RU2710317C1 - Air missile system with an unmanned percussive aircraft helicopter - Google Patents

Abstract

FIELD: military equipment.SUBSTANCE: invention relates to military equipment, particularly, to designs of missile systems. Aircraft missile system with an unmanned percussive aircraft helicopter includes a platform containing a launch station, a power plant and a control unit of unmanned multi-screw system (UMSS) flight. UMSS is made in the form of an unmanned percussive aircraft helicopter with integral aerodynamic configuration, having two coaxial double-blade rotors (DBR), a tail gully of a seagull type and a free power turbine, which is arranged in the stern nacelle, leading the DBR and a portable single-row fan which generates a short-takeoff/landing or horizontal flight of the propulsive thrust. UMSS is configured to fold the wing consoles, tail fins and the wing-like wings of the DBR along the axis of symmetry for transformation into the traveling configuration for transportation on the ground in the cargo compartment on the locating block of the reconnaissance and control vehicle.EFFECT: higher speed and range of flight, increased take-off weight and weight return, simplified control at hovering and provision of transformation into marching configuration.5 cl, 1 dwg, 1 tbl

Description

The invention relates to military equipment and can be used in the construction of autonomous rotorcraft weapons modules having two coaxial two-bladed main rotors (DNV), tail unit of the seagull type and free power turbines in nacelles located in the fuselage behind the wing, leading the DNV and in annular fairings external fans, creating vertical and short take-off / landing (GDP and KVP) propulsion-reactive thrust directed horizontally backward with working / autorotating DNV or fixed and x wing blades outward from the axis of symmetry or after landing and folding the wing consoles and DNV wing blades along the axis of symmetry in the traveling configuration — ground transportation in the cargo compartment on the lodgement of the reconnaissance and control vehicle as part of anti-tank missile systems.

A well-known vertical take-off and landing airplane model (VTOL) DO.31 of the Dornier company (FRG), having a highly located wing, at the ends of which there are mounted gondolas with lifting turbojet dual-circuit engines (TRD), creating vertical thrust along with the wing under-wing lifting and marching turbofan engines down-up lateral rotary nozzles that change the jet thrust vector of each turbofan engine, tail cross.

Signs that match - the combined power plant has eight lifting turbofan engines. RB. 162-4 thrust of 2000 kgf and two lift-marching turbofan engines company Bristol Siddle mod. BS.53 "Pegasus" 5-2 with a thrust of 7000 kgf installed in gondolas under the wing. On each side of the turbojet engine nacelle, there are two pairs of rotary nozzles with a controlled thrust vector that rotate in a vertical plane to direct the jet of gases exiting the turbojet engine backward parallel to the VTOL axis during horizontal flight or downward when GDP is fulfilled.

Reasons that impede the task: the first is that the underfloor arrangement of the turbofan engines with their lateral nozzles changing their thrust vector determines the presence of fairings on each side of the nacelle and a complex system of synchronous down-up deflection of the gas stream of each turbofan engine, which complicates construction. The second one is that for fulfilling GDP and freezing, there is a double separate system for creating vertical thrust and lateral-longitudinal controllability (lifting turbofan engines and side nozzles of turbofan engines), which inevitably leads to weighting, an increase in the volume of routine maintenance and an increase in the cost of operation, but also a decrease in weight recoil, since with its horizontal flight the lifting turbofan engines themselves, increasing the parasitic mass, are useless. All this limits the possibility of increasing the speed and range, but also the target load (CN).

Known anti-tank missile system with an air module of weapons (patent RU 2470250 A1, 03/29/2012), including a ground combat vehicle (armored personnel carrier) containing means for basing and controlling the air module of weapons - an unmanned electric helicopter of a twin-screw pine scheme, equipped with target designation equipment, an armament complex, mainly means of basing anti-tank guided missiles, made with the possibility of basing on a ground combat vehicle and connected to it by a communication cable.

Thanks to the use of an unmanned electric helicopter (BPEV) in the armament complex according to the aforementioned patent RU 2470250, the capabilities of target designation have been expanded, additional capabilities have been provided for autonomous combat operations, including firing from the move, but at the same time, the range of operation of the attached BPEV is very limited and, as consequence, limitation in firing range. In addition, the materials of the patent RU 2470250 do not disclose means that would ensure reliable interaction between the armored personnel carrier and BPVE, and especially during reloading, as well as the possibility of placing BPVE with coaxial screws with a diameter of 4.5 m in an armored personnel carrier without a folding system for their blades.

Closest to the proposed invention is an unmanned aerial system of the Israeli company IAI (Israel AircraftIndustries) (patent WO 2007/141795 A1, 12/13/2007), including a platform containing basing equipment with a launch station, a power plant and a flight control unit for an unmanned multi-rotor system (BPMS) with a power plant (SU).

Signs of coincidence - the unmanned aerial system also includes a leash, which quickly connects the ground platform with the BMS, which provides electrical communication between the BMS and the ground platform (NM). The use of an external energy source installed on the NM by the propulsion control system propulsion system propulsion system propulsion system drivers, as well as the inability to make an independent flight outside the NM configuration, greatly limit the functionality of the unmanned aircraft complex. In particular, the height of the BPMS lift is limited by the length of the leash, which is dictated, inter alia, by the mass of the cable included in it. In addition, the materials of patent WO 2007/141795 do not disclose means that would ensure reliable interaction between NM and tethered BPMS with a complex of weapons.

The present invention solves the problem in the aforementioned known unmanned aerial system to increase speed and range, increase take-off weight and weight return, simplify control during hovering, ensure the use of mobile and airmobile aviation anti-tank missile systems and transform it into a traveling configuration for ground transportation in cargo compartment on the cradle of the reconnaissance and control vehicle.

