RU2721808C1 - Surface-submerged ship with deck air strike complex - Google Patents

Abstract

FIELD: military equipment.

SUBSTANCE: invention relates to military equipment. Disclosed is a surface-underwater vehicle (SUV) with a deck-based aircraft strike complex (DACS) comprising an unmanned aerial vehicle, having a fuselage with a detachable guided missile, middle wing with its control elements, engine, on-board control system, which provides telemechanical control (TMC) from control station (CS). Ship with system using optionally and remotely piloted aircrafts of integral layout includes flying wing of duplex circuit, having multiple first and second swept wings (FSW and SSW) and at the ends of the FSW, two single-blade rotors (SBR) with counterweights and two wing nacelles combining the FSW and the SSW, having free power turbines (FPT), driving the transverse SBR and in annular fairings external fans, creating at vertical and short takeoff/landing propulsion-reactive thrust directed horizontally backwards with operating / autorotating SBRor their fixed blades-wings from FSW outside during horizontal flight with all-track variation of thrust vector of FPT in configuration of jet rotorcraft/gyro or deck-based transonic aircraft.

EFFECT: higher weight output and combat load, higher speed and range of flight, higher probability of destruction of surface, underwater and air targets.

6 cl, 1 dwg

Description

The invention relates to military equipment and can be used in the design of carrier-based aircraft strike systems using optional and remotely piloted helicopters of an integrated configuration, including a flying wing of a hollow circuit, having different first and second swept wings (UCS and VSC) and at the ends of the UCS two single-blade main rotors (ONV) with counterweights and two wing nacelles combining PSK and VSK, having free power turbines driving transverse ONVs and in annular cowlings, external fans creating propulsion-reactive during vertical and short take-off / landing (GDP and KVP) thrust directed horizontally backward with operating / autorotating ONV or their fixed wing blades from the UCS outwards during horizontal flight with an all-angle change in the CCT thrust vector in the configuration of a rotorcraft / gyroplane or transonic aircraft having aviation-controlled in the bomb bay on launchers missile and transformed after landing on the ship’s platform by the fixed placement of the blades of two ONV along the PSK consoles and folding their counterweights and external sections of the VSK in the marching-loading configuration for its transportation in the hangar with the fueling box and the ammunition loading station of the surface-mounted underwater ship (NPK) )

A well-known joint project of the British companies “BAE Systems” and “Vickers Shipbuilding and Engineering” to create an underwater carrier with a deck system “Skyhook” [1], including a submarine of the type "Vanguard", more than one vertical take-off and landing aircraft (VTOL) and more than one manipulator with captures for capturing the VTOL aircraft, flying up and hovering under the captures of the manipulator, and transferring it to the deck with the subsequent movement of the VTOL aircraft in the hangar of an aircraft-carrying submarine.

Signs that coincide - the presence of an underwater carrier with a carrier-based strike aircraft system, including a manipulator with grips for transferring a jet VTOL to the submarine deck, followed by its transfer to the hangar on the transport-fixing device and from the hangar back. The design of the Skyhook system was as follows: on the submarine along its sides in the aft cowling there were two mechanical manipulators with grippers, the landing Harrier aircraft flew up to the submarine, moved the nozzles to a vertical position and gradually hovered next to the side, after which the manipulator with several grabs hooked VTOL for special emphasis on the fuselage. The sensors synchronized the movements of the manipulator with the work of its capture and VTOL. After capturing the VTOL aircraft, the manipulator automatically transferred to the deck of the submarine and placed it on the transport device to move the submarine and the loaded and charged VTOL aircraft back into the hangar.

Reasons that impede the task: the first is that the presence of vertical tail on the top of the fuselage makes it difficult after the nozzles to move to the vertical position to freeze the VTOL aircraft near the side of the submarine and under the arms of the manipulator, and in case of failure of the sensors for synchronizing their movement and its flight forward from the grips of the manipulator, which does not exclude their subsequent contact with the possible destruction of the vertical tail itself and the inevitable collapse of the VTOL aircraft. The second one is that a jet VTOL with two pairs of rotary nozzles along its sides, when it hangs near the side of the submarine and under the arms of the manipulator, the necessary changes in the pitch, roll and yaw balancing are carried out in phase and differential corresponding to their deviation in two vertical longitudinal planes, which inevitably complicates the process of docking with the grips of the manipulator, especially when the roll of the submarine is up to 25 ° and with the location of the manipulators from its outer sides.

Known reconnaissance-strike unmanned aircraft mod. "Taranis" [2] of the British company "BAE Systems" is designed according to the scheme of a flying wing with internal armament compartments and without vertical tail, has one turbofan engine with an air intake located on its upper part, and a three-leg retractable wheeled landing gear. For transonic flight "Taranis", its Rolls-Royce Adour turbojet engine has a jet thrust of 4485 kgf, which provides a thrust speed of 0.64 at a flight altitude of 11.5 km and a speed of 1060 km / h. The interaction of aerodynamic, structural and control reactions - is the Achilles heel of "Taranis" in the scheme of the flying wing. To ensure control of its controllability, especially in the direction of all three control axes - pitch, roll and yaw, there are six integrated flight control surfaces at its rear edge. The effect of integrated surfaces changes depending on the control axis, especially when the yaw balance changes, which depends on the angle of the relative counter flow with the corresponding deviation of external interceptors, which cause constant control reactions of the control computer, which in the absence of a multi-angle deflected nozzle of the turbofan engine complicates controllability and does not provide stability.

Closest to the proposed invention is an anti-submarine ship (PLC), armed with a carrier-based aircraft strike complex (PAK) "Icara" [3] (UK), containing an unmanned aerial vehicle (UAV), having a fuselage with a detachable guided missile, a mid-wing with its organs control, engine, on-board control system (BSU), providing telemechanical control (TMU) from the command post (CP) PLC.

Signs that coincide - UAV dimensions without ship launchers: 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 UAVs with a torpedo Mk.44 of 1480 kg (with a mass of 13% of the target load, torpedoes are 196 kg, its length 2.57 m and diameter 324 mm) and short ranges of 24 km and a flight speed of 140-240 m / s, and of the warhead (torpedoes - 30 knots and a range of 5 km).

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 dropped torpedo. The target location data came from the sonar system (GAS) of the surface carrier ship, another ship or anti-submarine helicopter. Based on this information, data on the optimal torpedo release zone is constantly updated in the computer of the firing control system, which then transmitted them through the radio command control system to the UAV in flight. Upon arrival of the UAV in the area where the target submarine was located, a torpedo (self-guided MGT Mk.44), half recessed with its ventral position in the UAV case, detached by radio command, descended by parachute, went into the water and began searching for the target submarine. After that, the UAV continues the flight with the operating SU, leading 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 aforementioned well-known ship with a spider model "Icara" (UK) to increase the combat load and weight return, increase speed and range, increase the likelihood of hitting an underwater and surface target located at long range, but also the possibility of its attack after long flight in hover mode, return to the helipad of a surface-underwater ship for reuse.

