RU96123485A - MULTI-PURPOSE HIGH-MANEUVERED SUPERSONIC AIRPLANE, ITS PLANER UNITS, EQUIPMENT AND SYSTEMS - Google Patents

Claims (42)

1. A multi-purpose highly maneuverable supersonic aircraft with an integrated aerodynamic configuration, with an empty aircraft weight of approximately 18,000 - 19,000 kg, containing a single load-bearing housing, including: a wing deformed in the center surface of the consoles with developed root influx in front of the consoles, in one of which there is a rapid-firing gun, and deflectable socks and flaperons, smoothly transitioning in scope to the fuselage, which contains in the head part: nose radar fairing, fairing optical-radar station AI, a retractable rod for refueling in flight, two tandem cockpits with a common light and controls for the aircraft, its systems and equipment, in the middle part: a garrot with a brake flap and air intakes of the power plant located, respectively, above and below the center section, in the tail: the central beam connecting the nacelles of two turbojet engines, creating a possible total thrust of approximately 25,000 kgf, and the tail beams on the sides; bearing dorsal keels with rudders; all-round stabilizer halves, between which engine nozzles are located; and ventral keels; as well as: tricycle retractable landing gear with brakes; tail fuselage cock under the brake parachute; holders, launching devices and blocks for suspension under the load-bearing housing of cargoes, missiles, shells and bombs, on-board equipment, including: on-board radar station with control computer, interrogator and transponder of state recognition systems, information display equipment, on-board computer system, flight and navigation equipment , a weapon control system, an optical-location station, a helmet-mounted target designation system, a set of electronic countermeasures, radio communication equipment, medium registration and control systems; and aircraft systems: aircraft control system, hydraulic system, pneumatic system, power supply system, lighting equipment, air conditioning system, liquid cooling system, life support system, emergency exit system, characterized in that the vertical displacement of the rear cabin relative to the front one is made of conditions for ensuring equal viewing angles in the cabins, the power structure of the center section and its connection nodes with air intakes, garrot and the brake flap, the head and tail parts of the fuselage, wing consoles, landing gear and holders are made from the conditions of minimizing weight while ensuring sufficient integral strength; the vertical tail is made in magnitude with the condition of providing directional stability during flight with supercritical angles of attack and from the condition of compensating for the influence of the rear cockpit displacement on the track stability of the aircraft, and in terms of location relative to nozzles, from the condition of minimizing losses; the location of the stabilizer is determined from the conditions for preventing the destruction of the elytra ellipse vortices and providing a dive moment when flying at supercritical angles of attack; the sweep and the radius of rounding of the influx toe, the shape of its lower surface and the distance from the air intake are made from the condition of ensuring the greatest uniformity of the velocity field in the stream at the entrance to the air intake in the range of operational flight speeds at sub- and supercritical angles of attack; the power plant is equipped with a compensator for the non-rigidity of the bearing body in the cable wiring of the control system for each engine and is configured to supply fuel to the engines at any position of the aircraft and the priority fuel generation with a change in centering to a state of static instability; the aircraft control system is equipped with means to ensure flight with supercritical angles of attack, ensure the aerodynamic quality of the wing during maneuvering and adjust the handling characteristics when refueling in flight; the life support system is equipped with life support facilities for a long flight and means providing the pilot with protection from increased overload, low pressure and low temperatures; lighting equipment is equipped with lighting tools that provide the ability to visually control the process of refueling in flight at night; the automatic radio compass is equipped with a means for continuously adjusting the frequency of the pilot; a satellite navigation system is installed with an indication of the current coordinates of the aircraft; suspension and launch of air-to-air missiles with semi-active and active homing heads are provided; periodic shutdown of the power supply of missile equipment is provided to ensure their combat readiness in conditions of a long flight of the aircraft.  2. The aircraft according to claim 1, characterized in that onboard equipment and aircraft systems are integrated and interfaced into a single complex, in which a radar station with a phased antenna array is installed; an optoelectronic sighting and navigation complex with multifunctional control panels and displays has been formed; a block for converting and switching television signals was introduced; registration and control tools include an integrated information system for signaling; fuel refueling system is configured to return fuel in flight; the power supply system in each alternating current system is made with approximately double the power of the drive-generator, and in each direct current system with an increased degree of redundancy of the power supply of first-level consumers and a reduced approximately twice as much total power of simultaneously working consumers; it is possible to install containers with optical and infrared reconnaissance equipment; means are provided for suspension of a universal suspension unit for refueling and its connection with the fuel system of the aircraft; means are provided for suspension, power and launch of guided air-to-air missiles with a thermal homing head, air-to-air with an active radio head and a radio correction line, air-to-surface with a television command guidance system, and air-to-surface from a television homing, anti-radar, anti-ship, air-to-surface homing with a semi-active laser homing head, adjustable bombs with a television homing head, with a semi-active laser homing head; the chassis is made with increased strength, resource and uniformity of heat dissipation to enable takeoff and landing with a weight increased to 20%.  