RU2689065C1 - Method of flying an aircraft on a difficult-predictable and low-vulnerability trajectory in a zone of possible damage by guided missiles, as well as an aircraft required for realizing said method - Google Patents

Abstract

FIELD: aviation.SUBSTANCE: invention relates to aircraft engineering, particularly, to highly maneuverable aircraft with jet engines. Method of flying an aircraft with an integrated control system on a difficult-predictable and low-vulnerability trajectory consists in that in maneuvering mode to change the position of the aircraft in space, coordinated emission of the jet from nozzles with CTV, spatial action of vertical reactive moments, as well as axial traction forces on aircraft, which leads to abrupt change of flight trajectory on height, along horizontal and diagonal, in plane across direction of longitudinal flight of aircraft. Jet high maneuverable aircraft includes fuselage, wings with elements of mechanization, control system, power plant of jet engines with outlet nozzles located on perimeter of disk-like fuselage or on lateral arms of fuselage. On lateral sides of fuselage front part jet engines are located with possibility of rotation around vertical axis and change of thrust vector (CTV). Mid-flight engine in the tail part of the fuselage has a central nozzle and one or a group of side nozzles with CTV.EFFECT: higher maneuverability of high-speed aircraft.2 cl, 44 dwg

Description

The invention relates to the field of aviation, in particular to highly mobile manned or unmanned aerial vehicles with jet engines.

There is a method of maneuvering high-speed unmanned aerial vehicle in the area of possible action of anti-missile and air defense, (RF patent 2634659, the authors EI Zakharov, VV Maltsev, Yu.V. Bogachev, publication 02.11.2017) To implement This method sets the trajectory of mandatory maneuvering in the form of a sequence of individual sections corresponding to a certain duration, a certain distance and the direction of escape from a lesion, calculated in a certain way. It is necessary to recognize the proposed approach to defining the trajectory of the movement of the aircraft in the zone of possible destruction by means of missile defense and air defense. At the same time, in this method there are no examples of technical execution for the implementation of the movement of the aircraft along an invulnerable path.

Known jet aircraft with a shortened or vertical take-off and landing which includes a control cabin, fuselage, wings, elements of mechanization of wings and tail, jet propulsion system, air intake system, integrated control system of the aircraft, the power plant consists of jet engines. (Application for the invention N 2016117529, author Soushentsev B.N., published 10.11.2017) In the first version, jet engines have output nozzles with a variable power thrust vector (GIB), while being able to create a stable total balancing reactive moment relative to the center the gravity of the aircraft in the mode of vertical lifting, hovering and landing of the base of the nozzles with the jet propulsion jet engines are located on the perimeter of the disc-shaped fuselage, while the median axes of the bases of the single or group of nozzles with the jet guns to at least in three directions. In the second variant of creating a stable total balancing reactive moment relative to the center of gravity of the aircraft in the mode of vertical take-off, hang-up and landing, the median axes of the bases of single or nozzle groups are radially in three directions, with sections of rotary or rotary wings and variable profile above the output nozzles of jet engines to change the direction of the outgoing jet stream of engines. It should be noted that the possibility of creating efforts with alternating vertical jet moments on the perimeter of the disc-shaped fuselage, with a combination of axial traction forces, creates a spatial effect for a sharp unpredictable change in the flight path of the aircraft. The aim of the present invention is to improve the controllability and increase the maneuverability of a high-speed aircraft. This goal is achieved in the method of flight of an aircraft with an integrated control system along an unpredictable and low-vulnerability trajectory, in which one or several jet engines with exhaust nozzles are used in at least three directions relative to the center of gravity of the aircraft with variable thrust vectoring (ICT). perimeter of the disc-shaped fuselage, or on the side bearing consoles of the cigar-shaped fuselage, which consists in the fact that, in the low-vulnerability mode, for I unpredictable changes in the position of the aircraft in space by consistently emitting a jet from nozzles with an IHT create a spatial effect of vertical jet moments, as well as axial traction forces on the aircraft, which leads to a dramatic change in flight path in height, horizontally and diagonally, in the plane across the direction of the longitudinal flight of the aircraft. In addition, the achievement of this goal is implemented in a jet aircraft that includes the fuselage, wings with elements of mechanization, an integrated control system, a power plant made of rocket engines with output nozzles located on the perimeter of the disc-shaped fuselage, or on the side bearing consoles of the cigar-shaped fuselage, while on the sides the front of the fuselage are jet engines that can be rotated around a vertical axis, while the nozzles on the side jet engines x have a variable thrust vectoring (ICT), while the jet aircraft has one or two cruise jet engines in the rear fuselage, with each cruise engine having a central sustainer nozzle and one or a group of side nozzles with ICT, with this mode of low-vulnerability maneuvering, for unpredictable changes in the position of the aircraft in space by coordinated emission of a jet from the nozzles of side jet engines with ICT, as well as from the side nozzles with ICT from cruising jet engines This creates a spatial effect of vertical jet moments, as well as axial traction forces on the aircraft, which leads to a dramatic change in flight path along the height, horizontally and diagonally, in a plane across the direction of the longitudinal flight of the aircraft. On the submitted drawings positions indicated:

pos. 1 - fuselage disk-shaped streamlined shape;

pos. 2 - propulsion jet propulsion engine;

pos. 3 - side jet engine TRDTs with a nozzle with an IHT;

pos. 4 - sustaining nozzle in the rear fuselage;

pos. 5 - lateral nozzle of a propulsion jet engine of a turbofan with an ICT;

pos. 6 - the rotary part of the nozzle to change the thrust vector in the form of a two-row arrangement of the rotary planes with a slit arrangement between them;

pos. 7 - the rotary part of the nozzle to change the thrust vector in the form of a transformable multi-wing;

pos. 8 - the main profile of a multi-wing;

pos. 9 - retractable wing flaps of a multi-wing wing;

pos. 10 - retractable wing wings of a multi-wing wing;

pos. 11 - the rotary part of the nozzle to change the thrust vector in the form of hinged rotary planes;

pos. 12 - rotary platform for a side jet engine with nozzles with a computer-generated transformer;

pos. 13 - supporting supporting circular console;

pos. 14 - bearing wing console;

pos. 15- front stabilizer wing;

Mp ^Z - designation of the direction of the vertical reactive moment from the outgoing jet of engines relative to the center of gravity of the aircraft.

The illustrative examples of the present invention show variants of aircraft with an integrated control system for implementing the method of flight along a hard-to-predict and low-vulnerability trajectory:

in fig. 1 is a layout diagram of a jet plane in terms of vertical lifting, freezing and landing, including a control cabin, a disk-shaped fuselage, straight-winged wings, elements of wing mechanization and empennage, a jet propulsion unit, and the jet propulsion unit consists of two main propulsion engines for turbofan engines and two side jet engines for turbofan engines located on the perimeter of the disc-shaped fuselage on rotary platforms, while the main engines are equipped with a central sustainer nozzle and side oplom with the VPI, the lateral thrusters turbofan disposed along the perimeter of the disc-shaped fuselage provided with nozzles with VPI, the creation of a stable aggregate balanced vertical reaction moment provided outflowing jet from the nozzles with VPI two side jet turbofan disposed on the circumference of the disc-shaped fuselage, as well as two side nozzles with ICT of the central propulsion engines for turbofan engines in the rear fuselage;

in fig. 2 is a layout diagram of a jet plane in the plan of FIG. 1 in the mode of the start of horizontal flight and set speed;

in fig. 3 is a layout diagram of a jet plane in the plan of FIG. 1 in cruising horizontal flight mode;

in fig. 4 is a layout diagram of a jet plane in the plan of FIG. 1 in the mode of unpredictable change in the position of the aircraft in space by coordinated emission of a jet from the nozzles with ICT, this creates a spatial effect of vertical jet moments, as well as axial traction forces on the aircraft, which leads to an abrupt change in flight path along the horizontal and diagonally, in a plane across the direction of the longitudinal flight of the aircraft;

in fig. 5 is a layout diagram of a jet plane in terms of vertical lifting, freezing and landing, including a control cabin, a disk-shaped fuselage, straight-winged wings, elements of wing mechanization and tail assembly, a jet propulsion unit, and the jet propulsion unit consists of a central propulsion turbojet engine and two lateral rotary jet engines for turbofan engines located on the perimeter of the disc-shaped fuselage on the supporting support circular console, while the main engines are equipped with central main jet nozzle and side nozzles with ICT, while side turret jet engines of turbofan engines located along the perimeter of the disc-shaped fuselage are equipped with jet nozzles with ICT, while creating a stable total balanced vertical reactive moment is provided by flowing jets of nozzles with ICT of two side jet engines of the turbofan engine disc-shaped fuselage, as well as from two side nozzles with an IHT of a central propulsion engine for turbofan engines in the rear fuselage;

in fig. 6 is a layout diagram of a jet plane in the plan of FIG. 5 in the mode of the start of horizontal flight and set speed;

in fig. 7 is a layout diagram of a jet plane in the plan of FIG. 5 in the mode of cruising horizontal flight;

in fig. 8 is a layout diagram of a jet plane in the plan of FIG. 5 in the mode of unpredictable change in the position of the aircraft in space by coordinated emission of a jet from the nozzles with ICT, this creates a spatial effect of vertical jet moments, as well as axial traction forces on the aircraft, which leads to an abrupt change in flight path along the horizontal and diagonally, in a plane across the direction of the longitudinal flight of the aircraft;

