RU2743262C1 - Air ballistic attack system - Google Patents

Abstract

FIELD: missile systems.SUBSTANCE: invention relates to shipborne aircraft missile systems. The air ballistic attack system (ABAS) has an aircraft-carrying icebreaker (ACI) with jet unmanned aerial vehicles having a wing, a fuselage with a guided missile launcher (GML), a power plant engine and an onboard control system. The air ballistic attack system includes optionally and remotely piloted convertible aircraft with a diamond-shaped wing and combined gas turbine engines with free power turbines in the aft fuselage, driving two transverse main rotors (MR) mounted in the wing annular fairings and / or in the annular wing fairings turbofans creating lift and / or propulsion-jet thrust with operating / fixed MRs in the configuration of turbofan aircraft used with guided missiles and decks of a nuclear ACI.EFFECT: invention is aimed at increasing the likelihood of hitting a surface or ground target.3 cl, 3 dwg, 1 tbl

Description

The invention relates to shipborne missile and aviation systems with optionally and remotely piloted convertible aircraft, having a diamond-shaped wing and in the aft fuselage, combined gas turbine engines with free power turbines, driving two transverse main rotor beads mounted in wing annular fairings and or in the annular fairings of the wing nacelles two outboard turbofans creating lift and / or propulsion-jet thrust with working / fixed HB in the configuration of turbofan aircraft used with guided missiles and the deck of a nuclear-powered aircraft-carrying icebreaker.

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

Known aircraft vertical takeoff and landing (VTOL) model F-35B (USA) with a trapezoidal wing and on it side nozzles that create vertical thrust and roll control, has a turbojet bypass engine (TRDD) with a deflected thrust vector (OVT) of its jet nozzle and power take-off to drive the lifting fan with steering flaps and two-keel tail.

The reasons impeding the task: the first is that the rear location of the turbojet engine with its rotary nozzle, which changes the jet thrust vector, has a front shaft output for take-off power by means of a gearbox and a clutch to the lifting fan, which predetermines behind the cockpit in the design the fuselage has two upper and lower openable flaps of the lifting fan, which is also equipped with a complex system for deflecting its air flow in the longitudinal direction, which complicates the design. The second is that the location behind the cockpit of a lifting fan with a diameter of 1.27 m predetermines a large area of the fuselage amidships, which creates additional drag. The third is that for the performance of GDP and hovering, there is a double system for creating both vertical hot thrust from the turbojet engine rotary nozzle, which predetermines the heat-resistant design of the ship's deck, and cold thrust from the lifting fan and side nozzles, which, during its horizontal flight, increase the parasitic mass , are useless, which leads to a heavier structure and a decrease in weight return. In addition, the use of afterburner and non-afterburner operating modes of the turbojet engine accordingly increases specific fuel consumption by 46%, halves the flight range and limits the speed to no more than 950 km / h.

Closest to the proposed invention is the British [see. http: //rbase.new-factoria.ru/missile/wobb/ikara/ikara.shtml] anti-submarine aircraft complex (PAK) model "Icara" with jet unmanned aerial vehicles (UAV), having a wing, fuselage with a launching device (PU ) a guided missile (YP), a power plant engine (SU) and an onboard control system (BSU).

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

The reasons that impede the task: the first is that the launch of the subsonic UAV was carried out in the direction as close as possible to the target. Target location data came from the sonar system of a surface carrier ship, another ship, or an anti-submarine helicopter. This ensures, taking into account the air defense (AA) of the target, the constant updating of data on the optimal torpedo drop zone in the computer of the fire control system, which transmits them in flight through the BSU to the UAV. Upon the arrival of the UAV in the area where the target was located, the Mk.44 torpedo, semi-drowned with its ventral position in the UAV hull, separated by radio command, descended by parachute, entered the water and began to search for the target. After that, the UAV continues its flight with a working control system, taking it away from the landing site of the homing torpedo so as not to interfere with its homing system. The disposable UAV itself left the area and self-destructed.

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

Distinctive features of the proposed invention from the above-mentioned known PAK model "Icara", which is closest to it, are the presence of the fact that the aviation strike missile system (URKA) has a group of vertical take-off and landing (VLT) vehicles, including more than one optionally piloted convertible aircraft (OPKS) with more than one remotely piloted convertible aircraft (DPKS), used from more than one ANL helipad, and each deck DPKS and OPKS contains a diamond-shaped wing (RVK), having a twin-rotor transverse-carrying system (DPNS), used on transitional and accelerating flight modes, performing GDP and hovering, short takeoff and landing or vertical landing (KVP or KVVP), including with a variable pitch left and right three- or four-bladed rotor (HB), which are mounted inside the RVK in the corresponding wing annular fairings ( CCO), having automatically opened / closed transverse lower blades zir-rudders and longitudinal upper semicircular flaps or louvres-flaps, providing free air access to the CCO and the air flow out of them, forming, after they are closed, the corresponding surfaces of the RVK, integrated with its front and rear root influxes (PKN and ZKN) and according to the rule areas with a fuselage equipped in the aft part of it with at least two combined gas turbine engines (KGTD) made in the form of two-circuit jet engines with external three-stage fans (VTV) in annular fairings (KO) of wing nacelles mounted along the longitudinal axes of the KCO in the rear parts of the RVK and from the outer sides of the tail booms with their reactive round or rectangular flat nozzles (PPS) extended beyond the trailing edge of the SCZ, providing the creation of a vertical / inclined or horizontal thrust when performing a GDP / STOL or forward flight, respectively, but also more than one free power turbine (SST) transmitting takeoff power control system for the corresponding NV in their CCO and / or VTV in SC, creating synchronous cold thrust in the propulsive-reactive system (PRS), but also made with the possibility of converting its flight configuration after performing a vertical or short takeoff from the corresponding aircraft with its KGTD, leading to the DPNS-X2 a pair of NV and / or two VTV in PRS-R2, creating a lifting and / or lifting / sustainer thrust with working / fixed NV with automatically open / closed upper and lower, for example, shutters their CCO into a jet supersonic or transonic aircraft, respectively, at normal or maximum takeoff weight, but also vice versa, while the end parts of the low- or medium-located RVK are made as folding upwards in the parking lot to reduce their parking area by 1.5 ... 1.7 times from the takeoff, and deviated, respectively, up or down at an angle of 12 ° so that the front edge of the RVK consoles is located in the plan parallel to the corresponding edge on one side The lower trapezoidal one-piece pivoting keels mounted on top of the wing nacelles, placed at an angle of 40 ° with respect to the plane of symmetry, are deflected outward or inward, and during the execution of the GDP and hovering, the vertical application forces from two PPS and two HB, equidistant in plan from the axis of symmetry , are placed on transverse lines placed in plan from the center of mass, respectively, backward and forward along the flight at a distance inversely proportional to their lifting thrust.

