RU2717280C1 - Aeronautical reconnaissance-strike system - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to aircraft engineering, particularly, to antiship and anti-submarine defense systems. Decade aircraft reconnaissance-strike system includes optional and remotely piloted aircraft-helicopters of an integrated layout including a wing of a tandem circuit, having the first arrow-like and the second trapezoidal wings (FAW and STW). At ends of wings there are single-bladed rotors (SBR) with counterweights and two wing nacelles that combine FAW and STW. In the nacelle there are free power turbines bringing four SBR, in the annular fairings the external fans creating at the vertical and short takeoff/landing the propulsive thrust directed horizontally backwards. Aviation guided missiles are placed in the bomb compartment on launching devices. After boarding the ship, the helicopters are switched to the field-charging configuration by means of fixed location of the SBR blades along the FAW and STW consoles and their counterweights.

EFFECT: higher probability of destruction of surface, underwater target located at long range.

5 cl, 1 dwg, 1 tbl

Description

The invention relates to carrier-based aircraft reconnaissance and strike systems, including optionally and remotely piloted integrated helicopters, including a tandem flying wing, having a first swept and second trapezoidal wings (UCS and VTK) and at their ends single-blade main rotors (ONV with) counterweights and two wing gondolas, combining PSK and VTK, having free power turbines, leading four ONV and in annular fairings, external fans that create vertical and short takeoff / landing (propulsion and airborne landing gear) propulsion-jet thrust directed horizontally backward with working / autorotating ONV or their fixed wing blades from PSK and VTK to the outside during horizontal flight with an all-angle change in the CCT thrust vector in the configuration of a rotorcraft / gyroplane or transonic an aircraft having aviation guided missiles in the bomb bay on launching devices and transformed after landing on the ship’s landing site by means of a fixed placement of the blades of two ONVs in the share of the PSK and VTK consoles and folding their counterweights in the travel-charging configuration for its transportation in the hangar on the lodgement with the fuel station and the ammunition loading station of the aircraft carrier.

A known complex for hitting submarines (PL) at long ranges, patent RU 2371668 C2, made in the form of a ballistic missile (BR), in the bow of which is deployed a winged fairing cruise missile (CR); The BR contains aerodynamic surfaces with drives and an accelerating engine to ensure delivery of the RC to the firing range to the target area. For an economical flight in the atmosphere, the Kyrgyz Republic is docked with an accelerating engine by means of a separation device, configured to fly in the area of the PL target and contains a detachable underwater warhead (warhead) and a detachable sonar buoy; the control system of the Kyrgyz Republic is equipped with equipment for receiving information from a radio-acoustic buoy via radio channel about the location of the target. In accordance with the teams searching for the target, its detection, rapprochement with the target and its defeat by undermining the warhead. After that, the BR carrier continues the flight with the engine running, leading it away from the splashdown point of the underwater warhead so as not to interfere with its homing system. The disposable BR itself left the warhead splash area and self-destructed.

Known reconnaissance-strike unmanned aircraft mod. The British company BAE Systems "Taranis" [2] is designed as 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 retractable wheeled chassis. For transonic flight "Taranis", its Rolls-Royce Adour turbojet engine has a jet thrust of 4485 kgf, which ensures a speed of 1060 km / h with a thrust ratio of 0.64 at a flight altitude of 11.5 km. 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 an all-angle deflected nozzle of the turbofan engine complicates controllability and does not provide its stability. All this also limits the possibility of further increasing the speed and range of flight, improving weight recoil and increasing target load (CN).

Closest to the proposed invention is an anti-submarine ship (PLC), armed with an aviation system of the Icara model [3] (United Kingdom), containing an unmanned aerial vehicle (UAV), having a fuselage with a detachable guided missile, a mid-wing with its controls, an engine, airborne control system (BSU), providing telemechanical control (TMU) from the command post (CP) PLC.

Signs that coincide - UAV dimensions without naval 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. Target location data came from the sonar system (GAS) of the surface carrier ship, another ship or anti-submarine helicopter. Based on this information, the 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 submarine target 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 submarine target. After that, the UAV continues to fly with the operating SU, taking it away from the splashdown site of the homing MGT, so as not to interfere with its homing system. The disposable UAV itself left the area and self-destructed.

The proposed invention solves the problem in the above-mentioned known PLC with the Icara model system (Great Britain) to increase the combat load and weight return, increase flight 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 the aircraft carrier for reuse.

