Swept wing |
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IPC classes for russian patent Swept wing (RU 2221729):
   
 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 aeronautical engineering. The wing consists of a center section and console with supercritical profiles made with extension = 9-11, narrowing =3,5-4,2, sweep =25-32o. The wing is equipped with upper and lower wings of small aspect ratio, which is hinged in the rear part of the wing with the possibility of free rotation flow. The invention is aimed at improving operational angles of attack, and the expansion of the scope of the wing and the aircraft in General. 5 Il.
The invention relates to aircraft and can be used on subsonic aircraft.
There are various schemes swept wings (see Technical information TSAGI 23, 1980, copyright certificate 1580737 class: 6 64 3/14, encyclopedia of aviation", edited by G. P. Svishchev, publishing house "Russian encyclopedia", M , 1988). Recently, these wings are made using supercritical profiles. However, at high angles this leads to reduced performance. Due to an early breakdown on the upper or lower wing surface worsen bearing properties is to the wing at high angles of attack and the expansion of the scope.
To achieve this goal on a swept wing (with extension=9-11, narrowing =3,5-4,2 and sweep=25-32) and containing supercritical profiles in the aft part of the wing along the whole span or part of the profiles installed freely suspended sash of small length.
The proposal is illustrated in the drawings. In Fig.1 shows a swept wing; Fig.2 - typical profile of the wing of Fig.3 - typical normal flow profile at high angles of attack; Fig.4 is a flow profile in the application of the proposed solution; Fig.5 - comparison of the characteristics of normal profile when applying the inventive suggestions.
Swept wing 1 consists of a center section 2 and the console 3 and elongation= 9-11, narrowing=to 4.2 and sweep=25-32 and supercritical profiles 4. In the rear part of the profile is freely fixed upper 5 and lower 6 folds, which are self-aligning on stream, free spinning on the nodes 7 and 8.
It is known that at high angles of attack on supercritical profiles on ve who are stated, which leads to serious limitations on the use of profiles and operational restrictions on the aircraft (Fig.3).
In the proposed solution by reducing the local pressure on the upper surface of the wing upper 5 and lower 6 fold rise in the positions determined by the conditions of equality of the forces on the wings. This allows you to "tighten" the zone breakdown. Physically, it changes the flow profile and the position of the zones of failure (Fig. 4).
Integrated this allows you to maintain the health profile to higher angles of attack (Fig.5).
Unfortunately, the choice of design solutions and options in each individual case, it is still necessary to find experimentally. But carried out a purge of the model confirmed the claimed benefits and great features of the proposed design.
The claimed solution will allow without compromising aerodynamic performance on the basic modes and increase the weight of the structure to improve the performance of aircraft.
Claims The swept wing, consisting of a center section and console with supercritical profiles made with extension=9-11, narrowing=3,5-4,2, strelovymi wings of small aspect ratio, which are hinged in the rear part of the wing with the possibility of free rotation flow.
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