RU2778159C1 - Attack weapon aviation complex - Google Patents

Abstract

FIELD: aviation technology.

SUBSTANCE: invention relates to the field of aviation, in particular to the designs of aviation complexes. The attack weapon aviation complex includes a heavy aircraft carrier (HAC) and more than one unmanned aircraft of bilateral asymmetry (UABA), the fuselage of which is fixed on the underwing pylon of the HAC and has a folding wing of asymmetric sweep (FWAS), a Y-shaped tail and a turbojet engine with side air intakes, providing high-altitude flight in the configuration of a super-/transonic remotely operated UABA with its unfolded FWAS and opposite sweep χ=±60°/χ=±45°/ folded along the axis of symmetry to complete the mission when attacking the target/receiving it under the HAC pylon. The HAC is equipped with a flexible fastening system that releases a towed device with a cone on a cable, which, when docked with a retractable nose rod of the UABA, brings it in flight under the docking/undocking nodes of the HAC pylon for fixing and transporting to the UABA to the home airfield.

EFFECT: increase in the flight range of an unmanned aircraft, the probability of hitting a surface or ground target located at a long range is provided.

3 cl, 3 dwg, 1 tbl

Description

The invention relates to attack carrier aircraft, including a heavy aircraft carrier (TSAN) and more than one bilateral asymmetry unmanned aircraft (BSDA), the fuselage of which is fixed on the TSAN underwing pylon and has an asymmetric sweep wing (RKAS), a Y-shaped tail and turbojet engine with side air intakes, providing high-altitude flight in the configuration of a super-/transonic remotely driven BSDA with its RCAS unfolded and opposite sweep χ=±60°/χ=±45°/ folded along the axis of symmetry to perform a mission when attacking a target/reception it under the TSAN pylon, which is equipped with a flexible attachment system that releases a towed device with a cone on a cable, which, docking with the BSDA retractable nose bar, leads in flight under the TSAN pylon docking / undocking nodes for fixing on it and transporting the BSDA to the home airfield.

The Gremlins X-61A project of Dynetics (USA) is known, consisting of a four-rotor C-130 carrier aircraft and an air group that includes more than one unmanned attack aircraft (UAS), which has the ability to take to the air with the help of a carrier aircraft, to perform after its separation, independent flight, and then return to its board using flexible mounts.

Signs that match - the C-130 turboprop aircraft, which acts as a flying aircraft carrier, carries four X-61A BPUs in the compartment, is equipped with a retractable boom with a system holding it, capable of releasing a cable with a towing device, which, after docking, can pull up and put them all into cargo bay in 30 minutes. Each BPUS with a swing wing span of 3.47 m, contains a fuselage 4.2 m long, 0.52 m high and 0.57 m wide, has a takeoff weight of 680 kg, a payload of 66 kg and a Williams F107 bypass turbojet engine (TRDD) with a thrust of 318 kgf, providing a speed of Mach 0.6 and a flight range of 560 km.

The reasons that impede the task: the first is that this Gremlins system is dangerous due to powerful turbulences descending from an arrow retractable from the cargo compartment of the carrier aircraft, which has a bulky U-shaped holding system with grippers for the BPU, capable of releasing a cable with a towing device that docks with a retractable hook above the center of mass of the BCS, which reduces the safety of docking. The second one is that after docking in flight with the carrier aircraft, the RTU on the towing device cable can sway with a large amplitude, and the absence of an emergency undocking system can lead to the rupture of the towed device with the RTU retractable hook and not all the RTAs will be brought into the compartment. The third is that this concept is very dangerous when towing them, as turbulence and wakes are a serious problem, exacerbated by the propellers of the carrier aircraft, especially when the cargo ramp of the compartment is open, and the RTU fuselage rotates on the line of the towed device before docking. with U-shaped system. All this limits the increase in safety, but also stabilization during towing and the introduction of the BPU into the compartment.

A well-known project is a manned aircraft carrier of the Boeing Corporation (USA) (Patent US 2015/0115096 dated 04/30/2015), containing a twin-rotor longitudinal scheme of the CH-47F "Chinook" carrier helicopter with an unmanned strike aircraft (UAS), which has two engines on its wing consoles with screws, attached to the bottom of the carrier helicopter, can be separated from it and perform tasks independently.

Signs that match - the presence of a heavy carrier helicopter of the CH-47F "Chinook" model, which has a recess in the lower part of the fuselage for a special attachment point for the BPUS center section - "flying wing". Thanks to two propellers installed on the wing of the BPUS, a helicopter docked with it will be able to develop a much higher speed. The capabilities of the BPUS itself will also expand, since, due to the combined platform, it will be possible to deliver it to its destination without consuming its fuel. And the possibility of in-flight refueling of BPUs from a carrier helicopter with a small amount of fuel in modern BPUs, which increases their potential.