Distinctive features of the present invention from the above-mentioned known PLC with the Icara system closest to it are the presence of the deck-based aircraft reconnaissance and strike system (SAIL) comprising a group of ship-based vertical take-off and landing apparatus, which includes more than one optionally manned helicopter aircraft (OPSV) with more than one remotely piloted helicopter aircraft (DPSV), used from at least one helipad aircraft carrier to a booster carrier (AKN), each of which is made without vertical tailing according to the integral layout of a tandem-shaped flying wing, which has the first swept and second trapezoidal wings (PSK and VTK), spaced apart in the longitudinal direction, and equipped with a four-screw transverse tandem scheme (NPTS) with single-blade rotors (ONV) with their counterweights mounted on the profiled wing pylons PSK and VTK and wing gondolas constructively combining PSK with VTK, creating vertical thrust in the TPTS-X4 that only during vertical and short take-off / landing (GDP and KVP) or in transition flight modes, but it is also equipped with at least 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 (BOW) in the annular cowl and at least one free power turbine (CCT), having a round nozzle with all-angular control of the thrust vector (WHWT), before It takes the propulsion-reactive system (PRS-R2) to take-off power of the combined power plant (SU) by means of a transmission system to the corresponding ONV in a symmetrically balanced NPTS-X4 and / or WWII, having blades with a large twist, operating according to the pulling pattern. synchronous jet thrust during the performance of GDP and AEC or horizontal translational flight, but is also equipped in the tandem scheme of UCS and VTK, which have an equally large span, which is 1.04 times the diameter (D) of the airborne force at an angle of direct sweep along the front edge of the UCS, having front flows, forming in the plan a V-shaped configuration with its great excellent sweep angle from UCS, for example, χ = + 37 ° or χ = + 43 °, which is equal to the sweep angle along the front edge of the VTK, the trailing edge of which, having a reverse angle sweeps, forms 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 VTK, increasing their rigidity, counteracting the harmful effects of divergence, especially PSK consoles, but it is also configured to convert its flight configuration after performing a short or vertical take-off from a rotorcraft or helicopter, respectively, at its maximum or normal take-off weight, into the corresponding jet high-speed winged gyroplane or aircraft with four air force operating in autorotation modes or as wide-chord carriers wing-blades (SHLK), formed during the fixation of the ONV with their counterweights or the transformation of their counterweights, carried out in transition modes of flight of the last It is important that, after a vertical / short take-off, climb and acceleration flight, the front and rear NVG pairs are simultaneously pre-stopped so that their counterweights and blades are fixed in plan, respectively, from the end of the UCS and VTK inward to and out from the axis of symmetry or when stopped SLK their profiled counterweights are equipped with automatic assemblies for their synchronous folding by turning to the appropriate angles 127 ° or 133 ° in the horizontal plane and placing them back along the flight and parallel the axis of symmetry when fixed with the corresponding sweep along the front edge of the SLK of the front and rear ONV pairs, which form with SWK and the VTK their sweep along the leading edge and organize accordingly synchronously-symmetrical bearing surfaces of their SLK in the flight configuration of a jet aircraft with PRS-R2 and the system stepped tandem wings (SSTK), but also vice versa.