The distinguishing features of the present invention from the above-mentioned well-known Icara PAC, which is closest to it, are the fact that the low-crew NPK (MNPK) with an aircraft group of vertical take-off and landing apparatus in the PAC, including at least one optionally manned helicopter airplane (OPSV) with at least one remotely piloted helicopter aircraft (DPSV), which are used from at least one helipad MNPK, and each DPSV and DPSV made without vertical tail on the integral layout of the flying wing of the duplicated scheme, which has the first and second swept wings (PSK and VSK), spaced apart in the longitudinal direction, and is equipped with a twin-screw transverse-bearing circuit (DPS) with single-blade main rotors (ONV) with their counterweights mounted on profiled wing pylons PSK and wing gondolas, structurally combining PSK with VSK creating vertical thrust in DPS-X2 only with vertical th and short take-off / landing (GDP and KVP) or in transition flight modes, but also equipped with no less than a pair of combined gas turbine engines (KGTD), the left and right of which are installed in the corresponding wing nacelle and made in the form of a dual-circuit engine having an external and internal circuits, respectively, with an external single-row fan (BOB) in the annular cowl and at least one free power turbine (CCT) having a round nozzle with all-angular control of the thrust vector (VHWT) transmitting the take-off power of the combined power plant (SU) by the transmission system to the corresponding ONG in a symmetrically balanced DPNS-X2 and / or WWII, having blades with a large twist, working according to the pulling pattern, creates a synchronous reactive thrust in the propulsion-reactive system (PRS-R2) for vertical and short take-off / landing (GDP and KVP) or horizontal translational flight, but is also equipped in a hollow pattern with different-sized PSK and VSK, having the span is 1.04 and 1.965 times greater than the RVD diameter (D) at a straight sweep angle along the leading edge of the VSC, for example, χ = + 37 ° or χ = + 43 °, which is equal to the sweep angle along the leading edge of the VSC with frontal influxes forming a V-shaped configuration in plan with its great excellent sweep angle from UCS, the trailing edge of which is parallel to the rear edge of the outer sections of the VSC, the span of the inner sections of the latter is equal to the UCS spacing, placed in plan at the angle of the reverse sweep along the trailing edge of the inner sections VSKs, which form a profiled aft part with a V-shaped rear edge in plan, and integrated with wing gondolas mounted for the most part under or above PSK and VSK, increasing their rigidity, counteracting the harmful effects of divergence, especially of the outer sections of VSK, but also configured to convert its flight configuration after performing short or vertical take-off technology, respectively from a rotorcraft or helicopter at its maximum or normal take-off weight to the corresponding jet high-speed winged gyroplane or aircraft with transverse NVGs operating in the modes of their autorotation or as wide-chord wing-blades (SLK) carrying them, formed when the NVG is fixed with their counterweights or the transformation of their counterweights, carried out in transitional flight regimes in sequence, when after vertical / short take-off, climb and acceleration flight, both NNVs are simultaneously preliminarily stopped so that their counterweights and blades are fixed in plan, respectively, from the end of the UCS inwards to and outwards from the axis symmetries or when SLK is stopped, their profiled counterweights are equipped with automatic assemblies for their synchronous folding by turning them to the corresponding angles 127 ° or 133 ° in the horizontal plane and placing them back along the flight and parallel to the axis of symmetry when fixed with the corresponding sweep along the days to the edge of the SLK of the left and right ONV, which form a sweep with the PSK and VSK and arrange correspondingly-symmetrical bearing surfaces of their SLK in the flight configuration of a jet aircraft with PRS-R2 and a system of step multilevel wings (SSRK), but also back.

In addition, in the transmission system of the aforementioned SPSV and DPSV, each of their QGTDs, for example, with one CCT, for selecting its take-off power, has a front shaft output mounted along the longitudinal axis of its nacelle, in which, between the mentioned BOB and CCT, it is mounted coaxially with the last T- shaped as a top and side view of the intermediate gearbox having a longitudinal input shaft from the CCT and output both front longitudinal and transverse from the side, but also the upper shafts, the first of which transfers power through the clutch to the BOB, the annular cowling of which The air intake is adjustable with a conical central body, the second synchronizing one, laid in the PSK, rotationally connects the CCT of two KGTD, and the third transmits torque through the clutch to the input shaft of the corresponding ONV cantilever gearbox located in the wing pylon, has an output shaft, which is placed in plan on transverse axis passing through the center of mass and equidistant from the center of mass, but also tilted back along flight at an angle (α), which when viewed from the side is 1/2 or equal to the value of the angle of attack (α), respectively, UCS or VSC, and the incoming flow at their vertical and horizontal flight modes are simultaneously met respectively by the leading edges of the advancing ONV blades in the mentioned DPS X2 and their aforementioned SLK ONV, performing the role of the upper ones with the tiered placement of the outer sections of the PSK in the aforementioned SSK, transforming moderate elongation of the PSK and large VSK, respectively, with λ = 5.34 ... 5.39 and λ = 7.9 ... 8.0 to SSRK extensions with λ = 4.88 ... 4.96, and the inter-nacelle sections of their PSK and VSK are equipped with slats and internal flaps, respectively, used for take-off and landing or transitional flight regimes of APSV and DPSV, and the aforementioned round nozzles with VWTT of their CCT are equipped the possibility of both in-phase and differential synchronous deviation of both vertically up or down, both horizontally left or right and vertically one up and the other down to change accordingly a taste in pitch, heading and roll during horizontal translational flight of SPSV and DPSV, while the mentioned SPSS and DPSV on their GDP regimes and hovering in the aforementioned DPS-X2 left and right ONV, having the opposite direction of their rotation, respectively, clockwise and counterclockwise, made with rigid fastening of their blades and automatic swash, providing a change in the balance of pitch, heading and roll, which is created by changing the corresponding cyclic pitch and differential change in traction through the common pitch of the said ONV, respectively, and their outer sections of the said VSK have front and front ends on them behind at their ends are the corresponding infrared (IR) emitters and heat chambers, and after a vertical landing on the helipad of the MNPK of the mentioned OPSV and DPSV, the convertible system of the bearing surfaces of each of them has the ability to both pre-stop their ONV blades along the PSK consoles and place their tips to axis of symmetry with the subsequent folding of their counterweights when they are located forward along the flight and parallel to the axis of symmetry, as well as the simultaneous folding up of the outer sections of the VSC located above its outer sections, but also transporting them in the MNPK hangar with a decrease of 1.8 ... 2.0 times the area of their traveling configuration from their take-off area, and their mentioned VSK, having a ratio of 56.6% ... 57.1% of the sum of the areas of all bearing surfaces, including the areas of the mentioned PSK and VSK with their bearing fuselage and SLK of two ONVs, equipped with a feed fairing from its trailing edge along the axis of symmetry, having at its end a compartment with a retractable magnetometer rod and in its lower compartment with openable shutters a lowered winch and an antenna of a hydroacoustic station towed on a cable under water during its flight, while the above mentioned carrying aircraft anti-submarine and anti-ship missiles (APR and anti-ship missiles), provide an appropriate fight against a submarine (PL) and a surface ship (NK), and during anti-submarine defense, the aforementioned SPSV and DPSV use a lowered hydroacoustic system consisting of an indicator of acoustic signals and two receivers for receiving them from a hydroacoustic antenna, encoding them and transmitting them via eight-channel closed communication to IPPC for processing in real a time scale or a highly sensitive magnetometer having a magnetically sensitive element operating at a distance of 30 m from the water surface and connected with the BSU in the mentioned SPSV and DPSV, which provides for issuing commands to turn on the magnetometer at the calculated point and to control after the magnetometer is triggered when the PL- the purpose, but also registration in the BSU memory of the coordinates of the detection point of the PL target during transmission to the MNPK and its control gear, while in the mentioned OPSV and DPSV, their mentioned BSU has both a closed-circuit radio channel with the MNPC and a radar station with a command transmitter, optical -electronic system with a two-channel automatic conducting a target and a computer system with an automation unit of a multifunctional control panel that provides independent search for a PL target during barrage flight, identifies it, and makes a confirmed decision from the operator of the ISMC about destroying the chosen ones, and with anti-ship defense, the mentioned SPSV and DPSV using the flight configuration of the said jet aircraft with fixed ONV SLKs carrying the appropriate Kh-35U or Kh-38M anti-ship missiles in the bomb bay to create a buffer safe airspace between the main anti-aircraft missile and the NK target air defense, increasing the radius of the Kh-38M / Kh-35U anti-ship missiles from 40/130 to 400 km, while the H036 [4] type radar from the main SPSV provides target designation, and the DPSV control is provided by the second SPSV pilot using a low-altitude flight profile and self-defense system - the DPSV active electronic jamming station, and when reaching the area from which the NK target will be hit , said DPSV will launch a volley or sequential launch of anti-ship missiles with correction the error accumulated by the combined inertial control system according to the data of the GLONASS satellite navigation system signal receiver, the RCC’s flight end uses its homing IR head and autonomous target recognition software and hardware, then the DPSW at a distance of 1263 km automatically returns to the ISM with vertical a helipad landing, while in the aforementioned SPSV and DPSV the glider is made of aluminum-lithium alloys and composite materials using an inconspicuous technology with a radio-absorbing coating, equipped in its lower part with a wheeled landing gear with retractable supports in three compartments and weapon launchers in the bomb bay, each of them which has two automatic flaps with sawtooth transverse sides, and the BSA OPSV is equipped with the option of its optional control by pilots from a two-seat cockpit, having seats ejected into the upper hemisphere, placed side by side and operating on GDP and freezing modes I take turns, but also using it as part of the aviation group as the head one together with the mentioned, for example, two DPSVs, one of which, being a slave, automatically repeats the maneuvers of the main DPSV in the next flight, and the other is controlled by the co-pilot from the head DPSV, and then and vice versa, while the control system for the formation of a relative position in a follow-up flight, containing one or more sensors located on the slave DPSV, is configured to detect data regarding its position relative to the position of the head SPSV having a flight control computer in operational condition with one or several sensors, containing an additional sensor computer, which is configured to: determine the relative position between the slave DPSV and the head SPSV; Compare the relative position with the selected relative position; determine the speed of the driven DPSV necessary to move it to the selected relative position; convert the tracking device speed to flight control inputs; to limit the direct movement of the DPSV slave relative to the head SPSV, which ensures their relative safe position in the joint flight through the inputs of his flight control computer, the main struts of the side wheels being retracted forward along the flight into the ewing fairings integrated with the profiled sides of the wings the fuselage, located between the UCS and the ASC, have front and top radio-transparent compartments for installing antennas in them with a data transmission / reception channel.