или

раза больше диметра (D) ДНВ, внутренние и внешние секции, образующие НСК типа обратная чайка, смонтированы с отрицательным (ϕ_вну) и положительным (ϕ_вне) углами поперечного V соответственно и выполненный с возможностью преобразования полетной его конфигурации после выполнения технологии короткого и вертикального взлета соответственно с винтокрыла или вертолета при максимальном или нормальном взлетном его весе в соответствующий скоростной крылатый автожир или реактивный самолет соответственно с широкохордовыми ДНВ, работающими на режимах их авторотации или несущих их дупланных лопастей-крыльев (ДЛК), когда верхний и нижний ДНВ одновременно остановлены так, что при виде сверху их передняя и задняя лопасти как предварительно размещены перпендикулярно соответственно передней кромке левой и правой консолей НСК, так и снабжены автоматическими узлами синхронного их складывания посредством поворота на угол 90° в горизонтальной плоскости наружу от оси симметрии лопастей-крыльев ДНВ так, что они фиксируются с прямой стреловидностью по передним кромкам ДЛК ДНВ, образуя с НСК равновеликую стреловидность χ=+20°, организующим синхронно-симметричные несущие поверхности их ДЛК относительно оси симметрии и зафиксированным в плане параллельно передней кромке НСК в полетной конфигурации реактивного самолета с ПРС-R1 и системой бипланных разноуровневых крыльев (СБРК), преобразующей большое удлинение НСК с λ=10,5-11,5 до умеренного удлинения λ=5,0-6,0 СБРК, имеющей зафиксированные наружу от оси симметрии верхние и нижние ДЛК ДНВ, размещенные при виде спереди соответственно над левой и правой консолями НСК, но и обратно, при этом в мотогондоле КГтД с кольцевым обтекателем ВОВ по меньшей мере одна ССТ имеет промежуточный редуктор, снабженный продольными по его оси как входным валом, так и выходными внешним и внутренним соосными валами, первый из которых передает мощность через муфту сцепления на ВОВ, а второй - продлен за ВОВ и передает через муфту сцепления крутящий момент на соосный редуктор ДНВ, колонка выходных вертикальных соосных валов которого размещена в плане над центром масс, отклонена назад по полету на угол (∠α), который равновелик или равен 1/2 величине угла (∠α_вне) атаки внешней секции НСК, причем набегающий поток при вертикальном и горизонтальном режимах полета встречают одновременно соответственно передние кромки наступающих лопастей соосных ДНВ и зафиксированных соответствующим образом упомянутых их ДЛК, выполняющих над НСК в СБРК роль верхних разрезных крыльев с углом атаки ДЛК, который равновелик углу (∠α) отклонения назад колонки валов соосного редуктора двух ДНВ, при этом прямой стреловидности передняя кромка каждого бокового воздухозаборника КГтД как левого и правого размещена в плане параллельно соответственно передней кромке наплывов НСК, причем сопло ССТ и внешние борта двигательного отсека фюзеляжа размещены при виде сверху и спереди соответственно по оси симметрии и между отклоненными наружу от плоскости симметрии соответствующими секциями хвостового оперения типа чайка, внутренние и внешние стреловидные секции которого выполнены в виде килей и стабилизаторов, снабжены рулями направления и высоты соответственно.The distinguishing features of the present invention from the above-mentioned known unmanned aerial system, closest to it, are the fact that the aforementioned BMS is an unmanned attack helicopter (BMSV) with an integrated aerodynamic configuration, equipped as a fuselage, the nose of which is smoothly interfaced with a vortex forming frontal influxes having a sweep and attack angle different from the wing, increasing its carrying ability at large angles of attack, spreading extending from the leading edge of the wing and along the nose of the fuselage to its fairing, they form in plan a V-shape with a rounded apex configuration, and at least one combined gas turbine engine (KGTD), which is installed in the engine nacelle mounted in the fuselage behind the wing, 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), equipped with a front output in for power take-off and its transmission through an intermediate gearbox to the input shaft of the coaxial gearbox, redistributing the take-off power of the SU between the two-bladed HB (DNV) in a symmetrically balanced twin-screw coaxial bearing system (DPNS-X2) and the Second World War, with blades with a large twist operating according to the pulling scheme installed in front of and coaxially with the intermediate gearbox for creating in the propulsive-reactive system (PRS-R1 marching thrust directed parallel to the axis of symmetry during vertical and short take-off / landing (GDP and KVP) or horizontal translational flight, but also low-located swept wing (NSC), having an angle χ = + 20 ° sweep along the leading edge,

or

times the diameter (D) of the DNV, the internal and external sections forming an NSC of the type reverse gull are mounted with negative (ϕ _outward ) and positive (ϕ _out ) angles of the transverse V, respectively, and configured to convert its flight configuration after performing short and vertical technology takeoff, respectively, from a rotorcraft or helicopter at its maximum or normal takeoff weight into the corresponding high-speed winged gyroplane or jet aircraft, respectively, with wide-chord DNVs operating on a direct the scope of their autorotation or hollow wing-blades (DLK) carrying them, when the upper and lower DNVs are simultaneously stopped so that when viewed from above, their front and rear blades are both pre-arranged perpendicularly to the front edge of the left and right NSC consoles, and are equipped with automatic nodes their simultaneous folding by rotation through an angle of 90 ° in a horizontal plane outward from the axis of symmetry of the DNV wing blades so that they are fixed with a direct sweep along the leading edges of the DNV DLK, forming with the NSC equal sweep χ = + 20 °, organizing synchronously-symmetrical bearing surfaces of their DLK with respect to the axis of symmetry and fixed in plan parallel to the leading edge of the NSC in the flight configuration of the jet aircraft with PRS-R1 and the biplane system of different levels of wings (RBK), which transforms the large elongation of the NSC with λ = 10.5–11.5 to moderate elongation λ = 5.0–6.0 RBK, with the upper and lower DLK DNV fixed outward from the axis of symmetry, placed when viewed from the front, respectively, above the left and right NSC consoles, but also vice versa , at In the KGTD engine nacelle with a BHO annular cowl, at least one CCT has an intermediate gearbox equipped with both an input shaft and output external and internal coaxial shafts longitudinal along its axis, the first of which transfers power through the clutch to the BOB, and the second is extended behind the Second World War and transfers the torque through the clutch to the DNV coaxial gearbox, the column of the output vertical coaxial shafts of which is placed in plan above the center of mass, is deflected backward along the flight by an angle (∠α), which is the same or equal to 1/2 angle (∠α _outside) outer section attack SFN, wherein the incident flow in vertical and horizontal flight modes simultaneously meet respectively the front edge of the advancing blades and fixed coaxial DNV appropriately referred LDK their flying over NSC SBRK split upper part of the wings with an angle of attack LDK , which is equal to the angle (∠α) of the backward deviation of the shaft column of the coaxial gearbox of the two DNVs, with the forward sweep the front edge of each side air intake of the KGTD as the left and right times positioned parallel to the front edge of the NSC inflows in plan, moreover, the CCT nozzle and the outer sides of the fuselage engine compartment are placed in a top and front view respectively along the symmetry axis and between the corresponding tail sections of the seagull type, the inner and outer swept sections of which are made in the form of keels and stabilizers, equipped with rudders of direction and height, respectively.