The reasons that impede the task: the first is that a heavy helicopter of a twin-rotor longitudinal scheme, having a ventral mount of a twin-rotor BPU, which predetermines the need for a significant lengthening of the wheel landing gear of the carrier helicopter, which will increase the mass of its structure and reduce the weight return. In addition, the “flying wing” aerodynamic configuration without vertical keels will make it very difficult to dock without stability of control in the yaw channel, and even more so when the attachment points located on the upper part of the center section of the BPU and the response ones under the helicopter fuselage are combined. The second is that the wingspan of the BPUS is much larger than the track and the base of the wheeled chassis of the carrier helicopter, which will make it difficult for them to be jointly serviced on the ground. The third is that a small cruising speed of 253 km / h and a range of up to 465 km, but the practical ceiling of 3090 m of a heavy helicopter model CH-47F "Chinook" is much less than modern aircraft-type BPUS, which reduces their joint potential . The third is that in order to increase the horizontal translational flight with the joint use of the propulsion thrust of two main rotors (NV) having a mutual overlap of 21.4%, and two screws from the BPU docked with the helicopter, located just under the zone of overlap of the NV, will lead to harmful aerodynamic interference of the NV and smaller BPUS propellers and the strong influence of the vortex field of each NV on the thrust and torque of the traction propellers, which can lead to an imbalance of forces and moments acting on the carrier helicopter and, as a result, to the formation of "different thrust" of the side propellers movers. In addition, the placement of the attachment point for one BCS and only under the fuselage of the carrier helicopter, which makes it very difficult to perform docking / undocking in the air, especially for a heavy helicopter and BCS during their horizontal high-speed flight, but also limits the capabilities of a flying aircraft carrier with only one BCS . Whereas, when placed in the compartment of a carrier helicopter, it can be 2-3 heavy-class BPUs with a take-off weight of up to three tons.

The closest to the proposed invention is the project "Tom-Tom" (USA), consisting of a carrier aircraft and an air group, including two special fighters, having the ability to both dock to the carrier aircraft using flexible mounts between the wingtips of aircraft, and to be towed by an aircraft -carrier to increase the range of fighters.

Signs that coincide - the presence of a four-rotor aircraft carrier model EB-29A, which acts as a flying aircraft carrier carrying two special fighters at the ends of the wing, but also equipped with a system of flexible fasteners between the wingtips of the carrier aircraft and two EF-84B fighters, providing the possibility of horizontal during their flight, dock the latter to the carrier aircraft and undock simultaneously at a height sufficient for this.

The reasons that impede the task: the first is that this system of the Tom-Tom project proved to be dangerous due to powerful turbulences descending from the wingtips of the EB-29 carrier aircraft, which caused the strongest rolls of the EF-84B fighters, which reduced the safety of joint flights, and to perform their docked takeoff and landing, it was necessary to lengthen the height of the landing gear of each EF-84B, leveling the wing planes at the same level in the parking lot. The second is that after docking in flight with the carrier aircraft, one of the EF-84Bs began to sway with a large amplitude, but no emergency undocking systems were provided, and at the same time, the cone rod was torn out of the EB-29A wing, and not all aircraft successfully landed. The third is that this concept is very dangerous when towing them, since turbulence and wakes are a serious problem, exacerbated by the propellers of the carrier aircraft, especially when the consoles of the docked wings are in the same plane of their chords. All this limits the increase in safety, speed and flight range, but also lateral stabilization during towing flight.

The present invention solves the problem in the above-mentioned well-known project "Tom-Tom" of increasing the payload (PN) and weight return, increasing the speed and range of flight, the probability of hitting a surface or ground target located at a long range, but also docking the BSDA with the towing system and placing it under the pylon of a flying aircraft carrier to return to the home airfield.

