RU2768999C1 - Coastal air-rocket reusable autonomous complex - Google Patents

Abstract

FIELD: coastal aviation missile systems.SUBSTANCE: invention relates to coastal aviation missile systems with unmanned convertible aircraft (UCAC). The UCAC contains a turbofan engine (TFE), a Y-tail (YT) and a bidirectional wing (BDW) mounted on top of the fuselage with bilateral symmetry/asymmetry in two positions, having in any of a number of positions different-sized in span greater (GW) and smaller (SW) wings. The BDW is integrated with the upper hinge of the wing, the servo drive of which provides, after launch, the unfolding of the SW and the subsequent clockwise rotation of the high-lying BDW.EFFECT: reduction of dimensions in the transport and traveling configuration, increase in speed, flight range and target load.2 cl, 3 dwg, 1 tbl

Description

The invention relates to coastal aviation missile systems with an unmanned convertible aircraft (BPKS) having a Y-tail (YOO) and a bidirectional wing (DNA) mounted on top of the fuselage with bilateral symmetry/asymmetry in two positions at an angle of 75° with opposite/straight sweep along the leading edge of the DNA χ=±15°/+45°\folded DNA consoles and tail YOO keels, respectively, to perform a mission when approaching/attacking a target\for mortar launch from a vertical or with an accelerator BPKS of an inclined transport and launch container ground-based means after the release of the fairing from the folded keels of the YOO and the launch of the turbojet bypass engine, which, with side air intakes, provides the flight of a trans / supersonic returnable BPKS.

A known complex for destroying 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 BR contains aerodynamic surfaces with drives and an accelerating engine to ensure the delivery of the CR 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 a radio 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 splashdown area of the underwater warhead so as not to interfere with its homing system. The disposable BR itself 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 (KAIS), has two turbojet bypass engines (TRDD) in the engine nacelle with internal bomb bays and tricycle retractable wheeled landing gear. For supersonic flight "X-plane" his General Electric J85-21 turbofans have a jet thrust of 4485 kgf, which at a flight altitude of 15 km provides a speed of 1275/1487 km/h 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 twice the 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 a composite wing of two asymmetric wings.

Closest to the proposed invention is [see. http://rbase.new-factoria.ru/missile/wobb/ikara/ikara.shtml] British carrier-based aviation missile system (PARK) of the "Icara" model with an unmanned aerial vehicle (UAV) having a wing, a fuselage with a launcher (PU) of a guided missile (UR), 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 a homing anti-submarine torpedo (PLT) 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 hydroacoustic system (GAS) 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 PLT 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 a ground-based vehicle with a vertical landing of the BPKS using a parachute system, reducing the dimensions in a transport and marching configuration, increasing speed, flight range and target load, but also striking capabilities in a volume -unmanned unified system.