In addition, in the U-shaped in terms of the transmission shafts system of the aforementioned SPSV and DPSV, each of their QGTDs, for example, has one SST, which has a front shaft output for taking off its power mounted on the longitudinal axis of its nacelle, in which between the SEC and SST mounted coaxially with the latter, T-shaped in both top and side views, an 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 WWII the annular cowling of which has an air inlet adjustable with a conical central body, the second synchronizing one, laid in the UCS, rotationally connects the CCT of two CGTDs, and the third transmits torque through the clutch to the input shaft of the corresponding T-shaped when viewed from the side of the cantilever gearbox of one-sided ONVs located in the front wing pylon, has an output upper shaft and a longitudinal shaft with an angular gear, the first shaft and the second output shaft of the angular gear with the corresponding ONV are placed at the ends PSK and VTK are equidistant from the center of mass, but also bent 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 PSK or VTK, and the incident flow with vertical and horizontal flight modes meet simultaneously the leading edges of the upcoming ONV blades in the aforementioned NPTS-X4 and their mentioned SLV ONGs, which perform the role of the upper ones with the tiered arrangement of the outer sections of the UCS and VTK in the aforementioned CCT, which converts large elongations of the UCS and moderate VTK, respectively with λ = 8.0 and λ = 4.49, until the extension of the HSS with λ = 6.78 ... 6.79, and the inter-nacelle sections of their PSK and VTK are equipped with slats and flaps, respectively, used for takeoff and landing or transitional flight modes OPSV and DPSV, and the aforementioned round nozzles with VVVT their SST are equipped with the ability to synchronously deviate both vertically up or down, both horizontally left or right and vertically one up, and the other down, respectively, to change the balance by pitch, heading and roll at horizontal the forward flight of the SPSV and DPSV, while the mentioned SPSV and DPSV on their GDP regimes and hovering in the aforementioned NPTS-X4 pair of left and pair of right NVGs having the opposite direction of their rotation, respectively, clockwise and counterclockwise, are made with rigid fastening of their blades and without an automatic swash plate, providing a change in the pitch, roll and heading balancing, which is created by changing the installation angles of the front and rear NVG pairs, the left and right NVG pairs and the torques of the diagonally located NVGs, respectively but, and their wing front and rear profiled pylons on PSC and VTK have respectively front and rear infrared (IR) emitters and heat chambers on their respective edges, and after vertical landing on the helicopter landing pad of the aforementioned SPSV and DPSV, a convertible system of bearing surfaces of each of these, it is possible to pre-stop their ONV blades along the PSK and VTK consoles and place them with the tips to the axis of symmetry with the subsequent folding of their counterweights when they are located and forward along the flight and parallel to the axis of symmetry, and their transportation in the AKA hangar with a decrease of 1.9 ... 2.1 times the area of their traveling configuration from their take-off area, and their mentioned VTK, having a ratio of its area of 46.7% ... 46.8% of the total area of all bearing surfaces, including the areas of the aforementioned PSK and VTK with their supporting fuselage and SLK of four ONVs, is equipped with a feed fairing from its rear edge along the axis of symmetry, having a compartment with a magnetometer retractable rod at its end and in the lower his compartment with openable sash opus the antenna of the sonar station towed by a winch and towed on a cable under water during its flight, while the aforementioned SPSV and DPSV carrying aircraft anti-submarine and anti-ship missiles (APR and anti-ship missiles) provide appropriate combat against a submarine (SP) and a surface ship (NK) moreover, during anti-submarine defense in the mentioned OPSV and DPSV a omitted hydroacoustic system is used, consisting of an indicator of acoustic signals and two receivers for their reception from the hydroacoustic antenna, they are encoded transmitting via eight-channel closed communication to AKN for real-time processing or a highly sensitive magnetometer having a magnetosensitive element operating at a distance of 30 m from the water surface and connected to the BSU in the mentioned SPSV and DPSV, which provides for the issuance of commands for inclusion in the design point the magnetometer and control after the magnetometer has been triggered upon detection of the PL target, but also the registration in the BSU memory of the coordinates of the detection point of the PL target during transmission to the AKN and its gearbox, while the aforementioned SPSV and DPSV, the mentioned BSU has both a closed-circuit radio channel with AKN, and a radar station with a command transmitter, an optical-electronic system with a two-channel target tracking automaton, and a computer system with an automation unit for a multi-function control panel that provides independent search for PL purpose, its identification and adoption of a confirmed decision from the AKN operator on the destruction of his chosen ones, moreover, with anti-ship defense, the mentioned SPSV and DPSV, using using the flight configuration of the aforementioned jet aircraft with fixed SLV ONV, carrying the corresponding anti-ship missiles X-35U or anti-ship missiles X-38M in the bomb bay to create a buffer safe airspace between the main anti-aircraft missile and air defense of the NK-target, which increases the radius of the anti-ship missiles X-38M / X-35U with 40/130 to 400 km, while target type radar is provided by the H036 [4] radar from the main SPSV, and the DPSV-second pilot of the SPSV is controlled using the low-altitude flight profile and self-defense system - the station of active electronic interference of the SPSV, and when reaching the area from which the NK-target will be hit, the mentioned DPSV will launch a salvo or launch RCCs one by one 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 section of the RCC flight, its homing IR head and autonomous hardware and software target recognition, then the DPSV at a distance of 1263 km automatically returns to the aircraft with a vertical landing on its helipad, while in the aforementioned DPSV and DPSV glider flax from aluminum-lithium alloys and composite materials using an inconspicuous technology with a radio-absorbing coating, equipped at the bottom with a wheeled chassis with retractable supports in three compartments and weapon launchers in bomb compartments, each of which has two automatic wings with sawtooth transverse sides, and the BSA OPSV is equipped with the option of its optional control by pilots from a two-seat cockpit, which has seats ejected into the upper hemisphere, placed side by side and triggered on the scope of GDP and hovering one at a time, but also its use as part of the aviation group as the head one together with the aforementioned, for example, 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 OPSV, and then 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, configured to detect data relating to its polo eniya relative position OPSV head having a flight control computer that is operable with one or more sensors comprising an additional touchscreen computer, which is configured to: determine the relative position between the driven and head DPSV OPSV; Compare the relative position with the selected relative position; determine the speed of the driven DPSV necessary for its movement 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 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 wing section, which are pointed in the cross section, the fuselage, located between the UCS and the VTK, have front and top radio-transparent compartments for installing antennas in them with a receive-re-channel Achi data.

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 designed as with an additional sensor data summing computer and a data reception and transmission channel located on the head OPSV to obtain global data on the location from a slave DPSV, and with the possibility of converting images from each video sensor, providing the determination of the relative position, which through triangulation includes determining the relative range, azimuth and elevation, the additional computer for summing the sensor data and the data channel has multiband radio frequency equipment with directional antenna, capable of transmitting several video streams through closed communication channels, providing data collection from each video code sensor, and also 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 DPSV, while the computer for summing the data is fully integrated into the pilot interface and the SPSV control system providing the mentioned tracking flight of the slave DPSV, which, if necessary, can be disabled through one of the inputs of the pilot's interface for flight control, pilot activation of a button or switch controlled I, and the data summation computer is further provided with a possibility of independent action, it is determined that the flight OPSV unsafe for its relative position from the slave DPSV, but also the isolation forming said servo driven flying DPSV through the flight control computer.

In addition, for an economical high-speed horizontal flight of the aforementioned OPSV and DPSV of their ONV in a synchronously-balanced carrier and autorotating system, which includes an automatic transmission in each of the cantilever gearboxes of the front ONV pair, which has said output shafts for driving single-side ONVs, each of which creates two streams: the first - take-off with the issuance of the corresponding power from the corresponding gas turbine engine and the creation of lifting thrust from the ONV, the second - cruising in the configuration of an autogyro with the reception of power and from NVG unilateral autorotation at its proper level, by breaking all CAC CCT said drive KGtD leading synchronous generator and control and reduction of speed of rotation, e.g., up to 200 min ^-1 or 100 min ^-1, and the angle of attack of blades freewheeling NVG, providing a 1 / 3-1 / 4-fold increase in the required lifting force of the aforementioned PSK and VTK, but also by the plane of rotation of the ONV blades, which are almost aligned with the corresponding air flow at speeds for low- or high-speed flight, leading to a decrease in rotate nogo resistance NVG 12-15% of the total resistance profile blades NVG when autorotation and opportunities for cruising flight of calculating UCS and VTK reduced their geometry regimes component 2 / 3-3 / 4 of the same dimensions wing jet aircraft.

