RU2791754C1 - Multi-purpose unmanned aircraft missile system - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates in particular to designs of unmanned aerial systems. The unmanned aerial missile system contains a reusable aviation returnable missile (RATM) with a high-precision guided munition having a frontal guidance kit and a range extension kit installed behind it. The missile has a modular design that can be used with various types of bombs and their guidance units, and with the possibility of automatic vertical landing on the tail of the RATM by means of a propeller-jet system. The propeller-jet system includes a turbojet engine with a controlled thrust vector and power take-off for the drive of coaxial two-bladed main rotors (TMR), which enables flight at altitude with the X-shaped front fins, rear wing and pulling TMR or with folded TMR blades, respectively, to attack the target or for a mortar launch from a vertical transport and launch container.

EFFECT: increased flight range, reduced dimensions in the transport position, possibility of repeated use.

2 cl, 1 tbl, 3 ex

Description

The invention relates to unmanned aircraft missile systems (BARS) with a reusable aviation returnable missile (MAVR) and its corresponding high-precision guided munitions, having a frontal guidance kit and a range extension kit installed behind it, and a modular design that provides use with various types of bombs and their guidance units, but also with the possibility of automatic vertical landing on the tail of the MAVR by means of a propeller-jet system, including a turbojet engine with a controlled thrust vector and power take-off for the drive of coaxial two-blade main rotors (DNV), providing at altitude up to / supersonic flight with expanded X -shaped front plumage, rear wing and pulling DNV / with folded DNV blades, respectively, for performing a mission / when attacking a target / for a mortar launch from a vertical transport and launch container and an appropriate base.

Known complex for the destruction of submarines (submarines) at long ranges, patent RU 2371668 C2, made in the form of a ballistic missile (BR), in the bow of which a cruise missile (CR) is placed under a drop fairing; The missile launcher contains aerodynamic surfaces with drives and an accelerating engine to ensure the delivery of the missile launcher to the firing range to the target area. For economical flight in the atmosphere, the CD is docked with an accelerating engine by means of a separation device, made with the ability to fly in the area of the location of the submarine target and contains a detachable warhead (warhead) of underwater action and a detachable sonar buoy; the control system of the CD is equipped with equipment for receiving information from the sonar buoy via a radio channel about the location of the target. In accordance with the commands that search for the target, its detection, approach to the target and its defeat by undermining the warhead. After that, the BR-carrier continues to fly with the engine running, moving it away from the place of splashdown of the underwater warhead so as not to interfere with its homing system when the disposable BR left the warhead splashdown area and self-destructed.

Known unmanned aircraft project "X-plane" company "Northrop Grumman" (USA) [http://test.abovetopsecret.com/forum/thread398541/pgl], made according to the scheme of the flying wing asymmetrically variable sweep (CAIS), has a turbojet bypass engines (TRDD) in a nacelle with internal bomb bays and a tricycle retractable wheeled landing gear. For supersonic flight "X-plane", two General Electric J85-21 turbofan engines with a jet thrust of 4485 kgf provide a speed of 1275/1487 km / h at a flight altitude of 15 km with a thrust-to-weight ratio of 0.54 / 0.68. Aircraft with KAIS have a number of disadvantages, the main of which are: displacement of the aerodynamic focus with multidirectional sweep, which leads to an increase in balancing resistance; an increase in the mass of the structure due to the presence of rotary hinges of the consoles. In addition, at a large sweep angle of 45°, the forward-swept console has a larger effective angle of attack than the reverse-sweep console, which leads to drag asymmetry and, as a result, to the occurrence of parasitic turning moments in roll, pitch, and yaw. Moreover, KAIS is characterized by a twice as large increase in the thickness of the boundary layer along the span, and any asymmetric stall causes intense disturbances, and their elimination is achieved by using the bilateral airframe asymmetry.

Closest to the proposed invention is [see. http://rbase.new-factoria.ru/missile/wobb/ikara/ikara.shtml] British carrier-based anti-submarine aviation missile system (PARK) of the "Icara" model with an unmanned aerial vehicle (UAV) having a wing, a fuselage with a launcher device (PU) of ammunition (BP), the engine of the power plant (SU) and the onboard control system (BSU) for control from the command post of the home base.