in fig. 9, 10 - examples of unpredictable changes in the position of the aircraft in space in the plane across the direction of the longitudinal flight of the aircraft;

in fig. 11 - section A1-A1 for jet propulsion turbojet engines on side nozzles with ICT in the mode of creating a lifting vertical reactive moment, while the rotary part of the nozzle to change the thrust vector is in the form of a two-row arrangement of the rotary planes with a slot arrangement between them;

in fig. 12 - section A2-A2 for jet propulsion turbojet engines for side nozzles with ICT in the mode of creating axial thrust, while the rotary part of the nozzle to change the thrust vector is made in the form of a two-row arrangement of the rotary planes with a slit arrangement between them;

in fig. 13 - section A3-A3 for jet propulsion engines of turbofan engines along side nozzles with ICT in the creation mode of reducing vertical reactive torque, while the rotary part of the nozzle for changing the thrust vector is in the form of a two-row arrangement of the rotary planes with a slot arrangement between them;

in fig. 14 - section A4-A4 for jet propulsion jet engines for turbofan engines for a propulsion jet;

in fig. 15 - section B1-B1 along side jet engines of turbofan engines with nozzles with ICT located on the perimeter of the disc-shaped fuselage in the mode of lifting vertical reactive moment, while the rotary part of the nozzle to change the thrust vector is in the form of a two-row arrangement of the rotary planes;

in fig. 16, 17 - section B2-B2, section B3-B3 along side jet engines of turbofan engines through nozzles with ICDs located on the perimeter of the disc-shaped fuselage in the mode of creating axial thrust, while the rotary part of the nozzle for changing the thrust vector is in the form of a two-row arrangement of rotary planes with gap location among themselves;

in fig. 18 - section B4-B4 along side jet engines of turbofan engines with nozzles with ICT located on the perimeter of the disc-shaped fuselage in the mode of creating a lower vertical reactive moment, while the turning part of the nozzle to change the thrust vector is in the form of a two-row arrangement of the rotary planes with a slit arrangement between them;

in fig. 19, 20 - section B5-B5, B6-B6 along side jet engines of turbofan engines through nozzles with ICTs located on the perimeter of the disc-shaped fuselage in the mode of creating axial traction force at a diagonal reduction of the aircraft in the plane perpendicular to the direction of the longitudinal flight of the aircraft, with the turning part nozzles for changing the thrust vector are made in the form of a two-row arrangement of rotary planes with a slot arrangement between them;

in fig. 21, 22 - section B7-B7, B8-B8 along side jet engines of turbofan engines through nozzles with ICDs located on the perimeter of the disc-shaped fuselage in the mode of creating axial traction force with a diagonal lift of the aircraft in the plane perpendicular to the direction of the longitudinal flight of the aircraft, with the turning part nozzles for changing the thrust vector are made in the form of a two-row arrangement of rotary planes with a slot arrangement between them;

in fig. 23 - section A5-A5 for jet propulsion thrusters of turbofan engines along side nozzles with ICT in the mode of creating a lifting vertical reactive moment, while the rotary part of the nozzle to change the thrust vector is in the form of a transformable multi-wing;

in fig. 24 - section A6-A6 for jet propulsion turbojet engines on side nozzles with IWT in the mode of creating axial thrust, while the rotary part of the nozzle for changing the thrust vector is made in the form of a transformable multi-wing;

in fig. 25 - section A7-A7 for jet propulsion thrusters of turbofan engines along side nozzles with ICT in the mode of creating a lower vertical reactive torque, while the rotary part of the nozzle to change the thrust vector is in the form of a transformable multi-wing;

in fig. 26 is a section of C1-C1 along side jet engines for turbofan engines with nozzles with ICTs located on the perimeter of a disc-shaped fuselage in the mode of raising the vertical reactive torque, while the rotary part of the nozzle to change the thrust vector is in the form of a transformable multi-wing;

in fig. 27, 28 - section C2-C2, section C3-C3 along side jet engines of turbofan engines through nozzles with ICTs located on the perimeter of the disc-shaped fuselage in the mode of creating axial thrust, while the rotary part of the nozzle to change the thrust vector is in the form of a transformable multi-wing wing;

in fig. 29 - section C4-C4 along side jet engines for turbofan engines with nozzles with ICTs located on the perimeter of the disc-shaped fuselage in the mode of reducing vertical reactive torque, while the rotary part of the nozzle to change the thrust vector is in the form of a transformable multi-wing;