In addition, for horizontal flight at an altitude of 11 km of the aforementioned SPSV and DPSV, reaching the marching pull-order of the first level - 0.22 or 0.29 and the second - 0.29 or 0.35, their SU power is used 36% or 54% and 54 % or 72% of the working QGTD to drive their WWII, the mentioned SSRs of which, having a sweep angle χ = + 43 ° along its front edge, provides a speed of Mach 0.725 or M 0.753 and M = 0.87 or M = 0, 9, respectively, and when the marching pull-through rate is reached to 0.44, the speed will increase to M = 0.92, and each QGTD is equipped with an FTA in front of the VUVT mechanism of its reactive afterburner chamber used in take-off modes or horizontal flight with front-facing WWII and rear before the afterburner open controlled nacelle flaps for additional air supply to it, with their overload of 15% will increase marching propensity from 0.44 to 0.68 and achieve at a flight altitude of 11 km, the speed is M = 0.92 or M = 1.04, respectively, in the configuration of a trans- or supersonic aircraft.

Due to the presence of these features, which will allow you to master the SAIL, which includes a group of ship-based vertical take-off and landing vehicles, which includes more than one optional manned helicopter aircraft (APSV) with more than one remotely piloted helicopter aircraft (DPSV), used from at least one helipad of an aircraft carrier-carrier vehicle (AKN), each of which is made without vertical tail assembly integrated layout flying wing of the tandem scheme, which they it has the first swept and second trapezoidal wings (PSK and VTK), spaced from each other in the longitudinal direction, and is equipped with a four-screw transverse tandem scheme (TSC) with single-blade rotors (ONV) with their counterweights mounted on profiled wing pylons PSK and VTK and wing gondolas constructively combining PSK with VTK, creating vertical thrust in the NPTS-X4 only when the GDP and KVP are fulfilled or in transitional flight modes, but it is also equipped with no less than a pair of combined gas turbine engines (KGTD), the left and right of which is 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-round control of the thrust vector (WHWT), transmitting the take-off power of the combined power plant (SU) through the transmission system to the corresponding ONV in a symmetrically balanced NPTS-X4 and / or WWII, having with large twist blades, operating according to the pulling pattern, it creates synchronous reactive thrust in the propulsion-reactive system (PRS-R2) when performing GDP and KVP or horizontal translational flight, but it is also equipped in the tandem circuit of PSK and VTK, which have an equal size, which is 1.04 times larger than the NVG diameter (D) at a straight sweep angle along the leading edge of the UCS, having front arches that form a V-shaped configuration in plan with its large excellent sweep angle from UCS, for example, χ = + 37 ° or χ = + 43 °, which is equal to the angle p spruce on the front edge of the VTK, the trailing edge of which, having an angle of reverse sweep, forms a profiled aft part with a V-shaped rear edge in plan, and integrated with wing gondolas mounted most of them under or above the UCS and VTK, increasing their rigidity, counteracting the harmful effects of divergence, especially PSK consoles, it is also configured to convert its flight configuration after performing short or vertical take-off from a rotorcraft or helicopter, respectively its maximum or normal take-off weight into the corresponding jet high-speed winged gyroplane or an aircraft with four airborne forces operating in the modes of their autorotation or as the wide-chord wing-blades (SLKs) carrying them, formed by fixing the airborne vehicles with their counterweights or transforming their balances carried out on transient flight regimes sequentially, when, after vertical / short take-off, climb and acceleration flight, the front and rear NVG pairs are simultaneously preliminarily stopped that their counterweights and blades are fixed in plan, respectively, from the end of the UCS and VTK inward to and outward from the axis of symmetry or when the SLK is stopped, their profiled counterweights are equipped with automatic units for their synchronous folding by turning to the corresponding angles 127 ° or 133 ° in the horizontal plane and their placement backward along the flight and parallel to the axis of symmetry when fixed with the corresponding sweep along the front edge of the SLK of the front and rear ONV pairs, which form with the UCS and VTK equal in front Romke sweep and organize them respectively synchronously-symmetrical bearing surface of the FIR SHLK jet configuration with CP-R2 and the system of step tandem wings (SSTK) but also back. All this will make it possible to simplify the controllability and ensure its stability in jet OPSV and DPSV with PSK, VTK and in the presence of VUVT round jet nozzles of their gas turbine engine. In the configuration of jet gyroplanes and aircraft with symmetrically balanced, respectively, autorotating and supporting systems, the first of which is equipped with a multi-speed automatic gearbox that controls both the reduction of the speed of the ONV rotation to 200 min ^-1 or 100 min ^-1 , and the angle of attack of the ONV blades, but and the plane of their rotation, which are almost aligned with the corresponding air flow at speeds for low or high speed flight. Which leads to a decrease in the rotational resistance of the ONV by 15%. The transverse-tandem placement of the four ONVs at the ends of the PSV and VTK simplifies handling when hovering, and the implementation of the ONV without swashplate will eliminate the occurrence of vibrations. Placing two QGTDs in wing nacelles will allow the flying wing to be configured to carry the fuselage with its profile in thickness sufficient only to accommodate the internal arms bays, which will reduce its aerodynamic drag, and achieve 550/924 flight speeds in the configuration of a jet gyroplane / aircraft. km / h, but also in afterburner modes in the configuration of a transonic aircraft to ensure at a flight altitude of 11 km a speed of up to 1105 km / h.