In addition, the said MNPC has three strong housings arranged horizontally next to each other so that two more strong housings are mounted side by side on the sides of the middle strong housings, each of which is made with a smaller diameter, which is 55% of the diameter of the larger housing, but also the ability submerge from underwater position to underwater and vice versa, as well as move under water or on water and in a semi-submerged state, the latter, along with the radio-absorbing coating of a streamlined central superstructure with tilted side panels, increases stealth and determines greater stealth compared to conventional surface ships, while the MNPK, the underwater part of the body of which is made in the form of a tunnel type with one area of the waterline, has on both sides of its axis of symmetry, together with its side buildings, a curved shape of the lower part of its body and is equipped with two arched longitudinal channels open at the bottom, forming seen from the front comb This configuration, parallel to the axis of symmetry, is equipped along the longitudinal axis of each channel with left and right direct-flow high-efficiency pump-type water-jet propulsors (VDNT) with rotary ejector nozzles at their exit, providing in the configuration of the surface trimaran ship with the maximum width of the aft part of the MNPC hull use or in the absence of an air gap in the area of the upper surface of each arch channel to exclude the influence of vertical shock loads in this area of each arch channel when driving on counter-waves, or in the absence of large waves after blowing the corresponding ballast tanks can move, increasing the speed at the same engine power and having a geometry with minimal wave impedance due to the fact that the outer walls of the arched channels in the MNPK housing are parallel to its axis of symmetry, forming the width of the MNPK deck with the external walls of the MNPK lateral housings in the area of the aft end are almost parallel to the axis of symmetry and, therefore, the rarefaction that occurs on the hull in this area along the sides, when moving at a speed corresponding to FrL≅0.5, will not affect the resistance of the MNPK hull, especially with the use of the front hydrofoils, moreover, a small-sized sonar complex MGK-13P "Pripyat-Pm" [5], as well as four PTA-53 torpedo tubes of 533 mm caliber, located in its first compartment with ammunition of eight torpedoes, are installed in the forward part of the MPNK, with a robust wheelhouse equipped for two front-side anti-aircraft missile systems AK-630M-2 Duet [6] and anti-aircraft missile and artillery 3M87 Kortik [7], which are retractable in the marching underwater position into containers inside the lightweight housing of the MPC, equipped along the longitudinal axis of the middle body in the continuation of the stern aviation strong hangar for placement in it on stationary V-shaped lodges in terms of fixing the front and two rear scaffolding of the chassis, for example, of two DPSV and OPSV located in tandem, having automatically strong corresponding manholes automatically opening from its rear end, while the strong hangar is equipped with a telescopic telescopic stand-lodgement, the lodgement of which fixes the nose underwing part of the same DPSV and OPSV with clamps unlocking the three DPSV / OPSV wheels on the corresponding V-shaped lodgement and raising the lodgement rack with its front wheel nose support, as well as the possibility of towing the rear wheels along the longitudinal rails parallel to the axis of the MPPI axis with the raised lodgement stand, forward or back with a fixed placement on the lodgement stand of the DPSV / OPSV with its fixed ONV and folded outer sections of the VSK, respectively, in the charging or charged marching configurations, and the middle strong body on its upper part behind the aft hangar is equipped with a horizontal runway (GVPP) having equal length the length of the DPSV / OPSV fuselage with rotating ONV and the forced drying system for its surface, but also in its center is the DPSV / OPSV mooring and forced vertical landing (UWB) system on the lodgement stand extended from the hangar, while the UWB aft, providing the possibility of landing the DPSV / OPSV on the MNPK lodgement stand with its rolls up to 25 ° and representing, when viewed from the rear, a U-shaped frame with telescopic side racks placed perpendicular to the longitudinal axis of the MNPK middle body, made with the possibility of its rotation in the vertical plane along the latter from horizontal to vertical position, equipped with infrared detectors at the top and in the middle of its crosspiece that interact with the corresponding infrared emitters DPSV / OPSV and automatically correct its maneuvers when landing using UWB, and a collet assembly with a cable passed through it with a developed ellipsoid thimble placed in centering node strictly along the cross member with its larger axis and the interaction Acting with the catch of the DPSV and OPSV deflected downward during landing, fixed under the center of its mass, and when the DPSV / OPSV is vertically mounted after hooking the hook and the thimble of the cable, it is wound / unwound through the sealed deck unit on the GVPP and is provided with a winch with a drum and a follower an electric drive installed under the center of the runway in an airtight container inside the lightweight housing, with the subsequent releasing of the cross-member of the cross member and simultaneously retracting the U-shaped frame racks and turning them to a horizontal position so that its cross member with the collet assembly sliding along the cable is lowered and placed in the corresponding deepening above the center of the GVPP, after which the DPSV / OPSV carries out a vertical landing on the lodgement rack with the cable winding at the same time, then after fixing the nose part of the DPSV / OPSV, its hook is disconnected from the thimble of the cable and the lodgement stand with the front wheel strut of the DPSV fixed to it / OPSV is towed on back wheels in vnutren l the hangar and, accordingly, the rear wheels are fixed and the front wheel is lowered onto the stationary V-shaped lodges in the fueling and ammunition loading positions, for example, APRs located in six-position transport drives (SHN) of a revolving type mounted on two SHTNs from each sides inside each lateral casing, while along the longitudinal axis of the middle casing between each pair of barrels mounted on both sides of the position of automatic reloading DPSV / SPSV in the hangar, a mechanical arm with a gripper is mounted, which ensures automatic removal of the APR from the unloading position of one of the cnc, turn upward at an angle of 90 ° in the vertical transverse plane and climb to the top into the open hatch of the hangar subfloor and the DPSV / OPSV bomb bay for its suspension on the automatic locks of fastening the beam holder, and after performing all of the above operations in the reverse order with automatic rolling out of the lodgement post from GVPP hangar fuel and ammunition DPSV / OPSV, rigidly held by the latches of the rear wheels on the GVPP and the front wheel on the lodgement rack until its load-bearing system reaches the required level of lifting force, then the locks of all the latches are simultaneously and automatically switched off and its vertical takeoff.

