RU2192986C2 - Aircraft - Google Patents

Abstract

FIELD: aeronautical engineering. SUBSTANCE: aircraft is provided with rotating round wing 1 from which blades 2 are extended during takeoff and landing; blades 2 are controlled by servo-tabs forming main rotor; aircraft is provided with engines. Secured on fuselage 6 is horizontal tail with elevons and vertical tail with control surfaces 8 and interceptor 9 and braking system 10. EFFECT: extended field of application. 7 cl, 3 dwg

Description

 The invention relates to the field of aviation technology, in particular to aircraft and helicopter engineering, and can be used to create convertible aircraft (LA) to significantly increase the speed, carrying capacity and reduce kilometer fuel consumption compared to helicopters several times.

 Famous aircraft (Eger S.M., Mishin V.F., Liseytsev N.K. et al. Design of airplanes. - M.: Mashinostroenie, 1983 - 616s.) - [1], requiring for takeoff and landing (ViP) the presence of horizontal speed, and, consequently, an expensive runway, the absence of which when the engines stop, most often leads to disaster.

 Famous helicopter (Bogdanov Yu.S., Mikheev R.A., Skulkov D.D. Design of helicopters - M .: Mashinostroenie, 1990. - 272 p.) - [2], the aircraft is capable of carrying out vertical airborne aircraft, but having low flight speeds limited load capacity and high fuel consumption per kilometer of flight.

 The prototype of the invention may be a vertical take-off and landing airplane (FP Kurochkin Design and construction of vertical take-off and landing airplanes. - M.: Mashinostroenie, 1977. - 224 p.) - [3], convertiplane Bell XV-15 ([ 3], p. 107), during take-off and landing of which helicopter-type rotors are put into operation, and in horizontal flight these rotors are rotated to create horizontal thrust and the lifting force is created by the wing.

 The main disadvantages of the tiltrotor can be considered low speed in cruising flight due to the creation of horizontal thrust by large rotors, low load capacity due to the large weight of the gearboxes, transmission, wing weight, as well as the limited diameter of the rotors.

 The invention solves the problem of creating a high-speed and lifting aircraft with a vertical ViP.

 It can be passenger and transport, superheavy and ultralight, subsonic and supersonic, as well as unmanned aerial vehicles, high-speed rescue aircraft crews of ships and submarines, with the ability to save the aircraft as a whole in case of engine failure; Buran or Shuttle type spacecraft, cruise missiles, reusable rocket stages, landing capsules with space crews.

 The possibility of vertical airborne missile defense will make it possible to implement the concept of aerodrome-free aerodromes: to abandon the construction of expensive runways, bring aviation closer to the city and the countryside, engage in rotational exploitation of areas of Siberia, the Far North, the Arctic and Oceania, to master new technologies for construction, transport, rescue, and space exploration and the ocean, give a new impetus to the development of civilization.

 The task is achieved by the fact that in an aircraft having a wing, a rotor, a fuselage, plumage, engines and a control system, a wing made round in plan and rotating gases flowing out of its nozzles at a certain radius, contains rotor blades that extend from it which are controlled by a swash plate deflecting servo-drivers located at the ends of the blades. Engines produce gases to rotate the wing on the aircraft and create jet thrust in horizontal flight. At the same time, the wing participates in control according to the course of air defense, which, in the direction of rotation of the wing, is performed by braking the wing relative to the axis that is fixedly mounted in the fuselage, and in the direction opposite to rotation, by pulling the interceptor from the fuselage towards the nozzles of gases flowing from the wing. The wing allows in horizontal flight to control the aircraft rudders and elevons located on the plumage.

 The main distinguishing feature of the proposed aircraft is a circular rotating wing, which can be made in the form of an axisymmetric disk located above or below the fuselage, forming a high plane or low wing. The wing can consist of two disks rotating in opposite directions, located by analogy with helicopters in a longitudinal, transverse or coaxial pattern, in which the disks can be located above and below the fuselage. In a supersonic aircraft, the disk may have a lenticular or polygonal wing profile.

 The disk may have a cut parallel to the diametrical plane dividing it into two parts, one of which is rigidly connected to the fuselage structure, and the other has the ability to rotate and contains nozzles and retractable blades.

