RU2736530C1 - Strategic aviation trans-arctic system - Google Patents

Abstract

FIELD: military equipment.

SUBSTANCE: invention relates to military equipment. Strategic aviation trans-Arctic system contains optional and remotely manned convertiplane-missile carriers with bidirectional wing with double-sided symmetry in two perpendicular planes. Wing is mounted on pivot hinge of underwing fuselage-nacelle, in which combined gas turbine engines with free power turbines, leading two transverse lifting fans (LF), and/or in cowlings, two turbofans creating at vertical and short take-off/landing lifting and/or propulsive-thrust rod with operating or fixed LF with automatically open/closed upper longitudinal flaps and lower transverse louvered rudders of wing annular fairings in configuration of jet airplanes when performing short take-off/landing and horizontal flight. Convertiplane-missile carriers used from aircraft-carrying ice breaker carry guided missiles.

EFFECT: higher probability of destruction of surface or ground target located at long range.

4 cl, 1 dwg, 1 tbl

Description

The invention relates to aviation transarctic systems with optionally and remotely piloted tiltrotor-missile carriers having a bi-directional wing with bilateral symmetry in two perpendicular planes, mounted on a pivot hinge of the underwing fuselage-nacelle with two combined gas turbine engines and free power turbines (driving) and in the annular fairings, two turbofans, creating during vertical and short takeoff / landing (GDP and KVP) lifting and / or propulsion-jet thrust with working / fixed PV with automatically open / closed transverse upper louvres and lower louvers-rudders wing annular fairings in the configuration of jet aircraft when performing GDP, KVP / level flight, carrying guided missiles, used from a nuclear-powered aircraft carrier icebreaker.

Known complex for the destruction of submarines (PL) at long ranges, patent RU 2371668 C2, made in the form of a ballistic missile (BR), in the nose of which under the dropped fairing is placed a cruise missile (CR); BR contains aerodynamic surfaces with drives and an accelerating engine to ensure the delivery of the missile launcher at a firing range to the target area. For economical flight in the atmosphere, the RR is docked with the accelerating engine by means of a separation device, is made with the possibility of flight in the area of the target submarine and contains a detachable underwater warhead (CU) and a detachable hydroacoustic buoy; the control system of the RV is equipped with equipment for receiving information from a hydroacoustic buoy via a radio channel about the location of the target. In accordance with the teams searching for the target, its detection, approaching the target and its defeat by detonating the warhead. After that, the BR-carrier continues its flight with the engine running, taking it away from the landing site of the underwater warhead so as not to interfere with its homing system. The very same single-use ballistic missile left the area of the splashdown of the warhead and self-destructed.

Known unmanned aircraft of the project "X-plane" of the company "Northrop Grumman" (USA) [http://test.abovetopsecret.com/forum/thread398541/pg1], made according to the scheme of a flying wing of an asymmetrically variable sweep (KAIS), has two turbojets two-circuit engine (turbojet engine) in a nacelle with internal bomb bays and a tricycle retractable wheel chassis. For supersonic flight "X-plane" its General Electric J85-21 turbojet engine have a jet thrust of 4485 kgf, which at a flight altitude of 11 km provides a speed of 1275/1488 km / h with a thrust-to-weight ratio of 0.54 / 0.68. Known aircraft with KAIS have a number of disadvantages, the main of which are: displacement of the aerodynamic focus at multidirectional sweep, which leads to an increase in balancing resistance; an increase in the mass of the structure due to the presence of swivel joints of the consoles. In addition, at a large 45 ° sweep angle, a straight swept cantilever has a larger effective angle of attack than a reverse swept cantilever, which leads to an asymmetry of the drag and, as a consequence, to the appearance of parasitic turning moments in roll, pitch and yaw. Moreover, KAIS is characterized by a twofold increase in the thickness of the boundary layer along the span, and any asymmetric stall of the flow causes intense disturbances, and their elimination can be carried out using a bidirectional wing.

Closest to the proposed invention is a carrier-based aircraft complex (PAK) "Icara" (Great Britain) with an unmanned aerial vehicle (UAV) [http://rbase.new-factoria.ru ^/ missile / wobb / ikara / ikara.shtml], having fuselage, launching device (PU) with a guided missile, wing with its controls, power plant engine (SU), control system providing telemechanical control from the command post of the carrier ship.

Signs that match - the dimensions of the UAV without the ship's launcher: length 3.42 m, wingspan 1.52 m, height 1.57 m. Warhead: homing anti-submarine small-sized torpedo (MGT) Mk.44. Flight characteristics: maximum and minimum flight altitudes, respectively, 300 m and 15-20 m. Due to the significant weight of a UAV with a Mk.44 torpedo, which is 1480 kg (with a mass of 13% of the target load - a torpedo of 196 kg, its length is 2.57 m and a diameter of 324 mm) and short ranges of 24 km and a flight speed of 140-240 m / s, and a warhead (torpedoes - 30 knots and a cruising range of 5 km).

The reasons that impede the task: the first is that the launch of the subsonic UAV was carried out in the direction as close as possible to the target of the dropped torpedo. Target location data came from the sonar system (GAS) of a surface carrier ship, another ship, or an anti-submarine helicopter. Based on this information, the data on the optimal torpedo drop zone is constantly updated in the fire control system computer, which then transmitted them through the radio command control system to the UAV in flight. Upon arrival of the UAV in the target area, the torpedo (self-guided MGT Mk.44), semi-drowned with its ventral position in the UAV hull, separated by radio command, descended by parachute, entered the water and began to search for the target. After that, the UAV continues its flight with a working control system, taking it away from the splashdown site of the homing MGT so as not to interfere with its homing system. The disposable UAV itself left the area and self-destructed.

The proposed invention solves the problem in the above-mentioned known British PAK model "Icara" to increase the target load (CP) and weight recoil, increase the speed and range of flight, as well as the probability of hitting a surface or ground target located at a long distance, but also returning to the helipad nuclear aircraft carrier icebreaker (ANL) for reuse.