In addition, in the aforementioned OPSV and DPSV, the control system for the formation of their relative position in flight with one or more sensors includes one or more IR sensors, video sensors, radar, laser and ultrasonic sensors, sonars, global positioning sensors, while the flight control computer is made both with an additional computer for summing the sensor data and a data transmission channel located on the head OPSV for receiving global position data from the slave DPSV, and with the ability to convert images from each video sensor, which determines the relative position, which includes triangulation into determining 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 transmitting how many video streams, to ensure the collection of data from each video sensor, as well as to ensure the conversion of images from each video sensor to a relative position, which determines on the basis of the global position of the head SPSV transmitted to the slave SPSV, while the data summing computer is fully integrated into the pilot interface and the SPSV control system providing the aforementioned follow-up flight of the guided DPSV, which, if necessary, can be disabled by means of one of the inputs of the pilot interface for controlling the flight, activation by the pilot of a button or control switch, the data summing computer is additionally equipped with the possibility of its independent action, which determines that the flight of the SPSV is unsafe for its relative position from the slave DPSV, but also disabling the formation of the said follow-up flight by the slave DPSV through the flight control computer.

In addition, for an economical high-speed horizontal flight of the aforementioned OPSV and DPSV, each ONV in a synchronously-balanced carrier and autorotating system including an automatic gearbox in the said console gearbox having said output shafts for ONV drive, each of which creates two streams: the first one take-off with the issuance of the corresponding power from the corresponding turbojet engine and the creation of lifting thrust from the ONV, the second one is cruising in the gyroplane configuration with the power received from the autorotation of each ONV to its corresponding stage, disconnecting both ONVs from the CCT drive of the mentioned GTV, driving the generator and controlling the synchronous reduction and speed their rotation, for example, up to 200 min ^-1 or 100 min ^-1 , and the angle of attack of the blades of the autorotating ONV, providing a share of a 1 / 3-1 / 4 times increase in the required lifting force of the aforementioned PSK and VSK, but also by the plane of rotation of the ONV blades, which are nearly aligned with the corresponding airflow at speeds for low or high-speed flight, leading to a decrease in the rotational resistance of the ONV by 12-15% of the total profile resistance of the ONV blades during their self-rotation and the possibility for the cruise flight modes of calculating the mentioned PSK and VSK with their geometry reduced to 2 / 3-3 / 4 of the wing dimensions similar jet aircraft.

In addition, for horizontal flight at an altitude of 11 km of the aforementioned SPSV and DPSV, reaching marching thrust-to-weight ratio from 0.36 to 0.43, the power of their SU from 54% to 72% of the working KGTD is used to drive their WWII, the mentioned SSR of which, having along its front edge, the sweep angle χ = + 37 ° or χ = + 43 ° ensures a speed of Mach 0.725 (M) or 0.753 M, and when the marching thrust ratio reaches 0.54, the speed increases to M = 0.786 or M = 0.87 accordingly, each KGTD is equipped with an afterburner (FC) in the CCT in front of the IWT mechanism of its jet nozzle, the use of which with the front behind the WWII and the rear in front of the FC open controlled gondola wings for additional air supply to it during takeoff modes or horizontal flight at altitude 11 km with their overload of 15% achieve marching thrust-weight ratio up to 0.68 or speed up to M = 0.997 and M = 1.04, respectively, in the configuration of trans- and supersonic aircraft.

Due to the presence of these features, which enable one to master a low-crew NPC (MNPK) with an aircraft group of vertical take-off and landing vehicles in a PACA, which includes at least one optionally manned helicopter aircraft (OPSV) with at least one remotely piloted helicopter aircraft ( DPSV), which are used from at least one helipad MNPK, and each SPSV and DPSV made without vertical tailing on the integral layout of the flying wing of the duplicated scheme, which has the first and second swept wings (UCS and VSK), spaced from each other in in the longitudinal direction, and is equipped in a twin-screw transverse-bearing circuit (DPS) with single-blade rotors (ONV) with their counterweights mounted on profiled UCS pylons and wing gondolas, structurally combining UCS with VSC, creating vertical thrust in DPS-X2 only with vertical thrust and short take-off / landing (GDP and KVP) or in transitional flight modes, but also equipped with at least e than a pair of combined gas turbine engines (KGTD), the left and right of which are installed in the corresponding wing nacelle and made in the form of a dual-circuit engine having external and internal circuits, respectively, with an external single-row fan (BOB) in the annular cowl and at least one a free power turbine (CCT), having a round nozzle with all-angular control of the thrust vector (WHWT), transmitting the take-off power of the combined power plant (SU) through the transmission system to the appropriate ONV in a symmetrically balanced DPS-X2 and / or WWII, with blades with a large their twisting, working according to the pulling pattern, creates in the propulsive-reactive system (PRS-R2) synchronous reactive thrust during vertical and short take-off / landing (GDP and KVP) or horizontal translational flight, but it is also equipped in the hollow circuit with different-sized PSK and VSK, having a span of 1.04 and 1.965 times, respectively, more than the NVM diameter (D) at a straight sweep angle and along the leading edge of the VSC, for example, χ = + 37 ° or χ = + 43 °, which is equal to the sweep angle along the leading edge of the UCS, which has front arches that form a V-shaped configuration with its large excellent sweep angle from UCS, the rear the edge of which is parallel to the rear edge of the outer sections of the VSK, the span of the inner sections of the latter is equal to the span of the UCS, placed in the plan at the angle of the reverse sweep along the rear edge of the inner sections of the VSK, forming a profiled aft part with a V-shaped rear edge in the plan, and integrated with wing gondolas mounted for the most part under or above PSK and VSK, increasing their rigidity, counteracting the harmful effects of divergence, especially of the external sections of VSK, but it is also capable of transforming its flight configuration after performing short or vertical take-off technology, respectively, from a rotorcraft or helicopter at its maximum or normal take-off weight in accordance flying rocket fast winged gyroplane or aircraft with transverse NVG operating in the modes of their autorotation or as bearing wide-chord wing-blades (SLK) formed by fixing the NVG with their counterweights or transforming their counterweights sequentially during transitional flight modes, when after vertical / short take-off, climb and acceleration flight, both ONVs are simultaneously pre-stopped so that their counterweights and blades are fixed in plan, respectively, from the end of the UCS inward to and outward from the axis of symmetry, or when the SLK is stopped, their profiled counterweights are equipped with automatic synchronous folding by turning to the appropriate angles 127 ° or 133 ° in the horizontal plane and placing them back along the flight and parallel to the axis of symmetry when fixing with the corresponding sweep along the front edge of the SLK of the left and right ONV, which form with UCS and VSK equal in front edge their sweep and organize accordingly synchronously-symmetrical bearing surfaces of their SLK in the flight configuration of a jet aircraft with PRS-R2 and a system of step multilevel wings (SSRK), but also vice versa. All this will make it possible to simplify the controllability and ensure its stability in reactive OPSV and DPSV with PSK, VSK and in the presence of HLWT round jet nozzles of their QGTD. In cruise flight in the configuration of a jet gyroplane and an aircraft with symmetrically balanced, respectively, autorotating and carrier systems, the first of which is equipped with a multi-speed automatic gearbox that controls both the reduction of the speed of the ONG rotation to 200 min ^-1 or 100 min ^-1 , and the angle of attack of the blades NVG, but also by the plane of their rotation, which are almost aligned with the corresponding air flow at speeds for low- or high-speed flight. Which, with a decrease in rotational drag by ONG by 15%, leads to the possibility of calculating its PSK and VSK for cruise flight with a reduced geometry of 2/3-3/4 of the wing dimensions of a similar aircraft. Placing a QGTD in wing nacelles will allow the flying wing in the layout how to make the supporting fuselage with its profile in thickness sufficient only to accommodate the internal arms bays, which will reduce its aerodynamic drag, and to achieve in the configuration of a jet gyroplane / airplane with barrage / horizontal flight speed 550/924 km / h, but also in afterburner modes in the transonic aircraft configuration, to ensure at a flight altitude of 11 km its flight speed is up to 1060 ... 1105 km / h.