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

The reasons that impede the task: the first is that the 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. Based on this information, data on the optimal torpedo drop zone is constantly updated in the computer of the fire control system, which then transmitted them in flight through the BSU to the UAV. Upon the arrival of the UAV in the target area, the Mk.44 torpedo, semi-recessed with its ventral location in the UAV body, was separated by radio command, descended by parachute, entered the water and began searching for the target. After that, the UAV continues to fly with the operating control system, moving it away from the splashdown point of the homing SNT so as not to interfere with its homing system. The disposable UAV itself left the area and self-destructed.

The present invention solves the problem in the above-mentioned well-known PARK "Icara" of automatic return to the base with a vertical landing on the tail of the shock MAVR by means of a propeller-reactive system, reducing the dimensions in its transport and marching configuration, increasing the speed and flight range, but also economic efficiency due to reusable its use.

Distinctive features of the proposed invention from the above-mentioned well-known PARK "Icara", closest to it, are the fact that the multi-purpose AURUS includes more than one reusable aviation returnable missile (MAVR), made as a composite longitudinal triplane scheme, carrying a controlled BP (UBP ), which includes a frontal homing kit (KFSN) with duplanar X-shaped wings (DHOK) in front and a range extension kit installed behind it, which is a turbo-propfan unmanned helicopter (BPSV), made according to the "duck" aerodynamic configuration, so and in a modular design, ensuring its use with various types of bombs through the appropriate transition compartments and blocks with CFSN, but also with the possibility of automatic return and vertical landing with the vertical position of the fuselage of one BPSV or as part of the MAVR, respectively, without or with a high-precision UBP at a minimum or maximum landing ma ce by means of the BPSV propeller-jet system, including a bypass turbojet engine (TRDD) with side air intakes (BVZ) and 44% power take-off for the drive of coaxial two-bladed main rotors (DNV), providing sub-/supersonic flight at altitude with X-shaped front tail and rear wing (HOPO and HOZK) and DNV blades made with a rigid mount, without swashplates and with a change in their total pitch / with DNV blades folded down at an angle of 90 ° mutually perpendicular in plan to the longitudinal ledges of the fuselage, respectively, for mission / attack purposes / for a mortar launch, for example, from a vertical transport and launch container (TPK) of a ground or sea anti-ship complex (PKK), with provision outside the TPK of launching a turbofan engine and synchronous unfolding and fixing of the swept front wing consoles in the DHOK, including the all-swivel rear trapezoidal wing in DHOK, mounted on the body of the CFSN, as well as to increase the path howling stability at supersonic flight speeds all-moving HOPO and HOZK, mounted on the fuselage of the BPSV in the MAVR, carrying the UBP to carry out the mission and attack the target, for example, an armor-piercing aerial bomb (BrAB) of the BrAB-500DS type with a rocket booster located in the transition compartment, equipped with automatic docking / undocking units with the bow of the BPSV, flying with its covert extension to the surface target area to complete the mission and return flight of the BPSV to the launch site, for example, to a large missile ship (BRK), while the MAVR, made in the design for ground or sea or air-based and with the possibility of both an appropriate launch from a TPK or its launch from a carrier aircraft, and after completing its mission, returning the BPSV to a ground or sea-based base or to an airfield based on a carrier aircraft with its vertical landing in a covert position , for example, a ground-based PKK containing a self-propelled launcher (SPU) of the K-340P type with two TPK d for launching the MAVR and a self-propelled landing pad with its heat-resistant upper coating and a tilting mast to receive the BPSV after it has landed on the tail and folded its HOZK and DNV to bring them to a horizontal position and interact with the PKK transport and loading machine, and, for example, on a strike DBK containing more than one of its sea-based TPKs of the corresponding MAVR, which has, for example, BPSV, for landing operations in a vertical position of the fuselage, in the aft part of the latter there are landing trapezoidal in terms of four folding frames with self-aligning rounded ones in the plane of each blade of the DNV in terms of shock-absorbing supports located azimuthally through 90 °, connected with the telescopic rods of their main cylinders, providing from the corresponding ledges of its fuselage the opening of the landing supports, carried back along the flight and outward from the aft propulsion system (KDU), which ensures the execution of the MAVR mission in the mode its autonomous flight or in an anti-ship air group, while the fuselage of the BPSV in its aft part contains internal longitudinal compartments or niches in trapezoidal X-shaped root influxes (HOKN), designed for simultaneous laying in / unfolding of them HOZK consoles, made with their reverse narrowing and smoothly passing into its central part of the fuselage, equipped with BVZ, made unregulated to ensure subsonic and supersonic operation and placed behind its longitudinal ledges, designed to fit the blades of the upper DNV into them, and when performing vertical takeoff / landing and hovering, the transmission system provides transmission of power from the turbofan engine through the clutch to the intermediate reduction gear, the output shaft of which, located above and along the longitudinal axis of the fuselage of the BPSV, is rotatably connected to the angular intermediate gear when viewed from the side, which transmits torque to the coaxial main gearbox (MGR), in which the lower and upper DNV, fixed on its respective output shafts, the upper hollow of which is equipped with an internally hollow fixed shaft (PNV), which is rigidly fixed with its lower end inside the SHR body, mounted on stiffeners fixed inside the central part of the fuselage of the BPSV, and the output end is centered relative to the upper SGR shaft using a bearing assembly so that the output part of the NVG protruding from its upper shaft is fixed to the upper support housing, mounted, for example, on seven stiffeners fixed inside the forward part of the BPSV fuselage.

