Unmanned returnable aerial carrier

Abstract

FIELD: aviation.SUBSTANCE: designs of unmanned aerial vehicles. The unmanned returnable aerial carrier (URAC) has a fuselage, folding wings of forward and forward sweep, forming a double X-shape with opposite sweep along the leading edges χ = ±45° or χ = ±60° to perform the mission at transonic or supersonic speed, respectively, when approaching a target or attacking a target with its guided missile. The URAC is designed with the capability of mortar launch with folded wings and vertical tail from a vertical or jet-powered inclined transport and launch container, starting the turbojet engine, which ensures flight and automatic return to the launch site, and unfolding the supports in the aft part of the fuselage during a vertical landing on the tail using a gas-dynamic system.EFFECT: provides increased speed, flight range, and reduced dimensions in the travel configuration.2 cl, 3 dwg, 1 tbl

Description

[0001] The invention relates to adaptive reactive aircraft carriers (ARAC) having a fuselage, folding wings of forward and direct sweep, forming a double X-shape with their opposite sweep along the leading edges χ=±45° / ±60° for performing with trans- / supersonic speed, respectively, a mission when approaching a target / attacking a target with its guided missile, but also its mortar launch with folded wings and vertical tail from a vertical or with a jet booster inclined transport and launch container and starting a turbojet engine, ensuring flight and automatic return to the launch site, and unfolding of supports in the aft part of the fuselage with its vertical landing on the tail by means of a gas-dynamic system.

[0002] A system for engaging submarines (SSB) at long ranges is known, patent RU 2371668 C2, implemented in the form of a ballistic missile (BM), in the nose section of which a cruise missile (CM) is placed under a discardable fairing; BM contains aerodynamic surfaces with drives and a booster engine to ensure delivery of the CM to the firing range of the target area. For economical flight in the atmosphere, the CM is mated to the booster engine by means of a separation device, configured to fly in the area of ​​the target submarine and contains a detachable warhead (WV) of underwater action and a detachable radio-sonobuoy; the CM control system is equipped with equipment for receiving information from the radio-sonobuoy via a radio channel about the target location. In accordance with the commands, the target is searched for, detected, approached and destroyed by detonating the WV.After which the ballistic missile carrier continues its flight with the engine running, leading it away from the splashdown area of ​​the underwater warhead, so as not to interfere with its homing system when the disposable ballistic missile leaves the splashdown area of ​​the warhead and self-destructs.

[0003] The X-plane unmanned jet aircraft, manufactured by Northrop Grumman (USA) [https: / / en.wikipedia.org / wiki / Northrop_Grumman_Switchblade], is a well-known unmanned aircraft. It is designed with an asymmetrically variable sweep flying wing (AVS) design and has turbofan engines (TUF) in a tailplane with internal bomb bays and a retractable tricycle landing gear. For supersonic flight, the X-plane uses two General Electric J85-21 turbofan engines with a jet thrust of 4485 kgf, providing a speed of 1275 / 1487 km / h at a flight altitude of 15 km with a thrust-to-weight ratio of 0.53 / 0.68. Aircraft with a KAIS have a number of disadvantages, the main ones being: a shift in the aerodynamic focus with multidirectional sweep, which leads to an increase in trim drag; an increase in the structural weight due to the presence of rotating hinges on the consoles.Furthermore, with a large sweep angle of 45°, a forward-swept wing has a larger effective angle of attack than a forward-swept wing, resulting in asymmetric drag and, consequently, parasitic yaw moments in roll, pitch, and yaw. Furthermore, KAIS is characterized by a twice-large spanwise increase in boundary layer thickness, and any asymmetric flow separation causes intense disturbances, which are eliminated by a second KAIS, forming double-X wings.

[0004] The closest to the proposed invention is [see http: / / rbase.new-factoria.ru / missile / wobb / ikara / ikara.shtml] the unmanned aerial vehicle (UAV) "Icara", which has a wing, a tail unit, a fuselage with a launcher (LU) for a guided missile (GM), a power plant (PU) engine and an on-board control system (BSU) for control from the command post of the basing vehicle.