Distinctive features of the proposed invention from the above-mentioned well-known PAK "Icara", closest to it, are the presence of the fact that the complex aviation-missile reusable autonomous (KARMA) with a group of vertical launch vehicles, including more than one unmanned convertible aircraft (BPKS), made for ground-based with the possibility of both a mortar launch from a vertical transport and launch container (TPK) or an inclined TPK with an BPKS accelerator, and after it completes the mission and automatic return, and a horizontal or vertical landing of the BPKS using its retractable tricycle wheeled chassis or parachute -reactive system (PRS), respectively, at the airfield of its base or the place of launch or a covert position of a ground-based mobile base, while in the flight configuration of a trans- / supersonic BPS, including a bidirectional wing (DNA) turning in a horizontal plane, having in any of the series and positions at an angle of 75 ° are different-sized in span larger / smaller trapezoidal wings (BTK / MTK), mounted on the fuselage with bilateral symmetry / asymmetry in two or four positions at an angle of 75 ° or 30 ° \ 45 ° \ 75 ° with the opposite / straight DNA sweep along its leading edge χ=±15°/+45° or χ=±60°\±45°\±15°/+45°, integrated with the fuselage and its upper hinge, the servo drive mechanism of which from its original position to in terms of, for example, BTK, placed with its elongation λ = 3.9-4.0 along the axis of symmetry, after starting with the TPC and unfolding the MTK, and subsequent clockwise in terms of the rotation of the highly located DNA in the horizontal plane at an angle of 75 ° so, that the MTK is fixed along the axis of symmetry with its elongation λ=1.2-1.3 for subsonic flight modes or back counterclockwise to its original position, contains an inverted Y-tail (YOO) and a bypass turbojet engine (TEF) with side air intakes (BVZ) semitons spruce type, made unregulated to ensure both their subsonic and supersonic operation, and the corresponding flight mode of the BPKS launched from the TPK of the ground-based anti-ship complex (PKK), providing outside the TPK the launch of the turbofan engine and synchronous unfolding and fixing and consoles of its DNA after they turn from axes of symmetry at an angle of 75 ° clockwise when viewed from above and all-rotating keels (CPC) of the tail YOO, the upper and lower of which, to increase directional stability at supersonic flight speeds, are mounted respectively along the plane of symmetry and outward at an angle of 60 ° to the latter, carrying in its bomb bay to carry out the mission and attack the target, the mentioned missile defense system, for example, an anti-ship missile (ASM) of the Kh-38MK type, flying with its covert extension to the surface target area and performing a return flight and corresponding reception of the BPKS at the launch site, for example, from self-propelled launcher (SPU) type K-340P, containing two or three TPK for ground-mobile basing and launching strike-strategic BPCs, while the BPC fuselage has a truncated cone-shaped aft part, smoothly turning into its central part with a trapezoidal transverse shape (TPF), which, when viewed from the front, has a pyramidal nose with triangular BVZ or BVZ in the form of a sector of a circle , having air ducts feeding the turbofan engine, forming its square section with rounded edges or a square with rounded sides and an oval section, containing on a smaller TPF base a lower bomb bay with its automatic longitudinal flaps to accommodate the corresponding load in it, but also on top of the fuselage above the large TPF base the corresponding front and rear refinements for simultaneous unfolding of them / laying DNA consoles in them so that the tip of the right / left console of the BTK / MTK in the DNA, when placed along the axis of symmetry, is located under the dorsal C-shaped fairing (COO) when viewed from the side, with this for the reuse of the BPC center section of its DNA or long to the center of mass, trapezoidal in plan, developed SOO contains an internal compartment from above with an automatically reset fairing or opening flaps and simultaneous ejection of the PRS, used after opening the parachute and folding the CPC of the tail YOO and MTK consoles, the latter of which are laid down and fixed parallel to the plane of symmetry in refinements of the outer sides of the fuselage with the appropriate placement of the mentioned consoles of the BTK, but also to ensure vertical landing, for example, at the launch site of the BPKS with the help of its landing parachute and braking solid propellant engine, triggered by its fuselage ground proximity sensors of the brake jet system, with two TPF bases in its fuselage are correlated so that the width of the smaller one is 45 ... 55% of the width of the larger upper base, while the head BPKS, which is fully digitized and includes the use of a laser communication channel, which will the BSU mentioned by him at safe distances for him implements communication over a closed channel with geolocation of a surface target and control over a laser communication channel with weapons loads of his own and other BPCs with targeting of their supersonic anti-ship missiles of the Kh-38MK type as part of a strike air group used in conjunction with others air groups capable of exchanging information between their lead BPCs within their combined-combat single information cloud and transmitting target designation to a number of heavily armed BPCs that do not use their radars in their anti-ship KARMA.

