 17 shows an embodiment of the aircraft fuselage 30 and wings 1, with the parts 20 and 21 of the wings are placed to change the aerodynamically effective cross-section of the wing 1 in the cavities 40 (transport position), which fixed wing 1. In Fig. 18-23 presents different ways to execute parts of the wings on cryo wing 1 is adjacent to the upper surface 3 of part 20 of the wing and adjacent to the bottom surface 4 of part 21 of the wing. Parts 20 and 21 in Fig.18 pass from the front edge 24 of the wings 1 back and support the rear edge 23 of the wing 1, and the parts 20 and 21 are adjacent to each other on the plot, acting behind the rear edge 23 of the wing 1 and preferably connected to each other on this site. Fig.19 shows a modified embodiment of Fig.18, and in addition to the two parts 20 and 21 provide additional detail 35 wings, which covers both parts 20 and 21 plot the rear edge 23 of the wing 1. Thanks additional details 35 wings in combination with the parts 20 and 21 is achieved aerodynamically effective cross-section of the wings, which are especially suitable for flight with an extremely low speed. At the same time an additional item 35 of the wings may be provided with the parts 20, 21 in their current position. But there is also the ability to move additional item 35 wings to its operating position after the parts 20, 21 are in their working position. In the form shown in Fig.20 embodiment, the part 20 is made adjacent to the upper surface 3 of the wing 1 entire surface, and the part 21 is installed on the bottom surface 4 of the wing 1 with a gap. On the plot front edge 24 of the wing 1 part 21 covers perevyazyvaet option run similar to Fig.20, and the part 20 mounted above the wing 1, is located with a gap relative to the upper surface 3 of the wing 1. Fig.1 also shows that the portions 20 and 21 on the land, jutting out over the wing 1 back, adjacent to each other and can be connected between a connecting means 50. Fig. 22 shows an embodiment that is similar to the variant according to Fig.21, and between the wing 1 and the parts 20 and 21 of the wings shows schematically the coupling means 50. Such connecting means 50 may be provided in all shown embodiments, executing parts 20, 21 and additional parts 35 of the wings and it is preferably about connections with geometric circuit, which allows the relative displacement of the parts 20, 21 (35) between themselves and relative to the wing 1. For example, in the wings 1 are provided grooves (for example, grooves with a cross-section in the form of a keyhole), which are provided on parts of the wings of the interposer with the corresponding cross-section, for example with a cross-section in the form of a keyhole, and can move in the longitudinal direction. Such connecting means included in each other flush, the t can also be provided between the parts 25, 26, 28 parts 20, 21 of the wings. Fig. 23 shows an embodiment in which at least one part 20 of the wings relating to the upper surface of the wings 1, made whole, at least with one part 21 related to the lower part of the wings 1 or (rigidly) connected with it. In this example, run between the wing 1 and wing parts can be a gap at the top and/or bottom (see Fig. 20-22). Parts 20, 21 may be made of the receiving cavities 40, 41 or receptacles 40 in its operating position. Part of the wings, which can be placed in containers 40 on the wings 1, can be combined with parts of the wings, which are provided in the receiving cavities 40, 41 in the fuselage 30 aircraft. Thanks aerodynamically efficient parts 20, 21 of the wings, put forward from the fuselage 30 or executed on the wings of receiving cavities and containers 40, and in this case, due to additional parts 35 of the wings, the wing profile can be almost freely. This means that in the configuration for flight at high speed (is pushed into the transport position by the parts 20, 21 of the wings) with a very small wingspan and very small cross-section of the wing and the narrow front edge of the main wing 1 is achieved very high schaetze extremely large and hitherto unattainable by known means the cross-section of the wings and thereby high aerodynamic lift force. Very high speeds when pushed parts 20, 21 of the wings, however, does not prevent unwanted lift force and drag, and an unnecessarily large angle of attack. Small wingspan, can be used provided according to the invention parts of the wings, preventing the ends of the wings in the area of shock waves generated when approaching the sound barrier and overcoming it, and thus the violation of the stability of a lethal machine. The results of the application made according to the invention of wings of the aircraft wing, for example, the following: at low speeds and/or short runways and/or large useful goods provided by the invention of the parts 20, 21 of the wings and, if necessary, part 35 of the wings are fully extended, to create the maximum possible lift force. When reaching higher speeds of the wings slide in the fully-pushed state largely or entirely accommodated in the fuselage or under the wings of receiving cavities, vessels. In this case, aerodynamically efficient remains only a very short main wing, made with very small transverse the TEI 20, 21 wings. As a consequence, become possible maximum speed, which is impossible to achieve with conventional profiles and angles of attack of the wings, made for use in a range subsonic speeds. Summarizing, we can describe the preferred embodiment of the invention, as follows: wings 1 aircraft, in particular the wings with a cross-section and angle of attack suitable for flight at high speed, which is lent affecting their lifting force parts 20, 21 of the wings that can be moved from aerodynamically inefficient transport position inside the fuselage 30 or posted on the wings 1 cavities 40 in aerodynamically efficient working position and Vice versa from the operating position back into the transport position. Such parts 20, 21 of the wings is placed in its working position on the upper surface 3 and, if necessary, also