Distinctive features of the proposed invention from the above-mentioned well-known project "Tom-Tom", the closest to it, are the fact that the aircraft-carrying strike-combat integrating aircraft (ANUBIS) is made in the form of a heavy aircraft carrier (TSAN), has under its wing more than one double-sided asymmetry unmanned aircraft (BSDA), the fuselage of which is fixed on more than one TSAN underwing pylon with the possibility of both dropping the BSDA from it and, after unfolding its supporting aerodynamic surfaces, performing a remotely controlled or automatic pre-programmed independent flight of the BSDA, and then in reverse order, return under the free underwing pylon (PKP) of the TSAN after docking the BSDA in flight by means of a system of flexible fastenings of the TSAN, releasing a towed-holding safety device (BUL) on the cable, which, with its capture, overcoming turbulence from the TSAN flying ahead, docks with the mating part retractable but BSDA owl bar for towing and its automatic introduction under the TSAN control panel, moreover, the air-based BSDA, made according to the aerodynamic configuration of the mid-plane with a deployable wing of asymmetric sweep (RKAS) and its developed rounded tips (ROZ), when viewed from above, has a reverse Y-shaped tail (OYO) with its fully rotatable developed keels (TsPRK), but also a bypass turbojet engine (TRDD) with its side air intakes (BVZ) mounted from the outer sides of the fuselage and above the RKAS consoles configured to ensure their operation at supersonic and subsonic speeds flight, used with its RKAS synchronously decomposed and fixed and the corresponding flight mode of a jet BSDA carrying a 9-A2-7759 Grom type gliding bomb or the mentioned APR-3M type UR-torpedo, respectively, to perform its mission when attacking ground and surface or underwater goals, as well as covert advance into the attack zone, but also the execution of B The return flight SDA for its reception under an empty TSAN control panel, and when the BSDA is air-based at the corresponding TSAN control panel and after the BSDA mission is completed in its independent flight mode, it has the ability to use its retractable tricycle wheeled landing gear or landing parachute system when landing, or dock to the TSAN when their horizontal joint flight using a flexible attachment between them with their automatic docking / undocking systems to perform, respectively, a horizontal or vertical landing of the BSDA on a ground airfield using load-bearing aerodynamic surfaces or its ejected landing parachute, or after docking the BSDA with the BUL TSAN and its places on its free pylon for their respective joint horizontal landing as a flying aircraft carrier on a ground airfield, while the BSDA fuselage having a diamond-shaped or trapezoidal or cylindrical cross-section with a conical nose th and truncated conical aft parts, smoothly turning into its central cylindrical part, including from its sides paired triangular upper BVZ and lower conformal fuel tanks, forming a lenticular cross-section of it, having along its larger and smaller diagonals, respectively, side compartments with their spring-loaded doors, opening / closing with the corresponding simultaneous laying / unfolding of the RKAS consoles and the lower bomb bay with its automatic doors or the lower niche, respectively, for internal or semi-recessed placement on the mentioned launcher of a bomb load or a magnetometer, or sonar buoys, or an electronic warfare system, moreover, the head BSDA, which is fully digitized 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 BSU mentioned above, at safe distances for it, communicates via a closed channel with sonar buoys, both geolocation of an underwater target and control over a laser communication channel with weapons loads and their own and other BSDA with targeting of their mentioned APR-3M type UR torpedoes as part of a strike air group used in conjunction with a number of other air groups capable of exchanging information between their head BSDA within their single so-called information cloud, and transmit target designation to a number of BSDAs that do not use their radars in other anti-submarine ANUBIS.

), равным

, и упомянутые РОЗ, конфигурация которых в плане аналогична форме односторонних нижних и верхнего ЦПРК хвостового оперения OYO, причем упомянутое РКАС, интегрированное по правилу площадей с фюзеляжем БСДА, имеющее левую и правую консоли, вынесенные соответственно как назад и вперед по его полету, так и в сторону от фюзеляжа и его бортовых отсеков, размещенных сзади и спереди от центра масс, но и на раздельных узлах их поворота, изменяющих асимметричную стреловидность по передней кромке, например, при раскладывании в горизонтальной плоскости консолей РКАС соответственно с углами прямой χ=+60°/χ=+45° или χ=+15° и обратной χ=-60°/χ=-45° или χ=-15° при выполнении полета на высоте в конфигурации сверх-/транс- или дозвукового БСДА для реализации миссии при атаке цели/подлете в зону цели или его приема с фиксацией на упомянутом высотного ТСАН, при этом расширение двусторонне-асимметричной компоновки планера разведывательно-ударного БСДА может дополнительно включать асимметричное смещение в продольном направлении входов их упомянутых БВЗ, но и смещение в этом же направлении в его упомянутом оперении OYO левого и правого нижних ЦПРК, разнесенных с аналогичным смещением соответствующих консолей РКАС, причем планер каждого БСДА выполнен по малозаметной технологии с покрытием, поглощающим радиоволны разной длины, имеет монолитную конструкцию жесткого его корпуса с использованием алюминиево-литиевых сплавов и до 70% улучшенных по структурному старению композиционных материалов, усиленных лонжеронами и ребрами жесткости с общей композитной обшивкой фюзеляжа и БВЗ, армированных углеродным волокном, способных защитить его упомянутую БСУ от мощных электромагнитных вспышек или воздействия лазерного излучения, выдерживать значительные количества тепла и деформации, позволяющие снизить на порядок количество деталей, при этом каждый БСДА с его РКАС и разнонаправленной стреловидностью χ=±45° позволит, в сравнении с крылом реактивного самолета и углом его стреловидности χ=+45°, уменьшить волновое сопротивление в 2,8…3 раза и требуемую тягово-оруженность в 1,44 раза, причем для обеспечения на высоте транс- или сверхзвукового режима полета каждого БСДА соответственно в направлении выбранной для атаки цели или только как после 48% времени выполнения мисси и выработки топлива, так и при разнонаправленной стреловидности его РКАС 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 БСДА до 0,98 Маха или 1,06 Маха составит 20 к 1 или 11 к 1, при этом в малозаметном БСДА его адаптивный ТРДД снабжен реактивным плоским прямоугольным соплом (ППС), имеющим как термопоглощающее покрытие, так и заднюю V-образную в плане кромку, размещенную параллельно задней кромке нижнего кормового обтекателя его фюзеляжа.In addition, in the aforementioned tail unit OYO of the super-maneuverable BSDA, its upper and lower said CPRs, mounted respectively along the plane of symmetry and outward from it with the placement of the lower ones to the latter at an angle of 60 °, are made folded down in the refinement of the aft fuselage with their fixation in direction from the upper TsPRK, while in the remote-slave BSDA on the mentioned RCAS there are consoles with their narrowing (