раза и требуемую тяговооруженность в

раза, причем для обеспечения и поддержания на высоте транс- или сверхзвукового бесфорсажного режима полета БПКС соответственно в направлении выбранной для атаки цели или как после 49% времени выполнения мисси и выработки топлива, так и при разнонаправленной стреловидности упомянутого его БТК в ДНК с соответствующим углом χ=±45° или χ±60°, обеспечивающим увеличение показателей аэродинамических и структурных преимуществ планера двусторонней асимметрии, улучшающей отношение подъемной силы к его сопротивлению, которое при соответствующей скорости полета БПКС до 0,98 Маха или 1,2-1,3 Маха составит 20 к 1 или 11 к 1, при этом в малозаметном БПКС его упомянутый адаптивный ТРДД снабжен реактивным плоским прямоугольным соплом (ППС), имеющим термопоглощающее покрытие, уменьшая инфракрасное (ИК) излучение, но и заднюю V-образную в плане кромку, размещенную параллельно задней кромке нижнего кормового обтекателя его фюзеляжа, вынесенного от ППС назад по его полету, причем на горизонтальных режимах полета сверхманевренного БПКС путевое управление обеспечивается отклонением верхнего ЦПК хвостового YOO, а продольное и поперечное управление при этом осуществляется синфазным и дифференциальным соответствующим отклонением левого и правого нижних ЦПК хвостового YOO.In addition, in the transport and stowed position of the remote-slave BPKS, the folded said CPCs of its tail YOO are closed from the end of the aft propulsion system (KDU) by a split fairing that repeats the outer profile of the aft fuselage, which has the ability to automatically remove or reset it when the BPKS is launched into flight from TPK, and the mentioned MTK with its left and right consoles, taken out from the center of mass in the longitudinal direction, respectively, forward and backward along its flight and in the corresponding direction from the outer sides of the fuselage, have the corresponding sweep along their leading and trailing edges χ = +45 ° and χ=-45°, which provide parallel placement in terms of opposite sides of the carrier hexagonal configuration, while in the supersonic flight configuration of the BPKS, the mentioned MTK has a relative thickness of its profile ć=5% and endings with outer sides placed parallel to its axis of symmetry, performing in its trapezoidal consoles the role of smaller bases th (MO), having their length determined from the ratio: L _mo =b _kf : sin75 °, m (where: b _kf - the width of the central part of the fuselage with BVZ; sin75° - the sine of the DNA rotation angle), which, after DNA rotation by the mentioned angle of 75°, provides placement of both MTK consoles along the axis of symmetry of the BPKS and MO of its endings at an angle of 15° to the axis of symmetry without taking them outside the outer sides of its fuselage, but and left and right consoles of the BTK with the mentioned opposite sweep along its leading edge χ=+15° and χ=-15°, respectively, and the said consoles of the BTK having variable sweep along their front and rear edges and a span of 2.0 times more than the span mentioned MTK, contain their rounded tips, the configuration of which in plan is similar to the shape of the decomposed unilateral and upper CPC of the tail YOO with their forward sweep χ = +33 ° ... the direction of the inputs of their mentioned BVZ, but also the offset in the same direction in its mentioned tail YOO of its left and right CPCs, which are spaced apart from similar m displacement of the MTK consoles in DNA, and the airframe of the returned BPKS is made according to an inconspicuous technology with a coating that absorbs radio waves of different lengths, has a monolithic structure of its rigid body using aluminum-lithium alloys and up to 70% of composite materials improved in structural aging, reinforced with spars and ribs rigidity with a common composite skin of the fuselage and BVZ, reinforced with carbon fiber, capable of protecting its said BSU from powerful electromagnetic flashes or exposure to laser radiation, withstanding significant amounts of heat and deformation, making it possible to reduce the number of parts by an order of magnitude, while the reusable BPS during its takeoff from the ground airfield and launch from the mentioned TPK, respectively, with normal and maximum takeoff weight and its mentioned turbofan engine, which creates a normal cruising thrust-to-weight ratio (K _MT ), which is programmed for cruising thrust-to-weight ratio during horizontal flight: the first level is 0.2 or the second th - 0.28 or third - 0.53, using respectively 37.7% or 52.8% or 100% of the power of the turbofan engine of its adaptive control system and ensuring at a flight altitude of at least 12 km the maximum flight speed Mach (M) = 0, 94 or M = 0.98 or M = 1.2-1.3, and its mentioned MTK with bilateral asymmetry and sweep of its leading and trailing edges χ = ± 45 ° will allow, in comparison with the wing of a jet aircraft and its sweep angle χ \u003d + 45 °, reduce the wave resistance in