In addition, in the transport and stowed position of the MAVR, the folded consoles of its HOZK in the BPSV are closed with the mentioned KDU divided fairing, repeating the outer and inner profiles of the mentioned TPU and the aft part of its fuselage, respectively, having the ability to automatically remove it or reset it along with simultaneous reset and two fairings from the inputs of the BVZ when launching a composite MAVR into flight, respectively, from a TPK or launching a carrier aircraft, moreover, the mentioned CFSN in the mentioned UBP is equipped with a combined control system based on inertial and satellite modules, which include a hybrid inertial navigation system / global guidance positioning system with the possible addition of infrared homing or laser guidance to improve accuracy, while modules with an optoelectronic homing head or laser sensors for precise targeting, which are mounted in the bow of the KFSN hull or on the leading edges of the unfoldable consoles of the front wing in DHOK or HOPO, and the expansion of the bilaterally asymmetric layout of the MAVR airframe in its mentioned DHOC, HOPO and HOZK includes in the longitudinal direction an asymmetric displacement of their consoles, which provides, when overcoming the supersonic barrier, a sinusoidal distribution of the formation of air seals on the leading edges of their consoles spaced apart so that each upper right console in DHOK, HOPO and HOZK is moved forward in flight from each of their left upper console with a gap equal to, for example, δ _zaz , each of the latter, in turn, is moved back along the lash from each of their left lower console with a gap equal to 1/2 δ _zaz , each of which, in turn, is moved forward along the lash from each of their right lower console with a gap equal to δ _zaz , while the MAVR airframe is made using low-profile technology with a coating that absorbs radio waves of different lengths, has a solid structure of its rigid hulls using aluminum-lithium alloys and up to 75% improved in structural aging of composite materials reinforced with spars and stiffeners with a single fuselage skin and BVZ made of composite materials reinforced with carbon fiber, capable of protecting its said BSU from powerful electromagnetic flashes or exposure to laser radiation, withstand significant amounts of heat and deformation, allowing to reduce by an order of magnitude the amount parts, and MAVR, when it takes off from the deck of the said DBK or is launched from the said TPK, respectively, with a normal or maximum take-off weight with its said turbofan engine, creating with DNV their lifting thrust-to-weight ratio with the vertical position of the fuselage, which is K _Pt = 1.4 or K _Pt = 1.2, which, after the completion of the transitional maneuver, automatically changes with the horizontal position of the fuselage to the sustainer thrust ratio: the first level - 0.15 or the second - 0.3 or the third - 0.34, using the mentioned turbofan engine with 43.3% or 86, respectively, 6% or 100% takeoff power of its adaptive control system with the provision of n and at a flight altitude of at least 12 km, the maximum flight speed Mach (M) = 0.9 or M = 1.04 or M = 1.1, respectively, and its HOZK with sweep χ = + 60 ° will allow, in comparison with the jet wing of the aircraft and its sweep angle χ=+45°, to reduce the wave drag and the required thrust-to-weight ratio, while ensuring and maintaining at an altitude of the trans- or supersonic flight mode of the MAVR, respectively, in the direction of the target chosen for attack or only after 49% of the mission time and fuel generation, and when using the sweep of its HOZK, for example, with an angle χ=+30° or χ+60°, which will provide an increase in the aerodynamic and structural advantages of the airframe of bilateral asymmetry, which improves the ratio of aerodynamic quality to its resistance, which, with an appropriate MAVR flight speeds up to Mach 0.98 or Mach 1.1 will be 20 to 1 or 11 to 1, while in the inconspicuous MAVR, which has an effective dispersion area of 0.01 m ² , in its of the aforementioned KDU, the mentioned turbofan engine is equipped with a rotary jet nozzle (PRS) with a system of its all-aspect thrust vector control (VUVT), and the turbofan engine with VUVT in different directions of movement of its RRS is made with the possibility of deflection by angles of ±15 °, while in vertical flight modes and with the corresponding position of the fuselage, for example, a highly maneuverable BPSV and to perform the said landing on the tail, implemented using the mentioned DNV and the gas-dynamic method, which ensures the creation of control forces and moments during the operation of a turbofan engine with a VUVT of its RRS, equipped with the possibility of its deflection back and forth or to the left / to the right at angles of ±15° from the vertical, which creates a change in pitch or roll balancing, respectively, and in the event of a change in torques with the opposite rotation of the lower and upper mentioned coaxial DNVs, a change in balancing along the course is provided, moreover, on top of the fuselage of the BPSV in its longitudinal compartment, equipped with automatic doors and automatically ejected parachute system used for its emergency landing on a ground airfield with simultaneous folding of the mentioned consoles of its HOPO and HOZK.