[0005] Matching features - a UAV with dimensions without a ship's launcher: length 3.42 m, wingspan 1.52 m, height 1.57 m, carries an anti-submarine homing torpedo (SNT) of the Mk.44 type, which, with a weight of 196 kg, a length of 2.57 m and a diameter of 324 mm, has a speed of 30 knots and a range of 5 km. The UAV with the Mk.44 torpedo has a maximum / minimum flight altitude of 300 / 20 m and a significant weight of 1,480 kg, which limits the range to 24 km and the flight speed to 140 ... 240 m / s.

[0006] Factors hindering the assigned task: first, the subsonic UAV was launched in a direction that would bring it as close as possible to the target. Target location data was received from the sonar system of the surface carrier, another ship, or an anti-submarine helicopter. Based on this information, the optimal torpedo release zone was constantly updated in the fire control system computer, which then transmitted it to the UAV during flight via the fire control system. Upon arrival at the target area, the Mk.44 torpedo, semi-submerged and located under the fuselage of the UAV, was released by radio command, parachuted, entered the water, and began searching for the target. The UAV then continued its flight with its fire control system operating, guiding it away from the splashdown site of the anti-submarine torpedo to avoid interfering with its homing system. The disposable UAV itself then departed the area and self-destructed.

[0007] The proposed invention solves the problem of increasing the speed, flight range and economic efficiency of the above-mentioned known UAV of the "Icara" type due to its multiple use as part of an anti-tank or anti-ship or anti-aircraft defense system, reducing the dimensions in the transport-and-travel configuration and providing, by means of a gas-dynamic method, automatic return and vertical landing at the launch site or the deck of a ship or the airfield where the aircraft carrier is based.

[0008] Distinctive features of the proposed invention from the above-mentioned known UAV of the "Icara" type, which is closest to it, are the presence of the fact that it is made with the possibility of its release from the mentioned launcher of the carrier aircraft or mortar launch from a vertical transport and launch container (TLC) or launch with its rocket booster from an inclined launcher (NPU) or from an airfield wheeled trolley, but also after it has completed the mission of automatic return and its vertical landing on the tail, respectively, at the site of the covert launch position of the ground-mobile complex or at the airfield where its carrier aircraft or itself is based, and the repeated use of the reusable VARAN is carried out due to its vertical landing, which is ensured by means of a gas-dynamic system and after the automatic unfolding of the landing trapezoidal in plan four folding frames with self-installing rounded in plan shock-absorbing supports,located azimuthally at 90°, connected to the telescopic rods of their main cylinders, which ensure the deployment of landing gear from the corresponding steps of its fuselage, extended backward in flight and outward, while the reverse and direct swept wings (FW and KPS), mirror-imaged in the top view, contain folding consoles that are mounted in the central part of the fuselage in front and behind in flight from the center of mass, respectively, on the upper and lower sides of its hexagonal transverse shape (HTS), which has the shape of an irregular or regular hexagon, and are rigidly fixed with their tips rounded in plan when the FW and KPS are folded or unfolded, respectively, with their placement in the front and rear steps of the fuselage with the FW and on both sides of the axis of symmetry or with an outward extension from the latter, both with a negative, and positive the transverse angle V, and the