The present invention SAIL with OPSV and DPSV tandem scheme with UCS and VTK and their sweep along the leading edges χ = + 43 °, two QGTD, having in each CCT with VWTT jet nozzles installed in wing gondolas, combining UCS and VTK, leading in the annular fairings two WWII in PRS-R2 and in NPTS-X4 two pairs of ONV mounted at the ends of the UCS and VTK, is illustrated in FIG. 1 and general views of the front, top and side, respectively a), b) and c):

a) in the flight configuration of a winged gyroplane or jet aircraft with UCS and VTK, creating a higher lift force than the lift created by the autorotating ONV or fixed by their SSTK, and two KGTD with the Second World War, located in the nacelles, creating a marching thrust in PRS-R2 high-speed or a trans- and supersonic flight with the conditional placement of an autorotating pair of right ONVs with their profiled counterweights or fixed to the outside of the UCS and VTK pairs of left ONVs in their CCTS with their counterweights folded along the axis;

b) in the flight configuration of a helicopter or jet aircraft with UCS and VTK with their slats and flaps deflected, reducing the shadowing by 7% of the working four ONVs, creating lift when performing GDP and hovering or transonic flight with conditional placement of outward fixed from UCS and VTK pairs of left ONVs in their HFS with their counterweights folded along the axis of symmetry and working WWII with HWHM of their jet nozzles, creating a marching thrust in PRS-R2, driven from two QGTDs with two working HSTs.

c) in the flight configuration of the KVP rotorcraft with tandem PSK and VTK, two TVAD, leading through the ONV transmission system in the NPTS-X4 and the Second World War in the PRS-R2.

The multipurpose ship-based SAIL with an SPSV and two DPSVs is shown in FIG. 1 with one DPSV, made according to the concept of NPTS-X4 and PRS-R2 technology, has a glider of aluminum alloys and composite carbon fiber reinforced plastic, contains a carrier fuselage (NF) 1, PSK 2 with its slats 3 and front influxes 4 and VTK 5 with flaps 6. Between PSK 2 and VTK 5 and on the wing spans of NF 1, elytral fairings of 7 main landing gear wheels were mounted. The VTK 5 consoles form a V-shaped rear edge of the NF 1 with a profiled aft 8, equipped with a feed fairing 9 along the symmetry axis, with a magnetometer retractable rod and a winch lowered and a sonar antenna towed on a cable under water (Fig. 1 is not shown ) Each KGTD with CCT is installed in the wing nacelle 10, combining the consoles of PSK 2 and VTK 5, leads the BOB 11 in the annular cowl having an air intake with an adjustable conical body 12, screening blades of the BOB 11. Each KGTD with the BOB 11 and the CST has a VUVT of a round jet nozzle 13 and front and rear guided flaps 14 of the nacelle for additional air inlet therein. At the ends of PSK 2 and VTK 5, ewing pylons 15 and 16 are mounted with left 17-18 and right 19-20 ONVs, which have the opposite clockwise and counterclockwise rotation, respectively, for complete compensation of reactive torque in helicopter modes, without a swashplate and rigid fastening of their blades 17-20 and profiled counterweights 21. The ONV 17-20 cantilever gearboxes are located in profiled wing racks 15-16, the output vertical shafts of which are equidistant in plan from the center of mass and are deflected backward by flight angle (α), which is equal to 1/2 the angle of attack (α) UCS 2.

The combined control system includes two gas turbine engines, which have a hydraulic control system with a rotary-shaft rotary-tube rotary nozzle 13 and 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 ONVs 17-20, which transmit 100% or for intermediate gearboxes 36 ... 54% of the NVG 17-20 on the take-off power of the SU when fulfilling GDP and hovering or horizontal translational flight between respectively four NVGs 17-20 in the NPTS-X4 or two WWII 11 in the ORS-R2, respectively.