 Aircraft can have a disk cut in two planes parallel to the diametric, above and below it, and only the middle part containing the nozzles and blades rotates, and the upper and lower are rigidly interconnected via an axis and are stationary relative to the fuselage and form a single structure with it . The fixed part of the disk can be a fuselage with the plumage and engines fixed on it and the passenger cabin and the cockpit housed in it, and the rotating part contains nozzles and retractable blades. Such a plane, similar to a flying wing aircraft, may be called a flying disk.

 The drawings show one embodiment of the invention (the use of two-tail plumage is associated only with the location of the engines).

 Figure 1 - profile projection of the aircraft with the blades released.

 FIG. 2 is a plan view with gaps in the wing drawing, through which the tail of the aircraft and nozzles for blowing gases out of the wing are visible.

 Figure 3 - frontal projection of the aircraft.

 The aircraft contains a wing 1, blades 2, servo wheels 3, engines 4, nozzles 5, fuselage 6, elevons 7, rudders 8, spoiler 9, brake system 10.

 The wing 1, from which the blades 2 are pulled out, controlled by a swash plate deflecting the servo wheels 3, are rotated by the gases that enter it from the engines 4 and flow out through the nozzles 5, ensuring the rotation of the wing 1. On the fuselage 6, the horizontal tail with the elevons 7 and the vertical tail are strengthened with rudders 8, as well as an interceptor 9 and a brake system 10.

 Before takeoff, engines 4 start working, supplying gases under pressure to wing 1. The outflow of gases from nozzles 5 of wing 1 causes it to rotate. Reducing friction in the braking system 10, the pilot releases the blades 2 from the wing. By creating a common pitch of the blades by the servoruli 3, the pilot puts the aircraft in hover mode. Servoruli 3 using a swashplate creates a positive angle of attack of wing 1 and at the same time engines 4 create horizontal traction.

 Low-speed flight begins. Until the rudders of direction 8 are effective, the rotation of the fuselage 6 in the direction of rotation of the wing is controlled by increasing the friction moment between the wing and the axis of its rotation, fixedly mounted in the fuselage 6, using the brake system 10, and the rotation of the fuselage 6 in the direction opposite to the rotation of the wing 1 is created the extension of the interceptor 9 into the zone of blowing gases from the nozzles 5 of the wing 1. The heel angles at this time are created by servoruli 3 controlled by the swash plate. They change in azimuth the angles of attack of the blades 2.

 With increasing flight speed, the lifting force of wing 1 increases, and the blades 2 retract into wing 1 by the braking system 10. The roll and pitch control is carried out by the elevons 7, the course control and damping of the friction moment in the connection of the fuselage 6 with wing 1 - rudders 8. If the wing 1 does not rotate in flight, the control of the rudders 8 and elevons 7 is no different from the famous airplane.

 When the flight speed decreases before landing, the wing 1 spins up and the blades 2 are pulled out of it. The roll and pitch control is transferred to the swashplate unnoticed by the pilot, since the control of the elevons 7 and the swashplate are connected and performed by the same movements of the control wheel. Similarly connected with the pedals are the steering wheels 8 and directional control using the spoiler 9 and the brake system 10.

 After a vertical landing, the blades 2 are retracted into the wing 1 using the braking system 10. The flight is completed.

 The wing 1 may be an axisymmetric disk, which for supersonic aircraft has a lenticular or polygonal wing profile.

 The type of aircraft described above may be a high wing or a low wing when the wing 1 is located respectively above or below the fuselage 6.

 An aircraft can have two disk wings located along a longitudinal, transverse, or coaxial scheme, similar to the corresponding helicopters, but flying on the principles proposed above. In coaxial and longitudinal schemes, one disk can be located above and the other under the fuselage 6.

 The aircraft may have a disk wing 1, in which the disk is cut into two parts by a plane parallel to the diametrical plane. In this case, one part can be fixed and attached to the fuselage structure, and the other rotates relative to it, representing the actual wing with retractable blades 2.

 The aircraft may have a disk wing cut by two planes parallel to the diametrical plane, above and below the latter. The middle part rotates and blades are released from it, and the upper and lower are rigidly connected through the axis and are motionlessly connected with the fuselage structure.