In addition, in super-maneuverable OPKS and DPKS their transmission system, for example, with its two mentioned KGTD, mounted between the tail booms in the aft nacelles of the fuselage, in which a T-shaped main gearbox with longitudinal input shafts is located in front of their mentioned SSTs. , from two pairs of the SST cascade, but also the corresponding output transverse shafts, which are rotationally connected to the corresponding T-shaped wing gearbox in plan, the longitudinal front and rear output shafts of which transmit the distributed power, respectively, to the angular gearboxes of the mentioned right and left NV (PNV and LNV ) and / or to the VTV reducer in the KO of the wing nacelles, having at their input conical fairings of the wing reducer, shielding VTV blades and ensuring the removal of the boundary layer and increasing the total pressure recovery factor without a gap for draining the boundary layer, but also compressing the air flow and forming a conical its course, and in the modes of their GDP and freezing longitudinal control is carried out by changing the equal-size step in a pair of NVD and LNV, lateral control - by changing a different-sized step in both NVD and LNV, track control - by the mentioned louvers-rudders in their left and right CCOs, which are made with the possibility of their differential deviation from of the center of the spacecraft by angles forward in flight -40 ° and backward + 40 °, and in their modes of GDP and hovering with a specific load on the power of their combined control system, which is ρ _Ν = 1.15 kg / h.p., each mentioned CST is made with elements of digital program control, combining as a synchronization system of the SST cascade in their CGTDG equipped with a series-connected block for bringing pressure in the compressor of their SST, a unit for generating a set value of the frequency of rotation and angular position of the blades of their SST and executive bodies that correct the angular misalignment of the blades in the SST cascade and provide a given fuel consumption that forms the required power, and the hell system ptive control of the formation of a safe flight (UFBP) with a specific vertical thrust-to-weight ratio in the DPNS-X2, which, taking into account the losses from blowing the stiffeners, KCO ρ _VT = 1.15, includes the SST operating modes both takeoff and emergency mode (BP and PR) at selection of 3/4 and 1/4 of its required power to the drive of the mentioned NV and VTV, respectively, both from four operating SSTs and from three of the operating SSTs with automatic equalization and a corresponding redistribution of the remaining power between NV and VTV in case of failure of the corresponding SST in the KGTD, for example, even in the latter case, after the automatic switching on of the PD, the work of the remaining SSTs, which, with a specific vertical thrust-to-weight ratio in the DPNS-X2, equal to ρ _VT = 1.07, will provide an emergency vertical landing mode for 2.5 minutes, and in each of them CCT system UFBP contains: one or more sensors that are configured to detect data related to the air flow rate (G _B , kg / s) through the compressor CCT, temperature gas tours ( _TG , K) in front of the SST turbine, the total compression ratio (K) of the compressor, as well as one or more sensors that are configured to detect the relative position of their fuselage and rotation discs of their NV for their relative position relative to the ground level or the landing surface platforms, as well as various obstacles in the path of their tracking safe reduction; a flight control computer located in their said BSU and operating with one or more sensors; the flight control computer is configured to: determine the relative position between their wheeled chassis fuselage and ground level or surface of the landing pad; compare the relative position of their fuselage and their carrier system with their chosen relative position; determine the speed of automatic descent required to move them to the selected relative position; convert tracker speed to flight control inputs; and also to provide a direct automatic safe descent to the selected relative position through the flight control inputs, while each heavily armed DPKS and OPKS, made respectively without and with a cockpit, equipped inside with video cameras with autonomous manipulators connected to the OPKS controls and the possibility of its optional pilot control from the cockpit of the fuselage, and their fuselage for internal armament has automatic one- and two-wing corresponding side and lower compartments, the mentioned launchers of which are attached to them with air-to-air missiles of the R-77 type and strategic cruise missiles (SKR), which provide the fight against air and ground, surface purpose, mounted on the inner sides of the doors and inside the compartments, respectively, and their airframe is made according to an inconspicuous technology with a coating that absorbs radio waves of different lengths, and of aluminum-lithium alloys and composite materials reinforced with carbon fiber, capable of protecting them on-board equipment from powerful electromagnetic flashes or exposure to laser radiation, has a forward and aft fuselage and in its middle includes two composite monolithic S-shaped intake channels and rigid beams inside the center section and trapezoidal inner sections of the RVK, reinforced with spars and stiffeners with a common composite skin RVK and contains a tricycle wheeled chassis with nose and main struts, retracted, respectively, into the compartments of the fuselage and wing nacelles, and their left and right dorsal air intakes, which do not have plate cutoffs of the boundary layer and internal movable regulating elements, are made as for shielding the blades of the mentioned SST with double S-shaped when viewed from the side and from above, as well as diverting the boundary layer and increasing the recovery factor of the total pressure without a gap for draining the boundary layer, but also include ramps that compress the flow and form its conical flow, moreover, subtle DPKS \ OPKS to create a buffer safe air zone between the said ANL and air defense targets carrying 2 \ 1 + 1 TFR in the bomb compartments of their fuselage, increase after the implementation of the GDP / KVVP technology, respectively, the range of action to 6020/8155 \ 8020/10155 + 6020/8155 km SKR type Kh-555 \ Kh-101 + Kh-555, which, after their launch, form autonomous swarms of SKR with towed false targets, and their fuselage has from its pyramidal nose part beveled along its entire length, forming, when viewed from the front, five- or a hexagonal cross-section that reduces the effective scattering area, but also radar and visual visibility, and each mentioned PPS of their wing nacelles for thrust vector control (UHT) is equipped with upper 27 and lower 28 walls containing at their ends rectangular hatches-nozzles with transverse upper 29 and lower 30 flaps rotatable on their axes 31 and 32 in the vertical plane, having a length with their chamfers from the axes of their rotation, determined from the ratio: L _str = h _sop / 0.707, m (where: h _sop - the height of the nozzle, cos 45 ° = 0.707) and separate drives, providing between its lateral walls 33-34 their deviation to the longitudinal axis of the nozzle downward and upward synchronously by two at angles ± 22.5 °, closing their bevels, or one of them by angles of ± 22.5 ° with another closed in-phase or differential, respectively, for reverse thrust or for longitudinal or lateral control or only the lower flap 30 at an angle of + 45 ° until its chamfer contacts the surface of the upper closed flap 29 to change the direction of the horizontal thrust to vertical, and their fuselage between the mentioned CGTD is equipped with a stern fairing extended along its longitudinal axis with a compartment having a retractable false target towed on a cable at its end, while the electro-optical sensor (EOD), designed for target detection and identification, has a receiving part The EDI, which is closed from above with a sapphire crystal, is installed on top of the nose of the fuselage of the head OPKS equipped with a two-frequency airborne radio station (radar) with an active phased antenna array (AFAR), which with EDI at safe for OPKS distances provides target geolocation and control of weapons loads OPKS and through the laser communication channel DPKS with aiming at the target of their TFR and SD of air-to-air class air group, used in conjunction with a number of other air groups, capable of and exchange information between their head OPKS in the framework of their single so-called information cloud, and dynamically adapt to changing conditions, including the fact that if one of the air groups detects targets in more than can hit, then through the laser communication channel its OPKS transmits target designation to a number of OPKS that do not use their radars as part of other air groups, and they jointly attack targets, as well as their tactical control and coordination, which distributes both OPKS and DPKS of a number of air groups to selected targets and / or completely, increasing the effectiveness of their attack, integrated into their autonomous strategic swarming, moreover, the computer of the EDI system is connected to the central on-board computer OPKS with a high-speed fiber-optic interface, which ensures full integration of the general information system OPKS with the EDI system, which includes a mid-range infrared sensor, which, being a thermal imager, a laser and a camera with a CCD matrix, allows taking photos and high-resolution video shooting, automatic target tracking, search in the infrared range, laser target illumination, laser range measurement, and tracking of laser marks delivered by other tracking and guidance systems, while in each air group, each DPCS is controlled by a laser channel closed communication, not susceptible to interference from the enemy's electronic warfare (EW), is provided by the co-pilot of the OPKS, using his self-defense system and countering the enemy's EW - an active electronic jamming station, as well as compact solid-state laser and microwave installations of directional energies used as self-defense and accompanying air-based weapons, suppressing the enemy's missile homing heads and disabling the enemy's electronics, respectively, and in each air group, each OPKS on the leading and trailing edges, respectively, of the mentioned RVKs with PKN and ZKN up to the end parts of the RVK are mounted radars with a conformal active array and laser locators, which are used to track the corresponding air and ground targets, while its AFAR radar is used to provide ground strategic targets such as bases and infrastructure, while the nuclear ANL has an asymmetric body, is made with a two-landing its scheme, which allows the use of a draft in the range from 8.5 to 10.5 m to increase icebreaking capacity and perform special tasks in shallow water and river estuaries, equipped with a propulsion system consisting of a pair of main and a pair of additional, respectively, aft and bow rudder propellers ( BP K), each of which, working independently and increasing the efficiency of maneuvering in any direction and even rotation in place, can both rotate in a horizontal plane by 360 °, and is equipped with a built-in high-torque DC motor with a corresponding fixed-pitch propeller (FPP), mounted directly on the shaft inside the full-revolving propellers gondola, and the installation of forward propellers on the nuclear ANL provides high maneuverability in ice conditions, but also in clean water, which is very important in areas with limited water space, but also, achieving the effect of ice erosion by the operation of these propellers as reduces the ice strength and increases the ability to pass ice hummocks, and has a harmful effect on the operation of the aft propellers, while to increase the efficiency of the propulsive installation of the atomic ANL, a pair of forward propellers, which, providing the effect of divergence of their thrust vectors from the longitudinal axis of the ANL, are turned at an angle to each friend to the effective emphasis of ANL in in the mode of generating tractive effort, and the propulsion unit with four propellers and four control joysticks are combined in one bridge with the installation of two navigation bridges - the main and backup for the ANL control during the course and visual control, which improves the panoramic view from the second bridge when it moves obliquely.

