RU2651947C2 - Jet aircraft with shortened or vertical take-off and landing (options) - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: group of inventions refers to aircraft engineering. Jet aircraft with shortened or vertical take-off and landing includes a control cabin, a fuselage, wings, lift and flight control surfaces, a jet propulsion system, an air intake system, an integrated aircraft control system. Propulsion system consists of jet engines. In the first embodiment the jet engines have outlet nozzles with a variable thrust vector (VTV), thus in order to create a stable, total, balanced, reactive moment relative to the center of gravity of the aircraft in the vertical takeoff, hovering and landing mode. Bases of the jet engines nozzles with VTV are located on the perimeter of the disc-shaped fuselage. Medial axes of the bases of single or grouped nozzles with VTV are located radially in at least three directions. In the second variant of creating a stable total balanced reactive moment with respect to the center of gravity of the aircraft in the vertical takeoff, hovering and landing mode, the medial base axes of the single or grouped nozzles are radially arranged in three directions. Over the outlet nozzles of the jet engines there are sections of circular or rotary wings with a variable profile for changing the direction of the expiring jet of the engines.

EFFECT: group of inventions is aimed at improving the flight stability.

3 cl, 22 dwg

Description

The invention relates to the field of aviation, in particular to aircraft with shortened or vertical take-off and landing using jet engines. Known technical solutions of aircraft with the possibility of vertical take-off and landing using a flowing jet of engines along the perimeter of an annular or circular wing with a change in thrust vector (RF patent N 2005660, author Bragin SF, publ. 15.01.1994, RF patent N 2406650, author Andreev Yu.P., published on December 20, 2010, RF patent N 2491206, author Anserov D.O., Anserov A.D., published on 05.20.2013) With many layout and design flaws of the listed technical solutions, it should be noted the rationality of using uniform jet stream along the perimeter of the aircraft to create a total balanced reactive moment relative to the center of gravity of the aircraft with maximum eccentricity in the size of the perimeter radius of the annular or circular wing in the vertical lift, hover and landing mode. Implemented technical solutions of aircraft with shortened and vertical take-off and landing are also known (see book E. Ruzhitsky, "European Vertical Take-Off Aircraft", LLC publishing house "Astrel", LLC publishing house ACT, 2000) Yak-38 , Yak-141 and a series of modifications of the aircraft HARRIER GR.Mk.3 adopted as a prototype. This aircraft is made according to the monoplane scheme with one Bristol-Sidpi Pegasus turbofan engine, with rotary nozzles mounted on the sides of the fuselage. Side unregulated air intakes. All four nozzles rotate synchronously with a maximum nozzle rotation angle of 98.5 degrees. The disadvantage of this technical solution with the location of the nozzles near the center of gravity of the aircraft is its instability in the modes of vertical lift, hovering and landing, as well as in the intermediate mode of transition from hovering to horizontal flight. The aim of the present invention is to increase the stability of the aircraft in all flight modes, in addition to increasing its maneuverability and carrying capacity.

This goal is achieved for a jet aircraft with a shortened or vertical take-off and landing comprising a control cabin, fuselage, wings, wing and tail mechanization elements, a jet power plant, an air intake system, an integrated airplane control system, while the power plant consists of one or a group of single jet engines that have output nozzles with a variable power thrust vector (ISWT), while for the possibility of creating a stable total balanced power p of the active moment relative to the center of gravity of the aircraft in the vertical lift, hover and landing mode of the nozzle base with ISWT of all jet engines are located on the perimeter of the disk-shaped fuselage, while the middle axes of the bases of single or groups of nozzles with ISWT are located radially in at least three directions. The second version of a jet aircraft with a shortened or vertical take-off and landing includes a control cabin, fuselage, wings, wing and tail mechanization elements, a jet power plant, an air intake system, an integrated aircraft control system, while the power plant consists of one or a group of single jet engines, while for the possibility of creating a stable total balanced power reactive moment relative to the center of gravity of the aircraft in vertical lift mode a, hovering and landing, the middle axes of the bases of single or groups of nozzles are located radially in at least three directions, in addition, sections of circular or rotary wings with a variable profile for changing the direction of the outgoing jet of engines are provided above the output nozzles of jet engines. In addition, for the first and second versions of a jet aircraft with a shortened or vertical take-off and landing, jet engines can be installed on turntables to be able to rotate around a vertical axis. In addition, for the second embodiment of a jet aircraft with a shortened or vertical take-off and landing, jet engines can have nozzles with a variable maneuverable thrust vector (IMWT). In addition, for both versions of a jet aircraft with a shortened or vertical take-off and landing for each jet engine, air intake systems with injection compressors are provided. In addition, for both versions of a jet aircraft with a shortened or vertical take-off and landing, the control cabin has viewing windows on the underside of the cabin, and viewing cameras can be installed on the underside of the aircraft. In addition, for the first and second versions of a jet aircraft with a shortened or vertical take-off and landing, the control cabin can be installed on a turntable. Illustrative examples of the application of the present invention show embodiments of a jet aircraft with shortened or vertical take-off and landing. The drawings show:

in FIG. 1 - section A1-A1 for jet engines, for example turbofan engines, with round output nozzles with ISWT to change the direction of the flowing jet of engines for the possibility of creating a stable total balanced power reactive moment Mr relative to the center of gravity of the aircraft in the mode of lifting, hovering and landing;

in FIG. 2 - section A2-A2 for jet engines, for example turbofan engines, with round output nozzles with IMWT and with sections of circular or rotary wings with a variable profile located above the output nozzles with IMWT to change the direction of the outflowing jet of engines to create a stable total balanced power jet the moment Mr relative to the center of gravity of the aircraft in the mode of lifting, hovering and landing;

in FIG. 3 - section A3-A3 for jet engines, for example turbofan engines, with round output nozzles and with sections of circular or rotary wings with a variable profile located above the output nozzles to change the direction of the flowing jet of engines to create a stable total balanced power reactive moment M relative to the center the weight of the aircraft in the mode of lifting, hovering and landing;

in FIG. 4 - section A4-A4 on jet engines, for example turbofan engines, with flat output nozzles with ISWT to change the direction of the flowing jet of engines for the possibility of creating a stable total balanced reactive torque Mp relative to the center of gravity of the aircraft in the mode of lifting, hovering and landing;

in FIG. 5 - section A5-A5 for jet engines, for example turbofan engines, with flat output nozzles with IMWT and with sections of circular or rotary wings with a variable profile located above the output nozzles with IMWT to change the direction of the outgoing jet of engines to create a stable total balanced power jet the moment Mr relative to the center of gravity of the aircraft in the mode of lifting, hovering and landing;

in FIG. 6 - section A6-A6 for jet engines, for example turbofan engines, with flat output nozzles and sections of circular or rotary wings with a variable profile located above the output nozzles to change the direction of the flowing jet of engines to create a stable total balanced power reactive moment M relative to the center the weight of the aircraft in the mode of lifting, hovering and landing;

in FIG. 7 is a layout diagram of a jet plane in terms of vertical lift, hover and landing mode, including a control cabin, a disk-shaped fuselage, wings of a straight arrow-shaped shape, mechanization elements of wings and plumage, a jet power plant, while a jet power plant consists of three turbofan engines with round output nozzles with ISWT located around the perimeter of the disk-shaped fuselage on the annular supporting guides, while for the possibility of creating a stable total balanced th reactive torque relative to the aircraft center of gravity in the lifting mode, hovering and landing median axis bases ISVT nozzles arranged radially at an angle of 120 degrees;

in FIG. 8 - the same as in FIG. 7, with the location of the turbofan engines with round output nozzles with ISWT in the horizontal flight mode;

in FIG. 9 is a layout diagram of a jet plane in terms of vertical lift, hover and landing mode, including a control cabin, a disk-shaped fuselage, wings of a straight arrow-shaped shape, mechanization elements of wings and plumage, a jet power plant, while a jet power plant consists of three turbofan engines with paired round output nozzles with ISWT located around the perimeter of the disk-shaped fuselage on the annular support rails, while for the possibility of creating a stable total equilibrium reactive moment relative to the center of gravity of the aircraft in the mode of lifting, hovering and landing of the aircraft, the middle axes of the bases of the twin circular nozzles with ISWT are located radially at an angle of 120 degrees

