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Maneuvering aircraft |
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IPC classes for russian patent Maneuvering aircraft (RU 2503584):
Collapsible airfoil / 2492412
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.
Aircraft folding control surface / 2446988
Proposed control surface comprises root section and support. Root section is arranged aircraft airframe to turn thereon. Said root section accommodates support to turn about axis perpendicular to root section center surface. With support folded, part of control surface area ahead of root section turn axle is related to that behind said axle as 1:1 to 3:1. Folded control surface in unfolded position corresponds to condition of axial compensation.
Folding aerodynamic surface / 2349498
Invention relates to the designs of folding aerodynamic surfaces of pilotless flight vehicles. The proposed device comprises fixed (1) and rotary (2) part hinged thereon, pushrod sliding inside the hinge holes and a helical converter of the pushrod translation into rotation of the rotary part of the said aerodynamic surface including a cylinder with helical surfaces and a pin interacting them. The helical converter is furnished with the second cylinder with the helical surfaces direction other than that of the fist cylinder helical surfaces. The cylinders are arranged concentrically relative to each other. Note here that one of the cylinders is connected to the aerodynamic surface fixed part while the other one is jointed to the rotary part. The pushrod is arranged inside the inner cylinder to reciprocate and rotate therein. The pin is fitted on the said pushrod to interact with helical surfaces of both cylinders. Note that helical surfaces of each cylinder are formed by side surfaces of helical slots (5,6) made on diametrically opposite side of the cylinders shells.
Folded aerodynamic surface / 2338663
Aerodynamic surface comprises fixed and hinged parts, pusher sliding inside the hinge holes and helical converter of the pusher translation motion into the rotary motion of the aforesaid aerodynamic surface rotary part, the converter including a helical-surface cylinder and a pin interacting with the said helical surface. The helical converter is furnished with the second cylinder with helical surfaces with direction opposite to that of the fist cylinder and an additional pin interacting with the second cylinder helical surfaces. Both cylinders are arranged aligned and prohibited to reciprocate by a thrust bearing. One of the cylinders is linked with the aerodynamic surface fixed part while the other one with its rotary part. The pusher is arranged inside the cylinders to reciprocate and revolve therein, the pins being fitted on the said pusher to interact with the cylinders helical surfaces via the spherical sleeves. The said helical surfaces of every cylinder are formed by the side surfaces of helical slots made on the opposite sides of the cylinders rings.
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.
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.
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).
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 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.
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.
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.
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.
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FIELD: transport. SUBSTANCE: 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. EFFECT: higher safety and combat efficiency, better relationship between lift and drag. 3 dwg
The invention relates to aircraft, and to manoeuvre the aircraft and the control systems of the aircraft. Known maneuverable plane containing the fuselage, swept-wing moderate sweep, front nodules big sweep, controls, chassis (EN, 2302975 C2). Known the aircraft has a high load-bearing properties at subsonic and supersonic regimes. At supersonic speeds the front flows substantially shift the focus plane forward, thereby reducing the reserve static stability of the aircraft, which, in turn, reduces losses glide on balance, increases maneuvering capabilities of the aircraft. As disadvantages of the known aircraft should indicate the following. At supercritical angles of attack, when the terminal parts of the wing tip stalls, front flows continue to create a lifting force, creating a moment on pitching, which results in the reduction of available torque to the dive, and for aircraft with a full set of cargo on the external suspensions even its absence (maximum rear balance). The technical result, which is aimed invention is to improve the safety and combat effectiveness of the aircraft by increasing reserves icarousel moment and correspondingly wider range of balance and increase funds the military equipment of the aircraft, and implement the best ratio of lift and drag. This technical result is achieved that the switching plane containing the fuselage, swept wing, front swept flows, controls, chassis, front nodules located at the junction of the head and middle part of the fuselage and provided with a controllable