RU2130863C1 - Vertical take-off and landing aircraft - Google Patents

Abstract

FIELD: aeronautical engineering. SUBSTANCE: aircraft includes triangular fuselage with cabin, engine plant, lifting airscrew mounted on shaft and located in through opening of central fuselage, tilt propeller mounted on shafts symmetrically on either side from lifting airscrew; each tilt propeller is mounted in circular shroud mounted on horizontal shaft and in respective through opening; besides that, aircraft is provided with drive for synchronous turn of above-mentioned shrouds from horizontal to vertical position, swivel stabilizers for maneuvering in horizontal direction at their synchronous turn about respective vertical axis; these stabilizers are located behind tilt propellers; engine plant is provided with turbines; one turbine is mounted in central opening and its shaft carries airscrew; other turbines are arranged in circular shrouds in side openings; they are mounted on axles-supports which ensure their turn from horizontal to vertical plane; their shafts carry tilt propellers. EFFECT: increased lifting force and speed; enhanced efficiency of control. 9 cl, 3 dwg

Description

 The invention relates to the field of aviation and can find application in various fields.

 Known aircraft with vertical take-off and landing, containing a triangular-shaped fuselage with a cabin, a propulsion system, a lifting screw located in the through hole of the central part of the fuselage, through holes are symmetrically located on both sides of it, having rotation axes associated with the drive rotated synchronously from the horizontal plane of rotation into the vertical screws located in the through holes, and the stabilizers rotary synchronously around the vertical axis located behind the rotary screws (pa ent RF N: 1830016, IPC (5) B 64 C 29/00, 1991, the prototype).

 The well-known aircraft is characterized by high maneuverability, but it does not fully utilize the potential capabilities of the structure, namely, the ability to increase speed characteristics, lift and control efficiency.

 An object of the present invention is to provide an aircraft with a vertical take-off and landing with higher flight characteristics.

 The technical result of the invention is an increase in lifting force, an increase in speed capabilities and control efficiency.

 The specified technical result in an airplane with a vertical take-off and landing containing a triangular fuselage with a cabin, a propulsion system, a lifting screw located in the through hole of the central part of the fuselage, through holes are symmetrically located on both sides of it, in which there are shafts in the horizontal plane, associated with the drive of their synchronous rotation from a horizontal plane of rotation to a vertical, screws located in through holes, stabilizers rotary synchronously wok g vertical axis and located behind the pivot screws is achieved in that the propulsion unit is designed as a turbine, disposed on the shafts rotate in the central bore, and screws are mounted on respective shafts turbines.

In addition, additional differences may consist in the fact that:
- a wing with controls in a vertical plane is installed in the rear of the fuselage;
- in the stabilizers, cutouts are made in the form of a cross section of a wing having ends extending beyond the outer sides of the stabilizers;
- the controls are formed by slats, flaps, ailerons and interceptors;
- from the upper and lower planes of the fuselage, from the front and rear parts of viscous openings, smooth understatements are made;
- disk pads with stabilizers installed on them are located in understatements;
- the cabin is shifted to the nose of the fuselage, made in the form of thickening with a smooth transition into the fuselage;
- in the lower plane of the fuselage behind the cockpit and in the rear are retractable landing gear;
- a wing with controls installed on vertical racks mounted on the upper plane of the fuselage;
- propulsion systems located on the axes of rotation, with screws installed in the ring casing.

 The airplane is shown in FIGS. 1-3, in which FIG. 1 is a general plan view, in FIG. 2 is a side view, section AA in FIG. 1, in FIG. 3 is a side view, section BB in FIG. 1.

 The aircraft contains a fuselage 1 of a triangular shape with a cabin 2, offset into the nose and made in the form of thickening with a smooth transition into the fuselage 1, forming a fairing, a propulsion system made in the form of turbines 3 and 4. Turbine 3 is located in the central hole 5 and is mounted on supports 6. On the shaft of the turbine 3 is installed a lifting screw 7.

 Turbines 4 with screws 8 on their shafts are installed in annular casings 9, in through holes 10 located symmetrically relative to the through hole 5 and mounted on shafts - supports 11 installed in the horizontal plane and connected with the drive of their synchronous rotation from the horizontal plane of rotation to vertical and vice versa (not shown).

