RU2743311C1 - Modular x-wing aircraft for arctic rocket aviation complexes - Google Patents

Abstract

FIELD: weaponry.SUBSTANCE: invention relates to weaponry, in particular to the structures of aircraft missile systems. Arctic missile-aviation complex (AMAC) contains an air-capable icebreaker (AC) with jet unmanned aerial vehicle (UAV) with a wing, fuselage with a launching device (LD) of a guided missile (GM), a power unit engine (PU) and onboard control system (OCS). Complex includes modular unmanned and manned X-wing aircraft with asymmetric swept wings, containing docking nodes on the right and left tips, detachably connecting their consoles with the upper fairing of the guided missile they are carrying. X-wing aircraft have over-the-wing pylons with single-bladed rotors (SBR) and combined gas turbine engines with free power turbines, driving two SBRs and/or two turbofans in annular fairings, creating jet thrust with working/autorotating blades or their fixed blades.EFFECT: increase of the target load affecting the capabilities of the complex and the multiple use of X-wing aircraft.2 cl, 3 dwg, 1 tbl

Description

The invention relates to ship-aviation systems, including at least left and right modular helicopter aircraft, having asymmetric sweep wings, containing docking nodes on their right and left ends, detachably connecting their consoles with the upper fairing of a jointly portable guided missile and simultaneously detachable from it in flight for its launch, followed by their separate return to the icebreaker carrier, and underwing fuselages equipped with profiled pylons with their single-blade rotor propellers (ONV) and combined gas turbine engines with free power turbines, driving two of their ONV and / or two in their annular fairings, their turbofans, creating a jet thrust with working / autorotating NVGs or their fixed blades with counterweights when flying in a rotorcraft / gyroplane configuration or an aircraft with guided missiles.

Known complex for the destruction of submarines (PL) at long ranges, patent RU 2371668 C2, made in the form of a ballistic missile (BR), in the nose of which under the dropped fairing is placed a cruise missile (CR); BR contains aerodynamic surfaces with drives and an accelerating engine to ensure the delivery of the missile launcher at a firing range to the target area. For economical flight in the atmosphere, the RR is docked with the accelerating engine by means of a separation device, is made with the possibility of flight in the area of the target submarine and contains a detachable underwater warhead (CU) and a detachable hydroacoustic buoy; the control system of the RV is equipped with equipment for receiving information from a hydroacoustic buoy via a radio channel about the location of the target. In accordance with the teams searching for the target, its detection, approaching the target and its defeat by detonating the warhead. After that, the BR-carrier continues its flight with the engine running, taking it away from the landing site of the underwater warhead so as not to interfere with its homing system. The very same single-use ballistic missile left the area of the splashdown of the warhead and self-destructed.

Known unmanned aircraft of the project "X-plane" of the company "Northrop Grumman" (USA) [http://test.abovetopsecret.com/forum/thread398541/pg1], made according to the scheme of a flying wing of an asymmetrically variable sweep (KAIS), has two turbojets two-circuit engine (turbojet engine) in a nacelle with internal bomb bays and a tricycle retractable wheel chassis. For supersonic flight "X-plane" its General Electric J85-21 turbojet engine 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: shift 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 swivel joints of the consoles. In addition, at a large 45 ° sweep angle, a straight swept cantilever has a larger effective angle of attack than a reverse swept cantilever, which leads to an asymmetry of the drag and, as a consequence, to the appearance of parasitic turning moments in roll, pitch and yaw. Moreover, KAIS is characterized by a twice as large increase in the thickness of the boundary layer along the span, and any asymmetric stall of the flow 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 anti-submarine aviation complex (PAK) model "Icara", containing a carrier ship with jet unmanned aerial vehicles (UAVs), having a wing, fuselage with a launcher (PU) of a guided missile (UR), a power plant engine (SU) and an on-board control system (BSU).

Signs that match - a UAV with dimensions without a ship's 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, having a mass of 196 kg, length 2.57 m and a diameter of 324 mm, a speed of 30 knots and a cruising 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 1480 kg, which limits the range to 24 km and the flight speed to 140 ... 240 m / s.

The reasons that impede the task: the first is that the launch of the subsonic UAV was carried out in the direction as close as possible to the target. Target location data came from the sonar system (GAS) of a surface carrier ship, another ship, or an anti-submarine helicopter. Based on this information, the data on the optimal torpedo drop zone is constantly updated in the fire control system computer, which then transmitted them through the BSU to the UAV in flight. Upon the arrival of the UAV in the area where the target was located, the Mk.44 torpedo, semi-submerged with its ventral position in the UAV hull, separated by radio command, descended by parachute, entered the water and began to search for the target. After that, the UAV continues its flight with a working control system, taking it away from the landing site of the homing submarine, so as not to interfere with its homing system. The disposable UAV itself left the area and self-destructed.

The proposed invention solves the problem in the aforementioned known PAC "Icara" to increase the target load and weight recoil, eliminate mechanisms for transforming the ONV, reduce the parking area in the traveling configuration, increase the speed and range of flight, as well as the destructive capabilities and automatic return with a vertical landing on the aircraft carrier icebreaker (ANL).

