RU2753894C1 - Aircraft ship arctic system - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to the field of aviation, in particular to ship-based missile aircraft systems. The Arctic Ship Aircraft System (ASAS) is comprised of an aircraft-carrying icebreaker ship (ACIS), optionally and remotely piloted convertible planes with a bidirectional wing with bilateral symmetry in two positions, mounted on a rotary hinge of the fuselage. Two combined gas turbine engines are installed on the wing and have with free power turbines driving two pairs with overlapping rotors and/or in the annular fairings are two turbine fans creating lifting and/or propulsive-jet thrust with working/fixed transverse rotors when the upper and lower louver doors of the annular fairings in the configuration of jet planes are automatically open/closed. The converted planes carry guided aircraft missiles.

EFFECT: increase in the weight efficiency and target load, increase in the speed and range of flight, probability of hitting a surface or ground long-range target, and possibility of multiple use are provided.

3 cl, 5 dwg, 2 tbl

Description

The invention relates to Arctic ship-aviation systems with optional remotely piloted convertible aircraft having a rotary bi-directional wing with bilateral symmetry in two positions at 90 °, mounted on a fuselage having combined gas turbine engines with free power turbines, driving two pairs with overlapping rotor propellers ( HB) and / or in the annular fairings two turbofans creating lifting and / or propulsion-jet thrust with operating / fixed HB with automatically open / closed upper and lower longitudinal flaps of the wing annular fairings in the configuration of jet aircraft with guided missiles used from a nuclear 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 a cruise missile (CR); The ballistic missile 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 CD 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 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 landing gear. 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 1275/1487 km / h with a thrust-to-weight ratio of 0.54 / 0.68. Known aircraft with CAIS have a number of disadvantages, the main of which are: displacement of the aerodynamic focus with multidirectional sweep, which leads to an increase in balancing resistance; an increase in the mass of the structure due to the presence of pivot hinges 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 asymmetry of drag and, as a consequence, to the appearance of parasitic turning moments in roll, pitch and yaw. Moreover, KAIS is characterized by a twice as large 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 aviation complex (PAK) "Icara" (Great Britain) with jet unmanned aerial vehicles (UAVs) having a wing, fuselage with a launcher (PU) of a guided missile (UR), a power plant engine (SU) and an onboard control system (BSU) for control from the command post of the carrier vehicle.

Signs that coincide - a UAV with dimensions without a ship's launcher: length 3.42 m, wingspan 1.52 m, height 1.57 m, carries a homing anti-submarine torpedo (PLT) of the Mk.44 type, having a mass of 196 kg, length 2.57 m and a diameter of 324 mm, a speed of 30 knots and a cruising range of 5 km. A UAV with a Mk.44 torpedo has a maximum / minimum flight altitude of 300/20 m and a significant weight of 1480 kg, which limits the range to 24 km and the flight speed to 140 ... 240 m / s.

The reasons that impede the task: the first is that the subsonic UAV was launched in the direction as close as possible to the target. 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 are constantly updated in the fire control system computer, which then transmitted them through the BSU to the UAV in flight. Upon the arrival of the UAV in the area where the target was located, the Mk.44 torpedo, semi-submerged 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 landing site of the homing submarine, 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 likelihood 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 Arctic ship-aviation system (AKAS) has a group of ship-based vertical takeoff and landing (VLT) vehicles, including more than one optionally piloted convertible aircraft (OPKS) with more than one remotely piloted convertible aircraft (RPC), used from more than one ANL helipad, with each DPC and RCC in an aerodynamic configuration with variable airframe geometry, including U-shaped or V-shaped empennage and at least one rotary bidirectional wing (DNA) with bilateral symmetry in two perpendicular planes, having in any of two positions at 90 ° equal or different sizes in span trapezoidal or diamond-shaped consoles, respectively, with their rounded or triangular tips, or in their combination forming, for example, ro mb-shaped smaller / trapezoidal larger wings (RMK / TBK), the last of which has a multi-rotor transverse-carrying system (MPNS), used when it is installed with TBK 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), including with a variable pitch two front and two rear two- or three-bladed rotor (HB), the axes of rotation of which are equidistant in plan from the center of mass so that the first of them are located from the plane of symmetry further than the second rear of them, forming a line connecting their centers of rotation, which is located in the plan at an inverse angle of -45 ° to the axis of symmetry and mounted with coplanar overlap equal to a = 1.22 or a = 1.24 in the corresponding pairs of wing annular fairings ( KKO), having an oval plan or the number eight and automatically opening / closing longitudinal upper and lower or semicircular sashes, or louvre-sashes, or their Combinations that provide free access of air to the CCO and the exit from them of an air flow that does not blow over the PFG, forming, after closing them to the left or right of the center of their CCO, the corresponding surfaces of the TBC in DNA, integrated with the PFG and its upper hinge, the tracking drive mechanism of which is from the initial positions in the plan, for example, the TBC, located with its elongation λ = 4.1 perpendicular to the axis of symmetry, provides after the execution of the GDP, hovering and accelerating flight modes with the closed flaps of the KCO, the subsequent counterclockwise in plan rotation of the DNA in the horizontal plane at an angle of 90 ° so that the RMK are fixed perpendicular to the axis of symmetry with its elongation λ = 2.8 for high-speed flight modes or back clockwise to the initial position, but it is also equipped in the aft part of the PFG with at least two combined gas turbine engines (KGTD) equipped with side air intakes, made in the form of bypass jet engines, each of which has t 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 control system to the corresponding NW in their KCO and / or OTV to KO, creating a synchronous jet thrust when performing VVP, KVP and KVVP or horizontal flight, but it is also made with the possibility of converting its flight configuration after performing a vertical or short take-off from the corresponding aircraft, for example, with two KGTD, leading to MPNS-X4 two pairs of NV and / or two OTV in ITPC-R2, while creating lift and / or cruising thrust with operating / fixed NV with automatically open / closed upper and lower, for example, louvers-shutters of their KKO in a 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 aft engine nacelle, in which between the OTV and SST it is mounted coaxially with the last two T-ob a different axial 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 shaft to the main T-shaped in plan gearbox, the output longitudinal shaft of which is rotationally connected through the clutch to the angular fuselage gearbox, the vertical column of the output shaft of which, being a rigid axis of the DNA pivot joint, is located coaxially with the latter, has a vertical shaft, which is rotationally connected through the clutch to the wing T-shaped and through it with two cantilever T-shaped gearboxes, respectively, when viewed from behind and from above, transmitting their output shafts, laid respectively inside the TBC and stiffening ribs of one-sided KKO, the distributed power in MPNS-X4 to the angular vertical gearboxes of the corresponding front and rear NV (PNV and ZNV ).