), equal to

, and the mentioned ROZ, the configuration of which in plan is similar to the shape of one-sided lower and upper TsPRK tail OYO, and the mentioned RKAS, integrated according to the area rule with the BSDA fuselage, having left and right consoles, taken out, respectively, both back and forth along its flight, and away from the fuselage and its side compartments, located behind and in front of the center of mass, but also on separate nodes of their rotation, changing the asymmetric sweep along the leading edge, for example, when unfolding the RKAS consoles in a horizontal plane, respectively, with straight line angles χ=+60° /χ=+45° or χ=+15° and inverse χ=-60°/χ=-45° or χ=-15° when flying at altitude in super-/trans- or subsonic BSDA configuration for mission implementation at attacking a target / approaching the target zone or receiving it with fixation on the mentioned high-altitude TSAN, while the expansion of the bilaterally asymmetric layout of the airframe of the reconnaissance-strike BSDA may additionally include an asymmetric displacement in the longitudinal direction of the inputs of their mentioned BVZ, but also the displacement in the same direction in its said plumage OYO of the left and right lower TsPRK, spaced with a similar displacement of the corresponding consoles of the RKAS, and the airframe of each BSDA is made according to low-observable technology with a coating that absorbs radio waves of different lengths, has monolithic construction of its rigid hull using aluminum-lithium alloys and up to 70% improved structural aging composite materials, reinforced with spars and stiffeners with a common composite fuselage skin and BVZ, reinforced with carbon fiber, capable of protecting its said BSU from powerful electromagnetic flashes or impact laser radiation, withstand significant amounts of heat and deformation, allowing to reduce the number of parts by an order of magnitude, while each BSDA with its RKAS and multidirectional sweep χ=±45° will allow, in comparison with the wing of a jet aircraft and its sweep angle χ=+45°, decrease wave resistance by 2.8 ... 3 times and the required thrust-weight ratio by 1.44 times, moreover, to ensure at the height of the trans- or supersonic flight mode of each BSDA, respectively, in the direction of the target chosen for the attack, or only after 48% of the mission time and fuel depletion, and with multidirectional sweep of its RCAS with the corresponding angle χ=±45° or χ±60°, which provides an increase in the aerodynamic and structural advantages of the airframe of bilateral asymmetry, which improves the ratio of lift to its resistance, which, at the corresponding flight speed of the BSDA, is up to Mach 0.98 or Mach 1.06 will be 20 to 1 or 11 to 1, while in the inconspicuous BSDA, its adaptive turbofan engine is equipped with a reactive flat rectangular nozzle (PPS), which has both a heat-absorbing coating and a rear V-shaped edge in terms of placed parallel to the trailing edge of the lower aft fairing of its fuselage.