rotating surfaces, with the axis of rotation of the driven surface waves are perpendicular or at an angle to the longitudinal plane of the aircraft. The invention is illustrated by drawings, where Fig. 1 shows a maneuverable plane in the top view of Fig. 2 - maneuverable aircraft at the side view of Fig. 3 - maneuverable plane in the front view. Maneuvering the aircraft includes a fuselage 1, the swept wing 2, the front swept flows 3, governing bodies, including 4 vertical and 5 horizontal fins of the chassis. Front swept flows 3 are located at the junction of the head and middle part of the fuselage 1 and provided with a driven rotatable surface 6, with the axis of rotation of the front steering surfaces 6 flows 3 are perpendicular or at an angle to the longitudinal plane of the aircraft. Maneuverable aircraft, including articulated fuselage, wing and front swept flows large arrow the provider, it has high load bearing properties at angles of attack greater than the critical (26), disruption of the flow from the wing of this plane substantially extended to large angles of attack (up to α=35°). The combination of longitudinal static instability at subsonic regimes and reduced static stability at supersonic speeds significantly expands its maneuvering capabilities. However, the statically unstable in the longitudinal channel of the plane waves in front of the wing there is the problem of providing stock dive point at angles of attack greater than the critical. At angles of attack α close to critical (α=26°), there are disruptions of the flow at the end parts of the wing, disruption of the flow on a floating part occurs at much larger angles of attack. Which leads to an increase kairouseki the moment, coupled with the sharp drop in the efficiency of the longitudinal control leads to a decrease (or even failure) of disposable time to dive. In the case of unintentional contact with the aircraft at large supercritical angles of attack (for example, spin modes or hangs at high angles of attack) dive time pitch after setting bodies longitudinal control for descent with large angles of attack are insufficient for the transfer of aircraft at small angles of attack. Therefore, for both the cookies need disposable time limit permissible maximum rear alignment of the plane. Since modern combat aircraft suspended loads on the fuselage and wing basically shift the center of mass of the aircraft back, we have to reduce the amount of suspended loads, and consequently, degrade the military capabilities of the aircraft. In addition, fixed influx, increasing the lifting force of the wing, does not provide for small and medium angles of attack the implementation of the best value for the lifting force and resistance (polar) plane. To improve safety and operational effectiveness by increasing stocks dive time and the corresponding expansion of the range of valid balance and increase funds the military equipment of the aircraft, as well as the implementation of the best value for the lifting force and the resistance front flows 3 provided with a controllable rotating surfaces 6 and the rear edge is not in the deflected position tightly fixed to the front part of the influx 3, located in the track (on the stream). When the deviation managed rotatable surface 6 at supercritical angles of attack are reduced load-bearing properties and increases have a negative pitching moment of the aircraft. When the deviation managed rotatable surface 6 at low and medium angles of attack provides the best ratio of lift and drag of the aircraft. Deviation control is controlled rotary surfaces 6 automatically. The algorithm of the deviation depends on the current angle of attack (according to a certain law) and the provisions of the longitudinal body control - horizontal tail 5 and at the same time optimally retains a high load-bearing properties of the wing 2, provides the necessary supply of dive time at supercritical angles of attack and allows you to implement more rear alignment. The maximum deflection angle of the driven rotary surfaces 6 on the dive is about 60°. Managed rotatable surface 6 significantly improves the manoeuvrability of the aircraft, improving its combat capabilities and increases the safety of its operation. Additionally driven rotatable surface 6 are used for braking of the aircraft after landing on a runway after touching the runway the front by their deviations entirely on the dive. Managed rotatable surface 6 can be performed in the following ways: with the axis of rotation is angled to the longitudinal plane of the aircraft; with axis of rotation perpendicular to the plane of symmetry of the aircraft. At supersonic regimes driven rotatable surface 6 is located in a fixed position, i.e., not rejected. Maneuvering the plane containing the fuselage, swept wing, PE is one arrow-shaped nodules, controls, chassis, wherein the front nodules located at the junction of the head and middle part of the fuselage and provided with a controllable rotating surfaces, with the axis of rotation of the driven surface waves are perpendicular or at an angle to the longitudinal plane of the aircraft.
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