In addition, in the mentioned OPKS and DPKS, the mentioned U-shaped tail unit with triangular elevators and rudders, respectively, on a trapezoidal stabilizer and keels, deviated upward radially from the latter and the plane of symmetry outward and spaced from the symmetry axis for free rotation of the left wingtip in the system DNA, for example, of the mentioned TBC with appropriate fixation with the mentioned placement of its end parts, made in the parking lot folding vertically downward to reduce their parking area by 2.4 ... 2.6 times from the take-off area, and in the modes of their GDP and hovering, longitudinal control is carried out by changes in the step of a pair of night vision devices and a pair of ZNV, lateral control - a change in the step of two left night vision devices with a ZNV and two right night vision devices with a ZNV, directional control - a change in torque in the diagonally located left night vision device with a right ZNV and in the right night vision device with a left ZNV, which are in plan rotate in one direction, for example, clockwise and counterclockwise, and their mode ax of GDP and hovering at a specific load on the power of their combined CS, which is ρ _N = 1.15 kg / hp, each mentioned SST is made with elements of digital program control, combining an adaptive control system for the formation of a safe flight (FPBP) with a specific vertical thrust-to-weight ratio in MPNS-X4, which, taking into account the losses from blowing of the stiffeners, KCO ρ _ВТ = 1.15, includes the operating modes of the SST both takeoff and emergency mode (BP and CR) when the required power is taken to drive the mentioned NVV and ZNV, respectively both from four operating SSTs and from three of operating SSTs with automatic equalization and equal redistribution of the remaining power between the PNV and ZNV in the event of failure of the corresponding SST in the KGTD, for example, even in the latter case, after the automatic switching on of the PD, the work of the remaining SSTs in operation, which, when specific vertical thrust-to-weight ratio in MPNS-X4, which is ρ _VT = 1.07, will provide an emergency vertical landing mode for 2.5 minutes, and in each of their SSTs, the UVBP system contains: one or more sensors that are configured to detect data related to the air flow rate (G _B , kg / s) through the SST compressor, the gas temperature ( _TG , K) in front of the SST turbine, total the compression ratio (K) of the compressor, as well as one or more sensors that are configured to detect the relative position of their PFGs and rotation discs of their NV 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 said BSU and operating with one or more sensors; the flight control computer is configured to: determine the relative position between their PFG with a 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 automatic descent required to move them to the selected relative position; convert tracker speed to flight control inputs; and also provide a direct controlled safe descent to the selected relative position through the flight control inputs, as well as provide a direct controlled safe descent to the selected relative position through the flight control inputs; and also to provide a direct automatic safe descent to the selected relative position through the flight control inputs, while each OPKS and DPKS, made respectively without and with a cockpit, equipped inside with video cameras with autonomous manipulators connected to the OPKS 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 doors and their mentioned launchers with air-to-air missiles and aviation cruise missiles (AKR) attached to them, which, respectively, provide the fight against air and ground, surface targets, and their weapons complex has an aircraft cannon installed in the fairing on top of the nose of the PFG, striking subsonic shock UAVs and AKR, and their airframe is made of aluminum-lithium alloys and composite materials using an inconspicuous technology with a radio-absorbing coating, and their mentioned side air intakes that do not have a plate compartment for the boundary layer and internal movable regulating elements, they are made for shielding the OTV blades with a double S-shape when viewed from the side and from above, as well as for withdrawing the boundary layer and increasing the total pressure recovery factor, both without a slot for draining the boundary layer, but each also includes a ramp that compresses the flow and forms its conical flow, moreover, heavily armed DPKS and OPKS, carrying in the configuration of a jet aircraft in the bomb compartments of their PFGs, respectively, AKR type Kh-55SM and Kh101 to create a buffer safe air zone between the said ANL and the air defense system, increasing targets after they have completed the technology GDP / KVVP range of up to 5900/8155 km or 7900/10155 km, respectively, of strategic AKR of the Kh-55SM or Kh-101 type, after their launch, they form autonomous swarms of AKR with towed false targets, and their PFG, which has from its pyramidal bow lateral sides beveled along the length of its engine nacelles, forming five- and whether a hexagonal cross-section, which reduces the effective scattering area, and their PFG at the end of the tail booms has the mentioned V-shaped tail with integral rotary keels deflected up or down and outward from the plane of symmetry at an angle of 43 ° to the horizontal, and their PFG between the mentioned KGTD and their rectangular flat nozzles, made with a heat-absorbing coating, reducing infrared (IR) radiation and their radar visibility, is equipped with a stern fairing extended along their longitudinal axis with a compartment equipped at its end with a retractable false target towed on a cable; at the same time, the electro-optical sensor (EOD), designed for detecting and identifying a 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 OPKS and, with the latter's radar, provides target designation and control at large, safe for OPKS distances weapons loads OPKS and DPKS with aiming at the target of their air-to-ground and air-to-air missile launchers, and control of the DPKS is provided by the co-pilot of the OPKS, using the low-altitude flight profile of the DPKS and its self-defense system - an active electronic jamming station, and the mentioned BSU of the head OPKS, 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 option of its optional control by pilots from the cockpit mounted in their PFG, which has ejection seats into the upper hemisphere , srab automatically after firing the flashlight during the execution of the runway and hovering, but also its use as part of the air group as the head with the above-mentioned more than two DPKS, more than one of which, being the slave, automatically repeats it by the autopilot system in the tracking flight, the maneuvers of the head OPKS, and the other is controlled by the co-pilot from the head OPSS, and then vice versa, and in the absence of pilot intervention, the autopilot system performs flight control of the slave OPSS in accordance with the commands of the current state, repeating the flight profile and changing the route of the head OPSS, 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 DPKS, canceling the commands of the current state 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 about one or more sensors located on the slave OPCS are configured to detect data concerning its position relative to the position of the head OPCS, 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 the slave DPKS and the head OPKS; compare the relative position with the selected relative position; determine the speed of the slave DPKS required to move it to the selected relative position; convert tracker speed to flight control inputs; restrict the direct movement of the slave DPKS relative to the OPKS, providing 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 DPKS configured to calculate the ability to dynamically adapt to changing conditions or parameters, including the Ability to coordination of the 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 the autonomous strategic swarming, and the mentioned ANL, which has an asymmetric hull, made with its two-draft scheme, allowing the use of draft in the range of 8.5 up to 10.5 m to increase icebreaking capacity and perform special tasks in shallow water and river estuaries, equipped with a propulsion system consisting of a pair of main and a pair of additional aft and bow rudder propellers, each of which, working independently and increasing the efficiency of maneuvering in any direction and even rotation in place, it can both rotate in the horizontal plane through 360 °, and is equipped with an integrated high-torque DC motor with a corresponding fixed-pitch propeller (FPP) mounted directly on the shaft inside the gondola of a full-revolving propellers, while the installation of bow propellers on the mentioned ANL provides high maneuverability in ice conditions, but also in clear water, which is very important in areas with limited water space, but also, achieving the effect of ice erosion by the work of these propellers, as it reduces the ice strength and increases the ability to pass hummocks, and has a detrimental effect on the operation of the aft propellers, moreover, to increase the efficiency of the propulsion installation of the mentioned ANL, a pair of bow propellers, which, providing the effect of divergence of their thrust vectors from the longitudinal axis of the ANL, are deployed at an angle to each other on an effective stop ANL in Regi while creating a traction force, while the propulsion system with four propellers and four control joysticks are combined in one bridge with the installation of two navigation bridges - the main and backup for the ANL control during the run and visual control, which improves the panoramic view from the second bridge when it is moving and oblique underway, and only the stern superstructure with both artillery mounts and anti-torpedo missile systems, and anti-aircraft missile systems of the air defense of the nuclear ANL, which has in front of it multi-level aviation hangars with means, such as: cranes, elevators, lifts, systems and fixing OPKS and DPKS on its deck, the width and length with a bow springboard of which also ensures their short take-off along the oblique from its starboard side of the runway using at the start position a lifting gas baffle with its water cooling, and after they have completed their mission - vertical simultaneous or alternate landing to the appropriate helicopter deck platforms.