Distinctive features of the proposed invention from the above-mentioned known British PAK model "Icara", which is closest to it, are the presence of the fact that the Arctic missile and aviation complex (KARA) has a group of vertical take-off and landing vehicles, including more than two modular unmanned helicopter aircraft (MBSV) with more than a pair of modular manned helicopter aircraft (MHPV), used in pairs, both of the same type together, and in their combination, but also from more than one helipad of the said ANL, and in a combination of two MBSV / MHPV containing wings asymmetric sweep (CAS), having both on the right / left tips, respectively, of the left MBSV / right MPSV, their attachment and release mechanisms, forming a composite wing and detachably connecting them consoles with at least one underwing pylon or upper fairing together with the removable target load transferred by them ( SCN) - the mentioned UR and after its launch simultaneously detachable, on for example, from the UR fairing in flight or after landing, respectively, with their subsequent separate or joint return and their automatic vertical landing on the deck of the mentioned ANL, and along the leading edge, a different sweep, forming when connecting the corresponding KAS consoles, for example, with the upper fairing of the mentioned UR so that from the center of mass of the latter, the end chords of their outer two consoles are moved forward or backward or backward and forward along the flight, forming from the longitudinal axis of the mentioned UR, respectively, a composite wing of reverse or straight or asymmetric sweep, respectively, with an angle χ = -45 ° or χ = + 45 ° or χ = ± 45 °, but also two single-rotor bearing schemes (OVNS) used in vertical or short take-off / landing (GDP and KVP), including single-blade main rotor (ONV) with profiled counterweights, rigid attachment of their blades, mounted on the shafts of the profiled pylons of each underwing fuselage (PKF), the left / right of which are made with a Automated their skew, the ability to change their overall and cyclic pitch and automatically set their blades to the position of their autorotation, but also their free rotation with an overlap equal to a = 2.6 ... 2.7 in the transverse group of the ONV when the blades of one ONV pass in front of the blade of another so that their advancing blades in the run-off and hover modes pass over the right / left side of the left / right PCF, respectively, from its aft to the bow and create a harmonious combination of lateral and longitudinal control at an equal distance in terms of their axes of rotation from the center of mass and longitudinal axes the mentioned UR and their PCF, but also at least two combined gas turbine engines (KGTD), made in the form of two-circuit jet engines, containing as external three-stage fans (VTV) in annular fairings (KO) of the aft nacelles of the PCF, mounted along their longitudinal axes with their jet round or rectangular flat nozzles (PPS), carried out beyond the trailing edge of the UAN, executed with thrust vector control (UHT), ensuring the creation of vertical / inclined or horizontal thrust when performing GDP / KVP or translational flight, respectively, and more than two free power turbines (SST) mounted on the side of each PF in side nacelles with their air intakes, feeding VTV and SST, having jet flat nozzles (RPS), transmitting the takeoff power of the control system to their respective ONV in the doubled OVNS-X1 and their VTV in the propulsive-reactive system (PRS), the latter of which in the double PRS-R1 create synchronous cold jet thrust, but also equipped with the possibility of converting the flight configuration of deck-mounted connected MBSV / MPSV after their formation by two UAN of a composite wing and performing a vertical or short take-off at normal or maximum take-off weight, respectively, from a twin-rotor helicopter or rotorcraft with doubled both OVNS-X1 and PRS -R1 into a jet winged gyrocopter with autorotating NVG or an airplane with fixed their counterweights and blades placed in the plan along the longitudinal axes of the PCF, respectively, both forward and backward along the flight, and stopped at the vane position or zero angle of installation of their blades, which are fixed, respectively, vertically or horizontally parallel to the plane of symmetry of the MBSV / MPSV with their straight CAS , forming, for example, a composite CAS with an oppositely directed sweep χ = ± 45 °, having a total span determined from the relation: L _OP = R _OHB × a × cos χ = 45 °, m (where: R _OHB is the radius of the OHB, and - the value of the overlap of the ONV, χ is the sweep of the UAN) and its large elongation λ = 8.0, but also vice versa.