corresponding sweep (χ) along their leading edges, for example, χ=-45° and χ=+45° or χ= _60° and χ=+60°, providing a transonic or supersonic flight mode at altitude, but are also deployed manually by personnel on the GPU or with subsequent automatic readiness for flight with the formation of double X-shaped wings (DW) when viewed from the front and from above, with each KOS and KPS, hingedly attached to the fuselage so that in the extended position, when viewed from the front, they form a DW with angles of 30°…60° and 150°…120° between their planes, respectively, for their one-sided and multi-sided KOS and KPS and are rigidly fixed in the plane of the corresponding sides of the fuselage with the SPF, and in the folded position, each KOS and KPS is fixed, placing their consoles, the lower and upper surfaces of which are pressed parallel to the corresponding sides of the fuselage with the SPF, having their width equal to the chords of the KOS and KPS, while the fuselage contains a conical nose section integrated with the SPF of the central its parts,containing with its KDH front dorsal and aft ventral steps for simultaneous unfolding from them / staying in them the KOS and KPS, having rounded edges and smoothly turning into its aft part, made in the form of a truncated cone, including both a folding trapezoidal vertical tail (TVO) with its triangular rudder, and a mid-mounted stabilizer (MS), the span of which does not extend beyond the dimensions of the circumscribed circle of the fuselage SPF, but also a turbofan engine (TRFD) with a ventral air intake (VAI) of a recessed type, which is made non-adjustable with a short S-shaped air duct, forming a VAI length equal to three diameters of the circumscribed circle of the fuselage SPF and ensuring both its subsonic or supersonic operation, and the possibility of the corresponding flight mode of the VARAN, for example, after its launch from the mobile complex's transport and launch platform with its anti-tank or anti-aircraft missiles (ATGM or SAM),but also outside the TPK of the turbofan engine launch and the synchronous deployment and fixation of its HVO with the KOS and KPS, for example, after turning the latter in the KDH by the tracking drive from the axis of symmetry at an angle of, for example, χ = ±45 ° counter-clockwise and clockwise when viewed from above, respectively, carrying in its bomb bay or on the sides of the fuselage on its saddle-shaped sides of the SHPF for performing its mission and attacking a target with more than one, for example, an air-to-air SAM, located in more than one TPK on a catapult launcher or in more than one TPK on each side of the SHPF of the fuselage, respectively, flying with its covert extension to the target zone and performing a return flight to the launch site and its corresponding reception on a platform with a heat-resistant coating, for example, a transport and loading vehicle interacting with the self-propelled launcher (SPU) MZKT-7930, containing four or eight TPK for launching strike VARAN anti-tank / anti-ship or air defense (AT / ASD or AA),wherein the gas-dynamic system (GDS), which ensures control of the balance during vertical take-off and landing (VTL) and hovering or zeroing the vertical speed of descent for landing on the tail, includes a turbofan engine with the selection in its compressor of the volume of air supplied through the air duct system for four jet controlled ramjet nozzles (JCN), which, together with the turbofan engine, ensure the necessary stability and controllability at all speeds of ascent and hovering or descent, mounted on the end of the aft part of the fuselage and integrated in the steps of four landing hinged frames, having at the exit controlled flaps equipped with the ability to change the balance in pitch, roll and heading with the fuselage in a vertical position.