и сужением η_днк=0,53, имеет упомянутое РМК с относительной толщиной профиля

, а в полетной их конфигурации как реактивных до скорости полета 0,5 Маха (М), так и транс- или сверхзвуковых самолетов изменение балансировки по крену обеспечивается дифференциальным отклонением как внешних флапперонов упомянутого ТБК, так и цельно-поворотных в вертикальной продольной плоскости треугольных законцовок упомянутого РМК, а для повышения путевой их устойчивости при скорости полета М=0,5…М=0,8/М=0,8…М=1,6 концевые части их упомянутых РМК, смонтированных с ДНК по правилу площадей отклоняются вниз на угол 12°/30°, а для трансзвукового режима их полета с промежуточной под углом 45° к оси симметрии фиксацией консолей ДНК, преобразуя последнее в двунаправленное крыло асимметрично изменяемой стреловидности, которое при маршевой тяговооруженности первого уровня - 0,22 или второго - 0,25, используя соответственно 22% или 27% мощность их СУ, обеспечивает на высоте 11 км скорость М=0,894 или М=0,941, а для сверхзвукового режима полета упомянутое ТБК их ДНК фиксируется как над ПФГ с мотогондолами, имеющими скошенные в плане кромки и воздухозаборников, и сопел, смонтированными по правилу площадей с ПФГ, центральная часть которого с его воздухозаборниками образуют совместную планформу, которая меньше или соответствует планформе ТБК, так и с установкой законцовки правой консоли ТБК и ее фиксации в С-образном при виде сбоку переднем обтекателе ПФГ, размещенном в верхней утонченности ПФГ за двухместной кабиной пилотов с расположением пилотов бок о бок, выполненной только с боковыми застекленными ее окнами или без застекленной поверхности ее всех окон, а каждый их КГтД снабжен его реактивным соплом с форсажной камерой, используемой на самолетных взлетных и сверхзвуковых режимах полета с передними перед упомянутым ОТВ и задними перед форсажной камерой открытыми управляемыми створками упомянутой мотогондолы для дополнительного в нее подвода воздуха, что позволит с перегрузом 15% взлетного его веса на высоте 11 км повысить тяговооруженность СУ с 0,52 до 0,69 и достичь скорость до М=1,4, при этом отсутствие застекления лобовых окон или всех окон в кабине пилотов ОПКС позволит увеличить жесткость ПФГ и снизить толщину обшивки и, как следствие, уменьшить его массу, причем планер ОПКС с герметичной кабиной, имеющей автоматически сбрасываемый непрозрачный броне-фонарь для катапультирования пилотов и 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 ОПКС в режиме реального времени отображается модулем распределения видео на дисплеях кабины пилотов, делая ее обшивку как бы прозрачной, или видны на нашлемных дисплеях пилотов, которые, образуя общие окна просмотра, 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 aforementioned OPKS and DPKS, their DNA with the mentioned TBC, which has slats and flaps with external flappers over the entire span, made with a relative thickness of their profile

and the narrowing η _DNA = 0.53, has the above-mentioned RMC with a relative profile thickness