In addition, in the aforementioned MPSV / MPSV, when performing a runoff and hovering, the vertical application forces from the above-mentioned HWTs, for example, with the UHT of their PPS and the mentioned ONV, equidistant in plan from the axis of symmetry of the connected MPSV / MPSV, are placed on transverse lines extended in plan from their center of mass, respectively, back and forth along the flight at a distance inversely proportional to their lifting thrust, and in each mentioned side gondola of each of their PCFs, for example, one SST has a front shaft outlet for taking its power, which transmits torque by means of an angular gearbox to a cross-shaped unifying gearbox in plan, having front and rear output shafts along the longitudinal axis of the PCF, which transmit the distributed power, for example, the first of them and through the clutch to the angular gearbox ONV in the doubled OVNS-X1, and the second of them is rotationally connected to the VTV in the doubled PRS-R1, and each mentioned PPS of their aft nacelles PKF for thrust vector control (UHT) is equipped with an upper 27 and no 28 walls, containing at their ends rectangular in plan hatches-nozzles with transverse upper 29 and lower 30 rotary on their axes 31 and 32 in the vertical plane, having a length from the axes of their rotation with their chamfers, determined from the ratio: L _st = h _sop / 0.707, m (where: h _sop - the height of the nozzle, cos 45 ° = 0.707) and separate drives, providing between its side walls 33-34 their deviation to the longitudinal axis of the nozzle down and up synchronously Two at angles ± 22.5 °, joining their chamfers, or one of them at angles of ± 22.5 ° with the other closed in phase or differential, respectively, for reverse thrust or for longitudinal or lateral control or only the lower sash 30 at an angle of + 45 ° until its chamfer touches the surface of the upper closed flap 29 to change the direction of horizontal thrust to vertical, and each lower hatch-nozzle 35 in the lower wall 28 of each mentioned PPS to parry the torque and change the balance along the course when they fly separately in the modes of GDP and hovering, it is equipped from below with longitudinal controllable flaps-rudders 36, which, after their opening of the hatch-nozzle 35, deviate from the longitudinal axis of the PCF at angles to the left + 40 ° / right + 40 °, while the subtle MBSV / MPSV in the modes of their GDP and hovering at a specific load on the power of their _{adaptive control system, which is ρ N} = 1.26 kg / hp, each mentioned SST is made with elements of digital program control, combining an adaptive control system for the formation of a safe flight (UFBP) with a specific vertical thrust-to-weight ratio in doubled OVNS -X1, which, taking into account the losses from the blowing of the PCF and KAS ρ _BT = 1.85, includes the operating modes of the SST both takeoff and emergency mode (BP and CR) with 80% and 20% of the required power to drive the mentioned ONV and VTV, respectively, both from two operating SSTs and from one of the operating SSTs with automatic equalization and equal redistribution of the remaining power between the ONV in case of failure of the corresponding SST in the KGTD, for example, even in the latter case, after the automatic switching on of the PD of the work of the SST remaining in operation, which, with a specific vertical thrust-to-weight ratio in the doubled OVNS-X1, equal to ρ _VT = 1.07, will provide an emergency vertical landing mode for 2.5 minutes, and in each of their SST the system UFBP contains: one or more sensors that are configured to detect data concerning the air flow rate (G _B , kg / s) through the SST compressor, the gas temperature ( _TG , K) before the SST turbine, the total compression ratio (K) of the compressor, and also one or more sensors, which are configured to detect the relative position of the PCF and rotation disks of the NVD for their relative position relative to the ground level or the surface of the landing site, as well as various obstacles in the path of its tracking controlled descent; a flight control computer located in their BSU and operational with one or more sensors; the flight control computer is configured to: determine the relative position between their FSC with a wheeled chassis and the ground level or surface of the landing pad; compare the relative position of their PCF and their carrier system with their chosen relative position; determine the speed of automatic descent required to move them to the selected relative position; convert tracker speed to flight control inputs; and also to provide an automatic safe descent to the selected relative position through the flight control inputs, and their flight control computer is made both with an additional computer for summing sensor data, and with the ability to convert data from each sensor into a relative position, which is determined based on the global position, and in the modes of their GDP and hovering with their composite CAS, a change in the balancing in pitch, heading and roll, which is created by changing the corresponding cyclic step by means of the swashplate of each CAC and differential change in thrust, respectively, of the left and right CAS, which rotate in the opposite direction in plan, for example, counterclockwise and clockwise, and each MBSV / MPSV is made, respectively, without / with a cockpit, equipped inside with video cameras with autonomous manipulators connected to the MPSV controls and the possibility of its optional control by pilots from a two-seat cockpit, having seats ejected into the upper hemisphere, mounted side-by-side, which are triggered in the modes of running the runway and hovering automatically after firing off the ONV blades with squibs in an emergency, and their BSU is equipped with a fly-by-wire control system that responds to at least one of the autonomous flight control systems, remote control of the operator, control from the cockpit and / or their combination, and each of their PCF is equipped with front and rear main struts with wheels of a tricycle landing gear, retractable forward along the flight into their respective compartments, has at its end all-rotary keels (CPK), deflected downward, but also outward from the plane of symmetry of the MPSV and MPSV at an angle of 43 ° to the horizontal, and each of their CAS has endings triangular in plan with their outer sides located parallel to their axis of symmetry, is made with end parts folded up and back in the parking lot. flight or top and perpendicular to the axis of symmetry of MPSV and MPSV, placing above their PKF, with their separate placement in the hangar of the mentioned ANL with the blades of their ONV installed in a feathered position and, along with their folded keels up or down, reduce their parking area by 6.4 ... 6.6 times from the take-off area, and the strategic MPSV and MBSV , carrying under their composite KAS one air-to-surface air-to-surface missile (AKR) of the Kh-101 type, after their launch, forming autonomous swarms of AKR with towed false targets, using their low-altitude flight profile and their self-defense system - an active electronic jamming station, increase their range using the GDP / KVVP technology, respectively, up to 8125/10345 km, but also a destructive opportunity, create a safe air zone between the ANL and the air defense of the target, and their PKF for internal armament have single and double doors, respectively, side and lower compartments, PU which with fixed on them the air-to-air missile of the R-77 type and the anti-ship missile (ASM) of the Kh-38M type are mounted on the inner sides of the doors and inside the compartment kov, respectively, and under the pylon of their composite UAN, carrying the aforementioned STsN-fuel tank, using its fuel, it will allow each of their pairs in the air group to reach the surface target, then, separating and attacking it in a swarm, increase the destructive capability and range of the X-type anti-ship missiles -38M from 40 km to 1830 km, while heavily armed MBSV / MPSV, carrying hypersonic anti-ship missiles Kh-47M2 "Dagger" or anti-ship missiles of the Kh-32 type under the pylon of their composite UAN, provide its controlled launch at supersonic speed and an altitude of 15 km and will allow to achieve a range of its flight up to 2160/3570 km or 1860/3270 km, using the VVP / KVVP technologies, respectively, and the airframe MPSV and MBSV is made of aluminum-lithium alloys and composite materials using an inconspicuous technology with a radio-absorbing coating, and each of their PCF has from their pyramidal nose parts, beveled along their entire length, the lateral sides, forming with the mentioned side air intakes when viewed from the front, a five- or hexagonal cross-section, reducing effective scattering area, but also radar and visual visibility, and in their PCF the mentioned side air intakes, which do not have a lamellar cutter of the boundary layer and internal movable regulating elements, are also made to remove the boundary layer and increase the total pressure recovery factor as without a gap for draining the boundary layer layer, and shielding the compressor blades of the SST and VTV of their mentioned KGTD in an adaptive control system that changes the volume of air, which, providing greater thrust and fuel efficiency, passes through the SST and VTV, but each for the latter two includes corresponding ramps, each of which compresses the flow and forms a conical flow, while the electro-optical sensor (EOD), designed for detecting and identifying a target, has a receiving part of the EOD, which is closed from above with a sapphire glass, is installed in front of the MPSV cabin on top of the bow of the right PKF and, with the latter's radar, provides for large, safe ra states, target designation and control of weapon loads, both their own and MBSV with aiming at the target of the AKR and anti-ship missiles of the air-to-surface and air-to-air missile systems, but also its joint use as part of an aviation group as a head MPSV, for example, with one previous or more than one of the subsequent slave MBSV, and the mentioned ANL having an asymmetric hull, is made with its two-draft scheme, which allows the use of a draft in the range from 8.5 to 10.5 m to increase icebreaking capacity and perform special tasks in shallow water and river estuaries, equipped with a propulsion system , consisting of a pair of main and a pair of additional, respectively, aft and bow propeller-driven propellers (VRK), each of which, working independently and increasing the efficiency of maneuvering in any direction and even rotation in place, can both turn in a horizontal plane by 360 °, so and is equipped with a built-in high-torque DC motor with a suitable propeller with a fixed pitch propeller (FPP) mounted directly on the shaft inside the full-revolving propeller gondola, and the installation of bow propellers on the ANL provides high maneuverability in ice conditions, but also in clear water, which is very important in areas with limited water space, but also, achieving the effect erosion of ice by the work of these fixed pitch propellers both reduces the ice strength and increases the ability to pass ice hummocks, and has a harmful effect on the operation of the aft propellers, while in order to increase the efficiency of the propulsion unit of the aforementioned ANL, a pair of forward propellers, which, providing the effect of divergence of their thrust vectors from the longitudinal axis of the ANL , deployed at an angle to each other on the effective support of the ANL in the mode of creating a thrust, and the propulsion unit with four propellers and four control joysticks are combined in one bridge with the installation of two navigation bridges - the main and backup for controlling the nuclear ANL during the course and visual control improving from the second m the bridge has a panoramic view when it moves in an oblique motion.