In addition, each mentioned PKP 11 TSAN 1 (see Fig. 3) is equipped in front with an upper bracket 26, made with the possibility of its deflection from the PKP 11 up/down and along the plane of symmetry of the BSDA 2, equipped in front of the node of its rotation 27 with a cargo winch 28 with a system of internal blocks 29 for automatic control of the cable 30, passed to the BUL 31 through the upper hook-shaped bracket 26 and its cone-shaped fairing (KOO) 32 with a lower cutout for the produced BUL 31, which has, as on its cylindrical bow 33, unfoldable one-piece-swivel X-shaped placed four lattice steering wheel 34, but also inside the cone 35 BUL 31 collet grip 36, and the possibility after the deviation of the upper bracket 26 up its free extension on the cable back along the flight TSAN 2 to a distance multiple of the length of the fuselage of the mentioned BSDA 1, allowing to make it safe approach to TSAN 1 at low subsonic flight speed and perform a preliminary fixed docking by means of the above-mentioned flexible mounting system and its BUL 31 with a counterpart placed at the end of the said retractable nose bar 37 BSDA 1, followed by extension in the horizontal plane of the two upper L-shaped side guides 38, when viewed from behind, mounted on each side and at the end of each PKP 11, which, after closing, form composite skids with a reverse U-shape when viewed from the rear and their slot between their two horizontal shelves 39 interacting with the upper side rollers 40 of the fuselage 3 BSDA 2 T-shaped, retractable from the upper aft compartment 41 when viewed from the rear of the hook 42, mounted behind the rear automatic node 12 and 13 docking / undocking BSDA 2 with PKP 11 TSAN 1, while after preliminary docking BSDA 2 to TSAN 1 by means of a flexible system with BUL 31, which pulls the fuselage 3 BSDA with a cargo winch 28 2 to the main nodes 12 and 13 docking / undocking of their rigid attachment system with automatic compliance by each autopilot BSDA 2 and TSAN 1 both the coaxiality of two pairs of nodes 12 and 13 of the docking of the rigid attachment system, and the translational equal-sized approach with the required pulling of the BSDA 2 along the axis of the control panel 11 TSAN 1 by a cargo winch 28 as with the placement of the T-hook 42 after it is raised along the BSDA 2 flight from the aft compartment 41 of its fuselage 3 in the area of action of the then closed L-shaped guides 38, and to the main nodes 12 and 13 of the rigid system of its fastening, each of which, after the extension of the L-shaped sponge guides 38 and T-hook 42 back respectively to the outer sides of the PKP 11 and into the aft compartment 41 of the fuselage 3 BSDA 2 interacts with the mating part of the node of the rigid attachment system BSDA 2 with the PKP 11 TSAN 1, located below on the mentioned PU PKP 11 of the distant TSAN 1 or unmanned aircraft carrier (BSAN) and on top of the fuselage 3 BSDA 2, docking on a par with the nodes of the flexible docking / undocking system, provide a rigid attachment system with simultaneous interchangeable folding in BSDA 2 consoles RKAS 4 and TsPRK 6 and 8 and the implementation of their jointly docked horizontal flight in the configuration of an aircraft carrier.

The proposed invention of a high-altitude ANUBIS with a remotely driven BSDA, which, with its folded RKAS and TsPRK, is mounted on each underwing pylon of the TSAN with the tail assembly OYO removed from the end of its underwing pylon, has a turbofan engine with its jet PPS, is illustrated in Fig. 1-3 general views:

- in Fig. 1/2 - shows the BSDA with conformal tanks in the side/top view with a lenticular section of the fuselage, and unfolded TsPRK and RKAS at χ±45° and with a conditionally extended nose bar 37 and a T-hook 41;

- in Fig. 3- shows a side view of the underwing pylon TSAN with its upper hook-shaped bracket, having at its end a COC with its BUL and in front of its turn unit a cargo winch with a cable and a BUL for a flexible attachment system and placing the BSDA under the TSAN pylon (BSDA in view B is shown conditionally under the pylon).

The high-altitude ANUBIS shown in Fig. 1-3, contains a long-range TSAN 1 and more than one jet BSDA 2, which is made according to the aerodynamic scheme of a mid-wing with a fuselage 3 and RKAS 4, equipped with its end parts with ROZ 5, the configuration in terms of the latter is similar to the shape of the lower TsPRK 6 of the tail OYO, with forkle 7 of the upper TsPRK 8. Adaptive turbofan engine with jet PPS 9, used with two triangular BVZ 10 in front view, mounted from the outer sides of the fuselage 3 BSDA 2 and above the RKAS consoles 4. Rigid connection of the fuselage 3 BSDA 2 with PKP 11 TSAN 1 is provided by means of automatic docking/decoupling units 12 and 13, mounted respectively from below the control panel 11 TSAN 1 and from above the fuselage 3 BSDA 2.