, and in their flight configuration, both reactive up to a flight speed of Mach 0.5 (M), and trans- or supersonic aircraft, the change in roll balance is provided by the differential deviation of both the external flapperons of the said TBC and the triangular tips that are rotatable in the vertical longitudinal plane the mentioned RMK, and to increase their track stability at a flight speed of M = 0.5 ... M = 0.8 / M = 0.8 ... M = 1.6, the end parts of their mentioned RMK, mounted with DNA according to the area rule, deviate downward by an angle of 12 ° / 30 °, and for the transonic mode of their flight with an intermediate at an angle of 45 ° to the axis of symmetry by fixing the DNA consoles, converting the latter into a bidirectional wing of asymmetrically variable sweep, which, in the case of a marching thrust-to-weight ratio of the first level - 0.22 or the second - 0, 25, using respectively 22% or 27% of the power of their SU, provides a speed of M = 0.894 or M = 0.941 at an altitude of 11 km, and for the supersonic flight mode, the mentioned TBC, their DNA is recorded as above the PFG with m nacelles with beveled edges and air intakes and nozzles, mounted according to the area rule with a PFG, the central part of which with its air intakes form a joint planform, which is smaller or corresponds to the TBC plan, and with the installation of the tip of the right TBC console and its fixation in C -shaped when viewed from the side, the front fairing of the PFG, located in the upper refinement of the PFG behind the double cockpit with the pilots located side by side, made only with its side glazed windows or without the glazed surface of all its windows, and each of their KGTD is equipped with its jet nozzle with an afterburner a camera used in aircraft take-off and supersonic flight modes with open controllable flaps of the mentioned engine nacelle in front of the said engine and rear in front of the afterburner for additional air supply, which will allow, with an overload of 15% of its takeoff weight at an altitude of 11 km, to increase the thrust-to-weight ratio of the control system from 0 .52 to 0.69 and reach soon up to M = 1.4, while the absence of glazing of the front windows or all windows in the cockpit of the OPKS will increase the rigidity of the PFG and reduce the thickness of the skin and, as a result, reduce its weight, moreover, the OPKS airframe with a sealed cockpit having automatically reset opaque armor - a flashlight for ejection pilots and a means of 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, infrared sensors and video sensors that provide sensory shooting, recording all events in the front and rear hemispheres 360 °, while the image is digitally corrected and, for real-time control of the OPCS, is displayed by the video distribution module on the cockpit displays, making its skin appear transparent, or visible on the helmet-mounted displays of the pilots, which, forming common viewing windows, are connected to the first and the second processors of the extended system are configured to be worn by the first and second pilots, respectively, with the first and second common viewports and highlighted displayed lines of sight visible on the first and second helmet displays, respectively.

Due to the presence of these features, which will make it possible to master a strategic or strike AKAS, which has a group of ship-based vertical take-off and landing (VLT) vehicles, including more than one optionally piloted convertible aircraft (OPKS) with more than one remotely piloted convertible aircraft (DPKS), used from more than one ANL helipad, and each DPKS and OPKS in an aerodynamic configuration with a variable airframe geometry, including a U-shaped or V-shaped tail and at least one rotary bidirectional wing (DNA) with bilateral symmetry in two perpendicular planes, having in any of the two 90 ° positions, equal or different in span trapezoidal or diamond-shaped consoles, respectively, with their rounded or triangular tips, or in their combination, forming, for example, a diamond-shaped smaller / trapezoidal larger wings (RMK / TBC), the last of which has a multi-screw cross-bearing system to him (MPNS), used when it is installed with the TBC consoles perpendicular to the plane of symmetry in transient and accelerating flight modes, when performing a runoff, short takeoff and landing or vertical landing (KVP or KVVP), including with a variable step two front and two rear two- or three-bladed main rotor (HB), the axes of rotation of which are equidistant in plan from the center of mass so that the first of them are located farther from the plane of symmetry than the second rear ones, forming a line connecting their centers of rotation, which is located in the plan at a reverse angle -45 ° to the axis of symmetry and mounted with coplanar overlap equal to a = 1.22 or a = 1.24 in the corresponding pairs of wing annular fairings (CCR) having an oval plan or number eight and automatically opening / closing longitudinal upper and lower or semicircular shutters, or shutters-shutters, or their combinations, providing free access of air to the CCO and the exit from them of an air flow that does not blow over the PFG, forming after they are closed to the left or to the right of the center of their CCO, the corresponding surfaces of the TBC in DNA, integrated with the PFG and its upper hinge, the tracking drive mechanism of which from the initial position in the plan, for example, the TBC, placed with its elongation λ = 4.1 perpendicular to the axis symmetry, provides after the execution of the GDP, hovering and accelerating flight modes with the closed flaps of the KCO, the subsequent counterclockwise in terms of rotation of the DNA in the horizontal plane at an angle of 90 ° so that the RMK is fixed perpendicular to the axis of symmetry with its elongation λ = 2.8 for high-speed flight modes or back clockwise to the starting position, but it is also equipped in the aft part of the PFG with at least two combined gas turbine engines (KGTD) equipped with side air intakes, made in the form of bypass jet engines, each of which has a single-row turbofan (OTV) in an annular fairing (KO) and more than one free power turbine (SST) transmitting takeoff power of the control system for the corresponding NV in their CCO and / or OTV in SC, creating synchronous reactive thrust in the propulsive-reactive system (PRS) during the performance of the GDP, KVP and KVVP or horizontal flight, but it is also made with the possibility of converting its flight configuration after performing a vertical or short take-off from a corresponding aircraft, for example, with two KGTDs, bringing two pairs of NV and / or two OTVs to the PRS-K2 into the MPNS-X4, while creating a lifting and / or sustainer thrust with operating / fixed NVs when automatically open / closed upper and lower, for example, shutters-flaps of their KCO into a 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 located in the aft engine nacelle, in which between the OTV and SST is mounted coaxially with the last two.T-shaped axial gearbox in plan, having input shafts longitudinal along its axis, for example, from two SSTs, but also longitudinal and transverse nny output shafts, the first of which transfers power through the clutch to the OTV, and the second shaft to the T-shaped main gearbox in plan, the output longitudinal shaft of which is rotationally connected through the clutch to the angular fuselage gearbox, the vertical column of the output shaft of which, being rigid axis of the DNA pivot hinge, located coaxially with the latter, has a vertical shaft, which is rotationally connected through the clutch to the wing T-shaped and through it with two cantilever T-shaped gearboxes, respectively, when viewed from the rear and from above, transmitting them to the output shafts, laid respectively inside TBC and stiffeners of one-sided KKO, distributed power in MPNS-X4 to the angular vertical gearboxes of the corresponding front and rear NV (PNV and ZNV). All this will make it possible to simplify controllability and ensure its stability in reactive OPKS and DPKS with DNA of bilateral symmetry and two QGTDs, which bring two pairs of NVs to MPNS-X4. The placement of the NV in the KKO TBK near the center of mass ensures the predictability and stability of control during the GDP and hovering, and the implementation of the NV with a variable pitch will simplify the control, improve the weight return and increase the flight range of the OPKS, performed without the glazed surface of the cockpit windows containing digital image display means on cockpit displays or on helmet displays of pilots. In the event of a failure in the control system of one of the SSTs in the hover mode, its CGTDs are made with automatic leveling and equal redistribution of the remaining power of the SST between the NV, which increases the safety of the deck OPKS and DPKS. The use of rotary DNA in OPKS and DPKS will allow to reduce aerodynamic drag in the configuration of a supersonic aircraft and in non-afterburner / afterburner modes of operation of two CGTDs at an altitude of 11 km, trans- and supersonic speeds of 1052 km / h and 1275 km / h / 1700 km / h.