In addition, each turboprop fan OPKS and DPKS with cold air flows from the NV to the DPNS-X2 with a GDP and a jet jet of compressed air in PRS-R2 during cruise flight with a marching thrust yield of the first level - 0.225 or the second - 0.258 or the third level - 0.5 or fourth - 0.62, using respectively 22% or 27% or 72% or 100% of the power of their SU, provides at an altitude of 15 km a speed of Mach 0.894 (M) or M = 0.988 or a trans- or supersonic speed of M = 0.996 or M = 1.4 with the aforementioned RVK, which has a variable sweep sweep from its V-shaped nose section of the fuselage, and each of them is equipped with a rectangular flat nozzle with a thermally absorbing coating, reducing infrared (IR) radiation, has a rear V-shaped in plan, an edge located in continuation or parallel to the trailing edge of the said RVK, forming a sawtooth sweep with a tapered aft fairing and the trailing edge of the RVK, but also an afterburner used on aircraft flight and supersonic flight modes with open controllable flaps of its aft nacelle for additional air supply in front of the above-mentioned SST and rear in front of the afterburner, which will allow, at normal / maximum takeoff weight at an altitude of 15 km, to increase the thrust yield of their control systems from 0.62 / 0.5 to 0.78 / 0.63, while the absence of glazing of the front windows or all windows in the OPKS cockpit will increase the rigidity of the fuselage, reduce the skin thickness and reduce the weight, and the OPKS airframe with a pressurized cockpit with automatically resetting opaque armor - a flashlight for ejection pilots and a means of displaying a digital image representing part of the external scene, including the environment, stretching forward and sufficient for piloting, is equipped with a variety of video cameras, IR sensors and video sensors that provide all-weather sensory shooting, recording all events in the front and rear hemispheres 360 °, while for controlled the OPKS in real time, the image is digitally corrected and displayed by the video distribution module on the cockpit displays, making its skin either transparent, or visible on the helmet-mounted displays of the pilots, which, forming common viewing windows, are connected to the first and second processors of the extended vision system, configured to be worn by a first and a co-pilot, respectively, with the first and second common viewports and highlighted displayed lines of sight visible on the first and second helmet displays of the pilots, respectively.