[0009] In addition, in the transport and stowed position, the folded mentioned TVO is closed by a detachable fairing, repeating the outer profile of the fuselage from the end of the aft part of the fuselage and having the ability to automatically remove it or reset it when it is launched into flight, for example, from the mentioned TPK, while as part of the air defense air group, its lead VARAN, which is completely digitalized and its mentioned BSU is equipped in the nose of the fuselage with a fairing of a dual-frequency airborne radar (RLS) with an active phased antenna array (AESA), which, together with the optical-electronic station (OES), mounted below the nose of the fuselage, provide at safe distances for it both geolocation of a low-observable target and the transmission of target designation to a number of low-observable VARAN, but also control of its weapons loads and via a laser communication channel of others remotely controlled VARANs with target guidance for their SAMs, for example, the 9M342 Igla-S type,wherein the VARAN airframe is manufactured using low-observable technology with a radio wave-absorbing coating, has a one-piece rigid body structure using aluminum-lithium alloys and composite materials with improved structural aging, reinforced with spars and stiffeners in a single composite skin of the airframe with its aforementioned KOS, KPS and TVO, which are reinforced with carbon fiber, capable of protecting against powerful electromagnetic flares or the effects of laser radiation, withstand significant amounts of heat, especially its aforementioned BSU, which provides remote control by the operator from the command post of the basing facility or the pilot of a nearby carrier aircraft or the automatic execution of an over-terrain flight by means of a digital correlation system with the terrain, which with its GLONASS positioning channel and radar altimeter is supplemented by a digital thermal imaging camera installed in the nose of the fuselage,which ensures both the correlation of the display of the object for recording the terrain in front of the VARAN, and the comparison of information from the camera and its digital images obtained with the help of satellites or aerial reconnaissance and stored in the memory of the computer of the combat control system of digital maps of the terrain heights, over which, skirting the relief and obstacles, it is necessary to fly covertly, while in the adaptive control system its said turbofan engine is equipped with a jet ramjet flat rectangular nozzle (PRN) with a heat-absorbing coating and a V-shaped in plan rear edge, forming a sawtooth planform with the rear edge of the swept consoles of the said SRS, and the release from the carrier aircraft with a horizontal or vertical position of its fuselage is ensured respectively from its said launchers or airdroppable pallets with VARANs loaded into them, while performing the release outside the zone of action of the enemy air defense of the missile-destroying VARANs from below from cells with rack guides from four fifteen-round cargo pallets,parachuted from an Il-76MF aircraft during the deployment of sixty VARAN low-cost airborne air defense systems and guiding their 480 9M342 Igla-S SAMs from an A-50U airborne early warning and control (AWACS) aircraft, will make it possible to repel a global attack by subsonic cruise missiles and increase the combat stability of VARAN with their cruise thrust-to-weight ratio (K, MT), which is programmed for a cruising thrust-to-weight ratio: first level - 0.22 or second - 0.26 or third - 0.53 using 41.5% or 49.1% or 100% of the power of the said turbofan engine, respectively, to achieve at a flight altitude of 12 km the corresponding flight speed of Mach (M) = 0.84 or M = 0.94 or M = 1.1, and their said KDH with their said KOS and KPS, forming a two-sided asymmetry and their opposite sweep, equal to, for example, χ = ±45°, contribute, in comparison with the wing of a jet aircraft and a sweep angle χ = ±45°, to a decrease in the required thrust-to-weight ratio by 1.41 times and, as a consequence, at maximum takeoff weight, an increase of 20% ... 30% of their operating radius, while ensuring and maintaining a supersonic non-afterburning flight mode VARAN with its KDH, respectively, in the direction of the target selected for attack, or after 50% of the mission execution time and fuel depletion, as well as with a multi-directional sweep of its mentioned KOS and KPS with their angle χ=±45° or χ=±60°,providing at traction capacity K, MT ≥0.53 increase in the aerodynamic and structural advantages of the airframe with bilateral asymmetry, improving the ratio of the aerodynamic quality to its drag, which at a flight speed of VARAN up to 0.98 Mach or 1.2 Mach will be 20 to 1 or 11 to 1, respectively, wherein in the horizontal flight modes of the super-maneuverable VARAN with its mentioned control and dynamic characteristics, directional control is provided by the rudder on the mentioned TVO, and longitudinal and lateral control is carried out, respectively, on the mentioned KOS and KPS by in-phase and differential deflection of the control surfaces, which, under the control of the flight control software, perceive the flight control sensors and move the control surfaces using the control surface drives according to the readings of the flight control system and GLONASS sensors.