times and the required thrust-to-weight ratio in

times, moreover, to ensure and maintain at the height of the trans- or supersonic non-afterburner flight mode of the BPKS, respectively, in the direction of the target chosen for the attack, or both after 49% of the mission completion time and fuel depletion, and with the multidirectional sweep of its mentioned BPC in DNA with the corresponding angle χ \u003d ± 45 ° or χ ± 60 °, providing an increase in the aerodynamic and structural advantages of a two-sided asymmetry airframe, which improves the lift-to-drag ratio, which, at an appropriate flight speed of the BPKS up to Mach 0.98 or Mach 1.2-1.3, will be 20 to 1 or 11 to 1, while in the inconspicuous BPKS, its said adaptive turbofan engine is equipped with a jet flat rectangular nozzle (PPS) having a thermally absorbing coating, reducing infrared (IR) radiation, but also a rear V-shaped edge in plan, placed parallel to the rear the edge of the lower aft fairing of its fuselage, taken out from the PPS back along its flight, and in horizontal modes of the flight of a super-maneuverable BPKS, directional control is provided by the deviation of the upper CPC of the tail YOO, while longitudinal and transverse control is carried out by the in-phase and differential corresponding deviation of the left and right lower CPC of the tail YOO.

The proposed invention KARMA with a supersonic BPKS containing folded MTC and CPC is mounted in a TPC with the MTC placed parallel to the plane of symmetry, has a turbofan engine with PPS in the CDU, is illustrated in Fig. 1-3 general views:

- in Fig. 1 - shows the BPKS in side view contains folded MTK and CPC, mounted in a TPK for a mortar launch and launch from a K-340P SPU;

- in Fig. 2/3 - shows the BPKS in a top view with the unfolded CPCs of the tail YOO with their sweep χ=+33° and MTK/BTK in its DNA with a straight/multidirectional corresponding sweep χ=+45°/χ=±15°, but also to perform supersonic / subsonic modes of its horizontal cruising flight.

The coastal KARMA shown in FIG. 1-3, contains more than one TPK 1 jet BPKS 2, made according to the aerodynamic scheme of high-wing and rotary DNA, integrated with the fuselage 3 and the upper hinge 4 of its servo drive mechanism, has a BTK 5 / MTK 6 with bilateral symmetry / asymmetry in two positions at an angle of 75° with opposite/forward sweep along their leading edge χ=±15°/+45°\folded MTK consoles and YOO keels, respectively, to perform a mission when approaching/attacking a target\for a mortar launch from a vertical TPK 1. Configuration in in terms of endings 7 BTK 5 is similar to the shape of the lower 8 and having a fork 9 of the upper TsPK 10 of the tail unit YOO. Adaptive turbofan with jet PPS 11, used with two rounded BVZ 12 in front view, mounted from the outer sides of the fuselage 3 BPKS 2.

The fuselage 3 BPKS 2 with a pyramidal nose 13 in front view, smoothly turning into its central part with TPF 14, containing on its smaller base the lower bomb bay 15 with its flaps 16 to accommodate the corresponding load. Above the large base of the TPF 14 there are its refinements for the simultaneous unfolding of them / laying in them the BTK 5 / MTK 6 so that the tip 7 of the right console of the BTK 5 in the DNA, when placed along the axis of symmetry, is located in the dorsal side view of the C-shaped fairing 17 On top of the center section of the DNA 5-6 above the center of mass of the BPKS 2 there is an upper compartment 18 with an automatically ejected PRS used by a parachute with a solid propellant jet engine (not shown in Fig. 1-3) when landing at the launch site after folding the MTC 6 and CPC 8, 10 tail YOO. Reusable BPKS 2, performing autonomous flight after its launch from TPK 1 and resetting the rear fairing 19 (shown in dotted line, see Fig. 1) from the TsPK 8, 10 and its turbofan engine, creating its PPS 11 jet thrust for trans-/supersonic flight, with in which directional control is provided by the deviation of the upper CPC 10 of the tail YOO. Longitudinal and transverse control is carried out by in-phase and differential corresponding deviation of the left and right lower 8 CPCs of the tail YOO (see Fig. 2/3). The traffic control of BPKS 2 at all stages of flight is carried out by the navigation flight complex, which is part of the BSU, which provides reception and processing of information from navigation satellites and generates appropriate control signals. All this will allow in the distant BPKS 2 to simplify the controllability and increase the reliability, but also the safety of its remote control.