In addition, in terms of GDP and bushes hangs, the mentioned at least one of its FTAs is made with elements of digital program control, combining in a bimodal system of regulation and control its simultaneous mode of operation both when it takes 95% of its take-off power to the drive of the aforementioned DNVs, and when a balanced distribution of 5% of residual power to the drive of the mentioned WWII, creating a minimum marching thrust for the required horizontal translational flight, while for an economical high-speed horizontal 35% and 70% of the power, respectively, from more than one working mentioned KGTD in the control system, is used only to drive the mentioned VTBs in the aircraft configuration with PRS-R1, and at the GDP and hovering full compensation of reactive torque in DSNS-X2 from working DNVs, made with rigid fastening of their blades, is created by the opposite direction of rotation of the left and right DNV, respectively, in plan, only clockwise and counterclockwise, and the change in balancing and according to the course and pitch, the roll is provided by a differential change in the thrust of the common pitch of the coaxial DNVs and by changing the corresponding cyclic pitch by the lower DNV swashplate, respectively, while the autonomous BUSV control system includes both an autopilot for independent take-off after selecting and confirming the route, and the system automatic return to the departure point, which will turn on if the operator does not respond to requests from the on-board computer, but also tracking systems They identify the obstacles that appeared on the flight path and give a command to automatically fly around them, and then provide a soft landing at a given point, with the left and right outer sections folding downward from the corresponding fractures of the mentioned plumage-type plumage in the traveling BUS configuration, and in the flight configurations when viewed from the front, they are mounted horizontally or parallel to the inner section of the NSC, while in the kinks of the NSC consoles of the type reverse gull behind its rear edge there are wing gondolas with compartments for the rear of the main struts of the wheeled chassis, the inner sections of the NSC with winged gondolas have the same scale as the internal sections of the plumage such as a seagull, and the outer sections of the said NSC are made with double folding of its inner and outer end parts, which deviate successively upward respectively to the axis of symmetry and back down, while being inclined to the plane of symmetry and along the upper lateral sides of the fuselage and not higher and not wider than a folded tail such as a seagull, providing transport the corresponding configuration of the CWSW with the telescopic upper shaft retracted in the shaft column of its coaxial DNV shafts, the blades of which are folded in the DLK and their pairs are directed one above the other back in flight, and when performing GDP and hovering, there are signal lights and proximity sensors at the ends of the ends of the said NSC warning a siren about an unacceptable approach with extraneous objects, while the front and rear ends of the fuselage keels mounted under the corresponding internal sections are mentioned There are corresponding cameras and IR emitters, while the central part of the fuselage and the front flows of the NSC are equipped with lower intra-compartment ejection devices for transporting and launching, for example, guided aircraft missiles, which enable their use in various methods its execution and basing, and the tail boom, equipped at its end along the entire width of the fuselage with a flat fairing, which, forming a bearing surface, integrates IAOD on its outer sides with said inner section and tail type gull is V-shaped in terms of a trailing edge which is placed in plane parallel to a plane similar to the trailing edge nozzle adapted termopogloschayuschim coating that reduces the IR visibility.

In addition, the mentioned BUSW, having both a closed-circuit radio channel with a ground mobile platform made in the form of a reconnaissance and control vehicle (MRU), mainly floating with a caterpillar or six-wheel all-wheel drive propulsion, and a radar station with a command transmitter, an optical-electronic system with a two-channel automatic target tracking and a computer system with an automation unit of a multifunctional control panel that provides independent rowing when cruising horizontally goals, their identification and adoption of a confirmed decision from the operator of the MRU to destroy the chosen ones, is made in the form of a column of coaxial shafts and the tailings of the coaxial shafts and the corresponding blades of the corresponding DNV and rigidly fixed in the cargo compartment of the anti-tank missile complex (ATGM), while the closed cargo compartment of the anti-tank missile, which has a rigid frame, is equipped inside as appropriate with a lodgement for fixed placement of the BUSV fuselage in it with retractable landing gear racks in the marching configuration, and with openable rear doors for loading and unloading operations, but also with a crane-beam mounted on the ceiling of the cargo compartment and along the longitudinal axis of the MPU, with a telescopic boom and at its end, a cable with a block and corresponding grips for engaging the BUSV fuselage, lifting it after disabling the locks of all the latches and moving outward to the take-off platform on the ground for vertical with it a BUST system with ammunition, for example, with anti-tank guided missiles (ATGMs) located in transport and launch containers (TPK), fixed by two TPKs on each side of each beam holder mounted under the fuselage and under the inner sections of the NSC and alternately mounted / removed by operators manually.

In addition, the aforementioned platform is made in the form of a stationary charging station mounted on a launch and receiving platform, placed on a vehicle, for example, on a road, rail or water, providing its installation, transportation and operation with appropriate movement, while in a ship anti-submarine missile complex (KPLRK) deck-based BUSV, carrying more than one aircraft anti-submarine missile APR-3E, equipped with a lowered sonar system, consisting of indicators an acoustic signal generator and two receivers for receiving them from a sonar buoy, encoding them and transmitting them via an eight-channel closed connection to a ship for real-time processing, and a highly sensitive magnetometer mounted in an elongated fairing of the tail boom so that it is installed at the lower end a magnetically sensitive element operating at a distance of 30 m from the water surface, and below the fuselage under the center of mass is equipped with a mooring device with an automatic control lever having deflectable up / down telescopic arm locking mechanism and gripping device into contact with the cells of the lattice of the deck, providing the possibility of landing on a helipad ship rolls at 25 °.