The present invention is the preferred MNPK with reactive DPSV hollow circuit with PSK and VSK and their sweep along the leading edge χ = + 43 °, two QGTD, having in each CCT with WHWT jet nozzles installed in wing gondolas, combining PSK and VSK, leading in the annular two WWII fairings in PRS-R2 and in DPS-X2 two ONV mounted at the ends of the UCS are illustrated in FIG. 1 and general views of the front and top, respectively a) and b):

a) in the flight configuration of a winged gyroplane or a jet aircraft with UCS and ASC creating a higher lift force than the lift created by the autorotating ONV or fixed by their SSRK, and two KGTD with the Second World War, located in the nacelles, creating a marching thrust in PRS-R2 high-speed or transonic flight with the conditional placement of the right ONV autorotating outward with its profiled counterweight or fixed outward from the UCS and in front of the left ONV in the SSRK with its counterweight folded along the axis;

b) in the flight configuration of a helicopter or a jet airplane with UCS and ASC with their slats and flaps deflected, reducing the shadowing by 7% of the working transverse CIRs, creating lift when performing GDP and hovering or transonic flight with conditional placement fixed outward from the UCS and before The VSC of the left ONV in its SSRK with its counterweight folded along the axis of symmetry and working WWII with the VVVT of their jet nozzles, creating a marching thrust in the PRS-R2, driven from two QGTDs with two working FTAs.

In FIG. 1c shows MNPK 20 in three projections with PACS in the landing configuration of the DPSV 21 using the rotary U-shaped frame 22 of the UWBWS on the lodgement stand 23 of the satellite table 24, moving inside the first hangar 25 and lowered to stationary V-shaped lodgements 26 on parking positions when 17-18 ONV and external sections 7 of VSK 4 are laid down for transportation, refueling and ammunition loading at each station, including the second hangar 27 and the subsequent rolling out of the satellite table 24 with the rear DPSV 21 from hangar 27 on the GVPP 28 with unfolded external sections 7 VSK 4 and the blades of the left 17 and right 18 ONV for its vertical subsequent take-off from GVPP 28 MNPK 20.

The transonic DPSV in the composition of the PAHC based on the MNPC is presented in FIG. 1a and b, made according to the concept of DPSN-X2 with PRS-R2, has an airframe made of aluminum alloys and composite carbon fiber in the integrated layout of the flying wing of the hollow plan, contains a carrier fuselage (NF) 1, PSK 2 with its slats 3 and front influxes 4 and VSK 5 with inner flaps 6. Between PSK 2 and VSK 5 and on the wing spans of NF 1, elytral fairings 7 of the main landing gear wheels are mounted. The outer sections 8 of the VSK 5, folding upwards for their parking in the parking space above its inner sections 5, form a V-shaped planar rear edge thereof with a profiled stern 9 equipped with a feed fairing 10 along the symmetry axis, having a retractable magnetometer rod and lowered by a winch and the antenna of a hydroacoustic station towed on a cable under water (not shown in Fig. 1). Each QGTD with CCT is installed in the wing nacelle 11, which unites the consoles of PSK 2 and VSK 5, drives the BOB 12 in an annular cowl having an air inlet with an adjustable conical body 13 screening the blades of the BOB 12. Each KGTD with the BOB 12 and CST has a VUVT of a round jet nozzle 14 and front and rear guided flaps 15 of the nacelle for additional air inlet therein. At the ends of UCS 2, the eavesdropping pylons 16 with left 17 and right 18 NVGs are mounted, having their opposite clockwise and counterclockwise rotation, respectively, to fully compensate for the reactive torque in the GDP and hovering modes, are made with a swashplate and their blades 17- 18 and profiled counterweights 19. The ONV 17-18 cantilever gearboxes are located in profiled wing pylons 16, the output vertical shafts of which are equidistant in plan from the center of mass and are tilted back along the flight by an angle (α), which is 1/2 of the angle of attack (α ) UCS 2.

The combined control system includes two gas turbine engines, which have a CCT with a rotationally active rotary engine of their jet nozzles 14, are equipped with a front shaft output for selecting their power and the possibility of transmitting take-off power from them to cantilever gearboxes (not shown in Fig. 1) of transverse ONV 17-18, which transmit 100% or for intermediate gearboxes 36 ... 54% of the NVG 17-18 on the take-off power of the SU when fulfilling GDP and hovering or horizontal forward cruising flight between respectively two NVGs 17-18 in DPS-X2 or two WWII 12 in PRS-R2, respectively.

The control of the transonic DPSV is provided by the cyclic, general and differential variation of the ONV pitch 17-18, as well as the in-phase and differential deviation of the jet nozzles 14 with the VHWT in the gas turbine engine. When cruising a high-speed or high-speed flight in the configuration of a winged gyroplane or a jet aircraft, the lifting force is created by autorotating ONV 17-18 with PSK 2 and VSK 5 or PSK 2 and VSK 5 with fixed ONV 17-18 (see Fig. 1b) in SSRK, respectively marching jet thrust - with the PRS-R2 system through jet nozzles 14 with VUVT in KGTD mounted in nacelles 11, in the transition mode - PSK 2 and VSK 5 with ONV 17-18. After the ONV 17-18 lifting thrust is created in the DPS-X2, the GDP and freezing or KVP regimes are ensured when the reactive nozzles 14 with the VWT in the QGTD create the required marching thrust for the translational flight (see Fig. 1a). When performing GDP and freezing, a change in the balance in pitch, roll, and course is ensured by a change in the corresponding cyclic step and a differential change in the thrust of the total step of left 17 and right 18 ONV in DPS-X2 (see Fig. 16). After vertical take-off and climb, an overclocking flight is performed at speeds of more than 300 ... 350 km / h and a corresponding reduction in the rotational speed of the NVG 17-18 is carried out. As you accelerate with an increase in the lifting force of PSK 2 and VSK 5, the lifting force of the ONV 17-18 decreases. When reaching flight speeds of 400 ... 450 km / h and to switch to the airplane flight mode, the NVG 17-18 synchronously stop so that their wing blades 17-18 are preliminarily placed when viewed from above parallel to the front edge of the UCS 2, which then synchronously stop so that ONV 17-18 are fixed in the SSRK with a direct sweep along their leading edges, forming an equal sweep χ = + 43 ° with UCS 2 (see Fig. 1b). When creating jet thrust with round jet nozzles 14, a high-speed cruise flight of the DPSV is performed, in which the change in the balance in pitch, heading and roll is ensured by the corresponding deviation of the jet nozzles 14 with all-angular control of the thrust vector of each CGTD.

The inconspicuous MNPK 20 with front hydrofoils 29, presented in three general views with the necessary sections of its body in FIG. 1c, it has three strong different-sized enclosures, two strong smaller 30 enclosures of which are mounted with an average large 31 side by side, forming the underwater part of its tunnel-type enclosure 32, equipped with a left 34 and a right 35 direct-flow highly efficient VDNT in the aft part of the longitudinal longitudinal channels 33 rotary ejector nozzles 36 at their exit. With a vertical landing of the ДПСВ 21 after hooking of the hook 37 and thimble 38 of the cable 39, wound by a winch 40 with a drum and its follower electric drive, mounted under the center of the GVPP 28 in an airtight container, the U-shaped frame racks 22, which, after turning it down to the horizontal position , fits into a recess above the center of the GVPP 28. Then, simultaneously with the winding of the cable 39 on the winch 40, the DPSV 21 performs a vertical landing on the raised stand-cradle 23, the cradle 24 of which fixes the nose underwing part of the same DPSV 21 with clamps.

At the ammunition loading position, for example, APRs located in the ShTN 41 revolver type, mounted on two ShTN 41 on each side inside each side 30 of the MNPK case. Along the longitudinal axis of the middle housing 31 between each pair of SHTN mounted on both sides of the automatic reload position of the DPSV 21 in each of the hangars 25, 27, a mechanical arm 42 with a grip 43 is mounted, providing automatic removal of the APR 44 from the unloading position from the ShTN 41, it turning upward at an angle of 90 ° in the vertical transverse plane and rising to the top into the open hatches of subframe 45 of hangars 25, 27 and the bomb bay of DPSV 21 for its suspension on automatic fastening locks (not shown in Fig. 1c).