The proposed invention of a multi-purpose AURUS with its MAVR, having folded DHOC on the body of the CFSN and HOPO with HOZK on the fuselage of the BPSV, is mounted in a TPK, has a turbofan engine with a VUVT of its RRS, is illustrated in Fig. 1-3 general views:

- in Fig. 1/2 - shows the MAVR in the side / top view as part of a turbofan BPSV with HOPO and HOZK, which is docked by means of a transitional compartment with a high-precision UBP equipped in front with a KFSN housing with DHOK in the folded / unfolded form of their consoles (see view A) for a mortar cold start from a TPK of a ground-based PKK / after launch from a pylon of a carrier aircraft;

- in Fig. 3 - shows the BPSV in a top view with a deployed HOPO and a folded HOZK with its sweep χ + 30 ° in vertical flight modes and with the vertical position of the fuselage for landing on the tail using four shock-absorbing retractable landing legs having a trapezoidal shape when viewed from the side with rounded supports and carried back and out from its KDU.

The modular AURUS shown in FIG. 1-3, contains in the TPK 1 shock MAVR 2 with a resettable aft fairing 3 (shown in dotted line in Fig. 1), made according to the longitudinal scheme of the triplane, carries the UBP 4, including the hull 5 of the CFSN with a folding swept front wing 6 and a rear one-piece swivel trapezoidal wing (TsPTK) 7 in the DHOK 6-7 and the transition compartment 8 connecting the UBP 4 with the BPSV 9, having a one-piece rotary HOPO 10 with laser sensors 11 for precise targeting at its leading edge and laid out from the root influxes 12 of the reverse narrowing of the HOZK console 13. Inconspicuous BPSV 9, made according to the "duck" aerodynamic scheme, contains a fuselage 14 with two BVZ 15 and four longitudinal ledges 16, designed to accommodate four folding blades of the upper 17 and lower 18 coaxial DNV, as well as four deployable landing legs, mounted at the end of KDU 19, made in the form of folding trapezoidal frames 20 with self-aligning, rounded in terms of cushioned supports 21. Small-sized turbofan , located in KDU 19, is made with VUVT of its PRS 22 and a transmission system that, when performing vertical takeoff / landing and hovering, provides in the adaptive control system the transfer of 44% of the power from the turbofan engine to the drive of the upper 17 and lower 18 coaxial DNV. In the central part of the fuselage 14 of the BPSV 9 above its center of mass, the upper longitudinal compartment 23 is mounted with automatic flaps and an automatically ejected parachute system (not shown in Fig. 1-3), used for its emergency landing on the ground airfield basing its carrier aircraft with simultaneous folding consoles HOPO 10 and HOZK 13 BPSV 9.