The proposed invention of a strategic AKAS with deck OPKS and DPKS, having a rotary DNA with RMK and TBC, inverted V-shaped tail, two KGTD, bringing two-bladed NVV and ZNV, the blades of which are placed in their CCO parallel to the axis of symmetry and / or two OTV in the KO, illustrated by one OPCS in general front / top and side views, respectively, in FIG. 1/2 and fig. 3:

fig. 1/2 in the configuration of an airplane KVP or VVP with KGTD, bringing NV or NV with OTV to PRS-Ya2, and TBC with its mechanization, shown conditionally with open shutters in the left / right KKO with their planform in the form of an oval / number eight and a dotted line in an intermediate position at an angle of 45 ° to the axis and along the axis of symmetry;

fig. 3 in the configuration of a supersonic aircraft with closed shutters-flaps in the KKO DNA, with fixing its TBC / RMK along the / axis perpendicular to the axis of symmetry and deflection of the end parts of the RMK downward at an angle of 30 ° at a speed of M = 0.8 ... M = 1.6 ...

FIG. 4, 5 show side views, from above, respectively, the layout diagram of the atomic ANL, the composition of the equipment and technical requirements for the ANL in table. 2.

The strategic ACAS is shown in FIG. 1-5 OPKS and ANL. The reactive OPKS is made according to the MPNS-X4 and ITPC-R2 concept, has a PFG 1 with its upper pivot joint 2 DNA of bilateral symmetry with RMK 3 and TBC 4, the latter of which has slats 5 over its entire span, and flaps 6 with external flapperons 7. The end parts 8 of the RMK 3 are folded down in the parking lot, equipped to change the roll balance with all-round triangular endings 9 in plan (see Fig. 3). The large elongation PFG 1 contains one-piece rotary keels 10, deflected downward and outward, and between the KGTD and their flat jet nozzles 11, a stern fairing 12 with a compartment having a retractable false target towed on a cable at its end, but also a retractable wheel tricycle landing gear and side air intakes with S-shaped air ducts shielding the OTV (not shown in Figs. 1-3). Inside TBC 4 of the turning DNA 3-4, two left and two right KKO 13 are mounted with two transverse PNV 14-15 and two ZNV 16-17 in MPNS-X4, equidistant in plan from the center of mass. Each KKO 13 is equipped with longitudinal upper 18 and lower 19 louvres-shutters, organizing, after closing, the corresponding surfaces of TBC 4 in DNA 3-4. Each KGTD in the combined control system is equipped with front 20 in front of the OTV and rear 21 in front of the afterburner with open controllable nacelle flaps in the PFG 1 for additional air supply to it and has a front shaft outlet for power take-off and its transmission to a T-shaped axial gearbox with a longitudinal and transverse shafts (not shown in Figs. 1-3) transmitting torque through the clutches to the OTV and a T-shaped main gearbox in plan, the output longitudinal shaft of which is connected to the fuselage angular gearbox, which transfers power through the clutch to the wing and cantilever T-shaped gearboxes when viewed from the rear and from above and through the output shafts of the latter two to the corresponding angular gearboxes HB 14-17. At the same time, from the takeoff power of the SU, it is redistributed as 100% between NV 14-17, and 22% or 27%, but also 100% between two OTV in KO, respectively, when performing both GDP and hovering, and high-speed or trans-, but also supersonic flight.

Control of the deck OPKS is provided from a two-seat cockpit without a glazed surface 22, and target designation is provided by its radar with AFAR and EDI 23 (see Fig. 3). When flying as an airplane with speeds of M = 0.5 or M = 0.5 ... M = 1.6, the lift is created with fixed consoles RMK 3 or TBC 4 along the axis of symmetry and closed shutters 18-19 in KKO 13 (see Fig. 2), cruising jet thrust - by the ITPC-R2 system through flat nozzles 11 in two KGTD, mounted in the PFG 1 aft nacelles, in the transition mode - DNA 3-4 with HB 14-17. After the creation of the lifting thrust NV 14-17, the modes of GDP and hovering or KVP / KVVP are provided when the nozzles 11 in the KGTD create the required sustainer thrust for forward flight (see Fig. 1). When performing a runoff and hovering, longitudinal control is carried out by changing the step of a pair of PNV 14-15 and two ZNV 16-17, transverse control - by changing the step of two left PNV 14 C ZNV 16 and two right PNV 15 with ZNV 17, track control - by changing the torques in the diagonally located left PNV 14 with the right ZNV 17 and in the right PNV 15 with the left ZNV 16, which rotate in the plan in one direction, for example, clockwise and counterclockwise. After vertical take-off and climb, a transitional maneuver is performed and power is redistributed from the drive of a pair of PNV 14-15 and two ZNV 16-17 to the drive of two OTVs of their CGTD. As the OPKS accelerates and with an increase in the lifting force of its DNA 3-4, the lifting force decreases on two-bladed HB 14-17, which stop, are fixed parallel to the symmetry axis (see Fig. 2) when the shutters are synchronously closed to the left or right from the center of the KKO 13 - sash 18-19.

When the speeds M = 0.5 and M = 0.5 ... M = 0.8 are reached, transient and accelerating flight modes are provided (see Fig. 3). At flight speeds of the jet OPKS M = 0.5 ... M = 0.8 / M = 0.8 ... M = 1.6, both the RMK 3 consoles are fixed perpendicular to the plane of symmetry, and the right tip of the TBC 4 in the front fairing 24 PFG 1, but the end parts of the RMK 3 also deviate downward at an angle of 12 ° / 30 °, respectively. At the same time, the change in balancing in pitch and heading or roll is ensured by the deviation, respectively, of synchronous and asynchronous all-rotary keels 10 or differential triangular all-rotary tips 9 RMK 3. To reduce the visibility and aerodynamic resistance of the OPKS, each side air intake 25 is made without a lamellar cutter of the boundary layer and consists of a ramp 26, which compresses the flow and forms a conical flow.