In addition, for the trans- or supersonic flight mode of the connected MPSV / MPSV, reaching the marching thrust yield of the first level - 0.22 or the second - 0.26 or the third level - 0.5 or the fourth - 0.61, respectively 22% or 27 % or 72% or 100% of the power of their SU at an altitude of 15 km with the mentioned composite UAN, a speed of Mach 0.894 (M) or M = 0.988 is provided or a supersonic speed of M = 1.12 or M = 1.3, respectively, and each of them The SST is equipped with its aforementioned RPM with an afterburner used in aircraft takeoff and supersonic flight modes with open controlled flaps of the said side nacelle in front of its compressor and rear doors in front of the afterburner for additional air supply to it, which will allow at normal / maximum takeoff weight to flight altitude of 15 km, increase the thrust yield of their mentioned SU from 0.61 / 0.52 to 0.78 / 0.68 and achieve a supersonic flight speed M = 1.5 / M = 1.4, respectively, while the absence of glazing The installation of frontal windows or all windows in the cockpit of the MPSV pilots will increase the rigidity of the PCF and reduce the thickness of the skin and, as a result, reduce its weight, moreover, the MPSV glider with a sealed cockpit, which has an automatically dumped opaque armor lamp for ejection of pilots and a digital image display facility representing a part of the external scene, including the environment, stretching forward and sufficient for piloting, is equipped with a variety of video cameras, infrared sensors and video sensors that provide touch shooting, recording all events in the front and rear hemispheres at 360 °, while controlling the MPSV in the mode in real time, the image is digitally corrected and displayed by the video distribution module on the cockpit displays, making it either transparent or visible on the helmet displays of the pilots, which, forming common viewing windows, are connected to the first and second processors of the extended vision system, configured for wearing the first m and the co-pilot, respectively, with the first and second common viewports and highlighted displayed lines of sight visible on the first and second helmet-mounted displays of the pilots, respectively.

Due to the presence of these features, which will make it possible to master the attack-strategic KARA, which has a group of vertical take-off and landing vehicles, including more than two modular unmanned helicopter aircraft (MBSV) with more than a pair of modular manned helicopter aircraft (MPHC), used in pairs as one type together, and in their combination, but also from more than one helipad of the aforementioned ANL, moreover, in a combination of two MBSV / MPSV containing asymmetric swept wings (KAS), having both on the right / left tips, respectively, of the left MPSV / right MPSV their attachment and release mechanisms that form a composite wing and detachably connect them consoles with at least one underwing pylon or upper fairing together with a removable removable payload (SCN) - the mentioned UR and after its launch are simultaneously separated, for example, from the UR fairing in flight or after landing, respectively, with their subsequent separate or joint return and auto their automatic vertical landing on the deck of the above-mentioned ANL, and along the leading edge, a different sweep, which, when connecting the corresponding KAS consoles, for example, with the upper fairing of the said UR so that from the center of mass of the latter, the end chords of their outer two consoles are moved forward or backward or backward and forward along the flight, forming from the longitudinal axis of the mentioned UR, respectively, a composite wing of a reverse or a straight or asymmetric sweep, respectively, with an angle χ = -45 ° or χ = + 45 ° or χ = ± 45 °, but also two single-rotor carrier Schemes (OVNS) used for vertical or short take-off / landing (GDP and KVP), including single-blade rotor (ONV) with profiled counterweights, rigid attachment of their blades, mounted on the shafts of profiled pylons of each underwing fuselage (PKF), left / right of which are made with their skew automatic machines, the ability to change their overall and cyclic pitch and automatically set their blades in position f their autorotation, but also their free rotation with an overlap equal to a = 2.6 ... 2.7 in the transverse group of the ONV when the blades of one ONV pass in front of the blade of the other so that their advancing blades in the run-in and hover modes pass over the right / left side left / right PCF, respectively, from its aft to the bow and created a harmonious combination of lateral and longitudinal control with equal distance in terms of their axes of rotation from the center of mass and longitudinal axes of the mentioned UR and their PCF, but also at least two combined gas turbine engines (KGTD ), made in the form of two-circuit jet engines, containing as external three-stage fans (VTV) in annular fairings (CO) of the aft nacelles of the PKF, mounted along their longitudinal axes with their jet circular or rectangular flat nozzles (PPS), carried out beyond the rear edge of the UAN, made with thrust vector control (UHT), providing the creation of vertical / inclined or horizontal thrust when you completion of the GDP / KVP or translational flight, respectively, and more than two free power turbines (SST), mounted onboard each PCF in side nacelles with their air intakes feeding the VTV and SST, having jet flat nozzles (RPN), transmitting the takeoff power of the SU to their respective ONVs in the doubled OVNS-X1 and their VTVs in the propulsive-reactive system (PRS), the last of which in the doubled PRS-R1 create synchronous reactive cold thrust, but are also equipped with the possibility of converting the flight configuration of deck-mounted MBSV / MPSV after formation their two UAN of a composite wing and performing a vertical or short takeoff at normal or maximum takeoff weight, respectively, from a twin-rotor helicopter or rotorcraft with doubled and OVNS-X1, and PRS-R1 into a jet winged gyroplane with autorotating ONV or an aircraft with their counterweights and blades fixed, placed in the plan along the longitudinal axes of the PCF, respectively, both forward and backward along the field that, and stopped at a feathered position or a zero angle of installation of their blades, which are fixed, respectively, vertically or horizontally parallel to the plane of symmetry of the MBSV / MPSV with their straight CAS, forming, for example, a composite CAS with an oppositely directed sweep χ = ± 45 °, having a common the range determined from the ratio: L _OP = R _OHB × a × cos χ = 45 °, m (where: R _OHB is the radius of the ONV, a is the amount of overlap of the ONV, χ is the sweep of the UAN) and its large elongation λ = 8.0 but also vice versa. All this will make it possible to simplify their controllability and ensure its stability in a shock KARA with connected MPSV / MPSV, which have a KAS with two PKF. In the event of a failure of one of the SST in the GDP modes in their control system, its CGTD are performed with automatic equalization and equal redistribution of the remaining power of the SST between the ONV, which increases safety. A composite UAN with a multidirectional χ = ± 45 ° sweep will provide a speed of 750/950 ... 1050 km / h at the flight modes of the gyroplane / aircraft, and at a supersonic speed M = 1.12 ... M = 1.3 will reduce the wave drag by 2.8 times in comparison with the swept wing χ = + 45 ° (see patent US 3737121 A, NASA).