Modular MAVR 2 / low-profile BSV 9 perform a joint or separate flight, respectively, after launching a ground-based PKK from TPK 1 / to perform a mission when diving and creating a control system for the required jet thrust of its turbofan engine with a VUVT of its PRS 22 for trans- / supersonic cruising flight, in which longitudinal and directional control is provided by synchronous and asynchronous deviation of the two upper TsPTK 7/HOPO 10. Transverse control is carried out by differential corresponding deviation of the left and right lower TsPTK 7/HOPO 10 (see Fig. 1/2). The traffic control of both MAVR 2 and BPSV 9 at all stages of the flight is carried out by the navigation flight complex, which is part of the onboard control system, which receives and processes information from navigation satellites and generates appropriate control signals. All this will allow in the multi-purpose AURUS to simplify controllability and improve reliability, as well as the safety of remote control and MAVR 2 and BPSV 9.

Thus, the development of a mobile or deck AURUS with an air group of supersonic MAVR-0.66 based as part of a ground-based PKK, respectively, on a transport-loading vehicle (TZM) of the K-342R type or an atomic DBK, which may include at least twelve TPK of the ZS type -14-11442M, used both for launching the Oniks anti-ship missiles, and for the corresponding number of MAVR-0.66, carrying one BrAB-650DS each (see Table 1) and having a head BPSV reconnaissance, which is fully digitized and includes using a laser communication channel and the fourth level of the so-called manned and unmanned teaming (MUM-T), which will allow equipping it with a dual-frequency airborne radar with AFAR, which, at safe distances for it, communicates via a closed channel with other BPSV reconnaissance units in other AURUS, providing geolocation of a surface target and control over a laser communication channel of anti-ship weapon loads of their MAVR with target guidance of their BrAB-650DS as part of a strike air group, used in conjunction with a number of the home of other AURUS capable of exchanging information between their leading BPSV reconnaissance units within their unmanned unified system and transmitting target designation to a number of other MAVRs. In addition, the use of the MAVR-0.5 / MAVR-0.66 mortar launch capability from their TPK in mobile land-based / sea-based PKKs will increase the mass of their aviation fuel by 1.8 times, increase the destructive capability and combat stability of the PKK. At the same time, by converting MAVR-0.5 to a target load (TsN) = 0.52 kg and its UBP on the X-35U anti-ship missiles, and having a range of up to 1400 km, it will increase the range of anti-ship missiles to 1660 km, which is practically 6.3 times greater than the range of destruction of the coastal PKK "Bal" with anti-ship missiles Kh-35U.

Since the promising AURUS with advanced tactical and technical indicators for a mobile PKK delivering the MAVR-0.66 BPSV air group carrying BrAB-650DS to the Arctic region, its development, taking into account the experience of creating TPK of the ZS-14-11442M type, is also used for launching RCC "Onyx" is an economically preferable and technically feasible task. Only the development of the Arctic AURUS will significantly simplify the deployment of anti-ship aircraft and greatly increase its combat stability, especially at a great distance from the target and the base. In fact, the combat capabilities of the AURUS are not limited to the flight of its MAVR and are more dependent on the mobile PKK. Therefore, attack MAVRs, as elements of advanced military equipment, from the point of view of tactics, can occupy an intermediate place between cruise missiles and aircraft. The former are capable of independently attacking targets, but at the same time they are very expensive. Attack aircraft, taking into account its Arctic base, will also not be cheaper, but aircraft still have to fly into the target's air defense coverage area. The use of MAVR-0.66 will allow them to carry out a strike mission with the required efficiency and without risks for pilots, but also, playing the role of the so-called "arm's length", increase the damaging capability.

Claims (2)