разместить пару ККО с их двумя НВ, повысить аэродинамическое качество до 14 единиц, достичь на высоте полета 15 км транс- и сверхзвуковой скорости 1058 км/ч и 1478/1807 км/ч на безфорсажных/форсажных режимах работы КГтД.Due to the presence of these features, which will make it possible to master the Arctic URKA, which has a group of vertical takeoff and landing (VLT) vehicles, including more than one optionally piloted convertible aircraft (OPKS) with more than one remotely piloted convertible aircraft (DPKS), used with more than one helipad ANL, and each deck DPKS and OPKS contains a diamond-shaped wing (RVK), which has a twin-rotor transverse-carrying system (DPNS), used in transient and accelerating flight modes, performing GDP and hovering, short takeoff and landing or vertical landing (KVP or KVVP), including with a variable pitch left and right three- or four-bladed main rotor (HB), which are mounted inside the RVK in the corresponding wing annular fairings (KKO), which have automatically opened / closed transverse lower louver-rudders and longitudinal upper semicircular flaps or louvers -flaps, providing free air access to the CCO and outlet yes of them the air flow, after their closure, forming the corresponding surfaces of the RVK, integrated with its front and rear root influxes (PKN and ZKN) and, according to the area rule, with a fuselage equipped in its aft part with at least two combined gas turbine engines (KGTD), made in the form of two-circuit jet engines with external three-stage fans (VTV) in annular fairings (KO) of wing nacelles, mounted along the longitudinal axes of the KKO in the rear part of the RVK and from the outer sides of the tail booms with their jet round or rectangular flat nozzles (PPS), extended beyond the trailing edge of the ZKN, providing the creation of vertical / inclined or horizontal thrust when performing a GDP / KVP or forward flight, respectively, but also more than one free power turbine (SST), transmitting the takeoff power of the control system to the corresponding NV in their CCO and / or VTV in KO, creating in this propulsive-reactive system (PRS) synchronous th jet cold thrust, but it is also made with the possibility of converting its flight configuration after performing a vertical or short takeoff from the corresponding aircraft with its KGTD, bringing a pair of NV and / or two VTVs to PRS-R2 into the DPNS-X2, creating a lifting and / or lifting / cruising thrust with working / fixed NV with automatically open / closed upper and lower, for example, louvres-flaps of their KKO in a jet supersonic or transonic aircraft, respectively, at normal or maximum takeoff weight, but also vice versa, while the end parts are low - or a mid-position RVK are made as folding upwards in the parking lot to reduce by 1.5 ... 1.7 times their parking area from the takeoff, and deviated, respectively, up or down at an angle of 12 ° so that the front edge of the RVK consoles is placed in the plan parallel to the edge of one-sided trapezoidal one-piece pivoting keels, mounted on top of wing nacelles, placed at an angle of 40 ° with respect to yu to the plane of symmetry, are deflected outward or inward, moreover, when performing a GDP and hovering, the vertical forces of application from two PPS and two HB, equidistant in plan from the axis of symmetry, are placed on transverse lines, placed in the plan from the center of mass, respectively, back and forth along the flight at a distance inversely proportional to their lifting rods. All this will make it possible to simplify controllability and ensure its stability in turboprop-fan OPKS and DPKS. The placement of the NV in the RVK RVC near the center of mass ensures the predictability and stability of control at the runoff, and the implementation of the NV with a variable pitch will simplify the control of the OPKS, made without the glazed surface of the cockpit windows, containing means for displaying digital images on cockpit displays or on helmet-mounted displays of pilots. In the event of a failure in the control system of one of the SSTs in the hover mode, its CGTDs are performed with automatic equalization and equal redistribution of the remaining power of the SST cascade between NVs, which increases flight safety. The use of RVK with PKN and ZKN will allow in its trapezoidal inner sections with a relative profile thickness

place a pair of KKOs with their two NVs, increase the aerodynamic quality up to 14 units, reach a trans- and supersonic speed of 1058 km / h at a flight altitude of 15 km and 1478/1807 km / h in non-afterburner / afterburner modes of the KGTD.

The proposed invention, a strategic URKA with turboprop fan OPKS and DPKS, containing a RVK with a PCN and ZKN, two KGTD, driving the PNV and LNV in DPNS-X2 and / or in PRS-R2 two VTV in the KO wing gondolas, having one-piece rotary keels on top, deviated outward from the plane of symmetry, illustrated by one OPKS in general front / top and side views, respectively, in FIG. 1/2 and fig. 3:

fig. 1/2 in the configuration of an airplane KVP or VVP with two KGTD, bringing NV with VTV to PRS-R2 or NV, and RVK with its mechanization, shown with open longitudinal upper louvers-flaps / transverse lower louvers-rudders in their KKO;

fig. 3 in the configuration of a trans- / supersonic aircraft with closed shutters-flaps in the KKO of its RVK, the end parts of which are deflected downward at an angle to the horizontal ϕ = 12 ° and two PPS 9 with VUVT in their wing gondolas.