Distinctive features of the proposed invention from the above-mentioned known British PAK model "Icara", which is closest to it, are the presence of the fact that the strategic aviation transarctic system (ATAS) has a group of ship-based vertical take-off and landing (VLT) vehicles, including more than one optionally a manned missile carrier tiltrotor (OPKR) with more than one remotely piloted missile carrier (DPKR) tiltrotor, used from more than one helipad of an atomic ANL, and each DPKR and OPKR is made according to a hybrid layout, with at least one bidirectional wing (DNA ), having bilateral symmetry in two perpendicular planes and in any of two positions at 90 °, equal or different in span trapezoidal and rhomboid consoles, respectively, with their rounded and triangular tips, integrated with the underwing fuselage-nacelle (PFG) and its hinge, providing follower mechanism and from the initial position along the symmetry axis in the plan of the rhomboid DNA consoles, their rotation in the horizontal plane at an angle of 90 ° counterclockwise or backward so that the trapezoidal / rhomboid and rhomboid / trapezoidal DNA consoles are set in the plan, respectively, along the / axis perpendicular to the symmetry axis , are fixed in the last position, for example, trapezoidal large / diamond-shaped smaller DNA consoles with their corresponding lengthening λ = 3.3 ... 4.3λ = 2.5, but also contains a multi-fan transverse supporting system (MPS) on the trapezoidal DNA consoles, which is used for its installation with these consoles perpendicular to the plane of symmetry in transient and accelerating flight modes, performing runoff, short takeoff and landing or vertical landing (KVP or KVVP), but also including at least two lifting fans (PV), equidistant in plan from the center of gravity, mounted in wing annular fairings (KKO), having automatically opened / closed transverse as upper shutters-shutters and lower shutters-rudders, which provide free access of air to the corresponding CCOs and the exit from them of the air flow that does not blow over the PFG, and after they are closed back along the flight, the corresponding DNA surfaces, but is also equipped with at least two combined gas turbine engines (KGTD), mounted in the stern of the PFG, are equipped with side air intakes and round nozzles with all-course thrust vector control (VUVT) and are made in the form of bypass jet engines with a single-row turbofan (OTV) in an annular fairing (KO) and more than one free power turbine (SST), transmitting the takeoff power of the CS to the corresponding PS in the KCO and / or OTS in the KO, creating synchronous jet thrust in the propulsive-reactive system (PRS) when performing the GDP, KVP and KVVP or horizontal translational flight, but and is configured to convert its flight configuration after performing a vertical or short takeoff that from a corresponding aircraft with a gas turbine engine, for example, in the MPNS-X2, a pair of PV and / or two OTVs in a PRS-R2, creating a lifting and / or propulsive-jet thrust with working / fixed PV with automatically open / closed upper flaps and the lower louvers-rudders of their KKO in the configuration of jet supersonic or transonic aircraft, respectively, at normal or maximum takeoff weight, but also vice versa, while in the transmission system each of its KGTD is placed in the PFG aft nacelle, in which between the OTV and SST it is mounted coaxially with the last two are a T-shaped gearbox in plan, having input shafts longitudinal along its axis, for example, from two SST, but also longitudinal and transverse output shafts, the first of which transfers power through the clutch to the OTV, and the second synchronizing shaft transfers torque to The main gearbox is T-shaped in plan, the output shaft of which is rotationally connected through the clutch to the bevel gear, the vertical column of the output shaft of which is Being a rigid axis of the DNA pivot hinge, it is located coaxially with the latter, has a shaft that is rotationally connected through a clutch to a T-shaped gearbox when viewed from behind, transmitting it by output shafts laid inside the trapezoidal DNA consoles and KCO stiffeners, equal power to angle gearboxes PV.