1. Multi-purpose unmanned aerial missile system (BARS) with an unmanned aerial vehicle having a wing, a fuselage with an ammunition launcher (PU), a power plant engine (PU) and an onboard control system (BSU) for control from the command post of the home base , characterized in that it includes more than one reusable aviation returnable missile (MAVR), made as a composite longitudinal triplane scheme, carrying a controlled BP (UBP), including a frontal homing kit (KFSN) with duplanar X-shaped wings (DHOK) in front and a range extension kit installed behind it, which is a turboprop-fan unmanned aircraft-helicopter (BPSV), made according to the "duck" aerodynamic scheme, and in a modular design, ensuring its use with various types of bombs through the appropriate transition compartments and blocks with CFSN, but also with the possibility of automatic return and vertical landing when vertical position of the fuselage of one BPSV or as part of the MAVR, respectively, without or with a high-precision UBP at a minimum or maximum landing weight by means of a propeller-jet system BPSV, including a bypass turbojet engine (TEF) with side air intakes (BVZ) and 44% power take-off for the drive of coaxial two-blade rotors (DNV), which provides at altitude up to / supersonic flight with unfolded X-shaped front plumage and rear wing (HOPO and HOZK) and DNV blades made with a rigid mount, without swashplates and with a change in their total pitch / with folded down by an angle of 90° with mutually perpendicular blades of the DNV in the longitudinal ledges of the fuselage, respectively, for performing a mission / when attacking a target / for a mortar launch, for example, from a vertical transport and launch container (TPK) of a ground or sea anti-ship complex (PKK), with provision outside the TPK launch of the turbofan engine and synchronous unfolding and fixation of swept consoles her front wing in the DHOK, including the all-moving rear trapezoidal wing in the DHOK, mounted on the body of the CFSN, as well as to increase directional stability at supersonic flight speeds, the all-moving HOPO and HOZK, mounted on the fuselage of the BPSV in the MAVR, carrying to carry out the mission and attacking the UBP target, for example, an armor-piercing aerial bomb (BrAB) of the BrAB-500DS type with a rocket booster located in the transition compartment, equipped with automatic docking / undocking units with the bow of the BPSV, flying with its covert extension into the surface target area to complete the mission and return flight of the BPSV to the launch site, for example, to a large missile ship (BRK), while the MAVR, made for land or sea or air-based and with the possibility of both an appropriate launch from a TPK or its launch from a carrier aircraft, and after fulfillment of its mission of returning the BPSV to a land or sea home base or to a home airfield I am a carrier aircraft with its vertical landing in a covert position, for example, a ground-based PKK containing a self-propelled launcher (SPU) of the K-340P type with two TPKs for launching the MAVR and a self-propelled landing site with its heat-resistant top coating and a tilting mast to receive the BPSV after landing on the tail and folding its HOZK and DNV to bring them to a horizontal position and interact with the PKK transport and loading machine, moreover, for example, on a shock DBK containing more than one of its TPK for sea-based corresponding MAVR, which has to perform landing operations with the vertical position of the fuselage, for example, BPSV, in the aft part of the latter there are in the plane of each blade of the DNV landing trapezoidal in terms of four folding frames with self-aligning shock-absorbing supports, rounded in plan, located azimuthally through 90 °, connected with the telescopic rods of their main cylinders, providing from the corresponding ledges of its fuselage p concealment of landing supports moved back along the flight and outward from the aft propulsion system (KDU), which ensures the implementation of the MAVR mission in its autonomous flight mode or in an anti-ship air group, while the fuselage of the BPSV in its aft part contains internal longitudinal compartments or niches in trapezoidal X- shaped root influxes (HOKN), designed for simultaneous laying in / unfolding of them HOZK consoles, made with their reverse narrowing and smoothly passing into its central part of the fuselage, equipped with BVZ, made unregulated to ensure subsonic and supersonic operation and placed behind the longitudinal its ledges intended for laying the blades of the upper DNV in them, and when performing vertical takeoff / landing and hovering, the transmission system ensures the transfer of power from the turbofan engine through the clutch to the intermediate reduction gear, the output shaft of which, located above and along the longitudinal axis of the fuselage of the BPSV, rotator but connected with an angular intermediate gearbox in side view, which transmits torque to the coaxial main gearbox (SGR), in which the lower and upper DNV are fixed on its respective output shafts, the upper hollow of which is equipped inside with a hollow fixed shaft (NV), which is rigidly fixed with its lower end inside the SGR body, mounted on stiffeners fixed inside the central part of the BPSV fuselage, and its output end is centered relative to the upper SGR shaft using a bearing assembly so that the output part of the NVG protruding from its upper shaft is fixed to the upper housing of the support, mounted , for example, on seven stiffeners