The proposed invention of a shock-strategic KARA with deck-mounted MBSV / MPSV, having in the preferred embodiment a direct composite KAS with multidirectional sweep χ = ± 45 °, the right / left consoles of which are docked with the upper fairing of a hypersonic anti-ship missile system of the Kh-47M2 “Dagger” type, two PKF with their CGTD, having a PPS with an UHT and leading two NVGs and / or two VTVs, is illustrated in general front / top and front views, respectively, in FIG. 1/2 and fig. 3:

fig. 1/2 in the configuration of an aircraft / helicopter with a CGTD, leading to create horizontal thrust two VTB / vertical thrust two ONV, respectively, in high-speed flight modes with fixed blades located along the longitudinal axis of the PCF / operating ONV during GDP and hovering with two PCF, the right of them are shown with a side flap conventionally with a dotted line with an air-to-air launcher;

fig. 3 in the configuration of two aircraft, separated in flight from the UR fairing after its launch, for separate return of the MPSV / MPSV and automatic vertical landing on the ANL deck of each of them as an OVNS-X1 helicopter with PPS and UVT, ONV and a Perekos assault rifle changing the balancing according to pitch, heading and roll.

An impact KARA with connected MBSV / MPSV made with a glider made of aluminum alloys and composite carbon fiber and doubled OVNS-X1 and PRS-R1 is shown in Fig. LZ left MPSV with PKF 1 / right MPSV with PKF 2, having left 3 and right 4 consoles KAS 3-4 / left 5 and right 6 consoles KAS 5-6 with their sweep χ = + 45 ° and χ = -45 °, respectively , which are equipped along the entire span of the flaps 7 with outer flapperons 8 and triangular tips 9 in plan with their outer sides located parallel to the axis of symmetry. Consoles 3/5 straight KAS 3-4 / KAS 5-6 have attachment and release mechanisms (not shown in Fig. 1-3), forming a composite KAS 3-4 / 5-6 and detachable consoles connecting them with the upper fairing 10 together them portable UR 11, but also simultaneously separated from it in flight for its launch, followed by a separate return and automatic vertical landing on the ANL deck. Left 1 / right 2 PKF with side air intakes 12 have at their ends one-piece keels (CPK) 13, tilted down at an angle of 43 ° to the horizontal and outward from the plane of symmetry. On the PKF 1/2, profiled pylons 14 with shafts (not shown in Figs. 1-3) of the left 15 / right 16 ONV with their counterweights 17 are mounted, which, when running the GDP, rotate in the opposite direction, respectively, counterclockwise and clockwise (see. Fig. 2). Each PKF 1/2 is equipped with front and rear main struts with wheels of a tricycle landing gear, retractable forward along the flight into their compartments, and contains in the aft gondolas (not shown in Fig. 1-3) their CGTD, each of which contains external and internal contours respectively, with VTV in PRS-R1 and SST in the side nacelles 18, which have jet flat nozzles (RPS) 19 with a hot air flow, but also the front 20 and rear 21 controllable flaps for additional air supply in them in afterburner modes of operation are made with the front the output of the shaft for power take-off from the SST and the possibility of transferring power from it to the cruciform gearbox (not shown in Figs. 1-3), redistributing 40% and 40%, but also 72% and 100% of the takeoff power of the adaptive control system, respectively, when performing GDP and hovering between the angular gearboxes ONV 15-16 in the doubled OVNS-X1, but also during cruising on the VTV in the doubled PRS-R1. Two KGTD with HTV have reactive PPS 22 with UHT and cold air flow.

The control of the connected MPSV / MPSV is provided by the general, differential and cyclic Change of the ONV 15-16 step, the deviation of the CPC 13 and PPS 22 with the UHT. During horizontal flight in the configuration of a jet gyroplane or aircraft, the lift force is created, respectively, by autorotating ONV 15-16 with a composite CAS 3-4 / 5-6 or a composite CAS 3-4 / 5-6 (see Fig. 1), cruise jet thrust - in double PRS-R1 through PPS 22 in KGTD and on afterburner through RPS 19, mounted in side nacelles 18, in the transition mode - composite KAS 3-4 / 5-6 with ONV 15-16. After the creation of the lifting thrust ONV 15-16, made with a rigid attachment of the blades, the modes of the GDP or KVP are provided when the jet PPS 22 creates the required sustainer thrust for forward flight (see Fig. 2). When performing GDP and hovering, the change in pitch, heading and roll balancing is ensured by changing the corresponding cyclic step by means of the ONV 15-16 swashplate and their common step, respectively (see Fig. 2). After vertical take-off and climb, an acceleration flight is performed at speeds of more than 300 ... 350 km / h and the rotation speed of the ONV 15-16 decreases. As the acceleration progresses with an increase in the lifting force of the composite KAS 3-4 / 5-6, the lifting force of the ONV 15-16 decreases. When the speed reaches 400 ... 450 km / h and for the transition to the airplane mode of flight, the ONV 15-16 blades are synchronously stopped and fixed along the longitudinal axes of the PCF (see Fig. 1). BSU MPSV provides both its optional control by pilots from the right two-seater cockpit 23 without glazing its windows, and target designation - with a radar with AFAR 24 and EOD 25, which are mounted on the right PKF 2.

The composite KAS 3-4 / 5-6 is connected to the upper fairing 10, which is attached with the possibility of its automatic separation and discharge from the upper surface, for example, a hypersonic anti-ship missile system 11 (see Fig. 3) of the Kh-47M2 "Dagger" type after its launch ... Each side air intake 12 of its KGTD is made without a plate cutter of the boundary layer and has a conical body 26, which compresses the flow and forms its conical flow, but also shields the HTV in the KGTD. Each PPS 22 with UHT is made with upper 27 and lower 28 walls having at their ends rectangular in plan nozzle hatches with transverse upper 29 and lower 30 shutters rotatable on their axes 31 and 32 in the vertical plane, having separate drives that ensure their deflection to the longitudinal axis of the nozzle and between its side walls 33-34, respectively, down and up synchronously with two at angles of ± 22.5 ° or one of them at angles ± 22.5 ° in phase or differentially with the other closed (see Fig. 2, view A , when reversed). During horizontal flight of the connected MPSV / MPSV, a change in their balancing in pitch and heading or roll is provided by the deviation, respectively, of the synchronous and asynchronous CPC 13 or differential external flapperons 8 or the upper 29 and lower 30 flaps of their PPS 22 (see Fig. 2).