3. The aircraft according to claim 2, characterized in that it is made according to the “triplane” scheme with a controllable swept front horizontal tail mounted on sections of root flows, located behind the rear cockpit, with the possibility of generating on the front edge of each console a tail of a vortex system, which protects when flying at supercritical angles of attack, the flow stalls on the wing consoles, and at the junction of the front horizontal tail unit with the root influx, with the possibility of generating a system of vortices interacting with the median the surface of the wing console and keels of vertical tail, while the aircraft is controlled remotely in the longitudinal, transverse and track channels, and the longitudinal control channel is equipped with a self-adjusting device for adjusting control depending on the mismatch of flight parameters and their predetermined changes, and the aircraft is equipped with a hanging container with a television command guidance system associated with aircraft equipment.  4. The aircraft according to claim 3, characterized in that it is configured to control the thrust vector of each engine and provide super maneuverability to prevent the aircraft from falling into stall and corkscrew modes with a corresponding increase in flight safety, increasing combat efficiency due to a quick turn to the target, sharp braking and maneuverability at speeds less than evolutionary, reducing the geometrical space of maneuver and with the possibility of being ahead of the missile launch and expanding the launch zone, disrupting the attack of the enemy and ATA and from conditions impossible without over-maneuverability, for which each of the engines of the power plant is made with a rotary nozzle and the possibility of creating lateral force when turning the nozzle, and yaw and roll moments, and the hydraulic actuators of the nozzle rotation devices are included in the fuel system of the corresponding engine, the aircraft control system is equipped with a control system for common-mode and differential deviation of the rotary nozzles of the right and left engines, including a computer as part of the remote control system, If you turn on the nozzle turning mode, installed in the front cockpit, and driving devices, the aircraft is equipped with an overhead refueling unit connected to the fuel system for using the aircraft in flight as a refueling device, and the phased antenna array of the radar station is rotary.  5. The fuselage of a multi-purpose highly maneuverable supersonic aircraft, containing the head, middle and tail parts, in which the head part includes a nose radiolucent radome antenna radome, the front and rear crew cabs with a common light, the middle part - air intakes with weapon holder assemblies and internal protective nets, a garrot and a brake flap fastened with a center wing, and the tail part - two power gondolas with tail beams, interconnected by a central beam, and heads The main part of the fuselage is an all-metal half-monocoque formed by frames, spars, stringers and skin, made with a niche for cleaning the front support of the aircraft, with two side and central podkabinny compartments for electronic and aircraft equipment, with a cockpit compartment under the shock-absorbed electronic shelves hatches for access to equipment, and in the rear of the fuselage of the nacelle are equipped with engine mounts, made in half-monocoque With a working casing supported by frames and stringers having front hinge and rear engine mounts, the central beam has two end and three intermediate power walls connecting power frames of spaced nacelles and weapon holder assemblies mounted on its lower surface, and is made with a compartment for equipment, with a rear fuel tank, with a tail coke - a tip for a container of brake parachutes and side fins, the tail beams of the nacelles are made with a power part, stabilizer and keel mounts and equipment compartments in the front part, with access hatches for access to the remote box and other engine components located at the top of each nacelle, and the last two power frames of the nacelles are openable to allow removal engine when replacing it, characterized in that in the rear of the fuselage the front frame is sealed and consists of two whole-stamped frames, in the upper part of which There are butt pads for attaching the frame to the center section, and in the lower part there are units for installing hydraulic lifts, the frame on the hinged section of the engines and the front side members of the keels is made of titanium alloy and consists of closed frames with side beams connected by walls belonging to the fuel compartment tank in the central beam, and the frames are composite, welded from separate stamped sections, on the side beams there are eyes for fastening the front side members of the keels, and in the side parts There are bushes for engine mounting, an I-beam on the mounting section of the rear spars of the keels