[0010] The proposed invention of an unmanned VARAN, mounted in a TPK with folded TVO, KOS and KPS, which are rigidly fixed and parallel pressed to the sides of the fuselage SPF and, after the opening of two wings, asymmetrically change their sweep and form a KDH when viewed from the front and from above, has a GDS for controlling the thrust of a turbofan engine with its reactive PPS and UPS, is illustrated in Fig. 1-3:

[0011] - in Fig. 1 - shown in side view of VARAN with folded TVO, KOS and KPS, mounted in TPK for mortar launch and launch from SPU type MZKT-7930;

[0012] - in Fig. 2, 3 - is shown in the front / side view of the VARAN with the KDH and their KOS with KPS, having rounded tips and their multidirectional sweep x=±45° and X=±60° when performing trans- and supersonic flight / VTOL modes.

[0013] The reusable VARAN 1 is presented in TPK 2 (see Fig. 1), made with a bilaterally asymmetric layout of the airframe and its KOS 3-5 and KPS 4-6 with their control surfaces 7 and 8, forming the KDH 3-4 and 5-6 when viewed from the front and from above (see Fig. 2 and 3), installed on the fuselage 9 and hinges 10 with their tracking drive mechanisms for synchronous rotation and fixation in their two positions at angles of opposite sweep along the leading edges χ = ±45 ° / ±60 ° \ folded KOS 3-5 with KPS 4-6 and TVO 11 with its triangular rudder 12, respectively, to perform a mission when approaching / attacking a target \ for a mortar launch from a vertical TPK 2. The adaptive control system has The thrust control system of a small-sized turbofan engine, used with a recessed type underfuselage air intake 13 and its ramjet UPS 14 and PPS 15, which has a V-shaped trailing edge in plan, forming a sawtooth planform with the trailing edge of the swept consoles SRS 16 (see Fig. 3).The fuselage 9 has a conical nose 17 section when viewed from the side, smoothly transitioning into its central section with the nose cone 18, containing saddle-shaped sides on the sides for accommodating grouped TPK 19 with their SAMs and having front dorsal 20 and rear ventral 21 steps for simultaneously unfolding / staying the KOS 3-5 and KPS 4-6 from them so that the tips 22 of the left 3 / right 5 KOS consoles when placed along the axis of symmetry are located under the nose C-shaped fairings 23 when viewed from the side (see Fig. 1). The jet UPS 14 are mounted on the end of the aft section of the fuselage 9 and integrated into the ledges of four landing folding frames 24 with self-installing rounded in plan shock-absorbing supports 25, but also have at their exit controlled flaps 26, equipped with the ability to change the balance in pitch, roll and course with the fuselage 9 in a vertical position.The super-maneuverable VARAN 1, performing an autonomously loyal flight after its launch from the TPK 2 and jettisoning the rear fairing 27 (shown by the dotted line, see Fig. 1) with the TVO 11 and its turbofan engine, which creates its PPS 15 jet thrust for the trans- / supersonic flight mode, in which directional control is provided by deflecting the rudder 12 on the TVO 11, and longitudinal and lateral control is carried out by in-phase and differential deflection of the control surfaces 7 and 8, respectively, on the KOS 3-5 and KPS 4-6 of their corresponding KDH 3-4 and 5-6 (see Fig. 3). During operation, the flight control software system senses their control sensors and moves the control surfaces using their drives both to maintain the low-observable VARAN 1 on the desired trajectory and to direct it to the target using a TV camera (not shown in Figs. 1-3).

[0014] Thus, the development of the VARAN-174 and VARAN-140, respectively, for a mobile system based on the MZKT-7930 SPU, which destroys unmanned boats (UBK), and an air-based air defense system on the A-50U AWACS aircraft, each of which carries four and six corresponding VARANs with their Kornet-type ATGMs and Igla-S type SAMs in their transport and control panels, while the lead one has a dual-frequency airborne radar with an AESA in its combat control unit, which, at safe distances, communicates via a closed channel with a number of VARANs in other systems, providing geolocation of surface and air targets and laser control of their weapons payloads during target acquisition. It is known that at subsonic speeds, wave drag accounts for a relatively small part of the overall aerodynamic drag of an aircraft. However, wave drag increases significantly as transonic and supersonic flight speeds are approached.Therefore, wave drag reduction is achieved by minimizing the change in its longitudinal cross-sectional area, achieved through the bilateral asymmetry of the double-X-shaped wings. This results in a halving of the specific wing loading compared to cruise missiles (CMs), and by reducing wave drag, increases fuel efficiency and, consequently, the VARAN's speed and range.

[0015] Since the promising VARAN, with its advanced tactical and technical characteristics, is armed with Igla-S SAMs in their transport and launch containers, its airborne deployment, taking into account the experience of developing the KS-172 ultra-long-range air-to-air missile, is both economically preferable and technically feasible. Essentially, the combat capabilities of such an air defense system are not limited to the VARAN's flight and depend largely on the carrier aircraft itself. Therefore, the reusable VARAN, as an element of advanced military technology, can tactically occupy an intermediate position between the SAMs of mobile air defense systems such as the Buk, Tor-M2, and Pantsir-S, which are capable of attacking targets, but their SAMs are quite expensive. MiG-31 air defense interceptors, given their frontline deployment, will also be no less expensive. Only the development of a low-cost airborne air defense system will significantly simplify the deployment of anti-aircraft equipment, especially at great distances from the target and base.Therefore, using the ability to drop the VARAN-140 (see Table 1) from four fifteen-round pallets dropped by parachute with the deployment of 60 VARANs and the guidance of their 480 SAMs from Il-76MF aircraft and A-50U AWACS, respectively, will make it possible to repel a global attack by subsonic cruise missiles. At the same time, in air defense / air defense systems, increasing the mass of aviation fuel in the VARAN-174 / VARAN-140 to 625 / 463 kg and, having a range of up to 1,282 / 855 km, will make it possible to increase the range of the Kornet ATGM / Igla-S SAM to 1,287 / 860 km or loiter in direct radio visibility for 80 / 50 minutes when engaging kamikaze unmanned aerial vehicles / subsonic cruise missiles and attack UAVs.