Thus, the connected MBSV / MPSV, which have KGTD, leading to the creation of vertical thrust ONV and VTV with UVT their PPS or horizontal thrust VTV with operating ONV or their fixed blades, represent a turboprop fan tiltrotor with cold air flows from ONV in doubled OVNS-X1 and a jet cold jet of compressed air from the PPS in doubled PRS-R1 at GDP and during cruise flight. Their composite UAN with a sweep χ = ± 45 ° increases the aerodynamic and structural advantages, especially at supersonic speeds of M = 1.2. The synchronization system of the SST cascade in their CGTD is equipped with a series-connected unit for adjusting the pressure in the compressor of their SST, a unit for generating a set value for the frequency of rotation and angular position of their SST blades and executive bodies that provide a given fuel consumption that forms the required power and correct the angular misalignment of the blades in cascade SST, excluding mechanical synchronization of dual OVNSOP. Shock-strategic CAR with deck (see table. 1) MBSV-3.95 / MPSV-4.15, carrying in the PKF on - \ 6/2 \ 2 pcs. UR type P-37M \ P-77 and under the composite KAS 2/1 SKR type Kh-555 / Kh-102, allowing, when using the KAS and keels folding at the parking lot, to double their separate capacity on the ANL, but also of the fourth level the so-called manned and unmanned teaming (MUM-T) to receive to pilots of the IHPV not only real sensor images from the slave MBSV, but also to manage weapon loads, their navigation and global positioning with the creation of a safe air zone between the air defense of the target and the nuclear ANL, mastered on the platform of the two-landing scheme icebreaker project 22220.

The connected MBSV / MPSV, carrying in their PKF 2 \ 2 pieces of GZHRUUR type X-38M \ P-77 and under the composite UAN an outboard fuel tank, using its fuel, will allow several of their pairs to fly to the surface target, then, separating and attacking swarm it, improve the success of the anti-ship operation. Project 23900 helicopter carrier with MBSV-3.95 and MPSV-4.15, carrying the Kh-47M2 "Dagger" anti-ship missile, will make it possible to create a heavy anti-ship KARA. Possible development on the basis of four TVaD mods. TV7-117V heavy MBSV-6.0 and MPSV-5.6, carrying hypersonic anti-ship missiles Kh-32 or 95M6 Kontakt anti-satellite missiles based on the ships of the measuring complex, which will ensure their controlled launch at supersonic speed and an altitude of 15 km and will allow using VVP / KVP technologies, to increase their flight range to 1600/3207 or 1900/3507 km, but also to create a global anti-satellite system in the Indian, Pacific and Atlantic oceans.

Claims (3)