In addition, in the above-mentioned OPKR and DPKR, in order to reduce by 1.8 ... 2.3 times their parking area from the take-off, the end parts of the diamond-shaped DNA consoles are made folding downward with the fixation of the trapezoidal DNA consoles mentioned along the axis of symmetry, and their air flow control system, providing direction from the compressor of each KGTD of supersonic air flows, which in the modes of GDP and hovering to change the balance in pitch are fed to the jet rudders along the longitudinal air ducts to their valves and are blown out alternately from the jet upper or lower aft nozzle (CS) with the corresponding automatic flap open, forming, when it is closed, the corresponding surface of the aft fairing, and in the modes of their GDP and hovering for lifting and changing the balancing both along the roll and the course, the said louvers-rudders, for example, in their left and right KKO, which are installed on the transverse centerline of the mentioned trapezoidal consoles of DNA passing in plan through the center of mass, made with the possibility of a differential deviation from the center of the CCO by angles forward along the flight of -40 ° and backward + 40 ° as alternately in one of the CCOs on one side of their front and rear louvers-rudders, and simultaneously in a pair of CCOs with two sides of the front with rear louvers-rudders, respectively, and in their flight configuration of a jet aircraft, a change in the balance in pitch, heading and roll is created, respectively, by in-phase and differential deviation in two KGTD of their jet nozzles with the mentioned VUVT both vertically up and down, both horizontally to the left - to the right and vertically one up, and the other down, but also an increase in directional stability at a speed of their flight M = 0.7 ... M = 1.4, the end parts of their diamond-shaped consoles, mounted with DNA according to the area rule, deviate downward at an angle of 30 °, moreover, in the modes of GDP and hovering of the OPKR and DPKR with a specific load on the power of their combined CS, which is ρ _N = 1.15 kg / hp, each mentioned SS is made with digital elements th program control, combining the system of adaptive control of the formation of a safe flight (UFBP) with a specific vertical thrust-to-weight ratio, for example, in the MPNS-X2, which, taking into account the losses from blowing the stiffeners of the stiffeners, KCO ρ _VT = 1.15, includes the SST operating modes both takeoff and and emergency mode (BP and PD) when the required power is taken to drive the said PV, respectively, both from four operating SSTs and from three of the operating SSTs with automatic equalization and equal redistribution of the remaining power between the PS in case of failure of the corresponding SST in KGTD, for example, even in the latter case, after the automatic switching on of the PD, the operation of the SST remaining in operation, which, with a specific vertical thrust-to-weight ratio in the MPNS-X2 of ρ _VT = 1.07, will provide an emergency vertical landing mode for 2.5 minutes, and in each of their SST the system UVBP contains: one or more sensors that are configured to detect data related to air flow (G _B , kg / s) through the SST compressor, the gas temperatures ( _TG , K) in front of the SST turbine, the total compression ratio (K) of the compressor, as well as one or more sensors that are configured to detect the relative position and their PFG, and the rotation discs of their PV for their relative position relative to the ground level or the surface of the landing site, as well as various obstacles in the path of their tracking safe descent; a flight control computer located in their BSU and operational with one or more sensors; the flight control computer is configured to: determine the relative position between their PFGs with their wheeled chassis and the ground level or surface of the landing pad; compare the relative position of their PFG and their carrier system with their selected relative position; determine the speed of the controlled descent required to move them to the selected relative position; convert tracker speed to flight control inputs; and also to provide a direct controlled safe descent to the selected relative position through the flight control inputs, while each OPKR and DPKR, made respectively without and with a cockpit, equipped inside with video cameras with autonomous manipulators connected to the OPKR controls and the possibility of its optional control by pilots from the PFG cabins, and the lower bomb bays of their PFGs have internal armament with automatic flaps and their mentioned launchers with air-to-air missiles and aviation cruise missiles (AKR) attached to them, which provide, respectively, the fight against air and ground, surface targets, and their weapons complex has an aircraft cannon installed in the fairing on top of the PFG nose, striking subsonic shock UAVs and AKRs, and their airframe is made of aluminum-lithium alloys and composite materials using an inconspicuous technology with a radio-absorbing coating, moreover, the heavily armed DPKR and OPKR, carrying a jet aircraft configuration air in the bomb bays of their PFG, respectively, AKR type Kh-555 and X101 to create a buffer safe air zone between the head OPKR and air defense targets, increasing the range to 4750/7750 km, respectively, strategic AKR type Kh-555 / Kh-101, forming autonomous swarms of ACRs with towed false targets, and their PFG, having their sides beveled from the pyramidal nose along its entire length, forming with the mentioned air intakes when viewed from the front, its five- or hexagonal cross-section, which reduces the effective scattering area, and their PFG at the end of the tail booms it has either one-piece rotatable keels, deflected up or down and outward from the plane of symmetry at an angle of 47 ° to the horizontal, or a swept stabilizer with end keel washers, forming a U-shaped tail when viewed from the front, and their PFG between the nozzles The KGTD is equipped with a stern fairing with a compartment, extended along its longitudinal axis and from the end, equipped at its end with a retractable towed on the cable with a false target, while the electro-optical sensor (EOD), designed for detecting and identifying the target, has a receiving part of the EOD, which is closed from above with a sapphire glass, is installed at the bottom of the nose of the PFG of the head OPKR and, with the latter's radar, provides on large, safe for OPKR distances, target designation and control of weapons loads OPKR and DPKR with aiming at the target of their air-to-ground missile defense system and their air-to-air missile defense system, and DPKR control is provided by the OPKR co-pilot, using a low-altitude flight profile and a self-defense system DPKR-station of active electronic interference, and the mentioned BSU of the head OPKR, made with a fly-by-wire control system that responds to at least one of the systems of autonomous flight control, remote operator control, pilot control and / or their combination, is equipped with the possibility of its optional control by pilots from the cockpit mounted in their PFG having ejected to the upper floor armchairs, which are triggered automatically when performing GDP and hovering, but also using it as part of an air group as a head with the above-mentioned more than two DPKR, more than one of which, being a slave, automatically repeats it by the autopilot system in tracking flight the maneuvers of the head OPKR, and the other is controlled by the co-pilot from the head OPKR, and then vice versa, and in the absence of pilot intervention, the autopilot system performs flight control of the slave DPKR in accordance with the commands of the current state, repeating the flight profile and changing the route of the head OPKR, while in the event of an emergency situation, then To eliminate unforeseen problems with the safety of the tracking flight, the pilot takes over direct control of the slave DPKR, canceling the current state commands issued by the autopilot during autonomous operation of the tracking flight, and the control system for the formation of a relative position in the tracking flight, containing one or multiple sensors located on the slave DPKR configured to detect data relating to its position relative to the position of the head OPKR having a flight control computer operational with one or more sensors, containing an additional sensor computer that is configured to: determine the relative position between slave DPKR and head OPKR; compare the relative position with the selected relative position; determine the speed of the slave DPKR required to move it to the selected relative position; convert tracker speed to flight control inputs; to restrict the direct movement of the slave DPKR relative to the OPKR, which provides through the inputs of its flight control computer their relative safe position in a joint flight, while each touch computer of the previous and subsequent slave DPKR, configured to perceive acoustic signals, has a memory containing: data representing at least one flight trajectory of the head OPKR and the previous DPKR; data representing at least one profile of their joint flight; program instructions executed by the processor for calculating their group flight in order to execute at least the current flight route and at least its flight profile, and store the current flight in memory; program instructions executed by the processor for the flight of each DPKR in accordance with the current flight profile; multimodal logic executed by the processor to calculate the ability to dynamically adapt to changing conditions or parameters, including the ability to coordinate an air group, distributed tactical control, distributed over the targets of the air group and / or completely, increasing the effectiveness of its attack, are integrated into autonomous strategic swarming.

In addition, in the above-mentioned OPKR and DPKR, the control system for the formation of their relative position in flight with one or more sensors includes one or more infrared (IR) sensors, video sensors, radar, laser and ultrasonic sensors, sonars, global positioning sensors, when the above-mentioned flight control computer is made both with an additional computer for summing sensor data and a data reception and transmission channel located on the head OPKR to obtain global position data from the slave DPKR, and with the possibility of converting images from each video sensor, which ensures the determination of the relative position, which by means of triangulation, it includes the determination of the relative range, azimuth and elevation angle, and the additional computer for summing the sensor data and the data transmission channel has multiband radio frequency equipment with a directional antenna capable of being closed communication, transmit several video streams, ensure the collection of data from each video sensor, and also ensure the conversion of images from each video sensor to a relative position, which is determined based on the global position of the head OPKR transmitted to the slave DPKR, while the data summation computer is fully integrated into the pilot interface and a control system of the OPKR, which provides the mentioned tracking flight of the slave DPKR, which, if necessary, can be disabled by means of one of the inputs of the pilot interface for flight control, activation by the pilot of a button or control switch, and the data summation computer is additionally equipped with the possibility of its independent action, which determines that the flight The OPKR is unsafe for its relative position from the slave DPKR, but also disables the formation of the said tracking flight by the slave DPKR through the flight control computer.