and the stabilizer drive is made of titanium alloy and consists of closed frames welded from separate stamped sections with side beams connected by a ribbed wall belonging to the fuel tank compartment, and a closing frame the tail of the fuselage in front of its tail tail has a removable lower part and is a closed frame made of titanium alloy with side beams, while the frames consist of welded upper and lower arches, the side beam has an internal attachment point for the axle shaft of the stabilizer linkage, and the lower arch is attached together with the skin to the frame with the possibility of removal when installing and removing the engine, the tail coke is made with a ribbed partition for attaching the brake parachute in the frame in front of the crew cabin the niche for the refueling rod is located along the chord, the size of which slightly differs from the largest chord, the protective grid contains a frame and a monolithic panel with perforation made electroerosive method, and transverse ribs at an angle to the plane of the panel and has one of the supports movable with the possibility of rotation of the panel when the air intake is deformed, and the attachment point of the working position lock of the main landing gear is equipped with a longitudinal compensation device.  6. The fuselage according to claim 5, characterized in that in the head of the fuselage the frame for attaching the radar station is made with increased dimensions of the shelves, walls, ribs to increase rigidity and with the possibility of stabilizing the position of the radar station of increased weight when exposed to overloads, a niche and the front wing chassis supports are designed to accommodate a two-wheel support, the brake flap is made with a root lining in the form of a rectangle with a transverse dimension several times greater than the longitudinal size, and with with an angular protrusion at the connection section with a hydraulic actuator, in the middle part of the fuselage the lock of the released position of the main landing gear, the beam for attaching this lock and the frames to which the beam is attached are made with the possibility of perceiving dynamic load with increasing weight of the aircraft.  7. The fuselage according to claim 6, characterized in that its head is made with the possibility of installing the left and right root bumps-boules carrying rotary consoles of the front horizontal tail, with half shafts for mounting these consoles and their drives.  8. The fuselage according to claim 7, characterized in that the frame in the area of hinged mounting of the engines is configured to absorb loads when the nozzles of the engines are rotated, and the frame in the section of the rear mounting of the engines is made with nodes for mounting each engine in horizontal and vertical directions.  9. The all-metal wing of a multi-purpose highly maneuverable supersonic aircraft containing a center section, detachable consoles that are deformed in the middle surface and are equipped with deflectable socks and flaperons, boules root inflows installed in front of the consoles, and weapon holder assemblies located on the lower surfaces of the center section and consoles, the center section is formed by the upper and lower power panels and the frames and walls connecting them in such a way that the front - the first and located the second fuel tanks behind it, compartments, as well as niches for placing the main landing gear supports between these tanks, which are closed by the corresponding front and rear wings, and have combs on the end ribs for joining the wing consoles; a garrott is installed on the top panel riveted from aluminum alloys and units for installing and controlling the brake flap, and on the lower panel, made of sheets and a set of profiles made of titanium alloys, welded, there are installed units for connecting the air intakes, mounting the main landing gear supports, g of the tail and tail parts of the fuselage, the force structure of the wing includes ribs and walls in such a way that the caisson of each wing console accepts all external loads and transfers them to the center section, characterized in that the first tank is formed by a set of frames supporting the upper and outer upper and lower side panels , the inner walls of the truss type and the side members, the two lower panels of the tank being monolithic, docked along the axis of symmetry on a box-shaped profile adapted for fastening the fairing of the holder suspension assemblies, the upper and The lower panels are fastened to the corresponding panels of the second tank, the lower panels have protrusions for docking with the head of the fuselage, the two parts of the side lower panel are connected to the parts of the lower panel on the tape, corner profiles are attached to the lower panels for a contour joint with air intakes on the drain wedge, but the power the design of the second tank is formed by the upper and lower panels having sets of stringers, walls, ribs, and a chassis beam, and the tank walls have a channel section and stiffeners, on the front wall of the second about the tank there are mounted attachment points for the drives of the flaps of the niches of the main landing gear of the aircraft and along the axis of symmetry there is an arm with a rear suspension unit of the holder, nodes for mounting the air channels of the engines and attachment points for the struts of the truss brackets of the main supports are attached to the intermediate wall, and each of the extreme side the ribs of the second tank in the plane of the intermediate wall has a support node in the form of a tide with a hole with a pressed steel sleeve under the pin of the detachable part of the wing when it is docked with the