in FIG. 10 - same as in FIG. 9, with the location of the turbofan engines with round twin output nozzles with ISWT in horizontal flight mode;

in FIG. 11 is a layout diagram of a jet plane in terms of vertical lift, hover and landing mode, including a control cabin, a disk-shaped fuselage, wings of a straight arrow-shaped shape, mechanization elements of wings and plumage, a jet power plant, while a jet power plant consists of three turbofan engines with flat output nozzles with ISWT located along the perimeter of the disk-shaped fuselage on the annular supporting guides, while for the possibility of creating a stable total balanced of the reactive moment relative to the center of gravity of the aircraft in the mode of lifting, hovering and landing of the aircraft, the middle axes of the bases of the flat nozzles with ISWT are located radially at an angle of 120 degrees;

in FIG. 12 - same as in FIG. 11, with the location of the turbofan engines with flat output nozzles with ISWT in the horizontal flight mode;

in FIG. 13 is a layout diagram of a jet plane in terms of vertical lift, hover and landing mode including a control cabin, fuselage, straight arrow-shaped wings, wing mechanization and plumage mechanization elements, a reactive power plant, an air intake system, while the reactive power plant consists of a central axial marching jet engine, while the jet engine has six round or flat pairwise located output nozzles with ISWT, while for the possibility of creating a stable of the total balanced force reactive moment relative to the center of gravity of the aircraft, in the mode of lifting, hovering and landing of the aircraft, all the bases of the nozzles with the ISWT are located on the perimeter of the disk-shaped fuselage, while the middle axes of the bases of the paired nozzles with the ISVT are radially at an angle of 120 degrees;

in FIG. 14 - same as in FIG. 13 in horizontal flight mode;

in FIG. 15 is a layout diagram of a jet plane in terms of vertical lift, hover and landing mode, including a control cabin, a disk-shaped fuselage, three sections of rotary wings with mechanization elements to change the direction of the flowing jet of engines, each section of the rotary wing coaxially combined into a single unit with a turbofan engine with round or flat exit nozzles, while the combined blocks of sections of the rotary wings with jet engines of the turbofan engine are located on the perimeter in the case of a disk-shaped fuselage on annular support guides, while for the possibility of creating a stable total balanced power reactive moment Mr relative to the center of gravity of the aircraft in the mode of lifting, hovering and landing of the aircraft, the middle axes of the nozzle bases of the jet engines of the turbofan engines along with sections of the rotary wings are located radially at an angle of 120 degrees ;

in FIG. 16 - same as in FIG. 15, with the location of the turbofan engines and sections of the rotary wings in the horizontal flight mode;

in FIG. 17 is a layout diagram of a jet plane in terms of vertical lift, hover and landing mode, comprising a cigar-shaped fuselage, two sections of rotary wings with mechanization elements for changing the direction of the outgoing jet of engines, each section of the rotary wing coaxially combined into a single block with a jet turbofan engine with round or flat output nozzles, which are located on horizontal consoles with a rotary platform in front of the fuselage for the possibility of joint rotation of the two front turbofan engines and sections of the front rotary wings, and two rear jet engines of the turbofan engine, located under the side straight wings in the rear of the fuselage, in order to create a stable total balanced force reactive moment Mr relative to the center of gravity of the aircraft in the lift, hover and aircraft landing, the mid-axis of the bases of the nozzles of the jet engines of the turbofan engines, together with sections of the rotary wings, are radially in three directions;

in FIG. 18 is the same as in FIG. 17, with the location of the turbofan engines and sections of the rotary wings in the horizontal flight mode;

in FIG. 19 - in the mode of vertical lifting, hovering and landing, the layout of the aircraft with a shortened or vertical take-off and landing in plan with a disk-shaped fuselage, with three rotary jet engines of the turbofan engine located on the annular fuselage support rails is shown, while above the rotary jet engine of the turbofan engine is provided closed circular wing with mechanization elements to change the direction of the outgoing jet of engines, while in the vertical lift, hover and landing the resulting traction forces from the jet engines of the turbofan engine are directed radially in three directions at an angle of 120 degrees, in order to create a stable total balanced reactive torque Mp relative to the center of gravity of the aircraft;