 The disk wing 1, cut parallel to the diametrical plane, can be a “flying disk” aircraft, in which the fixed part is the fuselage with the plumage and engines located on it, and the passenger and pilot cockpits located in it, and the other is the wing itself with nozzles and retractable blades.

 The essence of the invention lies in the fact that the proposed aircraft with a rotating round wing, from which during take-off and landing (ViP) blades are advanced, forming a rotor. Engines in the cruise flight mode create horizontal thrust, and on the VIP they supply pressure to the gas channels of the wing, the rotation of which is carried out by the outflow of gases from nozzles located at some distance from the center of the wing.

 The roll and pitch control on the VIP is carried out by servo-drivers located at the ends of the blades and controlled by the swash plate. The friction moment in the fuselage hinge bearings is quenched and the directional control in the direction against the wing rotation on the aircraft is carried out by an interceptor pulled out of the fuselage in the gas blowing zone by the wing nozzles, the fuselage is turned in the direction of rotation of the wing by the wing braking relative to the axis, which is fixed in the structure the fuselage. In horizontal flight, control is carried out in an airplane - air rudders and elevons.

 Thus, an aircraft is proposed that is capable of vertically taking off and landing, moving horizontally at a high speed, including supersonic speed, an aircraft with a large carrying capacity and low fuel consumption.

 The wing of the aircraft described above can be an axisymmetric disk, which for supersonic flight must have a lenticular or polygonal wing profile.

 A plane with a disc located above the fuselage is a high plane, and a low plane under the fuselage.

 An airplane can have 2 disks rotating in different directions and located by analogy with helicopters in a longitudinal, transverse or coaxial pattern, in which the disks can be located above and below the fuselage.

 The aircraft can have a disk cut along a plane parallel to the diametrical plane dividing it into two parts, one of which is rigidly connected to the fuselage structure, and the other, which can be rotated, contains nozzles and retractable blades.

 The aircraft can have a disk cut in two planes parallel to the diametric, above and below it, and only the middle part containing the nozzles and blades can rotate, and the upper and lower, rigidly connected through the axis, are fixedly mounted on the fuselage.

 The aircraft can have a fixed part of the disk as an independent unit - the fuselage with the plumage located on it, engines and the cockpit and passengers located in it, and the rotating part contains nozzles and retractable blades. Such a device can be called a flying disc aircraft.

Claims (7)

 1. Aircraft having a wing, a main rotor, a fuselage, plumage, engines and a control system, characterized in that the wing, made circular in plan and rotating gases flowing out of it through nozzles at a certain radius, contains blades extending from it for take-off and landing rotor controlled by servos from the swashplate, jet engines generating gases for the wing to rotate on takeoff and landing and jet thrust in horizontal flight, while the wing is involved in controlling the course on takeoff and landing towards its BP braking of the wing relative to the axis fixed in the aircraft structure, and in the direction opposite to rotation — by pulling the interceptor from the fuselage structure toward the nozzles of the gases flowing from the wing and allows horizontal flight control of rudders and elevons located on the plumage.  2. The aircraft under item 1, characterized in that the wing is an axisymmetric disk, which for supersonic aircraft has lenticular or polygonal wing profiles.  3. Aircraft according to claim 2, characterized in that the disk, turning on takeoff and landing in the main rotor, is located above or below the fuselage, forming a high plane or low wing.  4. Aircraft according to claim 2, characterized in that it has two disks with rotation in different directions, located in a longitudinal, transverse or coaxial pattern, in which the disks can be located above and below the fuselage.  5. Aircraft according to claim 2, characterized in that the disk has a cut parallel to the diametrical plane, dividing it into two parts, one of which is rigidly connected to the fuselage structure, and the other, which can be rotated, contains nozzles and retractable blades.  6. The aircraft according to claim 2, characterized in that its disk has two cuts parallel to the diametrical plane, above and below it, and only the middle part has the ability to rotate, and the upper and lower, fixed on a common axis, are rigidly connected to the fuselage structure.  7. Aircraft according to claim 5 or 6, characterized in that the fixed part of its disk is a fuselage with engines and plumage fixed on it, with the goods located therein, cockpits of pilots and passengers, forming together with the movable part the plane "flying disk" .

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