и сужением η_днк=0,53, оснащенными по всему размаху предкрылками и закрылками, имеет упомянутые ромбовидные консоли с относительной толщиной их профиля

а для трансзвукового режима полета с промежуточной под углом 45° к оси симметрии фиксацией их консолей ДНК, преобразуя последнее в двунаправленное крыло асимметрично изменяемой стреловидности, которое при маршевой тяговоуроженности первого уровня - 0,246 или второго - 0,3, используя соответственно 22% или 30% мощность их СУ, обеспечивает на высоте 11 км скорость 0,829 Маха (М) или М=0,942, а для сверхзвукового режима полета с упомянутой фиксацией их трапециевидных консолей ДНК так, что в С-образном при виде сбоку переднем обтекателе ПФГ, размещенном за кабиной в верхней его утонченности, фиксируется законцовка правой его консоли, используя при этом 72% или 100% мощности их СУ, достигается при маршевой тяговоуроженности третьего/четвертого уровня К_мт=0,54/0,68 соответственно сверхзвуковая скорость М=1,2/М=1,4, а планер ОПКР, не имея застекленной поверхности кабины, содержащей средства отображения цифрового изображения, представляющего часть внешней сцены, включающей окружающую среду, простирающуюся вперед и достаточную для пилотирования, оснащен множеством видеокамер, ИК-датчиков и видеодатчиков, обеспечивающих сенсорную съемку, фиксирующими в передней и задней полусферах все события на 360°, при этом изображение проходит цифровую корректировку и для управления в режиме реального времени отображается модулем распределения видео на дисплеях кабины или видны на нашлемных дисплеях пилотов, которые подключены к первому и второму процессорам расширенной системы зрения, сконфигурированы для ношения первым и вторым пилотом соответственно, причем первое и второе общие окна просмотра и выделенные отображенные линии визирования видны на первом и втором нашлемных дисплеях соответственно.In addition, in the mentioned OPSV and DPSV, their DNA with trapezoidal consoles made with a relative thickness of their profile

and a narrowing η _DNA = 0.53, equipped with slats and flaps throughout the span, has the mentioned diamond-shaped consoles with a relative thickness of their profile

and for a transonic flight mode with an intermediate at an angle of 45 ° to the axis of symmetry by fixing their DNA consoles, transforming the latter into a bidirectional wing of asymmetrically variable sweep, which, with a marching thrust yield of the first level - 0.246 or second - 0.3, using respectively 22% or 30% the power of their control system, provides a speed of Mach 0.829 (M) or M = 0.942 at an altitude of 11 km, and for the supersonic flight mode with the above-mentioned fixation of their trapezoidal DNA consoles so that in the C-shaped front fairing PFG placed behind the cockpit its upper refinement, the ending of its right console is fixed, while using 72% or 100% of the power of their control system, is achieved with a marching thrust yield of the third / fourth level K _mt = 0.54 / 0.68, respectively, supersonic speed M = 1.2 / M = 1.4, and the airframe OPKR, without a glazed surface of the cockpit containing means for displaying a digital image representing a part of the external scene, including the environment, stretching forward and sufficient for piloting, equipped with a variety of video cameras, IR sensors and video sensors that provide touch shooting, capturing all events in the front and rear hemispheres 360 °, while the image is digitally corrected and displayed by the video distribution module for real-time control on cockpit displays or visible on helmet displays of pilots that are connected to first and second advanced vision processors configured to be worn by first and second pilots, respectively, with the first and second shared viewports and highlighted displayed lines of sight visible on first and second helmet displays, respectively ...

Due to the presence of these features, which will make it possible to master the strategic ATAS, which has a group of ship-based vertical take-off and landing (VLT) vehicles, including more than one optionally piloted missile carrier tiltrotor (OPKR) with more than one remotely piloted missile carrier (DPKR) tiltrotor, used from more than one helipad of an atomic ANL, and each DPKR and OPKR is made according to a hybrid layout, with at least one bidirectional wing (DNA) having bilateral symmetry in two perpendicular planes and in any of two positions at 90 ° equal or trapezoidal and diamond-shaped consoles of different sizes in scope, respectively, with their rounded and triangular tips, integrated with the underwing fuselage-nacelle (PFG) and its hinge, which provides the follower mechanism from the initial position along the symmetry axis in terms of the diamond-shaped DNA consoles, their rotation in the horizontal plane at an angle 90 ° against or back clockwise so that trapezoidal / diamond-shaped and diamond-shaped / trapezoidal DNA consoles are set in plan, respectively, along the / axis perpendicular to the axis of symmetry, are fixed in the last position, for example, trapezoidal large / diamond-shaped smaller DNA consoles with their corresponding elongation λ = 3.3 ... 4.3λ = 2.5, but also contains on the trapezoidal consoles of DNA a multi-fan transverse carrying system (MPSS), which is used when it is installed with these consoles perpendicular to the plane of symmetry at transient and accelerating flight modes, performing GDP, short takeoff and landing or vertical landing (KVP or KVVP), but also including at least two lifting fans (PV), equidistant in plan from the center of mass, mounted in wing annular fairings (KKO), with automatically opening / closing transverse like upper louvres-flaps and the lower louvers-rudders, providing free access of air to the corresponding KKO and the exit of air from them ka, which does not blow off the PFG, and after they are closed back in flight, the corresponding DNA surfaces, but is also equipped with at least two combined gas turbine engines (CGTD), mounted in the aft part of the PFG, are equipped with side air intakes and round nozzles with all-aspect thrust vector control ( VUVT) and are made in the form of two-circuit jet engines with a single-row turbofan (OTV) in an annular fairing (KO) and more than one free power turbine (SST), which transfers the takeoff power of the CS to the corresponding PS in the KKO and / or OTV in the KO, creating in a propulsive-reactive system (PRS) synchronous jet thrust during the performance of GDP, KVP and KVVP or horizontal translational flight, but also made with the possibility of converting its flight configuration after performing a vertical or short take-off from the corresponding aircraft with KGTD, leading, for example, to the MPS -X2 pair of PV and / or two OTV in PRS-R2, creating a lifting and / or passage lsive-jet thrust with working / fixed PV with automatically open / closed upper flaps and lower louvers-rudders of their KKO in the configuration of jet supersonic or transonic aircraft, respectively, at normal or maximum takeoff weight, but also vice versa, while in the transmission system each of them The KGTD is located in the PFG aft nacelle, in which between the OTV and the SST is mounted coaxially with the last two T-shaped gearbox in plan, having input shafts longitudinal along its axis, for example, from two SST, but also longitudinal and transverse output shafts, the first of which transmits power through the clutch to the OTV, and the second synchronizing shaft transmits torque to the T-shaped main gearbox, the output shaft of which through the clutch is rotationally connected to the angular gearbox, the vertical column of the output shaft of which, being a rigid axis of the DNA pivot joint, is located coaxial with the latter, has a shaft that is rotationally connected through a clutch with a T-shaped when viewed from the rear by a reducer transmitting it by output shafts laid inside the trapezoidal DNA consoles and KKO stiffeners, equal power to the PV angle reducers. All this will make it possible to simplify controllability and ensure its stability in heavily armed OPKR and DPKR with DNA of bilateral symmetry and in the presence of VUVT round jet nozzles of their KGTD. The placement of transverse PV in the KKO trapezoidal consoles of DNA near the center of mass ensures predictability and stability of control during hovering, and equipping the KKO with lower rudder louvers at the exit will simplify control, reduce the weight of the airframe, improve the weight return and increase the flight range of reactive OPKR and DPKR made according unobtrusive technology, but also without the glazed surface of the OPKR cockpit, containing the means of displaying digital images on cockpit displays or on helmet-mounted displays of pilots. The latter increases the likelihood of hitting a target, increases the effectiveness of the use of deck-based OPKR and DPKR, especially during their patrolling transonic flight. In the event of a failure in the combined control system of one of the SSTs in the hovering mode of the reactive OPKR and DPKR, their CGTDs are made with automatic leveling and equal redistribution of the remaining power of the SST between the PS, which increases safety. The use of rotary DNA will make it possible to reduce the aerodynamic drag in the configuration of a jet aircraft and, in non-afterburning modes of the KGTD operation, at an altitude of 11 km, trans- and supersonic speeds, respectively, 1000 km / h and 1275 ... 1488 km / h.