in FIG. 20 - same as in FIG. 19, with the location of the turbofan engines in horizontal flight mode;

in FIG. 21 is a layout diagram of a jet plane in terms of vertical lift, hover and landing mode including a control cabin, fuselage, wings, wing mechanization and tail components, a jet power plant, an air intake system, while the jet power plant consists of a central axial marching jet engine at this jet engine has six round or flat output nozzles, while for the possibility of creating a stable total balanced power jet m ment relative to the center of gravity of the aircraft, in the mode of lifting, hovering and landing of the aircraft, all the nozzle bases are located on the perimeter of the disk-shaped fuselage, while the middle axes of the bases of the twin nozzles are located radially at an angle of 120 degrees, in addition, sections of circular wings with variable profile to change the direction of the flowing jet of engines. The main wings for horizontal flight are telescopic in the form of a regular shamrock with axes at an angle of 120 degrees, which are smoothly mated with a disk-shaped fuselage;

in FIG. 22 - same as in FIG. 21 in horizontal flight mode.

In the drawings, the positions indicated:

1 - disk-shaped fuselage;

2 - cigar-shaped fuselage;

3 - wing;

4 - telescopic wing;

5 - wing with mechanization elements for changing the direction of the flowing jet of engines of turbofan engines;

6 - rotary wing with elements of mechanization for changing the direction of the outflowing jet of engines of turbofan engines;

7 - an annular wing with mechanization elements for changing the direction of the outflowing jet of engines of turbofan engines;

8 - wing of the front stabilizer;

9 - tail unit;

10 - elements of the mechanization of the wing for changing the direction of the flowing jet of engines of turbofan engines;

11 - central march jet engine turbofan engine;

12 - single jet engine turbofan engine;

13 - a rotary platform on a horizontal console in front of the fuselage, for a cigar-shaped fuselage, for rotating sections of rotary wings and turbofan engines around a vertical axis;

14 - annular supporting guides, for a disk-shaped fuselage, for turning sections of the rotary wings and jet engines of the turbofan engine around a vertical axis;

15 - a jet engine nozzle round with a variable power thrust vector (ISWT);

16 - jet engine nozzle flat with variable power thrust vector (ISWT);

17 - a jet engine nozzle round with a variable maneuverable thrust vector (IMWT);

18 - a jet engine nozzle flat with a variable maneuverable thrust vector (IMWT);

19 - a jet engine nozzle round with an unchanged thrust vector (NVT);

20 - a jet engine nozzle flat with an unchanged thrust vector (NVT);

Mr - jet moment from the flowing jet of engines relative to the center of gravity of the aircraft in the mode of lifting, hovering and landing of the aircraft.

Claims (3)

1. A jet aircraft with a shortened or vertical take-off and landing, including a control cabin, fuselage, wings, wing and tail mechanization elements, a jet power plant, an air intake system, an integrated aircraft control system, characterized in that the power plant consists of one or a group of single jet engines that have output nozzles with a variable thrust vector (ISWT), while to create a stable total balanced reactive moment relative Tel'nykh aircraft center of gravity in vertical lifting mode, hovering and landing base ISVT all nozzles with jet engines disposed on the circumference of the disc-shaped fuselage, the median axis bases of single or groups of nozzles with ISVT arranged radially in at least three directions. 2. A jet aircraft with a shortened or vertical take-off and landing, including a control cabin, fuselage, wings, wing and tail mechanization elements, a jet power plant, an air intake system, an integrated aircraft control system, characterized in that the power plant consists of one or a group of single jet engines, while for the possibility of creating a stable total balanced power reactive moment relative to the center of gravity of the aircraft in vertical lift mode a, hovering and landing of the aircraft, the middle axes of the bases of single or groups of nozzles are located radially in at least three directions, in addition, wing sections with a variable profile are provided above the output nozzles of the jet engines to change the direction of the outgoing jet of the engines. 3. A jet aircraft with a shortened or vertical take-off and landing according to claim 2, characterized in that all jet engines have nozzles with a variable maneuverable thrust vector.

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