[0016]

Claims

1. An unmanned re-entry vehicle-carrier (URC) having a fuselage with a launcher (LU) of a guided missile (GM), a wing, a tail unit, a power plant engine (PU) and an on-board control system (BSU), characterized in that it is designed with the possibility of its release from the launcher of a carrier aircraft or a mortar launch from a vertical transport and launch container (TLC) or a launch with its rocket booster from an inclined launcher (NPU) or from an airfield wheeled trolley, but also after it has completed the mission of automatic return and its vertical landing on its tail, respectively, at the site of a covert launch position of a ground-mobile complex or at the airfield where its carrier aircraft or itself is based, and the repeated use of the reusable URC is carried out due to its vertical landing,which is ensured by means of a gas-dynamic system and after the automatic unfolding of the landing trapezoidal in plan four folding frames with self-installing rounded in plan shock-absorbing supports, located azimuthally at 90°, connected with the telescopic rods of their main cylinders, providing from the corresponding steps of its fuselage the opening of the landing supports, carried back in flight and outward, while the wings of the reverse and direct sweep (KOS and KPS), mirror-image located in the top view, contain folding consoles, which are mounted in the central part of the fuselage in front and behind in flight from the center of mass, respectively, on the upper and lower sides of its hexagonal transverse shape (SHPF), having the shape of an irregular or regular hexagon,and are rigidly fixed with their tips rounded in plan in the folded or unfolded KOS and KPS, respectively, with their placement in the front and rear steps of the fuselage with the SHPF and on both sides of the axis of symmetry or with an outward extension from the latter as with a negative, and positive the transverse angle V, and the corresponding sweep (χ) along their leading edges, for example χ = -45° and χ = +45° or χ = _60° and χ = +60°, ensuring transonic or supersonic flight mode at altitude, but are also deployed manually by personnel on the GPU or with subsequent automatic readiness for flight with the formation of double X-shaped wings (DW) when viewed from the front and from above, wherein each KOS and KPS are hingedly attached to the fuselage so that in the extended position they form, when viewed from the front, a DW with angles of 30...60° and 150...120° between their planes, respectively, for their one-sided and multi-sided KOS and KPS and are rigidly fixed in the plane of the corresponding sides of the fuselage with the SPF, and in the folded position, each KOS and KPS fixedly places their consoles, the lower and upper surfaces of which are pressed parallel to the corresponding sides of the fuselage with the SPF, having their width equal to the chords of the KOS and KPS, while the fuselage contains a conical nose section integrated with the SPF of its central section,containing with its KDH forward dorsal and aft ventral steps for simultaneous unfolding from them / staying in them the KOS and KPS, having rounded edges and smoothly transitioning into its aft part, made in the form of a truncated cone, including both a folding trapezoidal vertical tail (TVO) with its triangular rudder, and a mid-mounted stabilizer (MS), the span of which does not extend beyond the dimensions of the circumscribed circle of the fuselage SPF, but also a turbofan engine (TRFD) with a ventral air intake (VAI) of a recessed type, which is made non-adjustable with a short S-shaped air duct, forming a VAI length equal to three diameters of the circumscribed circle of the fuselage SPF, and ensuring both its subsonic or supersonic operation, and the possibility of the corresponding flight mode BVLAN, for example, after its launch from the TPK of a mobile complex with its anti-tank or anti-aircraft missiles (ATGM or SAM),but also outside the TPK of the turbofan engine start and the synchronous deployment and fixation of its HVO with the KOS and KPS, for example, after the rotation of the latter in the KDH by the tracking drive from the axis of symmetry at an angle of, for example, χ = ±45° counterclockwise and clockwise when viewed from above, respectively, carried in its bomb bay or on the sides of the fuselage on its saddle-shaped sides of the SPF for performing its mission and attacking more than one target, for example, an air-to-air SAM located in more than one TPK on the ejection launcher or in more than one TPK on each side of the SPF of the fuselage, respectively, flying with its covert advancement to the target zone and performing a return flight to the launch site, wherein the gas-dynamic system (GDS), providing trim control during vertical takeoff and landing (VTL) and hovering or zeroing the vertical speed of descent for landing on the tail, includes the turbofan engine with selection in its air volume compressor,supplied through a system of air ducts for four jet-powered controlled ramjet nozzles (UPS), which, together with the turbofan engine, provide the necessary stability and controllability at all speeds of ascent and hovering or descent, mounted at the end of the aft fuselage and integrated into the steps of four landing hinged frames, having controlled flaps at the exit, equipped with the ability to change the balance in pitch, roll and heading with the fuselage in a vertical position.