The proposed invention ATAS with reactive OPKR and DPKR having DNA with different-sized consoles, KGTD with VUVT of their jet nozzles, leading to the MPNS-X2 a pair of PV in the KCO and two OTV in the KO of the PFG aft nacelles in PRS-R2, is illustrated in Fig. 1 and general front, top and side views, respectively a), b) and c):

a) in the configuration of the KVP aircraft with the KGTD feeding the KS 7-8, leading the PV with the OTV and deflected both by the slats and flaps of the trapezoidal consoles of the DNA, and by the louvers-rudders backward in flight and nozzles with the VUVT downward at an angle of 15 °;

b) in the configuration of the aircraft, the GDP with the KGTD, feeding two KS 7-8, bringing two PWs with open upper flaps and lower louvers-rudders of their KCO in DNA, shown in an intermediate position by a dotted line at an angle of 45 ° to the axis of symmetry;

c) in the configuration of a supersonic aircraft with closed upper flaps and lower KKO louvers, organizing the corresponding DNA surfaces and placing their smaller consoles perpendicular to the symmetry axis, deflected with their end parts downward at an angle of 30 ° at a flight speed of M = 0.7- M = 1.4.

A strategic ATAS with reactive OPKR and RPKR is shown in FIG. 1 with one OPKR, made according to the concept of MPNS-X2 and PRS-R2 with an airframe using an inconspicuous technology of aluminum alloys and composite carbon fiber, has a PFG 1, a rotary hinge 2 DNA with smaller 3 and large 4 consoles, the latter of which have slats throughout the entire span 5, flaps 6. The jet system delivers a supersonic air flow from the KGTD compressors to the lower 7 or upper 8 jet airflows mounted along the longitudinal axis of the PFG 1 in the aft fairing 9 with a compartment having at its end a retractable false target towed on a cable (in Fig. 1 not shown). The end parts 10 of the smaller diamond-shaped consoles 3 are made folding downward in flight and in the parking lot (see Fig. 1c). PFG 1 has one-piece rotary keels 11, retractable wheeled tricycle landing gear and side air intakes with S-shaped air ducts screening the OTV (not shown in Fig. 1). Each KGTD with OTV and SST has a VUHT of a round jet nozzle 12. Inside the large trapezoidal consoles 4 DNA 3-4 with bilateral symmetry are mounted two KKO 13 with left 14 and right 15 transverse PVs equidistant in plan from the center of mass. Each KKO 13 is equipped with transverse louvers 16 from above and from the bottom controlled louvers 17, organizing after closing the corresponding surfaces of DNA 3-4. Two KGTD in the combined control system contain jet circular nozzles 12 with VUHT, have air bleed from the KGTD compressors for jet KS 7-8 and a front shaft outlet for power take-off and its transmission to a T-shaped gearbox with longitudinal and transverse shafts (in Fig. 1 not shown), transmitting torque to the OTV and a T-shaped main gearbox connected through the clutch, angular and T-shaped gearboxes and its transverse shafts with angle gearboxes PV 14-15, redistributes 50 % between PV 14-15 or 22% and 30% between two RTV in KO, respectively, when performing GDP, hovering or level flight.