1. Arctic missile and aviation complex (KARA), containing an aircraft-carrying icebreaker (ANL) with jet unmanned aerial vehicles (UAVs) having a wing, a fuselage with a launcher (PU) of a guided missile (UR), a power plant engine (SU) and an onboard control system (BSU), characterized in that it has a group of vertical take-off and landing vehicles, including more than two modular unmanned helicopter aircraft (MBSV) with more than a pair of modular manned helicopter aircraft (MPHC), used in pairs as one type together , and in their combination, but also from more than one helipad of the aforementioned ANL, moreover, in a combination of two deck-mounted MBSV / MPSV, containing asymmetric swept wings (CAS), having both on the right / left tips, respectively, left MPSV / right MPSV their mechanisms fasteners and disengages, forming a composite wing and detachably connecting them consoles with at least one underwing pylon or upper fairing joint they have a portable detachable payload (STSN) - the mentioned UR and after its launch simultaneously detachable, for example, from the UR fairing in flight or after landing, respectively, with their subsequent separate or joint return and their automatic vertical landing on the deck of the mentioned ANL, and leading edge a different sweep, forming when connecting the corresponding consoles of the KAS, for example, with the upper fairing of the mentioned UR so that from the center of mass of the last the end chords of their outer two consoles are moved forward or backward or back and forth along the flight, forming from the longitudinal axis of the said UR, respectively a composite wing of reverse or straight or asymmetric sweep, respectively, with an angle χ = -45 ° or χ = + 45 ° or χ = ± 45 °, but also two single-rotor bearing schemes (OVNS) used for vertical or short takeoff / landing (GDP and KVP), including single-blade rotors (OHB) with profiled counterweights, rigid attachment of their blades, mounted bathtubs on the shafts of the profiled pylons of each underwing fuselage (PCF), the left / right of which are made with automatic skewers, the ability to change their total and cyclic pitch and automatically set their blades to the position of their autorotation, but also their free rotation with an overlap equal to a = 2.6 ... 2.7 in the transverse group of the ONV when the blades of one ONV pass in front of the blade of the other so that their advancing blades in the run-off and hover modes pass over the right / left side of the left / right PCF, respectively, from its aft to the bow and create a harmonious a combination of transverse and longitudinal control with an equal distance in terms of their axes of rotation from the center of mass and longitudinal axes of the mentioned UR and their PCF, but also at least two combined gas turbine engines (KGTD), made in the form of two-circuit jet engines, containing as external three-stage fans (VTV) in the annular fairings (KO) of the PKF aft nacelles, mounted along the longitudinal their axes with their reactive circular or rectangular flat nozzles (PPS), carried out beyond the trailing edge of the UAN, made with thrust vector control (UHT), providing the creation of vertical / inclined or horizontal thrust when performing GDP / STOL or translational flight, respectively, and more than two free power turbines (SST), mounted on the side of each PKF in side nacelles with their air intakes feeding VTV and SST, having jet flat nozzles (RPN), transmitting the takeoff power of the control system to their respective ONV in the doubled OVNS-X1 and their VTV in a propulsive-reactive system (PRS), the latter of which in a double PRS-R1 create synchronous reactive cold thrust, but are also equipped with the possibility of converting the flight configuration of the connected MPSV / MPSV after their formation by two UAN of a composite wing and performing a vertical or short takeoff when normal or maximum takeoff weight, respectively, from a twin-rotor helicopter or rotorcraft with doubled and OVNS-X1, and PRS-R1 into a jet winged gyroplane with autorotating ONV or an aircraft with their counterweights and blades fixed, placed in the plan along the longitudinal axes of the PKF, respectively, both forward and backward along the flight, and stopped at a feathered position or zero angle the installation of their blades, which are fixed, respectively, vertically or horizontally parallel to the plane of symmetry of the MBSV / MPSV with their straight UAN, forming, for example, a composite UAN with an opposite sweep χ = ± 45 °, having a total span determined from the relation: L _OP = R _OHB × a × cos χ = 45 °, m (where: R _OHB is the radius of the ONV, a is the overlap value of the ONV, χ is the sweep of the UAN) and its large elongation λ = 8.0, but vice versa. 2. KARA according to claim 1, characterized in that when performing the GDP and hovering, the vertical application forces from the said VTB, for example, from the UHT of their PPS and the mentioned ONV, equidistant in plan from the axis of symmetry of the connected MPSV / MPSV, are placed on transverse lines, taken out in plan from their center of mass, respectively, back and forth along the flight at a distance inversely proportional to their lifting thrust, and in each mentioned side gondola of each of their PCFs, for example, one SST has a front shaft outlet for taking its power, which, by means of an angular in plan of the gearbox transmits torque to a cross-shaped reducer in the plan, which has front and rear output shafts along the longitudinal axis of the PCF, which transmit the distributed power, for example, the first of them and through the clutch to the angular gearbox ONV in the doubled OVNS-HT, and the second of them rotationally connected to the VTV in the doubled PRS-R1, and each mentioned PPS of their aft nacelles PKF for thrust vector control (UHT) is equipped with an upper 27 and bottom 28 walls comprising at their ends rectangular-nozzle hatches with transverse upper 29 and lower 30 pivot on their axes 31 and 32 in the vertical flaps having from axes of rotation of the length of their chamfers defined by the relation: L _PTS = h _sop / 0.707, m (where: h _sop is the height of the nozzle, cos 45 ° = 0.707) and separate drives, providing between its side walls 33-34 their deviation to the longitudinal axis of the nozzle downward and upward synchronously by two at angles ± 22, 5 °, joining their chamfers, or one of them at angles of ± 22.5 ° with the other closed in phase or differential, respectively, for reverse thrust or for longitudinal or lateral control, or only the lower flap 30 at an angle of + 45 ° until its chamfer touches the surface the upper closed flap 29 to change the direction of the horizontal thrust to the vertical, and each lower hatch nozzle 35 in the lower wall 28 of each mentioned PPS to parry the torque and change the balancing along the course with their separate field those in the modes of GDP and hovering are equipped from below with longitudinal controllable flaps-rudders 36, which, after their opening of the hatch-nozzle 35, deviate from the longitudinal axis of the PKF at angles to the left + 40 ° / right + 40 °, while the subtle MBSV / MPSV in the modes of their GDP and hovering at a specific load on the power of their _{adaptive control system, which is ρ N} = 1.26 kg / hp, each mentioned CST is made with elements of digital program control, combining an adaptive control system for the formation of a safe flight (UFBP) with a specific vertical thrust-to-weight ratio of double OBHC-X1, which, taking into account the losses from the blowing of the PCF and KAS, ρ _VT = 1.85, includes the SST operating modes both takeoff and emergency mode (BP and CR) with 80% and 20% of the required power to drive the mentioned ONV and VTV, respectively, both from two operating SSTs and from one of the operating SSTs with automatic equalization and equal redistribution of the remaining power between the ONVs in case of failure of the corresponding SST in KGTD, for example, yes in the latter case, after the automatic switching on of the PD of the work of the SST remaining in operation, which, with a specific vertical thrust-to-weight ratio in the doubled OVNS-X1, equal to ρ _VT = 1.07, will provide an emergency vertical landing mode for 2.5 minutes, and in each of their SST the UVBP system contains: one or more sensors that are configured to detect data related to the air flow rate (G _B , kg / s) through the SST compressor, the gas temperature ( _TG , K) in front of the SST turbine, the total compression ratio (K) of the compressor, as well as one or more sensors, which are configured to detect the relative position of the PCF and rotation discs of the NVD for their relative position relative to the ground level or the surface of the landing site, as well as various obstacles in the path of its tracking controlled descent; a flight control computer located in their BSU and operational with one or more sensors; the flight control computer is configured to: determine the relative position between their FSC with a wheeled chassis and the ground level or surface of the landing pad; compare the relative position of their PCF and their carrier system with their chosen relative position; determine the speed of automatic descent required to move them to the selected relative position; convert tracker speed to flight control inputs; and also to provide an automatic safe descent to the selected relative position through the flight control inputs, and their flight control computer is made both with