center section, in the chassis The same beam has a recess for the bearing race of the main beam of the aircraft landing gear, the upper panels are made of monolithic plates and have a comb comb with pockets and bolt holes when the center section is joined with detachable wing parts, stringers are welded to the sheathing through the melt in the lower panels of titanium alloy and in the butt profile holes are made for the mounting pins of the detachable part, in the detachable wing consoles the upper and lower power panels are fastened to the front side member and three walls of the longitudinal set as well as ribs, the ribs are perpendicular to the intermediate wall, the spar and walls are supported by ribs and have a variable thickness along the length, the upper panel has stringer ribs included in the power longitudinal set, and transverse along the ribs, acting as their belts, the lower panel consists of a milled docking belt and extruded panel fastened with riveted sheet metal panels, while the pressurized compartment in the root of the console is the third fuel tank, cargo suspension units under the wing consoles are located in areas ervyur and each formed as a sleeve with flanges for mounting to the top and bottom panels, wherein for the installation pins cargo holders in these nodes are pressed sleeves.  10. The all-metal wing according to claim 9, characterized in that the attachment point of the front bracket holder of the holder under the center wing is provided with left and right fittings mounted on the lower panel of the rear compartment in the front fuel tank of the center wing, with the outer fairing of the strut-lift of the front landing gear and front the bracket of the suspension unit is made with a horizontal section in longitudinal section and a tip located under the center section in the section in front of the intermediate inner wall of the second tank.  11. The all-metal wing according to claim 10, characterized in that the root boules are made with the possibility of installing rotary consoles of the front horizontal tail with the half-axles of the hinges of these consoles and their drives, the frame in the section of the front wall of the front fuel tank in the center section is made in the area between each from the side walls of this tank and the side sheathing of the center section socks with the nodes of the front horizontal tail support and the holes for the hydraulic actuator rods, and the center section sock beams are made with niches and nodes fastenings for installation of these hydraulic drives, for which mounting hatches are made, while the wall of the front fuel tank in the center section in the section of the corresponding niche is made with a depression for the specified hydraulic drive, and in the tail section of each detachable wing console in the flaperon hitch assembly the first bracket is from the center section made of titanium alloy, the diaphragm located along the theoretical side, made with cutouts for communication and with eyes for attaching the rocking chair from the electrodistributor to supplement feedback traction to the flaperon, the rear wall in the section of the second bracket is removable with cutouts for wiring hydraulic tubes and bundles, on the wall of the first from the center section of the flangeron side member next to the hitch assembly to the center section, a bracket is mounted for fastening the feedback rod from the electrodistributor, and the thrust from the redundant flaperon position sensor installed in the tail of the flaperon is attached to the third flaperon drive assembly. 12. The plumage of a multi-purpose highly maneuverable supersonic aircraft, comprising vertical and horizontal plumage, of which the vertical plumage includes two keels with rudders located above the tail beams and side fairings of the fuselage, and two smaller bale keels located under the upper keels, with sweep all keels 35 ^o, a horizontal stabilizer comprises two separate halves of the stabilizer, each of which has an axis fixed at two points lead- of the fuselage frame, with the possibility of in-phase and differential rotation with the other half of the stabilizer, each of the upper keels is equipped with rudder drives, radome antennas and a cooling air intake and has a skeleton, skin panels, forklift and rudder hitch assemblies, each balk keel has a trapezoidal side the profile consists of a frame, sheathing and filler, each of the halves of the stabilizer has a central, tail and root parts, a windshield and a tip made with the corresponding and a frame and sheathing, characterized in that the bracket for connecting the half of the stabilizer with the drive in the dorsal fuselage is located behind the root fairing of this keel, the frame of the central part of the half of the stabilizer has a front wall, support, ribs, walls and a spar in the form of a stamped I-beam with variable shelves sections and a wall with reinforcing ribs, used to attach ribs, of which the side consists of a bow, a middle, combined with a drive bracket, and a tail, upper and lower panels the stabilizer is a glued-on structure made of sheathing and I-stringers, each of the dorsal fins has two spars ending in brackets for fastening to the fuselage of the I-section for fastening with sheaths, and between the elements of the power set, the thickness of the sheathing is reduced by dimensional etching, in one of the fuselage short-wave communication, which is a loop vibrator with a set of ribs, and the nasal ribs in the area of the vibrator and the skin panel are made They are made of fiberglass, each of the balkon keels is made with a honeycomb core, the honeycomb blocks of which are connected to the frame by means of foaming glue, ribs and a vertical spar of variable cross-section with a cylindrical root part for installation in the fuselage mounting bracket.  