Control of the deck OPKR is provided from a two-seat cockpit without a glazed surface 18, and target designation is provided by its radar with AFAR and OED 19 (see Fig. 1c). When flying as a jet aircraft, the lift force is created, respectively, by DNA 3-4 with fixed smaller or larger DNA consoles along the axis of symmetry with closed shutters 16 with shutters 17 in the KKO 13 (see Fig.1b), cruising jet thrust - by the system PRS-R2 through jet nozzles 12 with VUVT in KGTD, mounted in PFG 1 aft nacelles, in the transition mode - DNA 3-4 with PV 14-15. After the creation of the lifting thrust PV 14-15, the modes of the GDP and hovering or KVP are provided when the jet nozzles 12 with VUHT in the KGTD create the required sustainer thrust for translational flight (see Fig. 1a). When performing GDP and hovering to change the balance along the roll or course, the transverse lower louvers-rudders 17 in each KKO 13 are made with the possibility of their differential alternate or simultaneous deviation by angles forward along the flight -40 ° and backward + 40 °, respectively, but also the pitch - by alternating operation of the lower 7 or upper 8 CC on the aft fairing 9 (see Fig. 1c). After vertical take-off and climb, an acceleration flight is performed at speeds of 250 km / h and the flaps 16 of the rudder louvers 17 are deflected back and power is redistributed from PV 14-15 to OTV KGTD. As the acceleration progresses with an increase in the lifting force of DNA 3-4, the lifting force of the PV 14-15 decreases. When the flight speeds of 280 km / h are reached and to switch to the airplane flight mode, the PV 14-15 are stopped, fixed when the transverse shutters 16 and the shutters 17 of their KKO 13 are synchronously closed back in flight (see Fig. 1b). When creating jet thrust nozzles 12 and fixing the transverse centerline of large consoles 4 DNA 3-4 along the axis of symmetry and the right tip in the front fairing 20, a trans- or supersonic flight of the OPKR is performed, in which a change in the balance in pitch, roll and heading is ensured by the corresponding deflection of the jet 12 nozzles with VUVT of each KGTD and keels 11.

Thus, a strategic ATAS with OPKR and DPKR with DNA and two CGTDs, which have to create a vertical thrust of the PV in the CCO and / or horizontal thrust of the PT in the CC in the PFG with working or fixed PV, is a jet tiltrotor with a system of cold air flow from the PV in MPNS-X2 / X4 with GDP, hovering and hot exhaust of a jet stream in PRS-R2 during horizontal flight. Rotational DNA with bilateral symmetry when fixing trapezoidal DNA consoles along the axis of symmetry increases the aerodynamic and structural advantages in the configuration of a supersonic aircraft with a diamond-shaped wing and its ends deflected downward. The latter will increase the aerodynamic quality by 30%, fuel economy - by 20% or the flight range - by 29% when performing a transonic flight in an aircraft configuration at a speed of 880 ... 1000 km / h, but also at supersonic speeds to reduce drag by 12 ... 20 %, wave resistance - by 26% and achieve a speed of 1275/1488 km / h with a non-afterburner thrust-to-weight ratio K _mt = 0.54 / 0.68. In addition, KGTD circular nozzles with VUHT for horizontal flight control eliminate the traditional need for complex mechanical moving parts of their bearing surfaces used to deflect rudders, ailerons and control elevons. The electronic warfare and countermeasures system is an integrated set of hardware and software OPKR and DPKR, optimized with a high level of detection and self-defense, providing identification, find and counter threats with the following functions: radar warning; geolocation emitter; emitter location on multiple target ships, including wide frequency coverage, fast response times and countermeasures for self-defense.

Aviation group consisting of ATAS, including heavily armed OPKR and DPKR, used from the ANL helipad, carrying their PFGs in bomb compartments (see Table 1) DPKR-2.2 / OPKR-2.75 each 1/1 AKR type Kh-555 / X-101. The head OPKR, which is fully digitized using the latest technologies, including the joint use of the UAV air group, the so-called manned and unmanned teaming (MUM-T), which allows the pilots of the head OPKR to control the flight path of a group of slave DPKR and their combat loads. The fourth level MUM-T allows OPKR pilots not only to receive real sensor images from the air group of the slave DPKR and to control weapon loads, their navigation and global positioning with the creation of a buffer air zone between the air defense target and the OPKR, using the GDP / KVVP, increase the flight range of the AKR type X -102 to 7750/9812 km, which is comparable with the range of action of ICBMs of the Bulava-30 type, after the launch of a number of AKR type X-102 autonomous swarms with towed false targets, increasing the destructive capability and combat stability of the attack ANL-helicopter carrier, mastered based on the nuclear-powered icebreaker "Leader" of project 10510 with advanced adaptable capabilities, allowing the use of a large displacement of 71,380 tons to increase icebreaking capacity up to 4.3 m.

Claims (4)