In addition, the aforementioned platform, having a mobile or airmobile performance, is made in the form of an automobile wheeled trailer towed, for example, by a Tiger-M armored car, equipped with its retractable weapons modules, for example, with a Kornet-D type ATGM or equipped their separate mounting on pallets and, if necessary, landing from a transport aircraft on parachute systems for their quick deployment.

или

раза больше диметра (D) ДНВ, внутренние и внешние секции, образующие НСК типа обратная чайка, смонтированы с отрицательным (ϕ_вну) и положительным (ϕ_вне) углами поперечного V соответственно и выполненный с возможностью преобразования полетной его конфигурации после выполнения технологии короткого и вертикального взлета соответственно с винтокрыла или вертолета при максимальном или нормальном взлетном его весе в соответствующий скоростной крылатый автожир или реактивный самолет соответственно с широкохордовыми ДНВ, работающими на режимах их авторотации или несущих их дупланных лопастей-крыльев (ДЛК), когда верхний и нижний ДНВ одновременно остановлены так, что при виде сверху их передняя и задняя лопасти как предварительно размещены перпендикулярно соответственно передней кромке левой и правой консолей НСК, так и снабжены автоматическими узлами синхронного их складывания посредством поворота на угол 90° в горизонтальной плоскости наружу от оси симметрии лопастей-крыльев ДНВ так, что они фиксируются с прямой стреловидностью по передним кромкам ДЛК ДНВ, образуя с НСК равновеликую стреловидность χ=+20°, организующим синхронно-симметричные несущие поверхности их ДЛК относительно оси симметрии и зафиксированным в плане параллельно передней кромке НСК в полетной конфигурации реактивного самолета с ПРС-R1 и системой бипланных разноуровневых крыльев (СБРК), преобразующей большое удлинение НСК с λ,=10,5-11,5 до умеренного удлинения λ=5,0-6,0 СБРК, имеющей зафиксированные наружу от оси симметрии верхние и нижние ДЛК ДНВ, размещенные при виде спереди соответственно над левой и правой консолями НСК, но и обратно, при этом в мотогондоле КГтД с кольцевым обтекателем ВОВ по меньшей мере одна ССТ имеет промежуточный редуктор, снабженный продольными по его оси как входным валом, так и выходными внешним и внутренним соосными валами, первый из которых передает мощность через муфту сцепления на ВОВ, а второй - продлен за ВОВ и передает через муфту сцепления крутящий момент на соосный редуктор ДНВ, колонка выходных вертикальных соосных валов которого размещена в плане над центром масс, отклонена назад по полету на угол (∠α), который равновелик или равен 1/2 величине угла (∠α_вне) атаки внешней секции НСК, причем набегающий поток при вертикальном и горизонтальном режимах полета встречают одновременно соответственно передние кромки наступающих лопастей соосных ДНВ и зафиксированных соответствующим образом упомянутых их ДЛК, выполняющих над НСК в СБРК роль верхних разрезных крыльев с углом атаки ДЛК, который равновелик углу (∠α) отклонения назад колонки валов соосного редуктора двух ДНВ, при этом прямой стреловидности передняя кромка каждого бокового воздухозаборника КГтД как левого и правого размещена в плане параллельно соответственно передней кромке наплывов НСК, причем сопло ССТ и внешние борта двигательного отсека фюзеляжа размещены при виде сверху и спереди соответственно по оси симметрии и между отклоненными наружу от плоскости симметрии соответствующими секциями хвостового оперения типа чайка, внутренние и внешние стреловидные секции которого выполнены в виде килей и стабилизаторов, снабжены рулями направления и высоты соответственно. Все это позволит повысить скорость и дальность полета реактивного БУСВ с соосными ДНВ, которые при выполнении операций с вертикальным подъемом грузов весьма перспективны в качестве останавливаемых и не убираемых в полете винтов-крыльев, что исключит наличие весьма конструктивно сложных систем складывания колонки их валов и уборки ДНВ, что упростит возможность преобразования его полетной конфигурации с винтокрыла или вертолета исполнения ДСНС-Х2 в соответствующий скоростной крылатый автожир или высокоскоростной самолет с маршевой ПРС-R1. Кроме того, аэро- или мобильное исполнение БУСВ для МАРК обеспечит возможность его перевозки по воздуху или земле в грузовом отсеке МРУ и позволит, использую его комбинированную СУ с КГтД, выполнить энергозатратный вертикальный взлет БУСВ как вертолета с приводом ДНВ от ССТ, но и достичь времени полета до 2,4-2,8 часа и скорости 700 км/ч в конфигурации реактивного самолета с ПРС-R1. Поэтому в БУСВ коэффициент аэродинамической выгодности СБРК с НСК и ДЛК ДНВ будет выше, чем у реактивного СВВП. Что позволит улучшить и весовую отдачу в сравнении с вертолетом соосной схемы. Более того, все это позволит также в сравнении с реактивным СВВП монопланной схемы повысить маневренность на малых скоростях полета и при переходных маневрах, но и снизить скорость сваливания за сет увеличения в 1,2 раза коэффициент поднятия СБРК, создающей НСК совместно с ДЛК ДНВ преимущество в производстве подъемной силы при крейсерском полете БУСВ.The presence of the above features allows the multipurpose aircraft missile system (MARC) to execute its aforementioned BMP, which is an unmanned attack helicopter (BMSV) with an integrated aerodynamic configuration, equipped as a fuselage, the nose of which is smoothly conjugated with a vortex forming frontal influxes having an angle sweeps and attacks other than the wing, increasing its bearing ability at large angles of attack, extending from the leading edge of the wing and along the bow the fuselage to its fairing, form in terms of a V-shaped configuration with a rounded apex, and at least one combined gas turbine engine (KGTD), which is installed in the engine nacelle mounted in the fuselage behind the wing, and is made in the form of a dual-circuit engine having an external and internal circuits, respectively, with an external single-row fan (BOB) in the annular cowl and at least one free power turbine (CCT), equipped with a front shaft output for power take-off and its transmission through gearbox on the input shaft of the coaxial gearbox, redistributing the take-off power of the SU between the two-bladed HB (DNV) in a symmetrically balanced twin-screw coaxial bearing system (DPNS-X2) and the Second World War, which has blades with a large twist, operating according to the pulling pattern installed before and coaxially with the intermediate gearbox for creating in the propulsive-reactive system (PRS-R1 marching thrust directed horizontally backward and parallel to the axis of symmetry during vertical and short take-off / landing (GDP and KVP) or horizontal post flight flight, but also low-located swept wing (NSC), having an angle of χ = + 20 ° sweep along the leading edge, a span of