The Arctic URKA is shown in Fig. 1-3 with one OPKS, which is made according to the concept of DPNS-X2 and PRS-R2, contains a fuselage 1 and RVK, which has PCN 2 and ZKN 3, but also slats 4 and flaps 5 on its end parts 6. End parts 6 of the mid-position RVK, mounted with the fuselage 1 according to the area rule, are deflected downward at an angle of 12 ° and equal to the trapezoidal one-piece rotary keels 7, mounted on top of the wing nacelles 8, deflected outward from the plane of symmetry (see Fig. 1), increase the track stability, especially when flight speed M = 0.8 ... 1.4. Wing nacelles 8, mounted in the rear of the RVK, contain PPS 9 with the VUVT system, carried out beyond the trailing edge of the ZKN 3. Fuselage 1 contains aft nacelles 10 of their KGTD and between their jet flat nozzles 11 has a stern fairing 12 with a compartment equipped at its end a retractable false target towed on a cable, but also a tricycle landing gear retractable into the fuselage compartments 1 and wing nacelles 8 and dorsal air intakes with S-shaped air ducts shielding the CCT blades (not shown in Figs. 1-3). Internal trapezoidal sections 13 RVK contain left and right KKO 14 with transverse LNV 15 and PNV 16 in DPNS-X2. Each KKO 14 is equipped with longitudinal upper 17 louvers-flaps and transverse lower louvers-rudders 18, organizing, after closing, the corresponding surfaces of the RVK. Two KGTD in a combined SU contain a CST cascade with a front shaft outlet for power take-off and its transmission to a T-shaped main gearbox with transverse output shafts transmitting torque to T-shaped wing gearboxes, longitudinal front and rear output shafts which transmit power, respectively, through the clutches to the angular gearboxes (not shown in Figs. 1-3) NV 15-16 and / or to the VTB gearbox in the KO of the wing nacelles 8 having cone-shaped fairings 19 of the wing gearboxes at their input. At the same time, the take-off power of the control system is redistributed as 3/4 and 1/4 between a pair of HB 15-16 and two VTVs with PPS 9 in wing nacelles 8, and 22% or 27%, but also 100% between two VTVs in the CO of wing gondolas 8, respectively, when performing both GDP and hovering, and high-speed or trans-, but also supersonic flight. Aft nacelles 10 with their KGTD, mounted between the tail booms 20, equipped with reactive rectangular flat nozzles 11 and afterburners, but also front 21 in front of the cascade of their SST and rear 22 in front of the afterburner with controlled flaps.

Control of the super-maneuverable OPKS is provided from a two-seat cockpit without a glazed surface 23, and target designation is provided by its radar with AFAR and EDI 24 (see Fig. 3). When flying as an aircraft with speeds of M = 0.5 ... M = 1.7, the lifting force is created by the RVK with closed louvers / rudders 17/19 in KKO 14 (see Fig. 2), cruise jet thrust - by the PRS-R2 system through PPS 9 with VUVT in wing gondolas 8, in the transition mode - RVK with NV 15-16. After the creation of the lifting thrust NV 15-16, the modes of GDP and hovering or KVP are provided when creating the PPS 9 with the VUVT of the required inclined cruise thrust for acceleration flight (see Fig. 1). When performing the GDP and hovering, the longitudinal control is carried out by changing the equal-sized step in the HB 15-16 pair, transverse control - by changing the different-sized step both in the LNV 15 and in the PNV 16, the track control is the lower louvers-rudders 19 of their KKO 14, which are made with the possibility of their differential deviation from the center of the spacecraft by angles forward in flight -40 ° and backward + 40 °. After vertical take-off and climb, a transitional maneuver is performed and the power is redistributed from the NV 15-16 drive to the drive of two VTVs of their wing nacelles 8. As the OPKS accelerates and with an increase in the lift force of its RVK, the lift decreases by two NV 15-16, which stop and are fixed (see Fig. 2) with synchronously closed shutters / shutters / rudders 17/18 in KKO 14. When the speeds M = 0.5 and M = 0.5 ... M = 0.8 are achieved, transient and acceleration modes are provided flight (see Fig. 3). Each dorsal air intake 25 is made without a plate cutter of the boundary layer and consists of a ramp 26, which compresses the flow and forms its conical flow. Each PPS 9 is made with upper 27 and lower 28 walls having at their ends rectangular in plan nozzle hatches with transverse upper 29 and lower 30 shutters rotatable on their axes 31 and 32 in the vertical plane, having separate drives, ensuring their deflection to the longitudinal axis of the nozzle and between its side walls 33-34, respectively, downward and upward synchronously with two at angles of ± 22.5 ° or one of them at angles ± 22.5 ° in phase or differentially with the other closed (see Fig. 2, view A, with reverse). Balancing change along the course, pitch or roll is provided by the deviation, respectively, of the synchronous one-piece rotary keels 10 in phase or differential of the upper 29 and lower 30 flaps of the PPS 9 of the wing gondolas 8 (see Fig. 2).