in fig. 30, 31 - section C5-C5, C6-C6 along side jet engines of turbofan engines through nozzles with ICDs located on the perimeter of the disc-shaped fuselage in the mode of creating axial traction force at a diagonal reduction of the aircraft in the plane perpendicular to the direction of the longitudinal flight of the aircraft, with the turning part nozzles to change the thrust vector is made in the form of a transformable multi-wing;

in fig. 32, 33 - section C7-C7, C8-C8 along side jet engines of turbofan engines through nozzles with ICTs located on the perimeter of the disc-shaped fuselage in the mode of creating axial traction force with a diagonal lift of the aircraft in the plane perpendicular to the direction of the longitudinal flight of the aircraft, with the turning part nozzles to change the thrust vector is made in the form of a transformable multi-wing;

in fig. 34 - section A8-A8 for jet propulsion thrusters of turbofan engines along side nozzles with ICT in the mode of creating a lifting vertical reactive moment, while the rotary part of the nozzle for changing the thrust vector is in the form of hinged rotary planes;

in fig. 35 - section A9-A9 along jet propulsion engines for turbofan engines along side nozzles with IWT in the mode of creating axial thrust, while the rotary part of the nozzle for changing the thrust vector is made in the form of hinged rotary planes; on

FIG. 36 - section A10-A10 for jet propulsion turbojet engines for side nozzles with ICT in the creation mode of reducing vertical reactive torque, while the rotary part of the nozzle for changing the thrust vector is in the form of hinged rotary planes;

in fig. 37 - section D1-D1 along side jet engines of turbofan engines with nozzles with ICT located on the perimeter of the disc-shaped fuselage in the mode of lifting vertical reactive torque, while the rotary part of the nozzle to change the thrust vector is in the form of hinged rotary planes;

in fig. 38, 39 - section D2-D2, section D3-D3 along side jet engines of turbofan engines through nozzles with ICT located on the perimeter of the disc-shaped fuselage in the mode of creating axial thrust, while the rotary part of the nozzle to change the thrust vector is in the form of hinged rotary planes;

in fig. 40 - section D4-D4 along side jet engines of turbofan engines with nozzles with ICT located on the perimeter of the disc-shaped fuselage in the mode of creating a lower vertical reactive torque, while the rotary part of the nozzle to change the thrust vector is in the form of hinged rotary planes;

in fig. 41, 42 - section D5-D5, D6-D6 along side jet engines of turbofan engines through nozzles with ICDs located on the perimeter of the disc-shaped fuselage in the mode of creating axial thrust with a diagonal reduction of the aircraft in the plane perpendicular to the direction of the longitudinal flight of the aircraft, with the turning part nozzles for changing the thrust vector are made in the form of hinged rotary planes;

in fig. 43, 44 - section D7-D7, D8-D8 along side jet engines of turbofan engines through nozzles with ICTs located on the perimeter of the disc-shaped fuselage in the mode of creating axial thrust force with a diagonal lift of the aircraft in the plane perpendicular to the direction of the longitudinal flight of the aircraft, with the turning part nozzle to change the thrust vector is made in the form of articulated swivel planes.

Claims (2)

1. The method of flying an aircraft with an integrated control system along an unpredictable and low-vulnerability trajectory, in which one or several jet engines with exhaust nozzles are used in at least three directions relative to the center of gravity of the aircraft with variable thrust vectoring (ICT) that are located on the perimeter of the disc-shaped fuselage or on the side bearing consoles of the cigar-shaped fuselage, which consists in the fact that in the mode of low-vulnerability maneuvering for unpredictable change The position of the aircraft in space by coordinated emission of a jet from the nozzles with the ICT creates a spatial effect of the vertical jet moments, as well as axial thrust forces on the aircraft, which leads to a sharp change in flight path along the height, horizontally and diagonally, in a plane across the direction of the longitudinal flight of the aircraft. 2. Reactive highly maneuverable aircraft, including the fuselage, wings with elements of mechanization, integrated control system, power plant of rocket engines with output nozzles located on the perimeter of the disc-shaped fuselage or on the side bearing consoles of the cigar-shaped fuselage, characterized by the fact that on the sides of the front part fuselage jet engines are located with the possibility of rotation around the vertical axis, while the nozzles on the side jet engines have a variable vector t Yagis (ICT), while the jet aircraft has one or two cruise jet engines in the rear fuselage, each marching engine has a central sustaining nozzle and one or a group of side nozzles with ICT, while in the mode of low-vulnerable maneuvering for an unpredictable change of position the aircraft in space by coordinated emission of a jet from the nozzles of side jet engines with IHT, as well as from the side nozzles with IHT of the jet propulsion engines governmental impact of vertical jet moments and axial thrust forces on the aircraft, which leads to a sharp change in the trajectory of the flight height, horizontally and diagonally, in a plane transverse to the longitudinal direction of flight of the aircraft.

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