an additional computer for summing sensor data, and with the ability to convert data from each sensor into a relative position, which is determined based on the global position, and in the modes of their GDP and hovering with their composite CAS, a change in the balancing in pitch, heading and roll, which is created by changing the corresponding cyclic step by means of the swashplate of each CAC and differential change in thrust, respectively, of the left and right CAS, which rotate in the opposite direction in plan, for example, counterclockwise and clockwise, and each MBSV / MPSV is made, respectively, without / with a cockpit, equipped inside with video cameras with autonomous manipulators connected to the MPSV controls and the possibility of its optional control by pilots from a two-seat cockpit, having seats ejected into the upper hemisphere, mounted side-by-side, which are triggered in the modes of running the runway and hovering automatically after firing off the ONV blades with squibs in an emergency, and their BSU is equipped with a fly-by-wire control system that responds to at least one of the autonomous flight control systems, remote control of the operator, control from the cockpit and / or their combination, and each of their PCF is equipped with front and rear main struts with wheels of a tricycle landing gear, retractable forward along the flight into their respective compartments, has at its end all-rotary keels (CPK), deflected downward, but also outward from the plane of symmetry of the MPSV and MPSV at an angle of 43 ° to the horizontal, and each of their CAS has endings triangular in plan with their outer sides located parallel to their axis of symmetry, is made with end parts folded up and back in the parking lot. flight or top and perpendicular to the axis of symmetry of the MPSV and MPSV, located on the hell of their PKF, with their separate placement in the hangar of the mentioned ANL with the blades of their ONV installed in a feathered position and, along with their folded keels up or down, reduce their parking area by 6.4 ... 6.6 times from the take-off area, and the strategic MPSV and MBSV , carrying under their composite KAS one air-to-surface air-to-surface missile (AKR) of the Kh-101 type, forming after their launch autonomous swarms of AKR with towed false targets, using their low-altitude flight profile and their self-defense system - an active electronic jamming station, increase their range using the GDP / KVVP technology, respectively, up to 8125/10345 km, but also a destructive opportunity, create a safe air zone between the ANL and the air defense of the target, and their PKF for internal armament have single and double doors, respectively, side and lower compartments, PU which with fixed on them the air-to-air missile of the R-77 type and the anti-ship missile (ASM) of the Kh-38M type are mounted on the inner sides of the doors and inside the compartment kov, respectively, and under the pylon of their composite UAN, carrying the aforementioned STsN - a fuel tank, using its fuel, will allow each pair of them in the air group to fly to a surface target, then, separating and attacking it in a swarm, increase the destructive capability and range of an X-type anti-ship missile -38M from 40 km to 1830 km, while heavily armed MBSV / MPSV, carrying hypersonic anti-ship missiles Kh-47M2 "Dagger" or anti-ship missiles of the Kh-32 type under the pylon of their composite UAN, provide its controlled launch at supersonic speed and an altitude of 15 km and will allow reach a range of its flight up to 2160/3570 km or 1860/3270 km, using the VVP / KVVP technologies, respectively, and the airframe of the MPSV and MBSV is made of aluminum-lithium alloys and composite materials using an inconspicuous technology with a radio-absorbing coating, and each of their PCFs has from their pyramidal nose parts, beveled along their entire length, the lateral sides, forming with the mentioned side air intakes when viewed from the front, a five- or hexagonal cross-section, reducing e effective scattering area, but also radar and visual visibility, and in their PCF the mentioned side air intakes, which do not have a lamellar cutter of the boundary layer and internal movable regulating elements, are also made to remove the boundary layer and increase the total pressure recovery factor as without a slot for draining boundary layer, and shielding the compressor blades of the SST and VTV of their mentioned KGTD in an adaptive control system that changes the air volume, which, providing greater thrust and fuel efficiency, passes through the SST and VTV, but each for the latter two includes corresponding ramps, each of which compresses the flow and forms a conical flow, while the electro-optical sensor (EOD), designed for detection and identification of the target, has a receiving part of the EOD, which is closed from above with a sapphire glass, is installed in front of the MPSV cabin on top of the bow of the right PKF and, with the latter's radar, provides large , safe p At distances, target designation and control of weapons loads, both their own and MBSV with aiming at the target of AKR and anti-ship missiles of the air-to-surface and air-to-air missile systems, but also its joint use as part of an aviation group as a head MPSV, for example, with one previous or more than one of the subsequent slave MBSV, and the mentioned ANL having an asymmetric hull, is made with its two-draft scheme, which allows the use of a draft in the range from 8.5 to 10.5 m to increase icebreaking capacity and perform special tasks in shallow water and river estuaries, equipped with a propulsion system , consisting of a pair of main and a pair of additional, respectively, aft and bow propeller-driven propellers (VRK), each of which, working independently and increasing the efficiency of maneuvering in any direction and even rotation in place, can both turn in a horizontal plane by 360 °, so and is equipped with a built-in high-torque DC motor with a suitable propeller with a fixed pitch propeller (FPP) mounted directly on the shaft inside the full-revolving propeller gondola, and the installation of bow propellers on the ANL provides high maneuverability in ice conditions, but also in clear water, which is very important in areas with limited water space, but also, achieving the effect erosion of ice by the work of these fixed pitch propellers both reduces the ice strength and increases the ability to pass ice hummocks, and has a harmful effect on the operation of the aft propellers, while in order to increase the efficiency of the propulsion unit of the aforementioned ANL, a pair of forward propellers, which, providing the effect of divergence of their thrust vectors from the longitudinal axis of the ANL , deployed at an angle to each other on the effective support of the ANL in the mode of creating a thrust force, and the propulsion unit with four propellers and four control joysticks are combined in one bridge with the installation of two navigation bridges - the main and backup for controlling the nuclear ANL during the course and visual control improving from the second the bridge has a panoramic view when it moves obliquely. 3. CARA according to any one of paragraphs. 1, 2, characterized in that for the trans- or supersonic flight mode of the connected MPSV / MPSV, reaching the marching thrust-to-weight ratio of the first level - 0.22 or the second - 0.26, or the third level - 0.5 or the fourth - 0.61, is used respectively 22% or 27% or 72% or 100% of the power of their SU at an altitude of 15 km with the above-mentioned composite UAN, a speed of Mach 0.894 (M) or M = 0.988 or a supersonic speed of M = 1.12 or M-1.3, respectively , and each of their aforementioned SST is equipped with its mentioned RPM with an afterburner used in aircraft takeoff and supersonic flight modes with open controlled flaps of the said lateral nacelle in front of its compressor and rear in front of the afterburner for additional air supply to it, which will allow for normal / their maximum take-off weight at a flight altitude of 15 km to increase the thrust-to-weight ratio of their mentioned control system from 0.61 / 0.52 to 0.78 / 0.68 and reach a supersonic flight speed M = 1.5 / M = 1.4, respectively, while from the presence of glazing of the front windows or all windows in the cockpit of the MPSV pilots will increase the rigidity of the PCF and reduce the thickness of the skin and, as a result, reduce its weight, moreover, the MPSV glider with a sealed cockpit, which has an automatically reset opaque armor-lamp for ejection of pilots and a digital image display , representing a part of the external scene, including the environment stretching forward and sufficient for piloting, is equipped with a variety of video cameras, IR sensors and video sensors that provide touch shooting, recording all events in the front and rear hemispheres at 360 °, while controlling the MPSV in the mode in real time, the image is digitally corrected and displayed by the video distribution module on the cockpit displays, making it either transparent or visible on the helmet displays of the pilots, which, forming common viewing windows, are connected to the first and second processors of the extended vision system, configured for I was worn by the first and the co-pilot, respectively, with the first and second common viewports and highlighted displayed lines of sight visible on the first and second helmet displays of the pilots, respectively.

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