Thus, unobtrusive OPKS and DPKS with two KGTD, leading to create vertical thrust NV or horizontal thrust VTV with operating or fixed NV in their CCO, are turboprop fan VTOL aircraft with cold air flows from NV to DPNS-X2 and PPS with GDP and reactive jets of compressed air in PRS-R2 during cruise flight. Instead of the traditional design of a semi-rigid all-metal VTOL airframe, which includes more than 3300 original parts, deck-mounted OPKS and DPKS contain a monolithic structure of their rigid hull using up to 62 ... 66% of improved structural aging carbon composites capable of withstanding significant amounts of heat and deformation, allowing to reduce by an order of magnitude the number of parts, but also the costs of production and assembly. Of these, the head OPKS is fully digitized and includes the so-called manned and unmanned teaming (MUM-T) using a laser communication channel. The fourth level of MUM-T allows equipping the BSU of the head OPKS with a dual-frequency airborne radar with AFAR, which, with EDI at safe distances for it, provides geolocation of an inconspicuous target and control of weapon loads and OPKS, and via a laser communication channel DPKS with aiming at a target of their TFR and SD class air-to-air as part of an air group, used in conjunction with a number of other air groups, capable of exchanging information between their head OPKS within their single so-called information cloud and transmits target designation to a number of OPKS that do not use their radars in other URKA. When implementing the GDP technology, for example, the turboprop-fan DPKS-2.9 uses a takeoff power of 17,000 hp. its SU, which is 3.75 times less than that of a comparable jet VTOL model Yak-141 with a takeoff weight of 15,800 kg and its composite SU, consuming 63,950 hp. from the lift-and-cruise turbojet engine of the R-179-300 model and two lifting turbojet engines of the RD-41 model, mounted behind the cockpit in the engine compartment, which reduces the useful volume of the fuselage by 1.97 m ³ , increases the parasitic mass during cruising flight and predetermines the heat-resistant design decks of an aircraft carrier. Moreover, deck-mounted OPKS-4.15, using the VVP / KVVP technology, will increase the range of the Kh-102 type SKR with the Kh-555 to 8020/10155 km, respectively. After the launch of the Kh-102 type SKR with the Kh-555, which form autonomous swarms with towed false targets, which increase the destructive capability and combat stability of the atomic ANL as part of the strike URKA.

Strategic URKA with deck (see Table 1) DPKS-3.5 / OPKS-4.15, carrying 2/2 SKR type Kh-555 / Kh-101 with Kh-555, will allow OPKS pilots to control OPKS weapons loads and DPKS, but also their navigation and global positioning with the creation of a safe air zone between the air defense of the target and the nuclear ANL, mastered on the basis of a two-draft icebreaker of project 22220, used from the mouth of Siberian rivers. The latter and the creation of heavily armed DPKS-4.15 for the Arctic URKA, which are used at supersonic speed of their flight, anti-ship missiles (ASM) of the Kh-47M2 "Dagger" type, will increase the flight range of a hypersonic anti-ship missile system from 500 km to 2400 when they use the VVP / KVVP technology. / 4300 km, as well as to increase stealth, combat stability and the striking capability of carriers of the Aegis naval missile defense system in the Northern Sea Regions.

Claims (3)