Fuselage 3 BSDA 2 with aft part 14, made in the form of a truncated cone, equipped with aft fairing 15 with its V-shaped edge and passing into its central cylindrical part 16, equipped with lower left 17 and right 18 triangular conformal fuel tanks from its sides, forming with the upper triangular BVZ 10 a lenticular cross-section, having along both its smaller and larger diagonals the lower bomb bay 19 with its automatic doors 20, and the left 21 and right 22 side compartments with their spring-loaded doors 23, opening / closing when appropriately laid / unfolding of them consoles RKAS 4 BSDA 2. Left 21 and right 22 onboard compartments are placed in plan from the center of mass of BSDA 2, respectively, back and forth along its flight and from the corresponding side of its fuselage 3. In the central part of the fuselage 3 BSDA 2 above its center mass mounted upper compartment 24 with flaps 25 and automatically ejected parachute system (Fig. 1- 3 not shown), used for its vertical landing on a ground airfield with simultaneous folding in it of the consoles of its RKAS 4 and the end parts of the TsPRK 6 and 10 of the OYO tail unit. Jet BSDA 2, which performs a separate autonomous flight from TSAN 1 and creates the corresponding jet thrust PPS 9 of its turbofan engine for its trans-/supersonic cruising flight, in which directional control is provided by the deviation of the upper TsPRK 10 of the OYO plumage. Longitudinal and transverse control is carried out by in-phase and differential corresponding deviation of the left and right lower 6 TsPRK tail unit OYO (see Fig. 1/2). BSDA 2 traffic control at all stages of flight is carried out by the navigation flight complex, which is part of the onboard control system, which provides reception and processing of information from navigation satellites and generates appropriate control signals. The flight of TASN 1 with docked BSDA 2 ends with their joint horizontal landing at the home ground airfield. All this will allow in the long-range ANUBIS to simplify controllability and increase reliability, as well as the safety of piloting both high-altitude TSAN 1 and remote control BSDA 2.

Thus, the long-range ANUBIS with TSAN and its remote-slave BSDA, carrying APR-3M torpedo missiles, is an anti-submarine flying aircraft carrier mastered on the platform of the Il-38 turboprop aircraft. The head BSD A, which is fully digitized and includes, using a laser communication channel, the fourth level of the so-called manned and unmanned teaming (MUM-T), which will allow it to be equipped with a dual-frequency airborne radar with AFAR. The BSU of the head BSDA at safe distances for it communicates via a closed channel with sonar buoys that provide geolocation of an underwater target and control its own and other BSDA weapon loads via a laser communication channel with guidance of their APR-3M torpedo missiles at the target as part of a strike air group used together with a number of other air groups capable of exchanging information between their head BSDAs within their single so-called information cloud and transmitting target designation to a number of anti-submarine BSDAs that do not use their radars in other high-altitude ANUBIS, which also contain search BSDAs with a highly sensitive magnetometer having a magnetically sensitive element, operating at a distance of 30 m from the water surface, and associated with its BSU, providing for the issuance of commands to turn on the magnetometer at the calculated point and to control after the magnetometer is triggered when an underwater target is detected, but also its identification with the adoption of a confirmed decision from the CP TSAN operator for aiming one or two APR-3M volleys at the target with automatic determination of the value of the input adaptive lead angle, which is corrected when approaching the target.

When performing high-altitude ANUBIS anti-ship operations as part of a long-range TSAN or BSAN, respectively, of a Tu-95 turboprop aircraft or a jet BPS of the S-70 Okhotnik type, used as an aircraft carrier with BSDA-0.49, which will allow, having a range of up to 570 km and armed with the 9-A2-7759 Grom gliding bomb, will increase its flight range to 630 km, which will both create a safe air zone between the target’s air defense and distant ANUBIS, and ultimately increase the damaging capability and combat stability of the anti-ship TSAN or BSAN . Moreover, the creation of an Arctic ANUBIS based on a similar BSAN, mastered on the platform of a reactive BPS of the S-70 Okhotnik type, delivering BSDA-0.49 air groups to a given area to perform anti-ship operations, and then, after completing the mission, take them on board and return to the home airfield. All this greatly simplifies the deployment of reconnaissance and strike aircraft of a new integrating generation, which can be included in a single data exchange network between Arctic ANUBIS, including those at a great distance from their base airfield.

In fact, the combat capabilities of such an Arctic ANUBIS are not limited to the flight of its remote-led BSDA and are more dependent on the integrating TSAN or BSAN itself. Therefore, high-altitude ANUBIS as elements of advanced military equipment in terms of tactics can occupy an intermediate place between cruise missiles and attack fighters. The former are capable of independently attacking targets, but at the same time they are very expensive. Attack aircraft may be cheaper, but the fighter has to fly into the target's air defense coverage area. The use of TSAN or BSAN with a jet air group, for example, BSDA-0.49 (see Table 1) will make it possible to carry out a reconnaissance and strike mission with the required efficiency, but without risks for fighter pilots or expensive BSANs, as well as increase the lethality in the Northern Sea regions of the ships-carriers of the Aegis naval missile defense system, which is the core aspect of the anti-ship Arctic ANUBIS, namely: to detect and destroy the sea carriers of anti-missiles.