The control of the transonic DPSV is ensured by the general and differential change in the ONV pitch 17-20 and the deviation of the left and right round jet nozzle 13 with the VHWT in the 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 17-20 with PSK 2 and VTK 5 or PSK 2 and VTK 5 with fixed ONV 17-20 (see Fig. 1b) in SSRK, respectively marching jet thrust - by the PRS-R2 system through jet nozzles 13 with VUVT in KGTD mounted in nacelles 10, in the transition mode - PSK 2 and VTK 5 with ONV 17-20. After the ONV 17-20 lifting thrust is created in the NPTS-X4, the GDP and freezing or KVP regimes are ensured when the reactive nozzles 13 with the VHWT in the QGTD create the required marching thrust for the translational flight (see Fig. 1a). When performing GDP and freezing, the change in the balance of pitch, roll, and course, which is created by changing the installation angles of the front 17-19 and rear 18-20 NVG pairs, the left 17-18 and the right 19-20 NVG pair and the torques of the diagonally located ONV (see Fig. 1b). After vertical take-off and climb, an accelerating flight is performed at speeds of more than 300 ... 350 km / h and a corresponding reduction in the revolutions of the ONV 17-20 rotation is performed. As you accelerate with an increase in the lifting force of PSK 2 and VTK 5, the lifting force of the ONV 17-20 decreases. When reaching flight speeds of 400 ... 450 km / h and to switch to the airplane flight mode ONV 17-20 synchronously stops so that their wing blades 17-20 are preliminarily placed when viewed from above parallel to the leading edges of PSK 2 and VTK 5, which are then synchronously stop so that ONV 17-20 are fixed in the SSRK with a direct sweep along their leading edges, forming an equal sweep χ = + 43 ° with PSK 2 and VTK 5 (see Fig. 1b). When creating jet thrust with circular jet nozzles 13, a high-speed cruising 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 13 with all-angular control of the thrust vector of each CGTD.

Thus, the transonic OPSV and DPSV with PSK and VTK, two KGTD with SST, having for the creation of vertical thrust four ONV with their counterweights or horizontal thrust two WWII, respectively, with working ONV or fixed their SLK, is a convertiplane with ChPTS-X4, PRS -R2 and U-shaped in terms of transmission, which changes the 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 leading edges of the attack guides and blades fixed NVG SHLK them, increasing the bearing capacity of the CPM and VTC, performing the role of the upper sections.

The integrated layout of the tandem flying wing with PSK and VTK increases the aerodynamic and structural advantages when converting to a transonic aircraft with an HFS, especially with the presence of additional SLVs of four ONVs fixed at the ends of the PSK and VTK with the same sweep. This will make it possible to reduce the weight of the DPSV glider, made using low-observable 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 SAILS, including the same type of SPSV and DPSV (see Table 1, type 1.1), used alternately from the helicopter landing pad of the aircraft, carrying 3/4 pieces of APR-3ME or anti-ship missiles of the X-35UE type in the weapons bays. In SAIL, the main SPSV, 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 SPSS pilots to control the flight path of a group of guided DPSV and their combat loads, providing anti-submarine or anti-ship and / or anti-aircraft defense. The fourth level of MUM-T allows PPSV pilots not only to receive real sensory images from the air group of the guided DPSV and to control sensory and weapon loads, but also their navigation and global positioning during the next flight.

Undoubtedly, widespread use in a combined control system of one KGTD with WWII, in the design of which, using turbines from turbofan engines. AL-31F will make it possible to master the family of transonic OPSV and DPSV (see Table 1) for multi-purpose PAUKs based on ANK and deck IN, increasing their combat stability and safety, creating a buffer airspace between the air defense of the NK-target and ANK or its IN.

Sources of information:

1. Internet address: http: //www.wildwand.cora/en/Sikorsky_XV-2

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.

Claims (5)