on the bottom surface 4 of the wing 1, and is made, for example, so that the parts 21 of the wings, placed in its working position on the bottom surface 4 of the wing 1, preferably together with 20 parts of wings, placed in its working position on the upper surface 3 of the wing 1, change, in particular increase, lift, etc who was (1) aircraft, in particular, wing (1) with the cross-section and angle of attack suitable for flight at high speed, and wing (1) is equipped with influencing its lifting force parts (20, 21) wings that can be moved from aerodynamically inefficient transport position in aerodynamically efficient working position and Vice versa, from the working position to the transport position, characterized in that the portions (20, 21) of the wing is placed in position on the upper surface (3) and/or on the lower surface (4) of the wing (1), at least one part (20, 21) of the wing on each wing is on the top and/or bottom surface of the wing (1) in its working position, at least in the greater part of the width of the wing (1) between its front edge (24) and rear edge (23), and part (20) of the wing is placed in working position, increase the lifting force of the wing (1) and change, in particular increase, the angle of attack (2) wing (1). 2. Wing p. 1, characterized in that the part (20) of the wing is installed in its working position on the upper surface (3) of the wing (1), increase the lifting force of the wing (1). 3. Wing p. 1, characterized in that the part (21) of the wing is installed in position on the lower surface (4) of the wing (1) together with parts of what had been the (1). 4. Wing on one of the PP.1-3, characterized in that the portions (20, 21) of the wing is located on part of the length of the wing (1). 5. Wing on one of the PP.1-4, characterized in that the portions (20, 21) of the wing is placed on the front (24) to the rear edge (23) of the wing (1). 6. Wing on one of the PP.1-4, characterized in that the portions (20, 21) of the wing away from the leading edge (24) of the wing (1) and protrude above the rear edge (23) of the wing (1). 7. Wing on one of the PP.1-4, characterized in that the portions (20, 21) wing protruding beyond the front edge (24) of the wing (1) forward and reach the rear edge (23) of the wing (1). 8. Wing on one of the PP.1-4, characterized in that the portions (20, 21) wing bent forward over the front edges (24) and back over the rear edge (23) of the wing (1). 9. Wing on one of the PP.1-8, characterized in that the portions (20, 21) of the wing are located throughout the length of the wings (1). 10. Wing on one of the PP.1-9, characterized in that the portions (20, 21) wing protruding beyond the outer ends of the wing (1). 11. Wing on one of the PP.1-10, characterized in that the portions (20, 21) wing mounted for movement from a receiving cavity (40, 41) inside the fuselage (30) or in them or are made in the wing (1) of the cavities (40) or in them. 12. Wing on one of the PP.1-11, characterized in that the portions (20, 21) of the wing is made of several the capacity of the telescopic pull-out and lowering one another. 14. Wing on one of the PP.1-13, characterized in that the part (20) of the wing belong to the upper surface (3) and part (21) of the wing to the bottom surface (4) of the wing (1). 15. Wing on one of the PP.1-14, characterized in that the facing to the wing (1) surface parts (20, 21) of the wing is made coincident in shape with the shape of the profile of the upper surface (3) and/or bottom surface (4) of the wing (1). 16. Wing on one of the PP.1-15, characterized in that the portions (20, 21) wing, at least in part, adjacent to the upper surface (3) and/or to the lower surface (4) of the wing (1). 17. Wing on one of the PP.1-15, characterized in that the part (21) of the wing is mounted with a gap relative to the bottom surface (4) of the wing (1). 18. Wing on one of the PP.1-15, characterized in that the part (20) of the wing is mounted with a gap relative to the upper surface (3) of the wing (1). 19. Wing on one of the PP.6-18, characterized in that the portions (20, 21) of the wing adjacent to each other by segments above the front edge (24) and/or the rear edge (23) of the wing (1). 20. Wing under item 19, characterized in that the portions (20, 21) of the wing are interconnected in the area adjacent to each of the segments. 21. Wing on one of the PP.1-20, characterized in that at the area of the leading edge (24) and/or phase is p. 21, characterized in that the additional part (35) of the wing is installed in front and/or rear lap. 23. Wing on one of the PP.1-22, characterized in that the portions (20, 21) of the wing is made on the area of the leading edge (24) and/or the rear edge (23) of the wing (1) lap. 24. Wing on one of the PP.1-23, characterized in that attached to the bottom surface (4) of the wing (1) part (21) of the wing and/or the upper surface (3) of the wing (1) part (20) of the wing is made to overlap on the front edge (24) and/or on the rear edge (23) of the wing (1). 25. Wing on one of the PP.1-24, characterized in that is provided by the connecting means (50), through which part (20, 21, 35) connected with each other and/or with the wing (1). 26. Wing p. 25, characterized in that the connecting means (50) are included in each other guides in the form of grooves and ribs. 27. Wing p. 26, characterized in that the grooves are grooves with undercut, and the ribs are shaped in accordance with them. 28. The wing on the PP.1-27, wherein at least a portion (20) of the wing relating to the upper surface (3) of the wing (1), connected to at least one of the bottom sides (4) of the wing (1). 29. Wing p. 28, characterized in that the part (20) of the wing is made in one piece the go with the ability to move into position, regardless of the parts (20, 21) other wing (1). 31. The wing on the PP.1-30, wherein referring to the wings of the wings installed with the possibility of asynchronous move together or separately to generate control pulses.
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