13. The plumage according to p. 12, characterized in that in each of the dorsal fins the rudder is made with a tip extending beyond the edges of the upper and lower fairings of the keel, increasing from top to bottom, with an increase in the area of the rudder by 10 - 15%.  14. The plumage according to p. 13, characterized in that the horizontal plumage is equipped with two in-phase all-rotary consoles of the front horizontal plumage mounted on the root airway-boules of the wing and having nodes of the hinge and connection with the drive, electro-hydraulic distributors of the steering wheel are installed in the dorsal keels, position sensors the steering wheel and power multi-channel stabilizer drive of the aircraft’s remote control system; two brackets for reverse thrust are installed on the side member from the rudder side communication with electrohydrodistributor and rudder position sensor.  15. The plumage according to p. 14, characterized in that each of the halves of the stabilizer in the area behind the suspension axis in the fuselage and each of the dorsal fins on the underside of the fairing under the rudder are made with undercuts.  16. The propulsion system of a multi-purpose highly maneuverable supersonic aircraft, containing two turbojet small bypass engines, each of which is pivotally mounted to the nacelle in the front part, has an afterburner, adjustable tapering-expanding nozzle, coupled to a nacelle equipped with fire extinguishing means, equipped with an adjustable control system an air intake and a remote unit box for actuating a pump of one of the hydraulic systems, driving a constant speed alternator of the current and the motor centrifugal pump, and the fuel system, including a system for transferring fuel to the center section of the center section of the tanks partially filled with polystyrene, located in the wing and fuselage, a fuel supply system for engines, a fuel filling and refueling system, each of which is equipped with a protective retractable mesh, recharge flaps and an adjustable braking wedge, in which the front and rear movable panels are interconnected so that the rear panel forms the upper walls for the air diffuser, with the possibility of changing the area of the gap between the front and rear movable panels for suctioning the boundary layer from the braking surface simultaneously with its suction through perforations on the top panel and through the blinds and openings of the side slots and in the top panel, characterized in that in the system control of each engine between the levers in the cockpit and the pump-regulator in the cable wiring includes a gear reducer and a four-link hinged compensator for deformation of the fuselage in places the installation of the support rollers of the wiring, in each air intake the braking wedge is optimized for maximum flight speed with angles determined from the condition of minimizing the length of the nacelle due to the continuous flow of the stream with minimal losses, and the air intake control system is configured to move the front and rear movable panels from the condition of matching the air intake with reduced engine air flow at angles of attack and slip and flight speed during regulation, the fuel system and it is made from the condition of providing fuel to the engines at all positions and flight speeds of the aircraft, due to the boost of the fuel accumulator and the installation of two booster pumps in the supply compartment at different distances from the upper and lower panels of the center section, and the increase in the duration of use of the aircraft in high maneuverability modes due to the priority generation of fuel from the front tank in the center section.  17. The power plant according to claim 16, characterized in that the fuel system is configured to work together with a unified refueling suspension unit and with the possibility of pumping fuel from the fuel tanks of the aircraft, except for the emergency residue, into a refuelable aircraft with a hydraulic pump for the charge pump in the consumable compartment to the outlet of the charge pump in an outboard unit having an aerodynamic wind drive.  18. The power plant according to claim 17, characterized in that the fuel tank in the central fuselage beam is divided into front fifth and rear fourth fuel tanks associated with fuel transfer, refueling and refueling systems.  19. The power plant according to claim 18, characterized in that each of the engines is made with a rotary nozzle and the possibility of creating lateral force when turning the nozzle, and yaw and roll moments, and the hydraulic actuators of the nozzle rotation devices are included in the fuel system of the corresponding engine, the spherical surface is rotary part of the nozzle from the side of the nacelle interacts with movable sealing flaps, and from the side of the adjustable part of the nozzle - with elastic sealing elements fixed on it, and in the area before the turning hour your engine is connected to the nacelle with mutually perpendicular adjustable travel stops.  