Supersonic aircraft with adaptive wing |
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IPC classes for russian patent Supersonic aircraft with adaptive wing (RU 2198823):
   
 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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(57) Abstract: The invention relates to aeronautical engineering. The aircraft includes a fuselage, a wing, means of mechanization, designed to adapt the wing to the flight conditions by changing the geometry of the wing, horizontal stabilizer and controls the flight. The fuselage is equipped with a guide with lock, booster and sash, allowing to cover the mentioned guide, the wing is designed as a trapezoidal wing with a small extension, consisting of a fixed arrow-shaped parts with high aspect ratio and triangular parts with high aspect ratio, having a spar at the root portion, made with the possibility of rejection by the booster down and back. Trapezoidal wing is equipped with a hinge, designed for connection near the tips mentioned arrow-shaped and triangular parts. The spar is made with the possibility of telescopic extensions when moving the booster along the guide retainer. The invention is aimed at improving the efficiency of adaptation of the aircraft to the various flight modes. 3 C.p. f-crystals, 5 Il. The invention relates to the field of aircraft, namely the aerodynamic characteristics of supersonic aircraft on RA is e is intended for effective braking maneuvers, in particular in the field of military aviation. On take-off and landing modes, it is possible to create a powerful wing configuration that will allow the aircraft with good thavarungkul or accelerating the engine to safely fly at low speed, almost without changing the angle of attack of the entire plane. Now for supersonic flight effective is trapezoidal wing almost right angle rear edge and for subsonic - swept wing. Best so far is a compromise trapezoidal wing with a swept trailing edge that is used on such aircraft as the MIG-29, SU-27, F-15 and. so on, as a prototype of the selected aircraft of this class, in particular the invention (patent RU 2140376. Subbotin centuries, Blinov A. I.) related to multimode, maneuverable aircraft, able to adjust aerodynamic surfaces to different flight modes. However, minor changes mentioned surfaces is no longer enough to create next-generation aircraft. Known circuit braking of the aircraft in the air, by rejecting triangular wing tips offered on a small sports plane (application of UK 2237254. Barnard Richard). However, the greatest is their corkscrew. On take-off and landing modes are known with the idea to use two rectangular wings, one of which is rotary mounted below the front stationary, to create a single landing circuit (patent of Russia 2121940. Kiriakidi S. K., A. Panov Century, Chistov S. Century). A small plane is not effective due to the complexity of the design and weight, as well as the ability to reach for aircraft of this class is similar TOLC conventional methods. The invention has the above-mentioned possibilities of adaptation of the aircraft to the various flight modes on a higher and more effective level. The invention is explained in the description with reference to the accompanying drawings and graphics. Fig. 1 - type of aircraft in subsonic flight mode, moved down triangular part of the wing. The dashed line shows the supersonic configuration. The arrows indicate the possible relocation of a triangular wing. Fig.2 - type of aircraft in landing configuration. Fig. 3 is a diagram of a telescopic extension spar triangular part in the area of the swivel with swept part of the wing. Fig. 4 is a diagram version of the aircraft with articulated joint is of disobedience CX wing with different movements of the wing at subsonic and supersonic Mach numbers. On the plane normal aerodynamic scheme (Fig. 1) has a trapezoidal wing, consisting of the arrow-shaped front fixed part 1 and the triangular movable rear part 2, which can move down and back along the sidewall of the fuselage, being pivotally connected with the swept part of the wing in the area of the ends. This is ensured by the fact that the side member 5 (Fig. 3) triangular wing made telescopic, i.e., extends in the lower position, where the fixed and at the same time can serve as a brace for the swept portion of the wing, which increases the rigidity of the whole structure in subsonic, most maneuverable, the areas of the flight. Guide triangular wing is located on the side of the fuselage across the air flow, so it is covered by the shutter-plate 4 (Fig.2) advanced forward on the wing changes. On the graph (Fig.5) shows the dependence of the lift coefficient of the su from the resistance coefficient CX wing, changing its extension in flight withkr= 4.3 subsonic regimes tokr= 3.3V at supersonic (thesis Abdykarimov M. A., head, I. Shatalov And MAI, 1986). From the graph we see that the polar when t;1 exceed the ratio su/Sh in subsonic configuration. Approximately theoretical background and constructively manage to implement the present invention. Triangular part of the wing can be rotated a positive angle around the axis of the spar, floating along with it inside the fuselage for the common rail pivot mechanism. When a sudden this turn, as in the one with the arrow-shaped part of the wing, and in the lower position, it is possible to achieve a sharp deceleration of the aircraft to compensate for the work of the horizontal tail the resulting torque. The landing configuration (Fig.2) may be carried out without turning the triangular portion of the wing 2, but with the released flap 3 with swept wing 1, for example, for large type aircraft "Concorde" and turning, then guide the triangular part of the wing should reject it down and back a little, to create a single path: the swept part of the flap was rotated triangular part of the wing, which contributes to a significant increase in the lifting force without a major change in the angle of attack of the entire plane. In the case of combat aircraft, this circuit creates unlimited possibilities for tactics and combat use in combination with other vozmojnostyami each other, a compact and technologically similar to some systems housekeeping issue of the chassis. Therefore, this adaptive wing can be placed on the existing MIG-29, SU-27-37, F-15. In the circuit of Fig.4 shows a variant of aircraft on which to place the Aileron hinge connection parts of the wing are made at some distance from the ends of the swept wing. In civil aviation, aircraft type, "Concord", you can use this wing in the above embodiment, that is, without turning triangular part of the wing, thereby simplifying the design to improve the reliability of system adaptation. The transition of the wing with supersonic regime at subsonic happens here on a large, close to the cruising altitude of flight, which also affects the safety of the flight. Subsonic configuration contributes to the landing not on such high angles of attack, as the "Concorde, Tu-144, which promotes the use of aerodromes different classes and reduces restrictions on pogodnosti. Increases thus, flight safety, which may indirectly lead to higher projected passenger capacity. All these factors will lead to the most cost-effective passenger versuses, wing, means of mechanization, designed to adapt the wing to the flight conditions by changing the geometry of the wing, horizontal stabilizer and controls flight, characterized in that the fuselage is equipped with a guide with lock, booster and sash, allowing to cover the mentioned guide, the wing is designed as a trapezoidal wing with a small extension, consisting of a fixed arrow-shaped parts with high aspect ratio and triangular parts with high aspect ratio, having a spar at the root portion, made with the possibility of rejection by the booster down and back, trapezoidal wing is equipped with a hinge, designed for connection near the tips mentioned arrow-shaped and triangular parts, the said spar is made with the possibility of telescopic extensions when driving booster guide with lock. 2. The plane p. 1, characterized in that it is provided with a rotation mechanism triangular wing around the axis of the mentioned side member, and the swept portion of the wing is provided with a flap. 3. The plane p. 2, characterized in that the said mechanism is designed to rotate the triangular wing around the axis of said longer the ear. 4. The plane p. 2, characterized in that the said mechanism is designed to rotate the triangular wing around the axis of the mentioned side member in the lower position while deviation of the horizontal tail for braking aircraft in the air.
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