Thus, a transonic OPSV and DPSV of a hollow circuit with PSK and VSK, two KGTD with SST, having for the creation of horizontal thrust two WWII in PRS-R2 and vertical thrust two ONV in DPNS-X2 or lifting force, respectively, with operating ONV or their fixed SSRK , is a tiltrotor with DPS-X2 and PRS-R2, which changes its flight configuration only due to a change in operating conditions and fixation of the ONV by means of the fact that the incoming flow at the vertical and horizontal flight modes meet simultaneously the front edges of the oncoming vanes of the ONV and their fixed SLK, increasing bearing capacity of SSRK, performing the role of its upper sections.

The integrated layout of the flying wing of the hollow circuit with PSK and VSK increases the aerodynamic and structural advantages when converted to a transonic aircraft with SSRK, especially with the presence of additional SLK transverse ONV fixed at the ends of the PSK with the same sweep. This will reduce the weight of the DPSV glider, made by a low-tech technology with radar absorbing materials, increase take-off weight by 17% or flight range by 29% while maintaining take-off weight and ensure reconnaissance and strike operations in the configuration of a winged gyroplane at a speed of 550 km / h. An aviation group consisting of PAUK, including the same type of SPSV and DPSV (see Table 1, type 1.2), used alternately from the helipad of the MNPK, carrying 3/4 pieces of APR-3ME or anti-ship missiles of the X-35UE type in the weapon compartments of the OPSV / DPSV. In PACS, the head-mounted APSV, which is fully digitized using the latest technologies, including the joint use of manned and unmanned aerial vehicles, the so-called manned and unmanned teaming (MUM-T), which allows PPSV pilots to control the DPSV and control the flight path of a group of DPSV and their combat load, providing anti-submarine or anti-ship and / or anti-aircraft defense. The fourth MUM-T level used in the PACS allows the pilots of the main SPSV not only to receive real sensory images from the air group of the DPSV slaves and to control sensory and weapon loads, but also their navigation and global positioning during the follow-up joint safe flight.

Undoubtedly, the widespread use in the combined control system of two gas turbine engines with WWII, in the design of which, using turbines from turbofan engines. AL-31F will allow to master the family of transonic SPSVs and DPSVs (see Table 1) for multi-purpose PAUKs based on low-visibility MNPKs, increasing their combat stability and safety, creating a buffer airspace between the NK-target air defense and the MNPK aircraft carrier.

Sources of information:

1. Internet address: https://navy-chf.livejournal.com/1433004.html

2. Internet address https://en.wikipedia.org/wiki/BAE_Systems_Taranis

3. Internet address: http://rbase.new-factoria.ru/missile/wobb/ikara/ikara.shtml

4. Internet address: https://www.nasha-strana.info/archives/25587

5. Internet address: https://booksbunker.com/an_gusev/59167/280.html

6. Internet address: http://zonwar.ru/news/news_95_Duet.html

7. Internet address: https://topwar.ru/4864-tulskiy-kashtan.html

Claims (6)