20. A set of takeoff and landing devices of a multi-purpose highly maneuverable supersonic aircraft, containing a three-leg retractable landing gear and a brake landing parachute system, in which brake wheels are mounted on the main bearings and a non-brake wheel is mounted on the steered front one, and the wheel suspension on the main bearings is telescopic and the front support - half-lever, the shock absorption of the chassis - pneumohydraulic, on the front support there are two landing lights and one taxiing, suspension strut and the floor lock The main support legs are attached to the lower panel of the center section, the lock of the extended position of the support is attached to the power beams in the engine compartment, the lift brackets are attached to the power elements of the tail beam, each niche is closed by two flaps controlled by cylinders, the main strut bar is designed to hold the amortstand in the released position, the front support is suspended in the articulated bearings of three nodes, the protective shield of the slotted design is mounted on the axis of the wheel to protect the air intakes from concrete chips when the aircraft moves but on the earth; the brake landing parachute contains a cruciform brake parachute, a container with a sash and a sash opening mechanism, a lock, an electrical control system, the container being the tip of the fuselage tail, characterized in that the complex has a lock to hold the main landing gear in the released position, which captures when the release of the rod pivotally mounted on the support, so that the rod using the kinematic drive is installed in the process of cleaning the support in a position that provides mini the small dimensions occupied by the support in the recess, and the power lock holding the rack in the released position is made with the possibility of reliable locking of the support in the absence of hydraulic pressure in the system and providing angular movement of the rod to compensate for deformation of the fuselage and support, the emergency release system of the chassis with compressed nitrogen provides for the opening of the wings niches, the lock of the released position of the main support consists of a housing connected to a hook, kinematic links, a connecting earring and a drive in such a way that in the closed position, the hook is locked with a kinematic lock and fixed by the cylinder rod, which has a power reserve for release, and oil or nitrogen pressure, and in the open position it is fixed by the rod of another cylinder and held by a spring and two ball locks, while the cylinder rod has a power reserve for cleaning, moreover, in the closed position of the hook, his pharynx and the counterpart of the body forms a sphere in which the ball of the support rod is placed when it is released, located in the lower part of the container of the brake landing parachute system The limit switch mechanism, consisting of a spring booster, a rocking chair and mounting means with the ability to automatically reset the brake parachute when it is released spontaneously, is equipped with an exhaust parachute with a spring mechanism, two brake parachutes with cruciform domes and a connecting link attached to the fork.  21. The complex of take-off and landing devices of claim 20, characterized in that the landing gear is made with increased durability and the resource of the landing gear and is equipped with wheels that enable take-off and landing of an aircraft with a weight increased to 20%, while the front support is made with two wheels and increased depreciation stiffness, and the turning mechanism of the wheels is equipped with a means for switching on the main chassis supports by a crimp signal, each of the main chassis supports is made with a reinforced bar and an released position lock with an increased gesture bones, and in the cooling system of the wheels of the main rack It provides for automatic switching on of the fan motor during compression of the main supports, manual switching on and off of these electric motors, as well as turning off the cooling system during aircraft operation at low ambient temperatures.  22. The takeoff and landing device complex according to claim 21, characterized in that high-energy monocarbon brake discs are installed in the brakes of the wheels of the main landing gear with the ability to concentrate the braking energy of a heavily loaded aircraft over a short distance and evenly remove heat.  23. On-board equipment of a multi-purpose highly maneuverable supersonic aircraft, including an on-board radar station with a control computer, an interrogator and transponder of state identification systems, information display equipment, an on-board computer system, flight and navigation equipment, a weapon control system, an optical-location station, a helmet-mounted target designation system, a set of electronic countermeasures, a complex of radio communications, a means of registration and control; characterized in that in it the automatic radio compass is equipped with a means for continuously adjusting the frequency of the pilot; a satellite navigation system is installed with an indication of the current coordinates of the aircraft; periodic shutdown of the power supply of missile equipment is provided to ensure their combat readiness in conditions of a long flight of the aircraft.  24. On-board equipment according to claim 23, characterized in that it is integrated and interfaced into a single complex with aircraft systems and includes a radar station with a phased antenna array; optoelectronic sighting and navigation system with multifunctional control panels and displays; a block for converting and switching television signals, an integrated information system for signaling; the equipment is capable of interfacing with hanging optical containers with optical infrared reconnaissance equipment, the airborne radar station, together with the central processor for military use and the state identification system interrogator, is included in the radar control system made with the possibility of providing: simultaneous firing of guided missiles at long-range aerial combat air-to-air; close-range firing of an air target with guided missiles of a cannon mount; shelling of a sea target with guided air-to-ship missiles; firing at ground targets with guided