Thus, the development of coastal KARMA with supersonic BPKS-0.52, based as part of a mobile PKK on a wheeled self-propelled launcher (SPU) of the K-340P type, made on the MZKT-7930 chassis with three mounted K-341P TPKs used to launch anti-ship missiles "Onyx" in the coastal PKK "Bastion" and modified for the appropriate type and number of BPKS, which may include, for example, both three reconnaissance BPKS-0.52, carrying three R-77M air-to-air missiles, and 12-15 units of shock BPKS-0.52, armed with one anti-ship missile of the X-38MK type (see Table 1). The head returnable BPKS, 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 the BSU BPKS with a dual-frequency airborne radar with AFAR, which, at safe distances for it, communicates over a closed channel with reconnaissance BPCs, providing geolocation of a surface target and control over a laser communication channel of weapons loads and their own and other BPCs with targeting of their UR and anti-ship missiles of the X-38MK type as part of a strike air group used in conjunction with a number of other air groups capable of exchanging information between their head BPCs within their volume-unmanned unified system and transmit target designation to a number of strike BPCs that do not use their radars in other KARMA. In addition, the use in ground-mobile PKKs of the ability to launch reusable BPKS-0.52 mortars from their TPKs will increase the mass of aviation fuel by 1.94 times, increase the striking capability and combat stability, for example, of a reconnaissance and strike division with six PKKs. At the same time, increasing the mass of aviation fuel in BPKS-0.52 to 330 kg and, having a range of up to 2340 km, will increase the flight range of the X-38MK supersonic anti-ship missiles to 2380 km, which is almost 9.1 times greater than the range of destruction of the coastal PKK "Ball" with subsonic anti-ship missiles of the Kh-35EU type.

Since the promising KARMA with advanced tactical and technical indicators of the coastal PKK delivering heavily armed BPKS-1.5 with AL-55I turbofan engines carrying BrahMos-M anti-ship missiles to the Arctic region, its development, taking into account the experience of creating a TPK for the ZM- 55 complex "Mosquito" is a preferred and technically feasible task. Only the development of coastal KARMA will significantly simplify the deployment of anti-ship aircraft and increase combat stability, including at a great distance from the target and base. In fact, the combat capabilities of KARMA itself are not limited to the flight of the BPKS and are more dependent on the wheeled SPU on the MZKT-79305 chassis. Therefore, supersonic BPCs, as elements of advanced military equipment, in terms 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 long-range BPKS-1.5 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 flight range by 2025 km as a Kh-555 strategic missile with the creation of a safe air zone between air defense of the target and the strike-strategic PKK, and the BrahMos-M anti-ship missiles, but also its striking capability in the Northern sea regions of the carrier ships of the Aegis missile defense system, which is the core aspect of the coastal KARMA of the Arctic design, namely: to detect and destroy naval anti-missile carriers.

Claims (2)