or

times the diameter (D) of the DNV, the internal and external sections forming an NSC of the type reverse gull are mounted with negative (ϕ _outward ) and positive (ϕ _out ) angles of the transverse V, respectively, and configured to convert its flight configuration after performing short and vertical technology takeoff, respectively, from a rotorcraft or helicopter at its maximum or normal takeoff weight into the corresponding high-speed winged gyroplane or jet aircraft, respectively, with wide-chord DNVs operating on a direct the scope of their autorotation or hollow wing-blades (DLK) carrying them, when the upper and lower DNVs are simultaneously stopped so that when viewed from above, their front and rear blades are both pre-arranged perpendicularly to the front edge of the left and right NSC consoles, and are equipped with automatic nodes their simultaneous folding by rotation through an angle of 90 ° in a horizontal plane outward from the axis of symmetry of the DNV wing blades so that they are fixed with a direct sweep along the leading edges of the DNV DLK, forming with the NSC equal sweep χ = + 20 °, organizing synchronously-symmetrical bearing surfaces of their DLK with respect to the axis of symmetry and fixed in plan parallel to the leading edge of the NSC in the flight configuration of the jet aircraft with PRS-R1 and the biplane system of different levels of wings (RBK), which transforms the large elongation of the NSC with λ, = 10.5-11.5 to moderate elongation λ = 5.0-6.0 RBK, having the upper and lower DLK DNV fixed outward from the axis of symmetry, placed in front view, respectively, above the left and right NSC consoles, but also back when e In the KGTD engine nacelle with a BHO annular cowl, at least one CCT has an intermediate gearbox equipped with both an input shaft and output external and internal coaxial shafts longitudinal along its axis, the first of which transfers power through the clutch to the BOB, and the second is extended behind the Second World War and transfers the torque through the clutch to the DNV coaxial gearbox, the column of the output vertical coaxial shafts of which is placed in plan above the center of mass, is deflected backward along the flight by an angle (∠α), which is the same or equal to 1/2 at the angle (∠α _outside ) of the attack of the outer section of the NSC, and the incoming flow at vertical and horizontal flight modes meet simultaneously the front edges of the advancing blades of the coaxial DNVs and their respective DLC fixed accordingly, performing the role of the upper split wings with the angle of attack over the NSC in the RBNC DLK, which is equal to the angle (∠α) of the backward deflection of the shaft column of the coaxial gearbox of two DNVs, with the forward sweep the front edge of each side air intake of the KGTD as the left and right ra positioned parallel to the front edge of the NSC inflows in plan, moreover, the CCT nozzle and the outer sides of the fuselage engine compartment are placed in a top and front view respectively along the symmetry axis and between the corresponding tail sections of the seagull type, the inner and outer swept sections of which are made in the form of keels and stabilizers, equipped with rudders of direction and height, respectively. All this will make it possible to increase the speed and flight range of a reactive BUSW with coaxial DNVs, which, when performing operations with vertical lifting of cargoes, are very promising as wing-stopping and non-retractable flight screws, which eliminates the presence of very structurally complex systems for folding the column of their shafts and removing DNV , which will simplify the possibility of converting its flight configuration from a rotorcraft or helicopter of execution ДСНС-Х2 to the corresponding high-speed winged gyroplane or high-speed aircraft with marching PR -R1. In addition, the airborne or mobile version of the BUSV for the MARK will ensure the possibility of transporting it by air or land in the cargo compartment of the switchgear and will allow, using its combined SU with KGTD, to carry out the energy-consuming vertical take-off of the BUSV as a helicopter with a DNV drive from the CCT, but also to achieve time flight up to 2.4-2.8 hours and a speed of 700 km / h in the configuration of a jet aircraft with PRS-R1. Therefore, in the BUSW the coefficient of aerodynamic profitability of RBK with NSC and DLK DNV will be higher than that of jet VTOL. That will improve and weight return in comparison with the helicopter coaxial scheme. Moreover, all this will also make it possible to increase maneuverability at low flight speeds and during transitional maneuvers in comparison with a jet VTOL monoplane scheme, but also to reduce the stall speed for a set of increase by 1.2 times the coefficient of elevation of the RBF, which creates the NSC together with the DLK DNV advantage in production of lift during cruise flight BUSV.

The present invention is a MARK with a reactive BUSW, having reverse-seagull type NSC influxes, coaxial DNVs in DSNS-X2 and BOB in PRS-R1 with a jet flat nozzle at the end of the fuselage and between the feathers of the seagull type plumage, is shown in FIG. 1 with options for its use as part of an ATGM based on a floating MRS.