1. Strategic aviation transarctic system with an unmanned aerial vehicle (UAV) having a fuselage, a launcher (PU) with a guided missile (UR), a wing with its controls, a power plant engine (SU), an onboard control system (BSU), which provides telemechanical control from the command post of an aircraft-carrying icebreaker (ANL), characterized in that it has a group of ship-based vertical take-off and landing (VLT) vehicles, including more than one optionally piloted rocket carrier tiltrotor (OPKR) with more than one remotely piloted rocket carrier tiltrotor (DPKR), used from more than one helipad of the nuclear ANL, and each DPKR and OPKR is made according to a hybrid layout with at least one bidirectional wing (DNA) having bilateral symmetry in two perpendicular planes and in any of two positions at 90 ° equal or different in scope trapezoidal and diamond-shaped consoles correspond nno with their rounded and triangular tips, integrated with the underwing fuselage-nacelle (PFG) and its hinge, which provides the follower mechanism from the initial position along the symmetry axis in the plan of the rhomboid DNA consoles, their rotation in the horizontal plane at an angle of 90 ° counterclockwise or backward clockwise arrows so that trapezoidal / diamond-shaped and diamond-shaped / trapezoidal DNA consoles are set in plan, respectively, along the / axis perpendicular to the axis of symmetry, fixed in the last position, for example, trapezoidal large / diamond-shaped smaller DNA consoles with their corresponding lengthening λ = 3.3 ... 4 , 3λ / = 2.5, but also contains on the trapezoidal DNA consoles a multi-fan transverse carrying system (MPSS), which is used when it is installed with these consoles perpendicular to the plane of symmetry in transient and accelerating flight modes, performing GDP, short takeoff and landing or vertical landing (KVP or KVVP), but also including at least two lifting fans (PV), equidistant in plan from the center of mass, mounted in wing annular fairings (KKO), having automatically opening / closing transverse both upper louvres-flaps and lower louvres-rudders, providing free air access to and exit from the corresponding KCO air flow that does not blow over the PFG, and after they are closed back in flight, the corresponding DNA surfaces, but is also equipped with at least two combined gas turbine engines (CGTD) mounted in the aft part of the PFG, equipped with side air intakes and round nozzles with all-aspect thrust vector control (VUVT) and are made in the form of two-circuit jet engines with a single-row turbofan (OTV) in an annular fairing (KO) and more than one free power turbine (SST), which transfers the takeoff power of the CS to the corresponding PS in the KKO and / or OTV to the KO, creating synchronous reactive thrust in the propulsive-reactive system (PRS) when performing the GDP, KVP and KVVP and or horizontal translational flight, but it is also made with the possibility of converting its flight configuration after performing a vertical or short takeoff from a corresponding aircraft with a gas turbine engine, leading, for example, to the MPNS-X2 a pair of PV and / or two OTVs to IIPC-R2, creating a lifting and / or propulsive-jet thrust with working / fixed PV with automatically open / closed upper flaps and lower louver-rudders of their KKO in the configuration of jet supersonic or transonic aircraft, respectively, at normal or maximum takeoff weight, but also vice versa, while in the system transmission, each of its KGTD is placed in the PFG aft nacelle, in which between the OTV and the SST is mounted coaxially with the last two T-shaped gearbox in plan, having input shafts longitudinal along its axis, for example, from two SST, but also longitudinal and transverse output shafts, the first of which transmits power through the clutch to the OTV, and the second synchronizing shaft transmits torque to the T-shaped in plan, the main gearbox, the output shaft of which is rotationally connected through the clutch to the bevel gear, the vertical column of the output shaft of which, being a rigid axis of the DNA pivot hinge, is located coaxially with the latter, has a shaft that is rotationally connected through the clutch to the T-shaped one when seen behind the reducer, transmitting it by the output shafts, laid inside the trapezoidal consoles of DNA and the KKO stiffeners, equal power to the angular gearboxes PV. 2. The system according to claim 1, characterized in that in the above-mentioned OPKR and DPKR, in order to reduce their parking area by 1.8 ... 2.3 times from the take-off, the end parts of the rhomboid DNA consoles are folded downward with the fixation of the trapezoidal DNA consoles mentioned along the axis of symmetry , and their air flow control system, which ensures the direction of supersonic air flows from the compressor of each KGTD, which in the modes of GDP and hovering to change the balance in pitch are fed to the jet rudders along the longitudinal air ducts to their valves and are blown alternately from the upper or lower aft nozzles (CS) when the corresponding automatic flap is open, which, when it is closed, forms the corresponding surface of the aft fairing, and in the modes of their GDP and hovering to perform lifting and changing the balancing both in roll and heading, the mentioned louvers-rudders, for example, in their left and right CCO, which are installed on the transverse centerline of the mentioned trapezoid DNA consoles, passing in plan through the center of mass, are made with the possibility of differential deviation from the center of the CCO by angles forward along the flight of -40 ° and backward + 40 °, both alternately in one of the CCOs on one side of their front and rear louvers-rudders, so and at the same time in a pair of CCOs on both sides of the front ones with the rear louvers-rudders, respectively, and in their flight configuration of a jet aircraft, the change in pitch, heading and roll is created, respectively, by in-phase and differential deviation in two KGTD of their jet nozzles with the mentioned VUVT both vertically upward - down, both horizontally left-right and vertically one up, and the other down, but also an increase in directional stability at a speed of their flight M = 0.7 ... M = 1.4, the end parts of their diamond-shaped consoles, mounted with DNA according to the area rule, deviate downward by an angle of 30 °, moreover, in the modes of GDP and hovering of the OPKR and DPKR with a specific load on the power of their combined control system, which is ρ _N = 1.15 kg / h.p., each mentioned C ST is made with elements of digital program control, combining an adaptive control system for the formation of a safe flight (UFBP) with a specific vertical thrust-to-weight ratio, for example, in MPNS-X2, which, taking into account losses from blowing stiffening ribs, KKO ρ _VT = 1.15, includes the SST operating modes both takeoff and emergency mode (BP and CR) with the selection of its required power to drive the said PS, respectively, both from four operating SSTs and from three of the operating SSTs with automatic equalization and equal redistribution of the remaining power between the PS if the corresponding SST fails in KGTD, for example, even in the latter case, after the automatic switching on of the PD of the work of the SST remaining in operation, which, with a specific vertical thrust-to-weight ratio in the MPNS-X2, equal to ρ _VT = 1.07, will provide an emergency vertical landing mode for 2.5 minutes, and in each of their SSTs, the UFBP system contains: one or more sensors that are configured to detect data related to xxa air flow rate (G _B , kg / s) through the SST compressor, gas temperatures ( _TG , K) before the SST turbine, the total compression ratio (K) of the compressor, and one or more sensors that are configured to detect the relative position and their PFG, and disks of rotation of their PV for their relative position relative to the ground level or the surface of the landing site, as well as various obstacles in the path of their tracking safe descent; a flight control computer located in their BSU and operational with one or more sensors; the flight control computer is configured to: determine the relative position between their PFGs with their wheeled chassis and the ground level or surface of the landing pad; compare the relative position of their PFG and their carrier system with their selected relative position; determine the speed of the controlled descent required to move them to the selected relative position; convert tracker speed to flight control inputs; and also to provide a direct controlled safe descent to the selected relative position through the flight control inputs, while each OPKR and DPKR, made respectively without and with a cockpit, equipped inside with video cameras with autonomous manipulators connected to the OPKR controls and the possibility of its optional control by pilots from the PFG cabins, and the lower bomb bays of their PFGs have internal armament with automatic flaps and their mentioned launchers with air-to-air missiles and aviation cruise missiles (AKR) attached to them, which provide, respectively, the fight against air and ground, surface targets, and their weapons complex has an aircraft cannon installed in the fairing on top of the PFG nose, striking subsonic shock UAVs and AKRs, and their airframe is made of aluminum-lithium alloys and composite materials using an inconspicuous technology with a radio-absorbing coating, moreover, the heavily armed DPKR and OPKR, carrying a jet aircraft configuration air in the bomb bays of their PFG, respectively, AKR type Kh-555 and X101 to create a buffer safe air zone between the head OPKR and the target's air defense, increasing the range to 4750/7750 km, respectively, of strategic AKR type Kh-555 / Kh-101, forming autonomous swarms of ACRs with towed false targets, and their PFG, having their sides beveled from the pyramidal nose along its entire length, forming with the mentioned air intakes when viewed from the front, its five- or hexagonal cross-section, which reduces the effective scattering area, and their PFG at the end of the tail booms it has either one-piece rotatable keels, deflected up or down and outward from the plane of symmetry at an angle of 47 ° to the horizontal, or a swept stabilizer with end keel washers, forming a U-shaped tail when viewed from the front, and their PFG between the nozzles KGTD is equipped with a stern fairing with a compartment at its end, extended along its longitudinal axis and from the end, with a retractable towed dew with a false target, while the electro-optical sensor (EOD), designed for detecting and identifying the target, has a receiving part of the EOD, which is closed from above with a sapphire glass, is installed at the bottom of the nose of the PFG of the head OPKR and, with the latter's radar, provides on large, safe for OPKR distances, target designation and control of weapons loads of the OPKR and DPKR with aiming at the target of their air-to-ground missile defense system and their air-to-air missile defense system, and the DPKR control is provided by the OPKR co-pilot using a low-altitude flight profile and a self-defense system DPKR-station of active electronic interference, and the mentioned BSU of the head OPKR, made with a fly-by-wire control system that responds to at least one of the systems of autonomous flight control, remote operator control, pilot control and / or their combination, is equipped with the possibility of its optional control by pilots from the cockpit mounted in their PFGs having ejection to the upper hemisphere There are no seats that are triggered automatically when performing GDP and hovering, but also its use as part of an air group as a head with the above-mentioned more than two DPKR, more than one of which, being a slave, automatically repeats it by the autopilot system in tracking flight, the maneuvers of the head OPKR, and the other is controlled by the co-pilot from the head OPKR, and then vice versa, and in the absence of the pilot's intervention, the autopilot system performs flight control of the slave DPKR in accordance with the commands of the current state, repeating the flight profile and changing the route of the head OPKR, while in the event of an emergency situation, then for elimination of unforeseen problems with the safety of the tracking flight, the pilot takes over direct control of the slave DPKR, canceling the current state commands issued by the autopilot during autonomous operation of the tracking flight, and the control system for the formation of a relative position in the tracking flight, containing one or several sensors located on the slave DPKR are configured to detect data regarding its position relative to the position of the head OPKR having a flight control computer operational with one or more sensors, containing an additional sensor computer that is configured to: determine the relative position between slave DPKR and head OPKR; compare the relative position with the selected relative position; determine the speed of the slave DPKR required to move it to the selected relative position; convert tracker speed to flight control inputs; to restrict the direct movement of the slave DPKR relative to the OPKR, which provides through the inputs of its flight control computer their relative safe position in a joint flight, while each touch computer of the previous and subsequent slave DPKR, configured to perceive acoustic signals, has a memory containing: data representing at least one flight trajectory of the head OPKR and the previous DPKR; data representing at least one profile of their joint flight; program instructions executed by the processor for calculating their group flight to execute at least the current flight route and at least its flight profile and store the current flight in memory; program instructions executed by the processor for the flight of each DPKR in accordance with the current flight profile; multimodal logic executed by the processor to calculate the ability to dynamically adapt to changing conditions or parameters, including the ability to coordinate an air group, distributed tactical control, distributed over the targets of the air group and / or completely, increasing the effectiveness of its attack, are integrated into autonomous strategic swarming. 3. The system according to claim 2, characterized in that in the said OPKR and DPKR the control system for the formation of their relative position in flight with one or more sensors includes one or more infrared (IR) sensors, video sensors, radar, laser and ultrasonic sensors , sonars, global positioning sensors, while the said flight control computer is made both with an additional computer for summing sensor data and a data transmission and reception channel located on the head OPKR to obtain global position data from the slave DPKR, and with the ability to convert images from each video sensor, providing the determination of the relative position, which by means of triangulation includes the determination of the relative range, azimuth and elevation, and the additional computer for summing the sensor data and the data transmission channel has a multiband radio frequency equipment with a directional antenna, capable of transmitting several video streams through closed communication channels, ensuring the collection of data from each video sensor, and also ensuring the conversion of images from each video sensor to a relative position, which is determined on the basis of the global position of the head OPKR transmitted to the slave DPKR, while the data addition computer is fully integrated into the pilot interface and the OPKR control system, providing the mentioned follow-up flight of the slave DPKR, which, if necessary, can be disabled by means of one of the inputs of the pilot interface for flight control, activation by the pilot of a button or control switch, and the data summation computer is additionally equipped with the possibility of its independent action, which determines whether that the OPKR flight is unsafe for its relative position from the slave DPKR, but also disables the formation of the said tracking flight by the slave DPKR through the flight control computer. 4. The system according to any one of paragraphs. 1, 2, characterized in that in the mentioned OPSV and DPSV their DNA with trapezoidal consoles made with the relative thickness of their profile