1. An aviation strike missile system (URKA), containing an aircraft-carrying icebreaker (ANL) with jet unmanned aerial vehicles (UAVs) having a wing, a fuselage with a launcher (PU) of a guided missile (UR), a power plant engine (SU) and for control from the ANL command post an on-board control system (BSU), characterized in that it has a group of vertical take-off and landing (VTOL) vehicles, including more than one optionally piloted convertible aircraft (OPKS) with more than one remotely piloted convertible aircraft (DPKS), used from more than one helipad of the ANL, and each deck-based DPKS and OPKS contains a diamond-shaped wing (RVK) having a twin-rotor transverse-carrying system (DPNS) used in transient and accelerating flight modes, performing GDP and hovering, short takeoff and landing or vertical landing (KVP or KVVP), including with a variable pitch left and right three- or four-bladed rotor (HB), to which are mounted inside the RVK in the corresponding wing annular fairings (KKO), which have automatically opened / closed transverse lower louvers-rudders and longitudinal upper semicircular flaps or louvres-flaps that provide free air access to the KKO and the air flow out of them, forming after their closing corresponding surfaces of the RVK, integrated with its front and rear root beads (PKN and ZKN) and, according to the area rule, with the fuselage equipped in its aft part with at least two combined gas turbine engines (KGTD), made in the form of two-circuit jet engines having external three-stage fans (VTV) in annular fairings (KO) of wing nacelles, mounted along the longitudinal axes of the KKO in the rear part of the RVK and from the outer sides of the tail booms with their reactive round or rectangular flat nozzles (PPS) extended beyond the trailing edge of the ZKN, ensuring the creation of a vertical / inclined or horizontal thrust during the performance of the GDP / KVP or translational flight, respectively, but also more than one free power turbine (SST), transmitting the takeoff power of the SU to the corresponding NV in their CCO and / or VTV in the SC, creating at the same time in the propulsive-reactive system ( PRS) synchronous reactive cold thrust, but it is also made with the possibility of converting its flight configuration after performing a vertical or short takeoff from the corresponding aircraft with its KGTD, leading to the DPNS-X2 a pair of NV and / or two VTVs in PRS-R2, creating a lifting and / or lifting / cruising thrust with operating / fixed HBs with automatically open / closed upper and lower, for example, louvers-shutters of their KKO in a jet supersonic or transonic aircraft, respectively, at normal or maximum takeoff weight, but also vice versa, while the end parts of a low- or medium-located RVK are made both folding upwards in the parking lot to reduce their parking area by 1.5 ÷ 1.7 times from the take-off area, and tilted respectively up or down at an angle of 12 ° so that the leading edge of the RVK consoles is placed in the plan parallel to the corresponding edge of the one-sided trapezoidal one-piece rotary keels, mounted on top of the wing gondolas, placed at an angle of 40 ° with respect to the plane of symmetry, are deflected outward or inward, moreover, during the execution of the GDP and the hovering, the vertical application forces from two PTSs and two NVs, equidistant in plan from the axis of symmetry, are placed on transverse lines extended in plan from the center of mass, respectively, back and forth along the flight at a distance inversely proportional to their lifting thrust. 2. URKA according to claim 1, characterized in that in the super-maneuverable OPKS and DPKS their transmission system, for example, with its two mentioned KGTD, mounted between the tail booms in the aft fuselage nacelles, in which in front of their mentioned SST there is a T-shaped in plan main gearbox having longitudinal input shafts, for example, from two pairs of the CCT cascade, but also the corresponding output transverse shafts, which are rotationally connected to the corresponding T-shaped wing gearbox, the longitudinal front and rear output shafts of which transmit the distributed power to the angular gearboxes, respectively of the mentioned right and left NV (PNV and LPV) and / or to the VTV reducer in the KO of wing nacelles, having cone-shaped fairings of wing reducer at their input, shielding VTV blades and ensuring the removal of the boundary layer and an increase in the total pressure recovery factor without a gap for draining the boundary layer , but also compressing the air flow and forming its conical flow, and on In the modes of their GDP and hovering, longitudinal control is carried out by changing the equal-size step in a pair of NVD and LPV, transverse control - by changing a different-sized step in both NVD and LPV, track control - by the mentioned louvers-rudders in the mentioned left and right CCOs, which are made with the possibility of their differential deviation from the center of the spacecraft by angles forward in flight -40 ° and backward + 40 °, and in their modes of GDP and hovering with a specific load on the power of their combined control system, which is ρ _N = 1.15 kg / hp. , each mentioned SST is made with elements of digital program control, combining as a synchronization system of the SST cascade in their KGTD, equipped with a series-connected block for bringing pressure in the compressor of their SST, a unit for generating a set value of the frequency of rotation and angular position of the blades of their SST and executive bodies that correct angular misalignment of the blades in the SST cascade and provide a given fuel consumption, which forms the required power, and the system of adaptive control of the formation of a safe flight (UFBP) with a specific vertical thrust-to-weight ratio in the DPNS-X2, which, taking into account the losses from blowing the stiffening ribs, KCO ρ _VT = 1.15, includes the SST operating modes, both takeoff and emergency modes (BP and CR) with 3/4 and 1/4 of its required power to drive the mentioned NV and VTV, respectively, both from four operating SSTs and from three of operating SSTs with automatic equalization and a corresponding redistribution of the remaining power between NV and VTV in case of failure of the corresponding SST in the CGTD, for example, even in the latter case, after the automatic switching on of the PD, the work of the SSTs remaining in operation, which, with a specific vertical thrust-to-weight ratio in the DPNS-X2, equal to ρ _VT = 1.07, will provide an emergency vertical landing mode for 2, 5 minutes, and in each of their SSTs, the UVBP system contains: one or more sensors that are configured to detect data related to the air flow rate (G _B , kg / s) through the SST compressor, the gas temperatures ( _TG , K) in front of the SST turbine, the total compression ratio of the compressor (K), as well as one or more sensors that are configured to detect the relative position of their fuselage and their NV discs for their relative position relative to the level the land or surface of the landing site, as well as various obstacles in the path of their tracking safe descent; a flight control computer located in their said BSU and operating with one or more sensors; the flight control computer is configured to: determine the relative position between their wheeled chassis fuselage and ground level or surface of the landing pad; compare the relative position of their fuselage and their carrier system with their chosen relative position; determine the speed of automatic descent required to move them to the selected relative position; convert tracker speed to flight control inputs; and also to provide a direct automatic safe descent to the selected relative position through the flight control inputs, while each heavily armed DPKS and OPKS, made respectively without and with a cockpit, equipped inside with video cameras with autonomous manipulators connected to the OPKS controls and the possibility of its optional pilot control from the cockpit of the fuselage, and their fuselage for internal armament has automatic one- and two-wing corresponding side and lower compartments, the mentioned launchers of which are attached to them with air-to-air missiles of the R-77 type and strategic cruise missiles (SKR), which provide the fight against air and ground, surface purpose, mounted on the inner sides of the doors and inside the compartments, respectively, and their airframe is made according to an inconspicuous technology with a coating that absorbs radio waves of different lengths, and of aluminum-lithium alloys and composite materials reinforced with carbon fiber, capable of protecting them on-board equipment from powerful electromagnetic flashes or exposure to laser radiation, has a forward and aft fuselage and in its middle includes two composite monolithic S-shaped intake channels and rigid beams inside the center section and trapezoidal inner sections of the RVK, reinforced with spars and stiffeners with a common composite skin RVK and contains a tricycle wheel landing gear with nose and main struts, retracted, respectively, into the compartments of the fuselage and wing nacelles, and their left and right dorsal air intakes, which do not have plate cutoffs of the boundary layer and internal movable regulating elements, are made as for shielding the blades of the mentioned SST with double S-shaped when viewed from the