In FIG. Figure 1 shows a MARK with a BUS on general views of the front, top and side views of the MRI, respectively a), b) and c) for various uses of reactive BUSW:

a) in the flight configuration of a jet aircraft with an NSC, which creates greater lift than the lift created by autorotating coaxial DNVs or fixed by their DLK, and the Second World War, placed in the engine nacelle behind the NSC and before the plumage-type tail, creating a marching thrust in PRS-R1 for high-speed or high-speed flight and with the conditional placement of autorotating coaxial DNVs, the blades of which are shown by a dashed line in the configuration of a winged gyroplane;

b) in the flight configuration of the helicopter with the NSC and its sweep χ = + 20 °, wide-chord DNVs rotating above the NSC consoles, the wing-blades of the DNV are shown by dashed lines and with the conditional placement of the fixed DLK upper and lower DNV with a sweep of χ = + 20 ° in the configuration jet aircraft for high-speed flight and when performing takeoff and landing modes;

c) depicts a self-propelled MARK with an MPU, in the cargo compartment of which is fixed on a BUSH cradle with folded NSC and plumage consoles, retracted struts of its wheeled chassis and when the telescopic upper shaft is retracted, the axle shaft of axial DNV shafts, the blades of which are folded in the DLK and their pairs are directed back along flight for its transportation in a traveling configuration in the cargo compartment of the switchgear, which has a rigid frame and under its ceiling a crane-beam with a telescopic boom, cable and block with grips for loading and unloading operations.

A self-propelled MARK based on a floating MRU with a reactive BUSW of execution DSNS-X2 and WWII in PRS-R1, shown in FIG. 1, has an airframe made of aluminum alloys and composite carbon fiber in an integrated aerodynamic scheme, contains a fuselage 1, having both an NSC 2 with a vortex forming front 3 and developed rear 4 influxes, slats 5, inner and outer flaps 6 and ailerons 7, and tail such as a seagull having internal 8 and external 9 arrow-shaped sections, which are respectively equipped with rudders of direction 10 and height 11. Internal 12 and external 13 sections of NSK 2 with sweep χ = + 20 °, mounted respectively with positive and negative The right angles of the transverse V, forming the wing of the type of the reverse gull, have in their kinks and from the trailing edge of the NSC 2 underwing gondolas 14 with lower compartments for the rear main struts of the wheeled chassis (not shown in Fig. 1). The inner sections 8 of the tail unit of the seagull type are mounted on the outer sides of the tail beam 15, from the bottom of which the ventral keels 16 are mounted, having cameras 17 and IR emitters 18 at the front and back of their tips 18. The upper 21 is mounted behind the side air intakes 19 of the fuselage 1 on the vertical pylon 20 and lower 22 coaxial DNVs with rigid fastening of their blades, having for their full compensation of the reactive torque on the GDP regimes and hovering their opposite rotation, only clockwise and counterclockwise, respectively trolley, and in the column of coaxial shafts the inner shaft is made telescopic (in Fig. 1a, the telescopic shaft is shown in the lower position conventionally dashed). In this case, the control moments are provided by the lower DNV equipped with a swash plate (not shown in Fig. 1). In the engine nacelle 23 of the fuselage 1 in the PRS-R1 mounted one QGTD, which has an external and an internal contour, respectively, with the Second World War and CCT (not shown in Fig. 1). The combined control system is made with the front output of the shaft for power take-off from the CCT and the possibility of transmitting power from it through an intermediate gear to the DNV 21-22 coaxial gearbox (not shown in Fig. 1), which smoothly redistributes 95% and 5% of the control power take-off at fulfilling GDP and hovering between two DNV 21-22 in DPS-X2 and WWII in PRS-R1, respectively, having a flat nozzle 24 having a V-shaped trailing edge, which is parallel to the plan, at the end of the fuselage and between the inner sections 8 of the plumage type plumage similar trailing edge convenient btekaemogo fairing 25 of the tail boom 16, adapted termopogloschayuschim coating that reduces the IR visibility.

The control of the reactive BUSW is provided by the general and differential change in the pitch of the coaxial DNV 21-22 and the deviation of the ailerons 7 on the NSC 2, rudders 10 and 11 on the tail unit of the seagull type. When cruising high-speed or high-speed flight in the configuration of a winged gyroplane or jet aircraft, the lifting force is created by autorotating DNV 21-22 with NSK 2 or NSK 2 with fixed DLK of coaxial DNV 21-22 (see Fig. 1a) in RBK, marching jet thrust PRS-R1 system through a flat nozzle 24, in the transition mode - NSC 2 with DNV 21-22. After creating the lifting thrust, DNV 21-22 in DSNS-X2 provides the regimes of GDP and freezing or KVP when creating the marching thrust in PRS-R1 (see Fig. 1a). When performing GDP and freezing, a change in the balancing at the rate and pitch, roll is provided by the differential change in the thrust of the total pitch of the coaxial DNV 21-22 and the change in the corresponding cyclic step by means of the swashplate of the lower 21 DNV, respectively. 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 RPMs of the DNV 21-22 is carried out. As you accelerate with an increase in the lifting force of the wing of the NSC 2, the lifting force of the DNV 21-22 decreases. When reaching flight speeds of 400 ... 450 km / h and to switch to aircraft flight mode, DNV 21-22 synchronously stop so that their blades are pre-placed when viewed from above perpendicular to the leading edge of the NSC 2 consoles or parallel to the axis of symmetry and equipped with automatic nodes for folding their blades which then synchronously rotate outward from the axis of symmetry of the blades-wings of DNV 21-22 at an angle of 90 ° so that their DLK are fixed with a direct sweep along their front edges, forming an equal sweep of χ = + 20 ° with the NSC in the RBK (see Fig. 1B). When creating jet thrust in the PRS-R1, a high-speed cruise flight BUSV is performed, in which the directional control is provided by rudders 10. The longitudinal and lateral control in this case is carried out by in-phase and differential deviation respectively of rudders of height 11 of the tail unit of the gull and ailerons type 7 NSK 2. Radar station 26 with a command transmitter and an optoelectronic system with a two-channel automatic machine 27 target tracking mounted respectively in the nose of the fuselage 1 and fender in front GOVERNMENTAL gondolas 14.

The floating MPU 28 has a rigid frame with a closed cargo compartment 29, is equipped inside with a corresponding lodgement 30 for fixed placement of the fuselage 1 of the BUSV with its struts removed in its traveling configuration, but also with openable rear doors 31 for loading and unloading, but also a crane-beam 32 mounted on the ceiling of the cargo compartment 29 and along the longitudinal axis of the MPU 28, having a telescopic boom 33 and at its end a cable 34 with a block 35 and corresponding grips 36 for engaging the fuselage 1 of the BUSW, lifting it after off the operation of the locks of all the latches 37 on the lodgement 30 and moving outward to the take-off platform on the ground for vertical take-off of the BUSV with ammunition, for example, with anti-tank missiles, located on the lower intra-compartment ejection devices for transportation and their launch (not shown in Fig. 1) .