Thus, deck-mounted OPKS and DPKS with KGTD, bringing the PNV and ZNV to the CCO TBK and / or horizontal thrust OTV in the KO to create a lifting thrust with operating and / or sustainer thrust with fixed NVs, is a jet tiltrotor with a system of cold air flow from the PNV and ZNV in MPNS-X4 during run-off, hovering and hot exhaust of the jet stream in ITPC-R2 during level flight. Rotational DNA with bilateral symmetry when fixing the TBC 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 at an angle of 30 ° at a speed of M = 0.8 ... M = 1.6. That will increase aerodynamic quality by 30%, fuel economy - by 20% or flight range - by 29% in the configuration of a transonic aircraft at a speed of 1000 km / h, but also at supersonic speeds to reduce drag by 12 ... 20%, wave drag - by 26% and reach a speed of up to 1275 / 1700M487 km / h at a flight altitude of at least 11 km with non-afterburner / afterburner cruising thrust-to-weight ratio K _mt = 0.59 \ 0.79 / 0.69 of the combined SU, respectively, with normal / maximum takeoff weight at implementation of the GDP / WPC. The electronic warfare and countermeasures system is an integrated set of hardware and software OPKS and DPKS, optimized with a high level of detection and self-defense, providing identification, finding and countering 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.

Strategic AKAS with heavily armed OPKS and DPKS used with atomic ANL, carrying in bomb compartments deck DPKS-2.2 / OPKS-2.75 (see Table 1) 1/1 AKR type Kh-55SM / Kh-101. The head OPCS, which is fully digitized using the latest technologies, including sharing with more than one DPCS, the so-called manned and unmanned teaming (MUM-T).

The fourth level of MUM-T allows OPKS pilots not only to receive real sensor images with control of weapons loads, their navigation and global positioning with the creation of a buffer zone between the air defense target and the OPKS. In addition, using the VVP / KVVP technologies of deck-mounted OPKS-2.75, it will make it possible to increase the flight range of the Kh-102 type AKR up to 7900/10155 km, which is comparable to the range of the Bulava-30 type ICBMs. After launching a number of AKRs of the Kh-102 type, forming autonomous swarms with towed false targets, they increase the destructive capability and combat stability of the strategic atomic ANL. Moreover, the top-priority development of deck-mounted OPKS-2.75 will make it possible to create a relatively cheap shock AKAS, in which each OPKS-2.75, carrying an anti-ship supersonic missile of the 3M55 Onyx-A type, will ensure its launch at supersonic speed and an altitude of 15 km , and will also allow to increase, using the VVP / KVVP technology, the range of its flight from 300 km to 2100/3790 km, respectively. The strike ANL, mastered on the platform of the two-draft scheme of the nuclear icebreaker of project 22220, will provide the possibility of using supersonic OPKS-2.75 as part of the AKAS from the estuaries of Siberian rivers. The latter will make it possible to increase the secrecy of the anti-ship AKAS, as well as the striking ability and inaccessibility from enemy submarines, but also to exclude the presence of expensive strategic and anti-ship aviation airfields in the Arctic Circle.

Claims (3)