side and from above, as well as diverting the boundary layer and increasing the recovery factor of the total pressure without a gap for draining the boundary layer, but also include ramps that compress the flow and form its conical flow, moreover, subtle DPKS \ OPKS to create of the buffer safe air zone between the aforementioned ANL and the air defense, targets carrying 2 \ 1 + 1 TFR in the bomb compartments of their fuselage increase, after they have completed the GDP / KVVP technology, respectively, the range of action up to 6020/8155 \ 8020/10155 + 6020/8155 km TFR type X-555 \ X-101 + X-555, which, after their launch, form autonomous swarms of SKR with towed false targets, and their fuselage has from the pyramidal nose of its side beveled along its entire length, forming, when viewed from the front, a five- or hexagonal cross-section, which reduces the effective scattering area, but also radar and visual visibility, and each mentioned PPS of their wing nacelles for thrust vector control (SWT) is equipped with upper (27) and lower (28) walls containing at their ends rectangular hatches - nozzles with transverse upper (29) and lower (30) flaps rotatable on their axes (31) and (32) in the vertical plane, having from the axes of their rotation the length L _st with their chamfers, determined from the relation: L _st = h _{with n} / cos45 ° m, where h _sop is the height of the nozzle, and separate drives, providing between its side walls (33-34), their deviation to the longitudinal axis of the nozzle downward and upward synchronously by two at angles of ± 22.5 °, joining their chamfers, or one of them at angles of ± 22.5 ° with the other closed in phase or differential, respectively, for reverse thrust or for longitudinal or lateral control, or only the lower sash (30) at an angle of + 45 ° until its chamfer touches the surface of the upper closed sash (29 ) to change the direction of horizontal thrust to vertical, and their fuselage between the above-mentioned KGTD is equipped with a stern fairing extended along its longitudinal axis with a compartment having a retractable false target towed on a cable at its end, while an electro-optical sensor (EDI) designed to detect and target identification, has an EDI receiving part, which is closed from above with a sapphire glass, is installed on top of the nose of the fuselage of the head OPKS equipped with a dual-frequency onboard a radar station (radar) with an active phased antenna array (AFAR), which with EDI at safe distances for OPKS provides geolocation of the target and control of weapon loads of the OPKS and via the laser communication channel of the DPKS with aiming at the target of their TFR and SD of air-to-air class air group, used in conjunction with a number of other air groups, capable of and exchange information between their head OPKS in the framework of their single so-called information cloud, and dynamically adapt to changing conditions, including the fact that if one of the air groups detects targets in more than can hit, then through the laser communication channel its OPKS transmits target designation to a number of OPKS that do not use their radars as part of other air groups, and they jointly attack targets, as well as their tactical control and coordination, which distributes both OPKS and DPKS of a number of air groups to selected targets and / or completely, increasing the effectiveness of their attack, are integrated into the autonomous strategic and the computer of the EDI system is connected to the central on-board computer OPKS with a high-speed fiber-optic interface, which ensures full integration of the general information system OPKS with the EDI system, which includes a mid-range infrared sensor, which, being a thermal imager, a laser and a camera with a CCD matrix, allows perform high-resolution photo and video shooting, automatic target tracking, search in the infrared range, laser target illumination, laser range measurement and tracking of laser marks set by other tracking and guidance systems, while in each air group, each DPCS is controlled by a laser a closed communication channel not susceptible to interference from the enemy's electronic warfare (EW) is provided by the co-pilot of the OPKS, using his self-defense system and countering the enemy's EW - an active electronic jamming station, as well as compact solid-state laser and microwave installations directed energy, used as self-defense and accompanying air-based weapons, suppressing the enemy's missile seeker and disabling the enemy's electronics, respectively, and in each air group, each OPKS on the leading and trailing edges, respectively, of the mentioned RVK with PKN and ZKN up to the end parts of the RVK Conformal active array radar and laser locators, which are used to track relevant air and ground targets, while its AFAR radar is used to provide detailed views of strategic ground targets such as bases and infrastructure, while the nuclear powered ANL has an asymmetric hull , is made with its two-draft scheme, which allows the use of a draft in the range from 8.5 to 10.5 m to increase icebreaking capacity and perform special tasks in shallow water and river estuaries, equipped with a propulsion system consisting of a pair of main and a pair of additional, respectively, aft and nasal rudder propellers (RSP), each of which, working independently and increasing the efficiency of maneuvering in any direction and even rotation in place, can either rotate in the horizontal plane through 360 °, and is equipped with a built-in high-torque DC motor with a corresponding fixed-pitch propeller (Fixed pitch propellers) mounted directly on the shaft inside the full-revolving propellers gondola, and the installation of forward propellers on the atomic ANL provides high maneuverability in ice conditions, but also in clear water, which is very important in areas with limited water space, but also achieving the effect of ice erosion the operation of these fixed pitch propellers both reduces the ice strength and increases the ability to pass ice hummocks, and has a harmful effect on the operation of the aft propellers, while to increase the efficiency of the propulsive installation of the atomic ANL, a pair of forward propellers, which, providing the effect of divergence of their thrust vectors from the longitudinal axis of the ANL, are at an angle to each other a friend on the effective emphasis of the ANL in the mode of generating tractive effort, and the propulsion system with four propellers and four control joysticks are combined in one bridge with the installation of two navigation bridges - the main and backup one for controlling the ANL during the course and visual control, which improves the panoramic view from the second bridge when it moves obliquely. 3. URKA according to any one of paragraphs. 1, 2, characterized in that each turboprop fan OPKS and DPKS with cold air flows from the NV to the DPNS-X2 with a GDP and a jet jet of compressed air in PRS-R2 during cruising flight with a cruising thrust-to-weight ratio of the first level - 0.225 or the second - 0.258 or the third level - 0.5 or the fourth - 0.62, using respectively 22% or 27% or 72% or 100% of the power of their SU, provides Mach speed M = 0.894 or M = 0.988 at an altitude of 15 km or a trans- or supersonic speed M = 0.996 or M = 1.4 with the aforementioned RVK, which has a variable sweep with its PCN from the V-shaped nose of the fuselage, and each KGTD is equipped with its reactive rectangular flat nozzle with a thermally absorbing coating, reducing infrared (IR) radiation, has a rear V-shaped edge in plan, located in continuation or parallel to the trailing edge of the said RVK, forming a sawtooth sweep with a tapered aft fairing and the trailing edge of the RVK, but also the afterburner used on aircraft take-off and supersonic flight modes with open controllable flaps of its aft nacelle for additional air supply in front of the above-mentioned SST and rear in front of the afterburner for additional air supply, which will allow, at normal / maximum takeoff weight at an altitude of 15 km, to increase the thrust-to-weight ratio of their control systems from 0, 62 / 0.5 to 0.78 / 0.63, while the absence of glazing of the front windows or all windows in the OPKS cockpit will increase the rigidity of the fuselage, reduce the skin thickness and reduce the weight, and the OPKS airframe with a pressurized cockpit with an automatically reset opaque an armored flashlight for ejection pilots and a digital image display device representing part of the external scene, including the environment stretching forward and sufficient for piloting, is equipped with a variety of video cameras, infrared sensors and video sensors that provide all-weather sensory shooting, fixing everything in the front and rear hemispheres 360 ° events, while m to control the OPKS in real time, the image is digitally adjusted and displayed by the video distribution module on the cockpit displays, making it either transparent or visible on the helmet-mounted displays of the pilots, which, forming common viewing windows, are connected to the first and second processors of the extended system are configured to be worn by the first and second pilots, respectively, with the first and second common viewports and highlighted displayed lines of sight visible on the first and second helmet displays of the pilots, respectively.

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