1. Coastal complex aviation-missile reusable autonomous (KARMA) with an unmanned aerial vehicle having a wing, a fuselage with a launcher of a guided missile (UR), a power plant engine (SU) and an onboard control system for control from the command post of a home base, characterized in that that it is with a group of vertical launch vehicles, including more than one unmanned convertible aircraft (BPKS), made for ground-based with the possibility of both a mortar launch from a vertical transport and launch container (TPK) or an inclined TPK with a BPC accelerator, and after mission and automatic return, and horizontal or vertical landing of the BPKS using its retractable tricycle wheeled chassis or parachute-rocket system (PRS), respectively, at the airfield of its home base or the launch site or covert position of a ground-based mobile home base, while in the flight configuration trans / above sound BPKS, including a bidirectional wing (DNA) that can be rotated in a horizontal plane, having in any of a number of positions at an angle of 75 ° larger / smaller trapezoidal wings of different sizes (BTK / MTK), fixed on the fuselage with bilateral symmetry / asymmetry in two or four positions at an angle of 75° or 30°/45°/75° with opposite/direct sweep of the DNA along its leading edge χ=±15°/+45° or χ=±60°/±45°/±15°/+45 °, integrated with the fuselage and its upper hinge, the servo drive mechanism of which, from the initial position in the plan, for example, the BTK, placed with its elongation λ=3.9-4.0 along the axis of symmetry, provides after launch with the TPK and unfolding the MTK and subsequent clockwise rotation of the highly located DNA in the horizontal plane at an angle of 75° so that the MTC is fixed along the axis of symmetry with its elongation λ=1.2-1.3 for subsonic flight modes or counterclockwise back to its original position, contains an inverted tail Y-o tail (YOO) and turbojet bypass engine (TRDD) with side air intakes (BVZ) of a half-tunnel type, made unregulated to ensure both subsonic and supersonic operation, and the corresponding flight mode of the BPKS launched from the TPK of the ground-based anti-ship complex (PKK), with providing outside the TPK the launch of the turbofan engine and the synchronous unfolding and fixation and consoles of its DNA after they are rotated from the axis of symmetry at an angle of 75 ° clockwise when viewed from above and all-turn keels (CPC) of the tail YOO, the upper and lower of which are to increase directional stability at supersonic flight speeds, they are mounted, respectively, along the plane of symmetry and outward at an angle of 60 ° to the latter, carrying in its bomb bay to carry out the mission and attack the target, the mentioned SD, for example, an anti-ship missile (ASM) of the X-38MK type, flying with its covert advance into the zone surface target, and perform a return flight and the corresponding reception of the BPKS at the site of one hundred mouth, for example, from a self-propelled launcher (SPU) of the K-340P type, containing two or three TPKs for ground-mobile basing and launching strike-strategic BPCs, while the BPC fuselage has an aft part in the form of a truncated cone, smoothly turning into its central a part with a trapezoidal transverse shape (TPF), which, when viewed from the front, has a pyramidal bow with triangular BVZ or BVZ in the form of a sector of a circle, having air ducts that feed the turbofan engine, forming its square section with rounded edges or a square with rounded sides and an oval section, containing on the smaller base of the TPF, the lower bomb bay with its automatic longitudinal doors to accommodate the appropriate load in it, but also on top of the fuselage above the large base of the TPF, the corresponding front and rear refinements for the simultaneous unfolding of them / laying DNA consoles in them so that the tip of the right / left console of the BTK /MTCs in DNA, when placed along the axis of symmetry, are located under the supra huselage when viewed from the side of the C-shaped fairing (COO), while for the reuse of the BPKS, the center section of its DNA or elongated to the center of mass trapezoidal in terms of the developed COO contains an internal compartment on top with an automatically reset fairing or opening flaps and simultaneous ejection of the PRS used after disclosure parachute and folding CPC of the tail YOO and MTK consoles, the latter of which are laid down and fixed parallel to the plane of symmetry in the refinements of the outer sides of the fuselage with the appropriate placement of the mentioned BTK consoles, but also to ensure vertical landing, for example, at the launch site of the BPC using its landing parachute and brake solid-propellant engine, triggered by its fuselage ground proximity sensors of the brake jet system, and the two bases of the TPF in its fuselage are related so that the width of the smaller one is 45 ... van and includes the use of a laser communication channel, which will make it possible to equip it with a dual-frequency airborne radar with AFAR, and the mentioned BSU at safe distances for it implements communication over a closed channel with geolocation of a surface target and control over a laser communication channel with weapons loads of its own and other BPCs with targeting their supersonic anti-ship missiles of the X-38MK type as part of a strike air group used jointly with other air groups capable of exchanging information between their head BPCs within their combined-combat single information cloud and transmitting target designation to a number of heavily armed BPCs that do not use their radars in their anti-ship KARMA. 