2. The UAV according to paragraph 1, characterized in that in the transport and stowage position, the folded said UAV is closed by a detachable fairing, repeating the outer profile of the fuselage from the end of the aft part of the fuselage and having the ability to automatically remove it or reset it when it is launched into flight, for example, from the said UAV, the UAV is completely digitalized and its said BSU is equipped in the nose of the fuselage with a fairing of a dual-frequency airborne radar (RLS) with an active phased antenna array (APAA), which, together with the optical-electronic station (OES), mounted below the nose of the fuselage, are made with the ability to provide geolocation of a low-observable target at safe distances for it and the transmission of target designation to a number of low-observable unmanned re-entry carrier aircraft and control of its weapons loads and via a laser communication channel to others unmanned re-entry vehicles with their SAMs aimed at the target, for example,type 9M342 "Igla-S", and the BVLAN airframe is manufactured using low-observable technology with a coating that absorbs radio waves, has a one-piece rigid body structure using aluminum-lithium alloys and composite materials, reinforced with spars and stiffeners in a single composite skin of the airframe with its aforementioned KOS, KPS and TVO, which are reinforced with carbon fiber, capable of protecting against powerful electromagnetic flares or the effects of laser radiation, to withstand significant amounts of heat, especially its aforementioned BSU, which provides remote control by the operator from the command post of the basing facility or the pilot of a nearby carrier aircraft or the automatic execution of an over-terrain flight by means of a digital correlation system with the terrain, which with its GLONASS positioning channel and radar altimeter is supplemented by a digital thermal imaging camera installed in the nose of the fuselage,providing both the correlation of the display of the object for recording the terrain in front of the BVLAN, and the comparison of information from the camera and its digital images obtained using satellites or aerial reconnaissance and stored in the memory of the BSU computer digital maps of the terrain heights over which, skirting the relief and obstacles, it is necessary to covertly fly, while in the adaptive control system its said turbofan engine is equipped with a jet ramjet flat rectangular nozzle (RPN) with a heat-absorbing coating and a V-shaped trailing edge in plan, forming a sawtooth planform with the trailing edge of the swept consoles of the said SRS, to increase the combat stability of the BVLAN with their marching thrust-to-weight ratio (Kmt), which is programmed for a cruising thrust-to-weight ratio: first level - 0.22 or second - 0.26 or third - 0.53, using 41.5% or 49.1% or 100% of the power of the said turbofan engine, respectively, to achieve at a flight altitude 12 km corresponding to the flight speed Mach (M) = 0.84 or M = 0.94 or M = 1.1,and their mentioned control and landing characteristics with their mentioned control and landing system, forming a two-way asymmetry and their opposite sweep, equal to, for example, χ = ±45°, while in order to ensure and maintain the supersonic non-afterburning flight mode of the BVLAN with its control and landing characteristics, respectively, in the direction of the target selected for attack or both after 50% of the mission execution time and fuel depletion, and with a multi-directional sweep of its mentioned control and landing system with their angle χ = ±45° or χ = ±60°, and in the horizontal flight modes of the super-maneuverable BVLAN with its mentioned control and landing characteristics, directional control is provided by the rudder on the mentioned TVO, and longitudinal and lateral control is carried out, respectively, on the mentioned control and landing system and landing system by in-phase and differential deflection of the control surfaces,which, under the control of flight control software, sense flight control sensors and move control surfaces using control surface actuators based on data from flight control system and GLONASS sensors.

Images