fixed inside the forward fuselage of the BPSV. 2. The multi-purpose unmanned aerial missile system (BARS) according to claim 1, characterized in that in the transport and stowed position of the MAVR, the folded consoles of its HOZK in the BPSV are closed with the mentioned KDU divided fairing, repeating the outer and inner profiles, respectively, of the said TPU and the aft part of it fuselage, having the ability to automatically remove it or reset along with simultaneous reset and two fairings from the inputs of the BVZ when the composite MAVR is launched into flight, respectively, from the TPK or the launch of the carrier aircraft, moreover, the mentioned CFSN in the mentioned UBP is equipped with a combined control system based on inertial and satellite modules that include a hybrid inertial navigation system/global positioning positioning system with the possible addition of infrared homing or laser guidance to improve accuracy, while modules with optoelectronic homing head or laser sensors for precise targeting, which are mounted are installed in the forward part of the KFSN hull or on the leading edges of the forward wing consoles that can be unfolded in the DHOK or HOPO, and the expansion of the bilaterally asymmetric layout of the MAVR airframe in its mentioned DHOC, HOPO and HOZK includes an asymmetric displacement of their consoles in the longitudinal direction, which provides when overcoming the supersonic barrier sinusoidal distribution of the formation of air seals on the leading edges of their consoles, spaced so that each upper right console in DHOK, HOPO and HOZK is moved forward in flight from each of their left upper console with a gap equal, for example, δ _zaz , each of the latter in turn moved back in flight from each of their left lower console with a gap equal to 1/2 δ _zaz , each of which, in turn, is moved forward in flight from each of their right lower console with a gap equal to δ _zaz , while the MAVR glider is made using an inconspicuous technology with coating that absorbs radio waves of different lengths, has a one-piece design of its hard to hulls using aluminum-lithium alloys and up to 75% improved structural aging composite materials, reinforced with spars and stiffeners with a single fuselage skin and BVZ made of composite materials reinforced with carbon fiber, capable of protecting its said BSU from powerful electromagnetic flashes or exposure to laser radiation , withstand significant amounts of heat and deformation, which make it possible to reduce the number of parts by an order of magnitude, and the MAVR, when it takes off from the deck of the said DBK or is launched from the said TPK, respectively, with normal or maximum takeoff weight with its said turbofan engine, which creates with the DNV their lifting thrust-to-weight ratio in a vertical position fuselage component K _PT = 1.4 or K _pt = 1.2, which after the completion of the transitional maneuver automatically changes with the horizontal position of the fuselage to sustainer thrust-to-weight ratio: the first level - 0.15, or the second - 0.3, or the third - 0 ,34 using respectively mentioned th turbofan with 43.3%, or 86.6%, or 100% of the takeoff power of its adaptive control system with the provision at a flight altitude of at least 12 km of the maximum flight speed Mach (M) = 0.9, or M = 1.04, or M=1.1, respectively, so its HOZK with sweep χ=+60° will allow, in comparison with the wing of a jet aircraft and its sweep angle χ=+45 ⁰ , to reduce the wave resistance and the required thrust-to-weight ratio, while ensuring and maintaining at the height of the trans- or supersonic flight mode of the MAVR, respectively, in the direction of the target chosen for the attack, or only after 49% of the mission completion time and fuel depletion, and when using the sweep of its HOZK, for example, with an angle χ=+30° or χ=60 °, which will ensure an increase in the aerodynamic and structural advantages of a two-sided asymmetry airframe, which improves the ratio of aerodynamic quality to its resistance, which, at an appropriate flight speed of the MAVR up to Mach 0.98 or Mach 1.1, will be 20 to 1 or 11 to 1, with e volume in an inconspicuous MAVR having an effective dispersion area of 0.01 m ² , in its said KDU, the mentioned turbofan engine is equipped with a rotary jet nozzle (PRS) with its all-aspect thrust vector control system (VUVT), and the turbofan engine with VUVT in different directions of its movement The PRS is made with the possibility of deviation at angles of ±15°, while in vertical flight modes and with the corresponding position of the fuselage, for example, a super-maneuverable BPSV and to perform the aforementioned landing on the tail, implemented using the aforementioned DNV and a gas-dynamic method that provides the creation of control forces and moments during the operation of a turbofan engine with a VUVT of its RRS, equipped with the possibility of its deflection forward-backward or left-right at angles of ±15 ° from the vertical, creating a change in the balancing in pitch or roll, respectively, and in the case of a change in torque with the opposite rotation of the lower and upper mentioned coaxial DNV provides a change in balancing on the course, and sv top of the fuselage of the BPSV in its longitudinal compartment, equipped with automatic flaps and an automatically ejected parachute system used for its emergency landing on a ground airfield with simultaneous folding of the mentioned consoles of its HOPO and HOZK.

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