Claims (3)

1. A strike-combat aviation complex, including an aircraft-carrying strike-combat aircraft carrying unmanned aircraft (UAP) having a wing, a fuselage with a launcher (PU) of a guided missile (UR), a power plant engine and an onboard control system (BSU) for control from the command post (CP) of the carrier aircraft, characterized in that the aircraft-carrying strike-combat aircraft in the form of a heavy aircraft carrier (TSAN) has under its wing more than one bilateral asymmetry unmanned aircraft (BSDA), the fuselage of which is fixed on more than one underwing pylon of the TSAN with the possibility of both dropping the TSAN from it and, after unfolding its supporting aerodynamic surfaces, performing a remotely controlled or automatic pre-programmed solo flight of the TSAN, and then returning in reverse order under the free underwing pylon (PKP) of the TSAN after docking the BSDA in flight by means of a system of flexible fastenings TSAN, releasing a tug on a cable emo-holding catcher (BUL), which, with its capture, overcoming turbulence from the TSAN flying ahead, docks with the reciprocal part of the BSDA retractable nose bar for towing and its automatic insertion under the TSAN control panel, moreover, the air-based BSDA, made according to the aerodynamic scheme, is a mid-plane with a folding asymmetric sweep wing (RKAS) and its developed rounded tips (ROZ) when viewed from above, has a reverse Y-shaped tail (OYO) with its all-moving developed keels (TsPRK), but also a turbojet bypass engine (TRDD) with its side air intakes (BVZ) mounted from the outer sides of the fuselage and above the RKAS consoles, configured to ensure their operation at supersonic and subsonic flight speeds, used with its RKAS synchronously decomposed and fixed and the corresponding flight mode of a jet BSDA carrying a 9-A2-type glide bomb 7759 "Thunder" or the mentioned APR-type UR-torpedo -3M, respectively, to perform a mission when attacking a ground and surface or underwater target, as well as covert advance into the attack zone, but also to perform a return flight to receive it under an empty TSAN control panel, moreover, when the BSDA is air-based on the corresponding TSAN control panel and after performing BSDA mission in its independent flight mode, when landing, the BSDA has the ability to use its retractable tricycle wheeled landing gear or landing parachute system or dock to the TSAN during their horizontal joint flight using a flexible attachment between them with their automatic docking / undocking systems to perform, respectively, horizontal or vertical landing of the BSDA on a ground airfield using load-bearing aerodynamic surfaces or its ejected landing parachute, or after the BSDA has docked with the BUL TSAN in flight and it has been placed on its free pylon for their respective joint horizontal landing as a summer aircraft carrier to a ground airfield, while the fuselage of the BSDA, having a diamond-shaped or trapezoidal or cylindrical cross-section with a conical bow and a truncated conical aft parts, smoothly turning into its central cylindrical part, including paired triangular upper BVZs and lower conformal fuel tanks from its sides, forming a lenticular cross-section of it, having along its larger and smaller diagonals, respectively, side compartments with their spring-loaded doors that open / close with the corresponding simultaneous stacking / unfolding of the RKAS consoles in them, and the lower bomb bay with its automatic doors or the lower niche, respectively, for an internal or semi-recessed placement on the said launcher of a bomb load of either a magnetometer, or sonar buoys, or an electronic warfare system, moreover, the head BSDA, which is fully digitized and includes the use of a laser communication channel, which will allow it to be equipped with a multi-frequency airborne radar with AFAR, and the mentioned BSU at safe distances for it implements communication via a closed channel with sonar buoys, providing geolocation of an underwater target and control over a laser communication channel with weapon loads and its own and other BSDA with targeting of their mentioned UR- torpedoes of the APR-3M type as part of a strike air group used in conjunction with a number of other air groups capable of both exchanging information between their head BSDAs within their single so-called information cloud and transmitting target designation to a number of BSDAs that do not use their radars in other anti-submarine ANUBIS. 2. The complex according to claim. 1, characterized in that in the said tail unit OYO of the super-maneuverable BSDA, its upper and lower said TsPRK, mounted respectively along the plane of symmetry and outward from it with the placement of the lower ones to the latter at an angle of 60 °, are made folding down in the sophistication of the aft fuselage with their fixation in the direction from the upper TsPRK, while in the remote-slave BSDA on the mentioned RCAS there are consoles with their narrowing (