1. A surface-submarine ship (NPK) with a deck-based aircraft strike complex (PAUK) containing an unmanned aerial vehicle having a fuselage with a detachable guided missile, a mid-wing with its controls, an engine, an onboard control system (BSU), providing telemechanical control ( TMU) from the command post (CP) NPK, characterized in that the low-crew NPK (MNPK) with an aircraft group of vertical take-off and landing apparatus in a PACM, including at least one optionally manned helicopter aircraft (APSV) with at least one remotely piloted aircraft - a helicopter (DPSV), which are used from at least one helipad of MNPK, and each of the DPSV and DPSV is made without vertical empennage according to the integral layout of a flying wing of a hollow pattern that has first and second swept wings (UCS and VSC) spaced in the longitudinal direction, and is equipped in a twin-screw transverse-bearing circuit (DPS) single-blade main rotors (ONV) with their counterweights mounted on profiled UCS pylons and wing gondolas, structurally combining UCS with VSC, creating vertical thrust in DPS-X2 only during vertical and short take-off / landing (GDP and KVP) or in transition modes flight, but also equipped with no less than a pair of combined gas turbine engines (KGTD), the left and right of which are installed in the corresponding wing nacelle and made in the form of a dual-circuit engine having external and internal circuits, respectively, with an external single-row fan (BOB) in the annular cowl and at least one free power turbine (CCT) having a round nozzle with all-angular control of the thrust vector (VHWT) transmitting the take-off power of the combined power plant (SU) through the transmission system to the corresponding ONV in a symmetrically balanced DPS-X2 and / or BOB, having blades with a large twist, working according to the pulling pattern, creates a prop Ulsive-reactive system (PRS-R2) synchronous reactive thrust during vertical and short take-off / landing (GDP and KVP) or horizontal translational flight, but is also equipped in a hollow pattern with different-sized PSK and VSK, which have a span of 1.04 and 1.965 times, respectively more than the ONV diameter (D) at an angle of direct sweep along the leading edge of the VSC, for example, χ = + 37 ° or χ = + 43 °, which is equal to the angle of sweep along the leading edge of the VSC, which has front arches that form a V-shaped configuration with large its excellent sweep angle from the UCS, the trailing edge of which is parallel to the rear edge of the outer sections of the VSC, the span of the inner sections of the latter is equal to the span of the UCS, placed in the plan at the angle of the reverse sweep along the rear edge of the inner sections of the VSC, forming its profiled stern with V figurative in plan view with a trailing edge, and integrated with wing gondolas, mounted for the most part under or above PSK and VSK, increasing their weight precision, counteracting the harmful effects of divergence, especially of the outer sections of the VSK, but also made with the possibility of converting its flight configuration after performing short or vertical take-off technology, respectively, from a rotorcraft or helicopter with its maximum or normal take-off weight into corresponding jet high-speed winged gyroplane or aircraft with transverse NVGs operating under their autorotation regimes or as wide-chord wing-blades (SLKs) carrying them, formed when NVGs are fixed with their counterweights or their counterweights are transformed in transitional flight regimes sequentially when, after vertical / short take-off, climb and execution During a booster flight, both ONVs are simultaneously preliminarily stopped so that their counterweights and blades are fixed in plan, respectively, from the end of the UCS inward to and out of the axis of symmetry or when the SLK is stopped, their profiled counterweights are equipped with automatic assemblies synchronously folding them by turning to the appropriate angles 127 ° or 133 ° in the horizontal plane and placing them back along the flight and parallel to the axis of symmetry when fixing with the corresponding sweep along the front edge of the SLK of the left and right ONV, which form with the UCS and VSK equal in front edge their sweep and organize accordingly synchronously-symmetrical bearing surfaces of their SLK in the flight configuration of a jet aircraft with PRS-R2 and a system of step multilevel wings (SSRK), but also vice versa. 2. A ship with a complex according to claim 1, characterized in that in the transmission system of the mentioned SPSV and DPSV each of their KGTD, for example, with one SST, which has a front shaft output mounted on the longitudinal axis of its nacelle for selection of its take-off power, in which between the abovementioned WWII and CCT, a T-shaped intermediate gearbox is mounted coaxially with the latter, both in a plan view and on the side, having a longitudinal input shaft from the CCT and output both a front longitudinal and a transverse side, but also an upper shaft, the first of which transmits power through the clutch on the WWII, the annular cowling of which has an air intake adjustable with a conical central body, the second synchronizing one, laid in the air-tight fitting, rotationally connects the CCT of two CGTDs, and the third transfers the torque through the clutch to the input shaft of the corresponding ONV cantilever gearbox located in the overhead pylon has an output shaft, which is placed in plan on the transverse axis passing through the center of mass, and equidistant yen from the center of mass, but also deflected backward along the flight by an angle (α), which when viewed from the side is 1/2 or equal to the value of the angle of attack (α), respectively, of the UCS or VSC, and the incident flow in both their vertical and horizontal flight modes is met simultaneously accordingly, the leading edges of the upcoming ONV blades in the aforementioned DPS-X2 and their mentioned SLV ONGs, which act as the upper ones with a tiered arrangement of the outer sections of the UCS in the aforementioned CACS, transforming moderate elongation of the UCS and large CSC with λ = 5.34 ... 5.39 λ = 7.9 ... 8.0 to the extension of the SSRK with λ = 4.88 ... 4.96, and the inter-nacelle sections of their PSK and VSK are equipped with slats and internal flaps, respectively, used for take-off and landing or transitional flight modes of the SPSV and DPSV and the aforementioned round nozzles with VWHT of their CCT are provided with the possibility, when they are in phase and differential, synchronously deflect both vertically up or down, both horizontally left or right and vertically one up, and each move downward, respectively, to balance the pitch, heading and roll with horizontal translational flight of the SPSV and DPSV, while the mentioned SPSV and DPSV on their GDP regimes and hovering in the aforementioned DPS-X2 left and right ONV, having the opposite direction of their rotation, respectively, clockwise and counterclockwise, made with rigid fastening of their blades and their swash plate, providing a change in pitch, heading and roll balancing, which is created by changing the corresponding cyclic pitch and differential change in traction through the common pitch of the said ONV, respectively, and their outer sections of the said VSK have their tips at the front and rear at their ends correspond to infrared (IR) emitters and heat chambers, and after vertical landing on the helipad of the MNPK of the mentioned OPSV and DPSV, the convertible system of the bearing surfaces of each of them has the ability to pre-stop their ONV blades along the PSK and p placing them with the tips to the axis of symmetry with the subsequent folding of their counterweights when they are located forward along the flight and parallel to the axis of symmetry, and synchronously folding up the outer sections of the VSK located above its outer sections, but also transporting them in the MNPK hangar with a decrease of 1, 8 ... 2.0 times the area of their marching configuration from their take-off area, and their mentioned VSK, having, with a ratio of its area of 56.6% ... 57.1% of the sum of the areas of all bearing surfaces, including the areas of the mentioned PSK and VSK with their bearing fuselage and SLK of two ONGs, equipped with a feed fairing from its trailing edge along the axis of symmetry, having a compartment with a retractable bar of the magnetometer at its end and a winch lowering the shutters and an antenna of the hydro-acoustic station towed on a cable under water during its flight at the same time, the aforementioned SPSVs and DPSVs carrying aircraft anti-submarine and anti-ship missiles (APR and anti-ship missiles) provide there is a struggle against a submarine (PL) and a surface ship (NK), and in anti-submarine defense the aforementioned SPSV and DPSV use a lowered hydroacoustic system consisting of an indicator of acoustic signals and two receivers for their reception from the hydroacoustic antenna, their coding and transmission over eight-channel closed communication at the ISTC for real-time processing or a highly sensitive magnetometer having a magnetically sensitive element operating at a distance of 30 m from the water surface, and connected with the BSU in the mentioned OPSV and DPSV, providing for issuing commands to turn on the magnetometer at the calculated point and to control after magnetometer triggering upon detection of a PL target, but also recording in the BSU memory the coordinates of the detection point of a PL target during transmission to the MPD and its gearbox, while in the mentioned SPSV and DPSV, their BSU has both a closed-circuit radio channel and a radar station with command transmitter, optoelectronic a new system with a two-channel target tracking automaton and a computer system with an automation unit for a multifunctional control panel, which ensures independent identification of the PL target during barrage flight, its identification, and the adoption of a confirmed decision from the operator of an ISMP about destroying the ones he chose, and with anti-ship defense, the mentioned SPSV and DPSV, using the flight configuration of the aforementioned jet aircraft with fixed ONV SLKs carrying the corresponding Kh-35U or Kh-38M anti-ship missiles in the bomb bay to create a buffer safe airspace between the main anti-aircraft missile and the NK target air defense, increasing the radius of the Kh-38M / Kh-35U anti-ship missiles with 40/130 to 400 km, while target type radar is provided from the NPS36 radar from the main SPSV, and control of the DPSV-second pilot of the SPSV using the low-altitude flight profile and self-defense system is the station of active electronic interference of the DPSV, and when reaching the area from which the NK will be hit -the target mentioned by the DPSV will fire a volley or at the next launch of anti-ship missiles with the correction of the error accumulated by the combined inertial control system according to the data of the GLONASS satellite navigation system receiver, at the final missile flight section, its homing IR head and autonomous target recognition software and hardware are used, then the DPSW at a distance of 1263 km automatically returns to MNPK with a vertical landing on its helipad, while in the aforementioned SPSV and DPSV the glider is made of aluminum-lithium alloys and composite materials using low-visibility technology with a radio-absorbing coating, equipped in its lower part with a wheeled chassis with retractable supports in three compartments and weapon launchers in the bomb compartments, each of which has two automatic flaps with sawtooth transverse sides, and the FSB OPSV is equipped with the option of its optional control by pilots from a two-seat cockpit, which has ejected into the upper hemisphere seats placed side by side and a sling which alternate in the GDP regimes and hangs, but also of its use as part of the aviation group as the head one together with the aforementioned two DPSVs, one of which, being a follower, automatically repeats the maneuvers of the main DPSV in the next flight, and the other is controlled by the co-pilot the head SPSV, and then vice versa, while the control system for the formation of a relative position in the follow-up flight, containing one or more sensors located on the slave DPSV, is configured to detect data regarding its position relative to the position of the head SPSV having a flight control computer located in operating condition with one or more sensors, containing an additional sensor computer, which is configured to: determine the relative position between the slave DPSV and the head SPSV; Compare the relative position with the selected relative position; determine the speed of the driven DPSV necessary to move it to the selected relative position; convert the tracking device speed to flight control inputs; to limit the direct movement of the DPSV slave relative to the head SPSV, which ensures their relative safe position in the joint flight through the inputs of his flight control computer, the main struts of the side wheels being retracted forward along the flight into the ewing fairings integrated with the profiled sides of the wings the fuselage, located between the UCS and the ASC, have front and top radio-transparent compartments for installing antennas in them with a data transmission / reception channel. 