air-to-ground missiles; the use of unguided weapons in air-to-surface modes; in the attack mode of one ground target at the same time detecting air targets or firing in a long-range aerial battle of one air target; integrated processing and use of information data from airborne equipment, other aircraft and control centers to increase the effectiveness of combat use; flight control in air-to-air modes; air-sea "and" air-ground "with a leading radar channel; control of combat operations of groups of aircraft; information support of aircraft systems; assessment of the state of equipment and weapons at all stages of ground preparation and in flight; recognition of air targets in conjunction with the aircraft transponder, optical electronic sighting and navigation system is made with the possibility of functional integration of airborne electronic equipment for the use of weapons and aircraft control, including the organization of information o-control field of the cockpit for crew interaction with equipment; control of equipment interaction for all flight modes and preparation of the aircraft for departure; generation of information for exchange between aircraft; detection, recognition and tracking of passive thermal, thermal imaging, television and radio equipment of air, ground and surface goals, the formation and delivery of guided missiles the necessary information for their preparation; use of weapons; generating signals of automatic and director control of the aircraft using weapons; providing take-off, route, landing, barrage, re-entry; providing the ability to memorize and store: programmable flight points; specified landmarks in the geographical and polar coordinate system; landing aerodromes; beacons; providing the possibility of visual correction of location coordinates by the method of: flying around route points with previously known coordinates; by stamping on a visually visible landmark; the method of determining the coordinates to known; automatic, director and manual control when using weapons and navigation; integrated control of equipment with the issuance of information about the status of the subsystems of the complex to the crew and to the registration system; manual and automated input of the flight task into the on-board devices of long-term memory; providing training regimes for practicing the use of weapons and navigation; to control the combat operations of groups of aircraft, the equipment is configured to automatically exchange information about air targets and their whereabouts; manual target allocation of air target groups between groups at the level of the commander of the combined group; target distribution of air targets groups and goals for each group aircraft at the group commander level; organization of automatic exchange of information about land or sea targets and their own location; manual target allocation by transferring the coordinates of land or sea targets between groups of aircraft at the level of the group commander; manual target allocation and transmission of coordinates of land or sea targets for each group aircraft at the level of the group commander; an aircraft radar transponder is configured to receive and process interrogation signals and issue state-owned response signals; determining upon request the location of air objects; allocation at the request of objects suffering "Disaster"; automatic performance monitoring with alarm failure in case of failure; the on-board complex of radio communications is made with the possibility of radiotelephone communications and data transmission; organization of cyclic data exchange within a group and between groups of aircraft; internal communication with maintenance personnel during ground training; automated control of complex equipment from an integrated console; automated control of complex equipment; issuing signals for monitoring, display, registration and documentation; listening to emergency signals from a voice informant, signals from radio navigation devices, signals from an emergency receiver; registration and control facilities include an alarm system; integrated information alarm system; airborne registration system for flight parameters and operation of aircraft systems and equipment; video recording system; voice warning equipment, moreover, the alarm system is configured to notify the aircraft crew using light signals about failures, malfunctions and operating modes of aircraft systems and units and equipment and to ensure the operation of emergency, warning and notification light signals on the dashboard in the cockpit; a comprehensive informational alarm system is configured to: monitor flight systems and equipment in flight with warning and notification messages displayed on indicators; determination of malfunctions of aircraft systems and equipment during pre-flight preparation of the aircraft and advanced checks by analyzing information; ensuring storing of the results of equipment control and system failures that occurred during the flight in a long-term storage device with the issuance of information; analysis of information about the operation of aircraft systems to display the current parameters of the systems in the form of mnemo frames on indicators; warning and notification text messages about equipment failures; information for displaying mnemonic frames characterizing the operation of general aircraft systems; the registration and parameter control system is configured to register code information from air control systems; digital information; binary signals in the form of voltage drops of service information about the date and number of the flight; self-monitoring parameters of calibration voltage and overflow voltage; parameters of the current time; negotiations