), equal to

, and the mentioned ROZ, the configuration of which in plan is similar to the shape of one-sided lower and upper TsPRK tail OYO, and the mentioned RKAS, integrated according to the area rule with the BSDA fuselage, having left and right consoles, taken out, respectively, both back and forth along its flight, and away from the fuselage and its side compartments, located behind and in front of the center of mass, but also on separate nodes of their rotation, changing the asymmetric sweep along the leading edge, for example, when unfolding the RKAS consoles in a horizontal plane, respectively, with straight line angles χ=+60° /χ=+45° or χ=+15° and inverse χ=-60°/χ=-45° or χ=-15° when flying at altitude in super-/trans- or subsonic BSDA configuration for mission implementation at attacking a target / approaching the target zone or receiving it with fixation on the mentioned high-altitude TSAN, while the expansion of the bilaterally asymmetric layout of the airframe of the reconnaissance-strike BSDA may additionally include an asymmetric displacement in the longitudinal direction of the inputs of their mentioned BVZ, but also the displacement in the same direction in its said plumage OYO of the left and right lower TsPRK, spaced with a similar displacement of the corresponding consoles of the RKAS, and the airframe of each BSDA is made according to low-observable technology with a coating that absorbs radio waves of different lengths, has monolithic construction of its rigid hull using aluminum-lithium alloys and up to 70% improved structural aging composite materials, reinforced with spars and stiffeners with a common composite fuselage skin and BVZ, reinforced with carbon fiber, capable of protecting its said BSU from powerful electromagnetic flashes or impact laser radiation, withstand significant amounts of heat and deformation, allowing to reduce the number of parts by an order of magnitude, while each BSDA with its RKAS and multidirectional sweep χ=±45° will allow, in comparison with the wing of a jet aircraft and its sweep angle χ=+45°, decrease wave resistance by 2.8 ... 3 times and the required thrust-to-weight ratio by 1.44 times, moreover, to ensure at the height of the trans- or supersonic flight mode of each BSDA, respectively, in the direction of the target chosen for attack or only after 48% of the mission execution time and fuel depletion , and with multidirectional sweep of its RCAS with the corresponding angle χ=±45° or χ±60°, which provides an increase in the aerodynamic and structural advantages of the airframe of bilateral asymmetry, which improves the ratio of lift to its resistance, which, at the corresponding flight speed of the BSDA, is up to 0, Mach 98 or Mach 1.06 will be 20 to 1 or 11 to 1, while in the inconspicuous BSDA, its adaptive turbofan is equipped with a reactive flat rectangular nozzle (PPS) having both a heat-absorbing coating and a rear V-shaped edge in plan, placed in parallel trailing edge of the lower aft fairing of its fuselage. 3. The complex according to any one of paragraphs. 1, 2, characterized in that each said control panel of the mentioned TSAN is equipped in front with an upper bracket, made with the possibility of its deviation from the control panel up / down and along the plane of symmetry of the BSDA, equipped in front of its rotation unit with a cargo winch with a system of internal blocks for automatic control of the cable, passed to the BUL through the upper hook-shaped bracket and its cone-shaped fairing (KOO) with a lower cutout for the produced BUL, which has four trellis rudders deployed in an X-shaped one-piece rudder on its cylindrical nose, but also inside the BUL cone a collet gripper, and the possibility, after deflecting the upper bracket upwards, of its free extension on a cable back along the flight of the TSAN to a distance that is a multiple of the length of the fuselage of the mentioned BSDA, allowing it to safely approach the TSAN at a low subsonic flight speed and, after equalizing the speeds of their flight, preliminary docking by means of the mentioned gi a flexible fastening system with a BUL and subsequent expansion in the horizontal plane of two upper L-shaped, when viewed from behind, side guide jaws mounted on each side and at the end of each control panel, which, after closing, form composite skids with a reverse U-shape when viewed from behind and their slot between their two horizontal shelves interacting with the upper side rollers of the BSDA fuselage retractable from the upper aft compartment of the T-shaped hook, when viewed from the rear, mounted behind the rear docking / undocking unit of the BSDA with the TSAN control panel, while after the preliminary docking of the BSDA to the TSAN by means of a flexible systems with a BUL, which pulls the BSDA fuselage with a cargo winch to the main docking / undocking nodes of their rigid attachment system with automatic observance by each BSDA and TSAN autopilot of both the alignment of two pairs of docking points of the rigid attachment system, and the translational equal-area approach with the required pulling of the BSDA along axes PKP TSAN cargo and winch both with the placement of the T-hook after it is raised along the flight of the BSDA from the aft compartment of its fuselage in the area of \u200b\u200bthe action of the then closed L-shaped guides, and to the main nodes of the rigid system of its fastening, each of which, after the extension of the L-shaped sponges - guides and a T-hook back to the outer sides of the control panel and into the aft compartment of the fuselage, respectively. BSDA, docking on a par with the nodes of the flexible docking / undocking system, provides a rigid attachment system with simultaneous folding of the RKAS and TsPRK consoles into the BSDA and performing their jointly docked horizontal flight in the configuration of an aircraft carrier.

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