3. The ship with the complex under item 1, characterized in that the said MNPK has three strong hulls located horizontally side by side so that two more hull hulls are mounted side by side from the middle strong hull, each of which is made with a smaller diameter, making up 55% of the diameter of the larger hull, it is also capable of diving from the above-water position to the underwater and vice versa, as well as moving underwater or on water and in a semi-submerged state, the latter, along with the radar absorbing coating of the streamlined central superstructure having tilted side panels, increases stealth and predetermines greater secrecy in comparison with a conventional surface ship, while the MNPK, the underwater part of the hull of which is made in the form of a tunnel type with one waterline area, has on both sides of its axis of symmetry, together with its lateral hulls, a curved shape of the lower part of its hull and is equipped with two open bottom arched longitudinal channels located When forming a ridge configuration when viewed from the front, parallel to the axis of symmetry, it is equipped along the longitudinal axis of each channel with left and right ramjet high-performance pump-type water-jet propulsors (VDNT) with rotary ejector nozzles at their exit, providing in the configuration of a surface trimaran ship with a maximum width the aft part of the MNPC hull, the possibility of using it either in the absence of an air gap in the region of the upper surface of each arched channel to exclude the influence of vertical shock loads in this region of each arched channel when moving on counter-waves, or in the absence of large waves after blowing the corresponding ballast tanks, increasing the speed at the same engine power and having a geometry with minimal wave impedance due to the fact that the outer walls of the arched channels in the MNPK housing are parallel to its axis of symmetry, forming the width of the MNPK deck with the external the shafts of the lateral shells of the MNPC in the aft end area are almost parallel to the axis of symmetry and, therefore, the rarefaction that occurs on the housing in this region along the sides when moving at a speed corresponding to FrL≅0.5 will not affect the resistance of the housing of the MNPC, especially with using front hydrofoils, the MGK-13P Pripyat-PM small-sized sonar complex and five PTA-53 torpedo tubes of 533 millimeter caliber placed in its first compartment with ammunition of eight torpedoes, with a solid cabin equipped behind it and in front with complexes, respectively, of two airborne anti-aircraft AK-630M-2 Duets and anti-aircraft missile and artillery 3M87 Kortik, which are retractable in stowed underwater position in containers inside the light housing of the MNPK, equipped with a stern along the longitudinal axis of the middle body durable aviation hangar for placement in it on stationary V-shaped in terms of lodges fixing x front and two rear wheels of the chassis, for example, two DPSV and OPSV arranged in tandem, having automatically strong corresponding manholes automatically opening from its rear end, while the durable hangar is equipped with a retractable telescopic lodgement stand, the lodgement of which fixes the nose underwing part of the same DPSV and OPSV , has the ability after unlocking the three wheels DPSV / OPSV on the corresponding V-shaped lodgement and raising the lodgement rack with its front wheel nose support, and the possibility of towing the rear wheels along the longitudinal guides placed parallel to the axis with the raised lodgement rack MNPK symmetry, forward or backward, with fixed placement on the lodgement stand of the DPSV / OPSV with its fixed ONV and the folded outer sections of the VSK, respectively, in the charging or charged marching configurations, and the middle strong body on its upper part behind the aft hangar is equipped with a horizontal take-off and landing platform (GVPP) having a length equal to the length of the DPSV / OPSV fuselage with rotating ONV and the system of forced drying of its surface, but also in its center the mooring system and forced vertical landing (UWS) DPSV / OPSV on the lodgement stand extended from the hangar, while the aft UWB providing the possibility of landing DPSV / OPSV on the MNPK lodgement stand with its rolls up to 25 ° and representing, when viewed from the rear, a U-shaped frame with telescopic side racks placed perpendicular to the longitudinal axis of the MNPK middle body, made with the possibility of its rotation in a vertical plane along the last horizontal to vertical position, equipped with infrared detectors at the top and in the middle of its crosspiece that interact with the corresponding DPSV / OPSV infrared emitters and automatically correct its maneuvers when landing using UWBW, and a collet assembly with a cable passed through it with a developed ellipsoid thimble placed in the centering unit strictly along the cross member b its larger axis and interacting with the grasp of the DPSV and OPSV deflected downward when landing the hook fixed under the center of mass, and when the DPSV / OPSV is vertically seated after the hook and the thimble are hooked, it is wound / unwound through the sealed deck unit on the GVPP and is provided with a winch with the drum and its follower electric drive, installed under the center of the runway in an airtight container inside the lightweight housing, with the subsequent releasing of the collet assembly of the cross member and simultaneously pulling the U-shaped frame racks and turning it to a horizontal position so that its cross member with the collet assembly sliding down the cable goes down and placed in a corresponding recess above the center of the GVPP, after which the DPSV / OPSV carries out a vertical landing on the lodgement rack with the cable winding at the same time, then after fixing the nose part of the DPSV / OPSV, its hook is disconnected from the thimble of the cable and the lodgement stand with it fixed on it front wheel strut DPSV / OPSV is towed on and the rear wheels are fixed inside the hangar and the rear wheels are fixed and the front wheel is lowered onto the stationary V-shaped lodges in the fueling and ammunition loading positions, for example, APRs located in six-position transport drives (SHN) of a revolver type mounted on two barrels on each side inside each side casing, while along the longitudinal axis of the middle casing between each pair of barrels mounted on both sides of the position of automatic reload DPSV / SPSV in the hangar, a mechanical arm with a grip is mounted, which ensures automatic removal of APR from the unloading position of one from SHTN, its rotation upward at an angle of 90 ° in the vertical transverse plane and rise to the top into the open hatch of the hangar subfloor and the DPSV / OPSV bomb bay for its suspension on the automatic locks of fastening the beam holder, and after performing all of the above operations in the reverse order with automatic rolling lodgement racks from a Ngara at the gas-powered engine runway filled with fuel and with the DPSV / OPSV ammunition kit, which is rigidly held by the rear wheel clamps on the GVPP and the front wheel on the cradle until its load-bearing system reaches the required level of lift, then the locks of all the latches are automatically and automatically disabled it takes off vertically. 4. The ship with the complex according to claim 2, characterized in that in the mentioned OPSV and DPSV, the control system for the formation of their relative position in flight with one or more sensors includes one or more IR sensors, video sensors, radar, laser and ultrasonic sensors , sonars, global positioning sensors, while the mentioned flight control computer is made both with an additional computer for summing the sensor data and a data receiving and transmitting channel located on the head SPSV for receiving global location data from the slave DPSV, and with the ability to convert images from each a video sensor providing the determination of the relative position, which by means of triangulation includes determining the relative range, azimuth and elevation, the additional computer for summing the sensor data and the data transmission channel has multiband radio-frequency equipment with a directional antenna, the auxiliary channel through closed communication channels to transmit several video streams, to collect data from each video sensor, and also to provide conversion of images from each video sensor to a relative position, which determines based on the global position of the head OPSV transmitted to the slave DPSV, while the data summing computer is fully integrated into the pilot’s interface and the SPSV control system, which provides the mentioned tracking flight of the guided DPSV, which, if necessary, can be disabled via one of the inputs of the pilot’s interface for flight control, pilot activation 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 of the SPSV is unsafe for its relative position from the slave DPSV, but also disabling the formation of the mentioned follow-up flight by the slave DPSV through the flight control computer. 5. A ship with a complex according to any one of paragraphs. 1-3, characterized in that for an economical high-speed horizontal flight of the mentioned SPSV and DPSV, each ONV in a synchronously-balanced carrier and autorotating system including an automatic transmission in said console gearbox having said output shafts for ONV drive, each of which creates two streams: the first is take-off with the issuance of the corresponding power from the corresponding turbojet engine and the creation of lifting thrust from the ONV, the second is cruising in the gyroplane configuration with the power received from the autorotation of each ONV to its corresponding stage, disconnecting both ONVs from the CCT drive of the mentioned GTV, leading the generator and controlling a synchronous decrease and their rotation speed, for example, up to 200 min ^-1 or 100 min ^-1 , and the angle of attack of the blades of autorotating ONV, providing a share of a 1 / 3-1 / 4 times increase in the required lifting force of the aforementioned UCS and VSC, but also plane of rotation of the blades ONV, which are almost aligned with the corresponding air flow at speeds for low- or high-speed flight, leading to a decrease in the rotational resistance of the ONV by 12-15% of the total profile resistance of the ONV blades during their self-rotation and the possibility for cruising flight modes of calculating the mentioned UCS and VSC with their geometry reduced, which is 2 / 3-3 / 4 from the wing dimensions of a similar jet. 6. A ship with a complex according to any one of paragraphs. 1-3, characterized in that for a horizontal flight at an altitude of 11 km of the mentioned HPS and DPSV, reaching marching thrust-weight ratio from 0.36 to 0.43, the power of their control system is used from 54% to 72% of the working KGTD to drive their WWII, the aforementioned SSRs of which, having a sweep angle χ = + 37 ° or χ = + 43 ° along its front edge, provides a speed of Mach 0.725 (M) or 0.753 M, and when the marching thrust ratio reaches 0.54, the speed increases to M = 0.786 or M = 0.87, respectively, with each QGTD equipped with an afterburner chamber (FC) in front of the VWT mechanism of its jet nozzle, the use of which with the open behind the WWII and rear in front of the FC open controlled gondola wings for additional air supply to it during take-off modes or horizontal flight at an altitude of 11 km will allow, with their overload of 15%, to achieve marching thrust-weight ratio up to 0.68 or speeds up to M = 0.997 and M = 1.04, respectively, in the configuration of trans- and supersonic aircraft.

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