When fulfilling GDP in order to increase safety, at the ends of the NSC 2 there are signal lights 38 and proximity sensors 39 warning the sound siren of an unacceptable approach with extraneous objects. The BUSV autopilot system performs an independent take-off after selecting and confirming a route, identifies obstacles that appear along the route and gives a command to fly around them, and then ensures a soft landing at a given point. In addition, the reactive BUSW has a system of automatic return to the point of departure, which will turn on if the operator does not respond to computer requests. After landing on the ground on the ground, the outer tail sections 9 and 12 of the NSC 2 are folded up, and the DLK HB 21-22 are placed on the axis, then the Crane beam 32 of the BUSV is loaded onto the cradles 37 for transportation in the MRU 28 on the highway or on the ground.

Thus, the development of BUSW with improved tactical and technical indicators for MARC in modern conditions is a multifaceted task and is not technically unsolvable. Therefore, further research in the development process of a wide family of BUSWs, implemented according to the concept of DSNS-X2 and PRS-R1, then the task of mastering and deck-based BUSV-0.95 will be dictated by life itself (see table).

Claims (5)

1. An aviation missile system with an unmanned attack helicopter, including a platform containing basing equipment with a launch station, a power plant and a flight control unit for an unmanned multi-rotor system (BPMS) with a power plant (SU), characterized in that the said BPMS is an unmanned attack helicopter aircraft (BUS) with an integrated aerodynamic layout, equipped as a fuselage, the bow of which is smoothly interfaced with vortex-forming frontal influxes having an angle sweeps and attacks other than the wing, increasing its carrying ability at large angles of attack, propagating from the leading edge of the wing and along the nose of the fuselage to its fairing, form a V-shaped configuration with a rounded apex, and at least one combined gas turbine engine (KGTD), which is installed in the engine nacelle mounted in the fuselage behind the wing, and is made in the form of a dual-circuit engine having external and internal circuits, respectively, with an external single-row fan ohm (BOB) in the annular fairing and with at least one free power turbine (CCT) equipped with a front output of the shaft for power take-off and its transmission through the intermediate gear to the input shaft of the coaxial gear, redistributing the take-off power of the SU between the two-bladed HB (DNV) in symmetrically balanced twin-screw coaxial bearing system (DPNS-X2) and WWII, with blades with a large twist, working according to the pulling pattern, installed in front and coaxially with an intermediate gearbox to create a propulsion-reactive the PRS-R1 system of marching thrust directed parallel to the axis of symmetry during vertical and short take-off / landing (GDP and KVP) or horizontal translational flight, but also with a low swept wing (NSC) having a sweep angle χ = + 20 °, swing in