 On the fuselage 1, from its upper and lower planes and from the front and rear parts of the through holes 5, smooth understatements 12 are made to improve air intake by screws 8.

 Behind the rotary screws 8 on the fuselage 1 in understatements 12 are located disk pads 13 with stabilizers 14 rotary synchronously around the vertical axis.

 In the rear part of the fuselage 1, a wing 15 is installed with controls in a vertical plane formed by slats 16, flaps 17, ailerons 18 and spoilers 19.

 In the stabilizers 14, cutouts 20 are made in the form of a cross section of the wing 15 having ends extending beyond the outer sides of the stabilizers 14. The wing 15 is mounted on vertical struts 21, mounted on the upper plane of the fuselage 1.

 In the lower plane of the fuselage 1 behind the cockpit 2 and in the rear part are made retractable chassis 22.

 The principle of operation of the aircraft is as follows.

 The aircraft is lifted by starting all the turbines 3 and 4 of the propulsion system, the screws 7 and 8 of which, located in the horizontal plane, are rotated, as a result of which there is a lifting force in the vertical plane, and the plane rises into the air, the landing gear 22 is removed. At a certain height, the pilot, using the control system, transfers the side turbines 4 together with the screws 8 from a horizontal to a vertical position, after which the aircraft begins to move forward due to the appearance of thrust in the horizontal plane.

 Maneuvering in the horizontal plane is carried out by synchronously turning the pads 13 with stabilizers 14, and for maneuvering in the vertical plane is the control wing 15 with controls 16, 17, 18 and 19. So, the spoilers 19 serve as brake flaps for air flow around the wing surface . The slat 16 serves to increase the surface area of the wing 15, therefore, its lifting force. The flaps 17 also provide an additional increase in the lifting force of the wing 15. The ailerons 18 serve for the operational maneuverability of the aircraft in a vertical plane.

 Aircraft landing can be done in two ways: by conventional planning on the runway with impact only on the wing elements 15 and by vertical landing - by gradually moving the screws 8 from the vertical plane to the horizontal and with a smooth decrease in the number of revolutions of turbines 3 and 4.

Claims (9)

 1. Aircraft with vertical take-off and landing, comprising a triangular-shaped fuselage with a cockpit, a propulsion system, a lifting screw mounted on the shaft located in the through hole of the central part of the fuselage, rotational screws mounted symmetrically on both sides of the lifting screw, each of which which are housed in an annular casing mounted on a horizontal shaft and in a corresponding through hole, drives for synchronously turning said casing from horizontal to vertical rotary stabilizers for maneuvering in the horizontal direction when they are rotated synchronously around the corresponding vertical axis, said stabilizers being located behind the rotary screws, characterized in that the propulsion system has turbines, one of which is installed in the central hole and the lifting screw is installed on its shaft and other turbines are mounted in annular casings in through holes in conjunction with screws mounted on their shafts.  2. The aircraft according to claim 1, characterized in that in the rear of the fuselage there is a wing with controls in a vertical plane.  3. The aircraft according to claims 1 and 2, characterized in that the stabilizers are cut out in the form of a cross section of a wing having ends extending beyond the outer sides of the stabilizers.  4. The aircraft according to claim 2, characterized in that the controls are formed by slats, flaps, ailerons and interceptors.  5. The aircraft according to claim 1, characterized in that on the surface of the upper and lower parts of the fuselage, as well as the front and rear parts of the through holes, smooth understatements are made.  6. The aircraft according to claim 5, characterized in that on the fuselage in the understatement are located disk pads on which stabilizers are installed.  7. The aircraft according to claim 1, characterized in that the cockpit is shifted to the bow and made in the form of thickening with a smooth transition into the fuselage, forming a fairing.  8. The aircraft according to claims 1 and 7, characterized in that on the lower surface of the fuselage behind the cockpit and in the rear part are retractable landing gears.  9. Aircraft according to claims 1 to 4, characterized in that the wing with controls is mounted on vertical struts mounted on the upper surface of the fuselage.

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