2. Coastal KARMA according to claim 1, characterized in that in the transport and stowed position of the remote-slave BPKS, the folded mentioned CPCs of its tail YOO are closed from the end of the aft propulsion system (KDU) by a divided fairing that repeats the outer profile of the aft fuselage, having the ability to automatically its removal or reset when launching the BPKS in flight from the TPK, and the mentioned MTK with its left and right consoles, taken out from the center of mass in the longitudinal direction, respectively, forward and backward along its flight and in the corresponding direction from the outer sides of the fuselage, have the corresponding sweep along the front and their trailing edges χ=+45° and χ= ^_ 45°, which provide parallel placement in terms of opposite sides of the bearing hexagonal configuration, while in the supersonic flight configuration of the BPKS, the mentioned MTK has a relative thickness of its profile ć=5% and endings with external sides placed parallel to the axis of its symmetry, performing in its ladder in cius-shaped consoles, the role of smaller bases (MO), having their length, determined from the ratio: L _mo \ _u003d b cf: sin75 °, m (where: b _cf - the width of the central part of the fuselage with BVZ; sin75° - the sine of the DNA rotation angle), which, after DNA rotation by the mentioned angle of 75°, provides placement of both MTK consoles along the axis of symmetry of the BPKS and MO of its endings at an angle of 15° to the axis of symmetry without taking them outside the outer sides of its fuselage, but and left and right consoles of the BTK with the mentioned opposite sweep along its leading edge χ=+15° and χ=-15°, respectively, and the said consoles of the BTK having variable sweep along their front and rear edges and a span of 2.0 times more than the span mentioned MTK, contain their rounded tips, the configuration of which in plan is similar to the shape of the decomposed one-sided and upper CPC of the tail YOO with their forward sweep χ = + 33 ° ... the direction of the inputs of their mentioned BVZ, but also the offset in the same direction in its mentioned tail YOO of its left and right CPCs, which are spaced apart from similar m displacement of the MTK consoles in DNA, and the airframe of the returned BPKS is made according to an inconspicuous technology with a coating that absorbs radio waves of different lengths, has a monolithic structure of its rigid body using aluminum-lithium alloys and up to 70% of composite materials improved in structural aging, reinforced with spars and ribs rigidity with a common composite skin of the fuselage and BVZ, reinforced with carbon fiber, capable of protecting its said BSU from powerful electromagnetic flashes or exposure to laser radiation, withstanding significant amounts of heat and deformation, making it possible to reduce the number of parts by an order of magnitude, while the reusable BPS during its takeoff from the ground airfield and launch from the mentioned TPK, respectively, with normal and maximum takeoff weight and its mentioned turbofan engine, which creates a normal cruising thrust-to-weight ratio (K _MT ), which is programmed for cruising thrust-to-weight ratio during horizontal flight: the first level is 0.2 or the second th - 0.28 or third - 0.53, using respectively 37.7% or 52.8% or 100% of the power of the turbofan engine of its adaptive control system and ensuring at a flight altitude of at least 12 km the maximum flight speed Mach (M) = 0, 94 or M = 0.98 or M = 1.2-1.3, and its mentioned MTK with bilateral asymmetry and sweep of its leading and trailing edges χ = ± 45 ° will allow, in comparison with the wing of a jet aircraft and its sweep angle χ \u003d + 45 °, reduce the wave resistance in

times and the required thrust-to-weight ratio in

times, moreover, to ensure and maintain at the height of the trans- or supersonic non-afterburner flight mode of the BPKS, respectively, in the direction of the target chosen for the attack, or both after 49% of the mission completion time and fuel depletion, and with the multidirectional sweep of its mentioned BPC in DNA with the corresponding angle χ \u003d ± 45 ° or χ ± 60 °, providing an increase in the aerodynamic and structural advantages of a two-sided asymmetry airframe, which improves the lift-to-drag ratio, which, at an appropriate flight speed of the BPKS up to Mach 0.98 or Mach 1.2-1.3, will be 20 to 1 or 11 to 1, while in the inconspicuous BPKS, its said adaptive turbofan engine is equipped with a jet flat rectangular nozzle (PPS) having a thermally absorbing coating, reducing infrared (IR) radiation, but also a rear V-shaped edge in plan, placed parallel to the rear the edge of the lower aft fairing of its fuselage, taken out from the PPS back along its flight, and in horizontal modes of the flight of a super-maneuverable BPKS, directional control is provided by the deviation of the upper CPC of the tail YOO, while longitudinal and transverse control is carried out by the in-phase and differential corresponding deviation of the left and right lower CPC of the tail YOO.

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