or

times the diameter (D) of the DNV, the internal and external sections forming an NSC of the type reverse gull are mounted with negative (ϕ _outward ) and positive (ϕ _out ) angles of the transverse V, respectively, and configured to convert its flight configuration after performing short and vertical take-off, respectively, from a rotorcraft or helicopter at its maximum or normal take-off weight to the corresponding high-speed winged gyroplane or jet aircraft, respectively, with wide-chord DNVs operating on the scope of their autorotation or hollow wing-blades (DLK) carrying them, when the upper and lower DNVs are simultaneously stopped so that when viewed from above, their front and rear blades are both pre-arranged perpendicularly to the front edge of the left and right NSC consoles, and are equipped with automatic nodes their simultaneous folding by rotation through an angle of 90 ° in a horizontal plane outward from the axis of symmetry of the DNV wing blades so that they are fixed with a direct sweep along the leading edges of the DNV DLK, forming with the NSC equal sweep χ = + 20 °, organizing synchronously-symmetrical bearing surfaces of their DLK with respect to the axis of symmetry and fixed in plan parallel to the leading edge of the NSC in the flight configuration of the jet aircraft with PRS-R1 and the biplane system of different levels of wings (RBK), which transforms the large elongation of the NSC with λ = 10.5–11.5 to moderate elongation λ = 5.0–6.0 RBK, with the upper and lower DLK DNV fixed outward from the axis of symmetry, placed when viewed from the front, respectively, above the left and right NSC consoles, but also vice versa at e In the KGTD engine nacelle with a BHO annular cowl, at least one CCT has an intermediate gearbox equipped with both an input shaft and output external and internal coaxial shafts longitudinal along its axis, the first of which transfers power through the clutch to the BOB, and the second is extended behind the Second World War and transfers the torque through the clutch to the DNV coaxial gearbox, the column of the output vertical coaxial shafts of which is placed in plan above the center of mass, is deflected backward along the flight by an angle (∠α), which is the same or equal to 1/2 at the angle (∠α _outside ) of the attack of the outer section of the NSC, and the incoming flow at vertical and horizontal flight modes meet simultaneously the front edges of the advancing blades of the coaxial DNVs and their respective DLC fixed accordingly, performing the role of the upper split wings with the angle of attack over the NSC in the RBNC DLK, which is equal to the angle (∠α) of the backward deflection of the shaft column of the coaxial gearbox of two DNVs, with the forward sweep the front edge of each side air intake of the KGTD as the left and right ra positioned parallel to the front edge of the NSC inflows in plan, moreover, the CCT nozzle and the outer sides of the fuselage engine compartment are placed in a top and front view respectively along the symmetry axis and between the corresponding tail sections of the seagull type, the inner and outer swept sections of which are made in the form of keels and stabilizers, equipped with rudders of direction and height, respectively. 2. Aircraft missile system with BUSV according to claim 1, characterized in that at least one of the FTAs in the GDPs and the BUSs hangs up, said at least one FTA is made with digital program control elements that combines in a dual-mode regulation and control system its simultaneous operation as during selection 95% of its take-off power to the drive of the aforementioned DNVs, and with a balanced distribution of 5% of the residual power to the drive of the mentioned WWII, which creates the minimum marching thrust for the required horizontal translational flight, At the same time, for an economical high-speed horizontal flight, reaching marching thrust-weight ratios of up to 0.22 and 0.36, 35% and 70% of the power is used, respectively, from more than one working mentioned KGTD in SU only to drive the mentioned WWII in the configuration of the aircraft with PRS-R1, moreover, in the regimes of GDP and freezing, full compensation of the reactive torque in DSNS-X2 from working DNVs made with rigid fastening of their blades is created by the opposite direction of rotation of the upper and lower DNV, respectively, in plan, only according to clockwise and counterclockwise, and the change in the balancing along the course and pitch, roll is provided by the differential change in the thrust of the common pitch of the coaxial DNVs and the change in the corresponding cyclic step by the automatic lower left DNV swashplate, respectively, while the autonomous control system of the BUSV, including as an autopilot for independent take-off after selection and confirmation of the route, as well as the system of automatic return to the departure point, which will turn on if the operator does not respond to and on-board computer requests, but also tracking systems that identify obstacles that appeared on the flight path and give a command to automatically fly around them, and then provide a soft landing at a given point, and in the traveling configuration of the BUSW its left and right outer sections folding downwards corresponding fractures of the said plumage type plumage, and in the flight configuration, when viewed from the front, they are mounted horizontally or parallel to the inner section of the NSC, while in the fractures of the NSC consoles of the type the reverse gull behind the rear the edge has underwing gondolas with compartments for accommodating the rear main struts of the wheeled chassis in them, the inner sections of the NSC with the wing gondolas having a span equal to the span of the internal sections of the plumage such as a seagull, and the outer sections of the said NSC are made with double folding of the inner and outer ends which are sequentially deflected upward respectively to the axis of symmetry and back downwards, while being inclined to the plane of symmetry and along the upper lateral sides of the fuselage and not higher and not the tail of a folded plumage such as a seagull, providing a transport configuration of a BUSW with a telescopic upper shaft retracted by a column of shafts of its coaxial DNV shafts, the blades of which are folded in the DLK and their pairs are directed one above the other, while performing GDP and hovering to increase safety at the ends of the endings of the aforementioned The NSC has signal lights and proximity sensors that warn the siren of an unacceptable approach with foreign objects, while the front and rear ends of the ventral fins are mounted There are corresponding cameras and infrared emitters under the corresponding internal sections of the said plumage type plumage, which are deflected outward from the plane of symmetry, and the central part of the fuselage and the front flows of the NSC are equipped with lower intra-compartment ejection devices for transporting and launching, for example, guided aircraft missiles, which enable their use in various ways of its execution and basing, moreover, the tail beam, equipped at its end across the entire width of the fuselage btektelekom, which, forming a bearing surface, is integrated over its outer sides with the inner sections of the plumage type plumage and has a V-shaped rear edge in plan, which in plan is placed parallel to the same rear edge of the flat nozzle, made with a heat-absorbing coating that reduces IR visibility . 3. Aircraft missile system with BUSV according to any one of paragraphs. 1, 2, characterized in that the said BUSW, having both a closed-circuit radio channel with a ground mobile platform made in the form of an intelligence and control machine (MRU), mainly floating with a caterpillar or six-wheel all-wheel drive propulsion, and a radar station with a command transmitter, optical -electronic system with a two-channel target tracking automaton and a computer system with an automation unit of a multifunctional control panel, which provides for independent cruise flight walking a number of targets, identifying them and making a confirmed decision from the MRU operator about destroying the chosen ones, is made in the form of a column of coaxial shafts transported in a traveling configuration with folded external sections of the NSC and tail unit with the internal telescopic shaft lowered and the corresponding blades of the corresponding DNV and rigid fixing in the cargo compartment of the MRU anti-tank missile system (ATGM), while the closed cargo compartment of the MRU, having a rigid frame, is provided inside to as an appropriate lodgement for fixed placement of the BUSV fuselage in it with retractable struts of its chassis in the traveling configuration, as well as openable rear doors for loading and unloading operations, but also with a crane beam mounted on the ceiling of the cargo compartment and along the longitudinal axis of the MPU having a telescopic an arrow and at its end a cable with a block and corresponding grips for engaging the fuselage of the BUSV, lifting it after disabling the locks of all the latches and moving outward to the take-off ground on the ground for vert of a rocket take-off of a BUSV with an ammunition load, for example, with anti-tank guided missiles (ATGMs) placed in transport and launch containers (TPK), fixed by two TPKs on each side of each beam holder mounted under the fuselage and under the internal sections of the NSC and alternately mounted / manually filmed by operators. 4. Aircraft missile system with BUSV according to any one of paragraphs. 1, 2, characterized in that the said platform is made in the form of a stationary charging station mounted on a launch and receiving platform, placed on a vehicle, for example, on a road, rail or water, ensuring its installation, transportation and operation with appropriate movement, with this in the ship’s anti-submarine missile system (KPLRK) carrier-based BUSW, carrying more than one aircraft anti-submarine missile APR-3E, equipped with a lowered sonar system, comp boxes from the indicator of acoustic signals and two receivers for their reception from a sonar buoy, their encoding and transmission via an eight-channel closed connection to the ship for real-time processing, and a highly sensitive magnetometer mounted in an elongated fairing of the tail boom so that the lower end of the part a magnetically sensitive element is installed, operating at a distance of 30 m from the water surface, and is equipped with a mooring device with an automatic control lever below the fuselage below the center of mass Ia having a deflectable on up / down telescopic arm locking mechanism and gripping device into contact with the cells of the lattice of the deck, providing the possibility of landing on a helipad ship rolls at 25 °. 5. Aircraft missile system with BUSV according to any one of paragraphs. 1, 2, characterized in that the said platform, having a mobile or airmobile design, is made in the form of an automobile wheeled trailer towed, for example, by a Tiger-M armored car, equipped with its retractable weapons modules, for example, with ATGMs of the Kornet- type D ", or equipped with the possibility of their separate mounting on pallets and, if necessary, landing from a transport aircraft on parachute systems for their quick deployment.

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