RU2174484C2 - Vertical take-off and landing aircraft - disk-type flying vehicle - Google Patents

Abstract

FIELD: heavier-than air flying vehicles. SUBSTANCE: aircraft has wing, flaps, suction chambers open upward and provided with doors, centrifugal compressors used for creation of reactive thrust force and pressure jets of air flow at each half of wing, volute for each compressor and pressure branch pipe for forming air-flow around wing flaps. Adaptive wing is provided with sections of deflectable leading-edges, slats, ailerons and flaperons for deformation of wing, as well as with device for suction of boundary layer from wing surface. Each volute of centrifugal compressor is provided with additional port fitted with damper for delivery of additional air flow under aircraft through planar nozzle at take-off and landing. Doors of each suction chamber have aerodynamic profile; they are located over entire span of wing at small distance from each other and at slot for suction of boundary layer at advance of aircraft and for opening of respective suction chamber at take-off and landing. EFFECT: increased flying range. 6 cl, 9 dwg

Description

 The invention relates to light aircraft heavier than air, short or vertical take-off and landing, multi-purpose, mass use.

 A vertical or short take-off and landing aircraft is known, including a wing, wing flaps, upwardly suction chambers with wings, centrifugal compressors designed to create jet thrust and pressure jets of air flow on each half of the wing, a snail for each compressor mentioned, and also a pressure pipe for blowing wing flaps. [1. French Application N 2269451, B 64 C 29/00, 1975].

 The disadvantages [1] include the large diving moment in the take-off mode, created by intensive blowing of the elevator located on the trailing edge of the apparatus, and the loss of translational speed due to the creation of vortex air flows by the suction chamber, opened upwards.

 The objective of the invention is to increase the lifting force of the wing by supplying an additional pressure air stream under the device at take-off and landing mode in its front part and to improve the quality of the wing through the use of maneuvering load control systems and boundary layer control systems.

 The solution to which the invention is directed is achieved by the fact that the wing is made adaptive, equipped with sections of deflectable socks, slats, ailerons and flypers for deformation of the wing, means of suction from the surface of the wing of the boundary layer to create a laminar flow and a flat nozzle that is placed along the front edge of the wing so as to direct the pressure jets of the air stream from the said compressors under the front of the aircraft during takeoff and landing; the fact that in each scroll of the centrifugal compressor there is an additional window with a shutter for supplying during take-off and landing of additional air flow under the plane through the aforementioned flat nozzle; the fact that the said wing is equipped with an air inlet in the form of a scoop, and each said suction chamber is made in the form of a spiral and is designed to suck the boundary layer from the surface of the wing; the fact that the flaps of each suction chamber are made with an aerodynamic profile, are located along the wing span at a small distance from each other with a slit, and are designed to suck the boundary layer from the wing surface during the translational movement of the aircraft and to open the corresponding suction chamber during takeoff and landing; the fact that the discharge pipe of each centrifugal compressor is equipped with a nozzle with an ejector for suctioning air from the wing surface through slots between the flaps located outside the limits of the suction pipe; the fact that the aircraft is equipped with control wheels designed to interact with both the air flow from the aforementioned compressors and the air stream flowing around it in flight, and has an integrated aerodynamic layout.

 In FIG. 1 shows a top view of an airplane; FIG. 2 is a side view, in FIG. 3 is a front view, in FIG. 4 is a plan view with the upper skin removed, in FIG. 5, 6, 7 - section AA of the wing in FIG. 4 at various stages of flight; FIG. 8, 9 - the 2nd version of the layout.

 Designated: (in Fig. 1) 1 - adaptive wing, 2 - deflected wing toe, 3 - deflectable, multi-section wing shank, (in Fig. 4) 4 - centrifugal compressor, 5 - compressor scroll, 6 - additional window in the scroll, 7 - a shutter, 8 - a flat nozzle, 9 - an air intake in the form of a scoop, 10 - a spiral-shaped suction chamber, (in Fig. 5) 11 - shutters of the suction chamber, (in Figs. 5 and 6) 12 - a gap between the shutters, 13 - pressure chamber, 14 - ejector nozzle, 15 - ejector flaps, 16 - wing mechanization elements, (in Fig. 4) 17 - steering wheel, 18 - engine with exhaust pipe and hl a catcher, (in Fig. 7) 19 - brake flap.