1. Deck aviation reconnaissance and strike system (SAIL), containing an unmanned aerial vehicle (UAV), 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) with the command post (CP) of the carrier ship, characterized in that it includes a group of vehicles for vertical take-off and landing of ship-based, which includes more than one optionally manned helicopter years (OPSV) with more than one remotely piloted helicopter aircraft (DPSV), used from at least one helipad of an aircraft carrier-carrier carrier (AKN), each of which is made without vertical tail unit according to the integrated layout of the flying wing of the tandem scheme, which It has the first swept and second trapezoidal wings (PSK and VTK), spaced from each other in the longitudinal direction, and is equipped with a four-screw transverse tandem scheme (NPTS) with single-blade main rotors (ONV) with their counterweights, mounts They are designed on profiled wing pylons PSK and VTK and wing nacelles constructively combining PSK with VTK, creating vertical thrust in the NPTS-X4 only during vertical and short take-off / landing (GDP and KVP) or in transition flight modes, but it is also equipped with at least 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 an annular cowl and at least one 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 corresponding ONV in a symmetrically balanced NPTS- X4 and / or WWII, having blades with a large twist, operating according to the pulling pattern, creates synchronous reactive thrust in the propulsion-reactive system (PRS-R2) when performing GDP and KVP or horizontal translational flight, but also cascaded in the tandem scheme of UCS and VTK, having an equally large span, which is 1.04 times greater than the NVG diameter (D) at a straight sweep angle along the front edge of the UCS, which has front arches that form a V-shaped configuration with a large excellent sweep angle from UCS, for example, χ = + 37 ° or χ = + 43 °, which is equal to the sweep angle along the front edge of the VTK, the trailing edge of which, having an angle of reverse sweep, forms a profiled stern part with a V-shaped rear edge in plan, and integrated with winged gondo most mounted under or above the UCS and VTK, increasing their rigidity, counteracting the harmful effects of divergence, especially UCS consoles, but also made with the possibility of converting its flight configuration after performing short or vertical take-off from a rotorcraft or helicopter, respectively, at maximum or normal its take-off weight in the corresponding jet high-speed winged gyroplane or aircraft with four air force units operating in their autorotation modes or as wide-chord flying carriers astea wings (SLK), formed during the fixation of the ONV with their counterweights or the transformation of their counterweights, carried out in transitional flight modes in series, when after vertical / short take-off, climb and acceleration flight, the front and rear pairs of ONV are simultaneously preliminarily stopped so that their counterweights and blades are fixed in plan, respectively, from the end of the UCS and VTK inward to and outward from the axis of symmetry or when the SLK is stopped, their profiled counterweights are equipped with automatic nodes folding them in by turning them to the appropriate angles of 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 front and rear ONV pairs, which form with the UCS and VTK equal in front the edge of their sweep and organize accordingly the synchronously-symmetrical bearing surfaces of their SLK in the flight configuration of a jet aircraft with PRS-R2 and a system of step tandem wings (SSTK), but also uh. 2. The system according to p. 1, characterized in that in the U-shaped in terms of the transmission shafts of the mentioned OPSV and DPSV each of their KGTD, for example, with one SST, which has a front shaft output mounted on its longitudinal axis to select its take-off power a nacelle in which, between the above-mentioned WWII and CCT, a T-shaped gearbox is mounted coaxially with the latter, both from a top and a side view, having an longitudinal input shaft from the CCT and output both front longitudinal and transverse from the side, but also upper shafts, the first of which transmits power Without a clutch on the BOB, 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 KGTDs, and the third transmits torque through the clutch to the input shaft of the corresponding T-shaped when viewed from the side of the cantilever a single-side ONV gearbox located in the front wing pylon has an output upper shaft and a longitudinal shaft with an angular gearbox, a first shaft and a second output shaft of the angular gearbox with the corresponding they placed ONV at the ends of UCS and VTK, equidistant from the center of mass, but also bent backward along the flight by an angle (a), which when viewed from the side is 1/2 or equal to the angle of attack (a) respectively of UCS or VTK, and the incident flow in vertical and horizontal flight modes, they simultaneously meet the leading edges of the upcoming ONV blades in the aforementioned NPTS-X4 and their mentioned SLV ONGs, which act as the upper with tiered arrangement of the outer sections of the UCS and VTKs in the aforementioned CCTS, transforming large elongations P K and moderate VTK with λ = 8.0 and λ = 4.49, respectively, until the extension of the HFS with λ = 6.78 ... 6.79, and the inter-nacelle sections of their PSK and VTK are respectively equipped with slats and flaps used on take-off and landing or transitional flight regimes of the SPSV and DPSV, and the aforementioned round nozzles with the VVVT of their SST are equipped with the possibility of synchronous deviation of both vertically up or down, both horizontally left or right and vertically one up and the other down to change the pitch balance accordingly, the course and roll during horizontal translational flight of SPSV and DPSV, while the mentioned SPSV and DPSV on their GDP regimes and hovering in the aforementioned NPTS-X4 pair of left and pair of right NVGs having the opposite direction of their rotation, respectively, clockwise and counterclockwise, are made with rigid fastening their blades and without their swash plate, providing a change in the pitch, roll and heading balancing, which is created by changing the installation angles of the front and rear pair of ONV, the left and right pair of ONV and the torques diagonally distributed laid ONV, respectively, and their front and rear profiled pylons on PSC and VTK have respectively front and rear infrared (IR) emitters and heat chambers on their respective edges and, moreover, after vertical landing on the helicopter landing pad of the aforementioned DPS and DPSV convertible system of bearing surfaces each of them has the ability to both pre-stop their ONV blades along the PSK and VTK consoles and place them with their tips to the axis of symmetry with the subsequent folding of their prot balances when they are located forward along the flight and parallel to the axis of symmetry, and their transportation in the ACN hangar with a decrease of 1.9 ... 2.1 times the area of their marching configuration from their take-off area, and their mentioned VTK, having a ratio of 46 , 7 ... 