and a narrowing η _DNA = 0.53, equipped with slats and flaps throughout the span, has the mentioned diamond-shaped consoles with a relative thickness of their profile

, and for a transonic flight mode with an intermediate at an angle of 45 ° to the axis of symmetry by fixing their DNA consoles, transforming the latter into a bidirectional wing of asymmetrically variable sweep, which, with a marching thrust yield of the first level - 0.246 or the second - 0.3, using respectively 22% or 30 % the power of their control system, provides a speed of Mach 0.829 (M) or M = 0.942 at an altitude of 11 km, and for the supersonic flight mode with the above-mentioned fixation of their trapezoidal DNA consoles so that in the C-shaped front fairing PFG, located behind the cockpit in its upper refinement, the ending of its right console is fixed, while using 72% or 100% of the power of their SU, it is achieved with a marching thrust yield of the third / fourth level K _mt = 0.54 / 0.68, respectively, supersonic speed M = 1.2 / M = 1.4, and the airframe OPKR, without a glazed surface of the cockpit, containing means for displaying a digital image representing a part of the external scene, including the environment , stretching forward and sufficient for piloting, is equipped with a variety of video cameras, IR sensors and video sensors that provide touch shooting, capturing all events in the front and rear hemispheres 360 °, while the image is digitally corrected and displayed for real-time control by the distribution module video on cockpit displays or visible on pilots' helmet displays that are connected to first and second advanced vision processors, configured to be worn by first and second pilots, respectively, with first and second shared viewports and highlighted displayed lines of sight visible on first and second helmet displays respectively.

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