 The layout of the device is integral with the supporting fuselage and adaptive wing 1 (Fig. 1) with the possibility of deformation of the wing by sectional deviation of the slats, socks 2, ailerons, flaps, flypers 3; the wing is laminarized with the possibility of suctioning the boundary layer from the surface of the wing and the ability to direct additional pressure jets of the air stream under the apparatus in its front part during take-off and landing, while the scroll 5 (Fig. 4) of the centrifugal compressor 4 is equipped with an additional window 6 with a shutter 7 for to ensure the possibility of take-off and landing to supply an additional stream of air under the device through a flat nozzle 8 located along the front edge of the wing, which is equipped with an air intake in the form of scoops and 9 with a spiral-shaped suction chamber 10, which simultaneously has the ability to suck the boundary layer from the wing surface, which significantly improves its quality, and the flaps of the suction chamber 11 (Fig. 5) are made with an aerodynamic profile, are located along the entire wingspan, at a short distance away from each other with a slit 12 and have the ability to open the suction chamber 10 on take-off and landing and provide the suction of the boundary layer from the wing surface with the translational movement of the apparatus, and the discharge pipe of the centrifugal lump Spring 13 is equipped with an ejector nozzle 14 for sucking air from the surface of the wing through the gaps 12 between the flaps 15 positioned beyond the suction pipe 9. Furthermore, said aircraft is equipped with control rudders 16, 17 (FIG. 4), which have the ability to interact with both the pressure flow from the compressor, and with the air flowing around the apparatus during the flight, as well as with the brake flaps 19 (Fig. 7).

 The vertical take-off (see Fig. 5) is carried out by pulling upward of the suction chamber 10, intense air flow downward from the flat nozzle 8 and intensive blowing of the mechanization elements of the wing 16, for which the flaps 11 of the suction chamber 10 are opened, the toe 2 is deflected upward, while a flat nozzle 8 with a shield opens, the rudders of height 16 are deflected downward, centrifugal screws are given high revolutions. Take off.

 The transition from vertical take-off to horizontal flight (Fig. 6) is carried out by transferring the toe 2 of the wing 1 to the normal angle of attack, closing the wings 11, translating the elements of mechanization 16 to the desired angle of flight, with the transition to the air intake through the air intake in the form of a scoop 9 and the suction of the boundary layer from the surface of the wing through the slots 12.

 The reduction and inhibition (Fig. 7) is carried out by installing elements of the sectional mechanization of the adaptive wing - socks down, shanks - up. In certain modes, it is possible to use the brake flap 19.

 Landing is carried out in the reverse order of take-off, only before landing a “blasting” is performed (sharply, but for a short time, the rotational speed of the screws is increased).

 Blowing the air stream with a wide front along the front edge of the device in combination with intensive blowing of the wing mechanization provides a balanced stable balance of the device on takeoff and landing.

 Sectional mechanization of the adaptive wing provides high maneuvering and control of maneuverable loads.

 The use of the boundary layer control system, the suction of the boundary layer from the wing surface through thin slots in combination with a laminarized wing, allows increasing the flight range by 40 - 50%.

 A significant increase in speed and efficiency is expected compared to a helicopter. Public vertical take-off and landing aircraft can be widely used in the country's economy, including as a family transport.

Claims (6)

 1. Aircraft of vertical take-off and landing, including a wing, wing flaps, open upward suction chambers with wings, centrifugal compressors designed to create jet thrust and pressure jets of air flow on each half of the wing, a snail for each compressor mentioned, and also a pressure pipe for blowing the wing flaps, characterized in that the wing is adaptive, equipped with sections of deflectable socks, slats, ailerons and flyerons for deformation of the wing, a means of suction from the wing surface boundary layer to create a laminar flow and a flat nozzle, which is placed along the leading edge of the wing so as to direct the pressure jet of air flow from the above compressors under the front of the aircraft during takeoff and landing.  2. The aircraft according to claim 1, characterized in that in each scroll of the centrifugal compressor there is an additional window with a shutter for supplying, during take-off and landing, an additional air stream under the aircraft through the aforementioned flat nozzle.  3. The aircraft according to claim 1, characterized in that the said wing is equipped with an air intake in the form of a scoop, and each said suction chamber is made in the form of a spiral and is designed to suck the boundary layer from the wing surface.  4. The aircraft according to claim 1, characterized in that the flaps of each suction chamber are made with an aerodynamic profile, are located along the wing span at a small distance from each other, with a slit, designed to suck the boundary layer from the wing surface during translational movement of the aircraft and to open appropriate suction chamber during take-off and landing.  5. Aircraft according to claim 1, characterized in that the discharge pipe of each centrifugal compressor is equipped with a nozzle with an ejector for suctioning air from the wing surface through slots between the wings located outside the suction pipe.  6. The aircraft according to claim 1, characterized in that it is equipped with steering wheels designed to interact with both the air flow from the said compressors and the air stream flowing around the aircraft in flight, and has an integrated aerodynamic layout.

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