1. Arctic ship-aviation system (AKAS), containing an aircraft-carrying icebreaker (ANL) with jet unmanned aerial vehicles (UAV), having a wing, a fuselage with a launcher (PU) of a guided missile (UR), a power plant engine (SU) and for control from the ANL command post an on-board control system (BSU), characterized in that it has a group of ship-based vertical take-off and landing (GDP) vehicles, including more than one optionally piloted convertible aircraft (OPKS) with more than one remotely piloted convertible aircraft ( DPKS), used from more than one ANL helipad, and each DPKS and OPKS in an aerodynamic configuration with variable geometry of the airframe, including U-shaped or V-shaped empennage and at least one rotary bi-directional wing (DNA) with bilateral symmetry in two perpendicular planes, having in any of two positions at 90 ° equal or different in span pezoidal or diamond-shaped consoles, respectively, with their rounded or triangular tips, or in their combination, forming, for example, a diamond-shaped smaller / trapezoidal larger wings (RMK / TBC), the latter of which has a multi-screw transverse-carrying system (MPNS) used for its installation with TBC consoles perpendicular to the plane of symmetry on transient and accelerating flight modes, performing runway, short take-off and landing or vertical landing (KVP or KVVP), including with a variable pitch two forward and two rear two- or three-bladed rotors (HB), axles whose rotations are equidistant in plan from the center of mass so that the first of them are located from the plane of symmetry further than the second rear ones, forming a line connecting their centers of rotation, which is located in plan at an inverse angle of -45 ° to the axis of symmetry, and mounted with coplanar overlap equal to a = 1.22 or a = 1.24, in the corresponding pairs of wing annular fairings (KCO) having a planfo oval or figure eight and automatically opening / closing longitudinal upper and lower or semicircular sashes, or louvre-sashes, or their combinations, providing free access of air to the CCO and the exit from them of an air flow that does not blow the PFG, forming after they are closed to the left or to the right of the center of their CCO the corresponding surfaces of the TBC in DNA, integrated with the PFG and its upper hinge, the follower mechanism of which from the initial position in the plan, for example, the TBC, placed with its elongation λ = 4.1 perpendicular to the axis of symmetry, provides after execution GDP, hovering and acceleration modes of flight with closed flaps of the KCO, subsequent counterclockwise in terms of rotation of DNA in the horizontal plane at an angle of 90 ° so that RMK are fixed perpendicular to the axis of symmetry with its elongation λ = 2.8 for high-speed flight modes or vice versa. clockwise to its original position, but it is also equipped in the aft part of the PFG with at least two combined gas turbine engines (KGTD) equipped with side air intakes are made in the form of bypass jet engines, each of which has a single-row turbofan (OTV) in an annular fairing (CO) and more than one free power turbine (SST), which transfers the takeoff power of the control system to the corresponding NV in their KCO and / or OTV in KO, creating synchronous jet thrust in the propulsive-reactive system (PRS) when performing GDP, KVP and KVVP or horizontal flight, but also made with the possibility of converting its flight configuration after performing a vertical or short takeoff from the appropriate aircraft, for example, with two KGTD, leading to the MPNS-X4 two pairs of NV and / or two OTV in PRS-R2, creating a lifting and / or sustainer thrust with working / fixed NV with automatically open / closed upper and lower, for example , the shutters-flaps of their CCO into a jet supersonic or transonic aircraft, respectively, at normal or maximum takeoff weight, but also vice versa, at the same time, in the transmission system, each of its KGTD is located in the aft engine nacelle, in which between the OTV and the SST is mounted coaxially with the last two, a T-shaped axial gearbox in plan, having input shafts longitudinal along its axis, for example, from two SST, but also a longitudinal and transverse output shafts, the first of which transmits power through the clutch to the OTV, and the second to the T-shaped main gearbox in plan, the output longitudinal shaft of which is rotationally connected through the clutch to the angular fuselage gearbox, the vertical column of the output shaft of which, being rigid with the axis of the DNA pivot hinge, located coaxially with the latter, has a vertical shaft, which is rotationally connected through a clutch to the wing T-shaped and through it with two cantilever T-shaped gearboxes, respectively, when viewed from the back and from above, transmitting them to the output shafts, laid respectively inside TBC and stiffeners of one-sided KKO, distributed power in MPNS-X4 for angular vertical gearboxes of the corresponding front and rear NVs (PNV and ZNV). 2. AKAS according to claim 1, characterized in that in said OPKS and DPKS, said U-shaped tail unit with triangular elevators and rudders, respectively, on a trapezoidal stabilizer and keels deflected upward radially from the latter and the plane of symmetry outward and spaced from symmetry axes for free rotation of the left ending in the DNA system, for example, the mentioned TBC with appropriate fixation with the mentioned placement of its end parts, made in the parking lot folding vertically downward to reduce by 2.4 ... 2.6 times their parking area from the takeoff, and by modes of their GDP and hovering, longitudinal control is carried out by changing the step of a pair of night vision devices and a pair of ZNVs, lateral control - by changing the pitch of two left night vision devices with a ZNV and two right night vision devices with a ZNV, directional control - by changing the torques in the diagonally located left night vision devices with a right ZNV and in right NVD with left NVV, which rotate in plan in one direction, for example, clockwise and counterclockwise new arrow, and in their modes of GDP and hovering with a specific load on the power of their combined _{control system, which is ρ N} = 1.15 kg / hp, each mentioned CST 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 in the MPNS-X4, which, taking into account the losses from blowing of the stiffeners, KCO ρ _VT = 1.15, includes the SST operating modes both takeoff and emergency mode (BP and CR) when selecting its required power for the drive of the mentioned PNV and ZNV, 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 PNV and ZNV in case of failure of the corresponding SST in the KGTD, for example, even in the latter case after the automatic switching on of the PD of the work of the remaining in the operation of the SST, which, with the specific vertical thrust-to-weight ratio in the MPNS-X4, which is ρ _VT = 1.07, will provide the emergency vertical mode landing for 2.5 minutes, and in each of their SSTs, the UVBP system contains: one or more sensors that are configured to detect data related to the air flow rate (G _B , kg / s) through the SST compressor, 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 of their PPG and their NV discs for their relative position relative to the ground level or the surface of the landing site, as well as various obstacles on the way of tracking their safe decline; a flight control computer located in their said BSU and operating with one or more sensors, the flight control computer is configured to: determine the relative position between their PFG with a 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 automatic descent required to move them to the selected relative position; convert tracker speed to flight control inputs; and also to provide a direct automatic safe descent to the selected relative position through the flight control inputs, while each DPKS and OPKS, made respectively without and with a cockpit, equipped inside with video cameras with autonomous manipulators connected to the OPKS 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 doors and their mentioned launchers with air-to-air missiles and aviation cruise missiles (AKR) attached to them, which, respectively, provide the fight against air and ground, surface targets, and their weapons complex has an aircraft cannon installed in the fairing on top of the nose of the PFG, striking subsonic shock UAVs and AKR, and their airframe is made of aluminum-lithium alloys and composite materials using an inconspicuous technology with a radio-absorbing coating, and their mentioned side air intakes that do not have a plate compartment for the boundary layer and internal movable regulating elements, they are made for shielding the OTV blades with a double S-shape when viewed from the side and from above, as well as for withdrawing the boundary layer and increasing the total pressure recovery factor, both without a slot for draining the boundary layer, but each also includes a ramp that compresses the flow and forms its conical flow, moreover, heavily armed DPKS and OPKS, carrying in the configuration of a jet aircraft in the bomb compartments of their PFGs, respectively, AKR type Kh-55SM and Kh101 to create a buffer safe air zone between the said ANL and the air defense system, increasing targets after they have completed the technology GDP / KVVP range of up to 5900/8155 km or 7900/10155 km, respectively, of strategic AKR of the Kh-55SM or Kh-101 type, after their launch, they form autonomous swarms of AKR with towed false targets, and their PFG, which has from its pyramidal bow lateral sides beveled along the length of its engine nacelles, forming five- and whether a hexagonal cross-section, which reduces the effective scattering area, and their PFG at the end of the tail booms has the mentioned V-shaped tail with integral rotary keels deflected up or down and outward from the plane of symmetry at an angle of 43 ° to the horizontal, and their PFG between the mentioned KGTD and their rectangular flat nozzles, made with a heat-absorbing coating, reducing infrared (IR) radiation and their radar signature, is equipped with a stern fairing extended along their longitudinal axis with a compartment equipped at its end with a retractable false target towed on a cable, while an electronic-optical the sensor (EDI), designed for detection and identification of the target, has an EDI receiving part, which is closed from above with a sapphire glass, is installed at the bottom of the nose of the PFG of the head OPKS and, with the latter's radar, provides target designation and control of weapons loads OPKS and DPKS at large, safe for OPKS distances with aiming at the target of their AKP air class - the ground and the air-to-air missile launcher, and the control of the DPKS is provided by the co-pilot of the OPKS, using the low-altitude flight profile of the DPKS and its self-defense system - an active electronic jamming station, and the mentioned BSU of the head OPKS, made with a fly-by-wire control system that responds to at least one of systems of autonomous flight control, remote control of the operator, pilot control and / or their combination, is equipped with the possibility of optional control of it by pilots from the cockpit mounted in their PFG, which has ejection seats into the upper hemisphere, which are triggered automatically after the flashlight is fired when performing a runoff and hovering, but and its use as part of an air group as a lead one with the above-mentioned more than two DPSS, more than one of which, being a follower, automatically repeats it by the autopilot system in tracking flight, the maneuvers of the head OPSS, and the other is controlled by the co-pilot from the head OPSS, and then vice versa, and in the absence of pilot disturbances, the autopilot system performs flight control of the slave DPKS in accordance with the commands of the current state, repeating the flight profile and changing the route of the lead OPKS, while in the event of an emergency situation, to eliminate unforeseen problems with the safety of the tracking flight, the pilot takes over direct control of the slave DPKS, canceling the commands of the current state issued by the autopilot during autonomous operation of the tracking flight, moreover, the control system for the formation of a relative position in the tracking flight, containing one or more sensors located on the slave DPKS, configured to detect data concerning its position relative to the position of the head OPKS, which has a control computer in flight, operational with one or more sensors, containing an additional touch computer that is configured to: determine the relative position between the slave DPKS and the head OPKS; compare the relative position with the selected relative position; determine the speed of the slave DPKS required to move it to the selected relative position; convert tracker speed to flight control inputs; to restrict the direct movement of the slave DPKS relative to the OPKS, providing through the inputs of its flight control computer their relative safe position in a joint flight, while each sensor computer of the previous and subsequent slave DPKS configured to calculate the ability to dynamically adapt to changing conditions or parameters, including the ability to coordination of the 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 the autonomous strategic swarming, and the mentioned ANL, which has an asymmetric hull, made with its two-draft scheme, allowing the use of draft in the range of 8.5 up to 10.5 m to increase icebreaking capacity and perform special tasks in shallow water and river estuaries, equipped with a propulsion system consisting of a pair of main and a pair of additional aft and bow rudder propellers, each of which, working independently and increasing the efficiency of maneuvering in any direction and even rotation in place, it can both rotate in the horizontal plane through 360 °, and is equipped with an integrated high-torque DC motor with a corresponding fixed-pitch propeller (FPP) mounted directly on the shaft inside the gondola of a full-revolving propellers, while the installation of bow propellers on the mentioned ANL provides high maneuverability in ice conditions, but also in clear water, which is very important in areas with limited water space, but also, achieving the effect of ice erosion by the work of these propellers, as it reduces the strength ice and increases the ability to pass hummocks, and has a detrimental effect on the operation of the aft propellers, and to increase the efficiency of the propulsion installation of the aforementioned ANL, a pair of bow propellers, which, providing the effect of divergence of their thrust vectors from the longitudinal axis of the ANL, are rotated at an angle to each other by an effective emphasis ANL in dir having the creation of tractive effort, while the propulsion unit with four propellers and four control joysticks are combined in one bridge with the installation of two navigation bridges - the main and backup for the ANL control during the course and visual control, which improves the panoramic view from the second bridge when it is moving and oblique underway, and only the aft superstructure with both artillery mounts and anti-torpedo missile systems, and anti-aircraft missile systems of the air defense of the nuclear ANL, which has in front of it multi-level aviation hangars with means, such as: cranes, lifts, lifts, roll-out and fixation systems for OPKS and DPKS on its deck, the width and length with a bow springboard of which also ensures their short take-off along the oblique from its starboard side of the runway using a lifting gas baffle with its water cooling at the start position, and after they have completed their mission - a vertical simultaneous or alternate landing to the appropriate ve flight deck decks. 3. AKAS according to any one of paragraphs. 1, 2, characterized in that in the mentioned OPKS and DPKS their DNA with the mentioned TBC, which has slats and flaps with external flappers throughout the entire span, made with the relative thickness of their profile