46.8% of the sum of the areas of all bearing surfaces, including the areas of the mentioned UCS and VTK with their supporting fuselage and SLK of four ONVs, is equipped with a feed fairing from its trailing edge along the axis of symmetry, with a compartment with a magnetometer retractable rod at its end and in its lower compartment with open with the help of irrigation flaps, the antenna of the hydroacoustic station, which is lowered by the winch and towed on a cable under water, during its flight, while the aforementioned SPSV and DPSV, which carry aircraft anti-submarine and anti-ship missiles (APR and RCC), provide appropriate combat against a submarine and surface ship ( NK), and during anti-submarine defense in the aforementioned OPSV and DPSV a omitted hydroacoustic system is used, consisting of an indicator of acoustic signals and two receivers for their reception from hydroacoustic antenna, their encoding and transmission via eight-channel closed connection to the AKN 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 to the BSU in the mentioned SPSV and DPSV, which provides for issuing commands to inclusion in the calculated point of the magnetometer and control after the magnetometer is triggered upon detection of the PL target, but also registration in the BSU memory of the coordinates of the detection point of the PL target during transmission on the AKN and its control gear, and in the mentioned SPSV and DPSV the mentioned BSU has both a closed-circuit radio channel with the AKN, and a radar station with a command transmitter, an optical-electronic system with a two-channel target tracking automaton, and a computer system with an automation unit for the multifunction control panel , which provides for the independent search of the PL-target during barrage flight, its identification and adoption of a confirmed decision from the AKN operator on the destruction of the chosen ones, and with anti-ship defense omniparized SPSV and DPSV, using the flight configuration of the aforementioned jet aircraft with fixed HVAC ONV, carrying the corresponding anti-ship missiles X-35U or anti-ship missiles X-38M in the bomb bay to create a buffer safe airspace between the main anti-aircraft missile and air defense of the NK target, which increases the radius of action of the anti-ship missiles / X-35U 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 pilot of the SPSV using a low-altitude flight profile and self-defense system - a station of active electronic interference of the DPSV, and at before to reduce the area from which the NK target will be hit, the mentioned DPSV will launch a salvo or launch RCCs one by one with correction of the error accumulated by the combined inertial control system according to the data of the GLONASS satellite navigation system receiver, the homing head and software are used on the RCC flight end hardware autonomous target recognition, then DPSV at a distance of 1263 km automatically returns to the AKN with a vertical landing on its helipad, while I mention The APSV and DPSV 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 chassis with retractable supports in three compartments and weapon launchers in the bomb compartments, each of which has two automatic wings with sawtooth transverse sides thereof, and the BSA OPSV is equipped with the option of its optional control by pilots from a two-seat cockpit, having ejected into the upper hemisphere seats placed side by side side and triggered by GDP and hovering alternately, but also using it as part of the aviation group as a head group together with the aforementioned two DPSVs, one of which, being a slave, automatically repeats the maneuvers of the main SPSV in a follow-up flight, and the other is controlled by the second pilot from the main 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 relating to its position with respect to the position of the head OPSV, having a flight control computer, in working condition with one or more sensors, containing an additional touch computer that 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 for its movement 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 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 wing section, which are pointed in the cross section, the fuselage, located between the UCS and the VTK, have front and top radio-transparent compartments for installing antennas in them with a receive-re-channel Achi data. 3. The system according to p. 2, characterized in that in the aforementioned OPSV and DPSV 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 said flight control computer is configured as an additional computer for summing the sensor data and a data receiving and transmitting channel located on the head OPSV to obtain global point data on the location from the slave DPSV, and with the possibility of converting images from each video sensor, providing the determination of the relative position, which through triangulation includes determining the relative range, azimuth and elevation angle, and the additional computer for summing the sensor data and the data channel has a multi-band radio-frequency equipment with a directional antenna, capable of transmitting several video streams through closed communication channels, to ensure collection 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 computer for summing data is fully integrated into the pilot interface and the SPSV control system providing the aforementioned tracking flight DPSV slave, which, if necessary, can be disabled through one of the inputs of the pilot interface for flight control, pilot activation of the button and and a control switch, wherein the data summation computer is further provided with possibility of independent action, determining if the flight OPSV unsafe for its relative position from the slave DPSV but isolation and forming said servo driven DPSV flying through the flight control computer. 4. The system according to any one of paragraphs. 1, 2, characterized in that for an economical high-speed horizontal flight of the aforementioned SPSV and DPSV, their NVG in a synchronously-balanced carrier and autorotating system, including in each of the cantilever gearboxes of the front pair of VVF an automatic gearbox having said output shafts for driving one-side VVF, each of which creates two streams: the first is take-off with the issuance of the corresponding power from the corresponding gas turbine engine and the creation of lifting thrust from the air force, the second is cruising in the configuration of an autogyro with emom power from autorotation unilateral NVG at its proper level, by breaking all CAC CCT said drive KGtD leading synchronous generator and control and reduction of speed of rotation, e.g., up to 200 min ^-1 or 100 min ^-1, and the angle of attack of blades freewheeling NVG providing a share of a 1 / 3-1 / 4-fold increase in the required lifting force of the aforementioned PSK and VTK, but also with the plane of rotation of the ONV blades, which are almost aligned with the corresponding air flow at speeds for low or high speed flights, leading to NIJ rotational resistance NVG 12-15% of the total resistance profile blades NVG when autorotation and opportunities for cruising flight regimes calculating UCS and VTK reduced their geometry, component 2 / 3-3 / 4 of the same dimensions wing jet aircraft. 5. The system according to any one of paragraphs. 1, 2, characterized in that for horizontal flight at an altitude of 11 km of the mentioned SPS and DPSV, reaching the marching thrust-weight ratio of the first level - 0.22 or 0.29 and the second - 0.29 or 0.35, the power of their control system is 36% or 54% and 54% or 72% of the working QGTDs to drive their WWII, the mentioned SSRs of which, having a sweep angle χ = + 43 ° along its front edge, provides a speed of Mach 0.725 (M) or 0.753 M and M = 0.87 or M = 0.9, respectively, and when the marching thrust-weight ratio is reached to 0.44, the speed will increase to M = 0.92, and each KGTD is equipped with an FTA in front of the VUVT mechanism the active nozzle with the afterburner used in take-off modes or in horizontal flight with front guided nacelles behind the WWII and rear in front of the afterburner for additional air supply to it, with their overload of 15% will increase the marching thrust-weight ratio from 0.44 to 0.68 and reach a speed of M = 0.92 or M = 1.04 at a flight altitude of 11 km, respectively, in the configuration of a trans- or supersonic aircraft.

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