and the narrowing η _DNA = 0.53, has the above-mentioned RMC with a relative profile thickness

, and in their flight configuration, both reactive up to a flight speed of Mach 0.5 (M), and trans- or supersonic aircraft, the change in roll balance is provided by the differential deviation of both the external flapperons of the said TBC and the triangular tips that are rotatable in the vertical longitudinal plane the mentioned RMK, and to increase their track stability at a flight speed of M = 0.5 ... M = 0.8 / M = 0.8 ... M = 1.6, the end parts of their mentioned RMK, mounted with DNA according to the area rule, deviate down at an angle of 12 ° / 30 °, and for the transonic mode of their flight with an intermediate at an angle of 45 ° to the axis of symmetry by fixing the DNA consoles, converting the latter into a bidirectional wing of asymmetrically variable sweep, which, with a marching thrust-to-weight ratio of the first level - 0.22 or the second - 0 , 25, using respectively 22% or 27% of the power of their SU, provides a speed of M = 0.894 or M = 0.941 at an altitude of 11 km, and for the supersonic flight mode, the mentioned TBC, their DNA is recorded as above the PFG with engine nacelles with beveled edges and air intakes and nozzles, mounted according to the area rule with a PFG, the central part of which with its air intakes form a joint planform, which is smaller or corresponds to the TBC plan, and with the installation of the tip of the right TBC console and its fixation in C -shaped when viewed from the side, the front fairing of the PFG, located in the upper refinement of the PFG behind the double cockpit with the pilots located side by side, made only with its side glazed windows or without the glazed surface of all its windows, and each of their KGTD is equipped with its jet nozzle with an afterburner a camera used in aircraft take-off and supersonic flight modes with open controllable flaps of the mentioned engine nacelle in front of the said engine and rear in front of the afterburner for additional air supply, which will allow, with an overload of 15% of its takeoff weight at an altitude of 11 km, to increase the thrust-to-weight ratio of the control system from 0 , 52 to 0.69 and reach speed awn up to M = 1.4, while the absence of glazing of the front windows or all windows in the OPKS cockpit will increase the rigidity of the PFG and reduce the thickness of the skin and, as a result, reduce its weight, moreover, the OPKS glider with a sealed cockpit having an automatically reset opaque armored flashlight for ejection of pilots and means of displaying a digital image representing part of the external scene, including the environment stretching forward and sufficient for piloting, is equipped with a variety of video cameras, infrared sensors and video sensors that provide sensory shooting, capturing all events in the front and rear hemispheres 360 ° , while the image is digitally corrected and, for real-time control of the OPCS, is displayed by the video distribution module on the cockpit displays, making its skin seem transparent, or visible on the helmet-mounted displays of the pilots, which, forming common viewing windows, are connected to the first and second extended system processors are configured to be worn by the first and second pilots, respectively, with the first and second common viewports and highlighted displayed lines of sight visible on the first and second helmet displays, respectively.

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