of the aircraft crew, with fixing in the long-term storage device failure codes with timestamps of their occurrence; voice warning equipment is configured to notify the pilot with a voice command about system failures, emergency situations on an airplane and duplication of an integrated information system in emergency situations; electronic countermeasures include: an individual and group defense active jamming station, a group protection active jamming station, passive missile control equipment, and the individual defense active jamming station is configured to determine the direction to radiating radar stations; determine the operation mode of stations and their degree of danger; choose the type of interference; reproduce the signals of the emitting stations, and emit them in the direction of the irradiating stations; a group protection active jamming station is configured to determine a direction to radiating radar stations; determine the operation mode of stations and their degree of danger; choose the type of interference; reproduce the signals of the emitting stations and emit them in the direction of the irradiating stations; individual and group defense stations are capable of operating in the front and rear hemispheres; at the same time, passive missile control equipment is made with the ability to control missiles according to targeting information and with autonomous guidance.  25. On-board equipment according to paragraph 24, characterized in that it is equipped and interfaced with a television command guidance system located in a hanging container.  26. On-board equipment according A.25, characterized in that the phased antenna array of the radar station is made with electric control of the beam and a mechanical turn in azimuth.  27. A control system for a multi-purpose highly maneuverable supersonic aircraft, comprising longitudinal and lateral and heading control channels, including control posts in the cockpit equipped with loading mechanisms, a remote control system that contains redundant computers, position sensors of control and controlled bodies, sensors of flight parameters and is designed to ensure stability and controllability of the aircraft in the intervals of allowable angles of attack and overloads, with each of hydraulic socks of the wing consoles, flaperons, stabilizer and rudders are connected with two independent hydraulic systems of the aircraft, and an automatic control system with calculators and flight controls for stabilization and approach approaches, flight along the route, control by command of guidance and homing points by signals airborne weapons controls and associated with the aiming and navigation system, weapons control and command guidance, characterized in that it is equipped with means for providing access to supercritical angles of attack, including a device for switching off the limiter of limit modes; devices for adjusting the characteristics of controllability during fuel refueling in flight by connecting pitch and roll angle sensors to calculators of longitudinal and lateral control by means of memory and restrictive devices; a means of increasing the reliability of stabilizer servo drives due to redundancy of control means and a majority assessment of their serviceability; means of ensuring flight safety in case of failure of the wing sock control system by connecting an additional hydraulic actuator to deflect the socks to the maximum angle down; a means of ensuring the aerodynamic quality of the wing during maneuvering due to automatic deflection of the flaperons when changing the angle of attack.  28. The control system according to item 27, wherein the longitudinal control channel is equipped with a self-adjusting device for changing the gain of the control signal specified by the pilot or automatic control system, depending on the mismatch between the signals corresponding to the flight parameters and the signals of the device simulating a given changing flight parameters, and is also equipped with an electro-hydraulic system for turning the front horizontal tail consoles, including hydraulic cylinders with golden kovymi devices associated with these aircraft hydraulic systems and servo associated with the calculator remote control system, the hydraulic drives rudders and flaperons are equipped with electro-hydraulic valves and amplifiers connected to the corresponding outputs of the remote control system amplifiers.  29. The control system according to p. 28, characterized in that it is equipped with an electro-hydraulic system in-phase and differential deviation of the rotary nozzles of the right and left engines of the power plant of the aircraft, and this electro-hydraulic system contains a computer included in the remote control system, a device for turning on the nozzle rotation mode, installed in the cockpit, and drive devices, each of which contains a drive amplifier associated with the output of the specified computer, electro-hydraulic drive associated with the fuel system of the respective engine.  30. The hydraulic system of a multi-purpose highly maneuverable supersonic aircraft, consisting of the first and second hydraulic systems, each of which contains a variable-speed hydraulic pump driven by a remote box of units of the corresponding engine of the aircraft power plant, and a hydraulic compensator in which the high-pressure cavity is in communication with the gas cavity of the gas-liquid accumulator, and the low-pressure cavity is connected to the suction line of the hydraulic pump and its discharge line through the fi a liter and a fuel-oil heat exchanger; moreover, the drain-suction and discharge lines of the hydraulic pump are equipped with corresponding on-board valves for connecting a ground hydraulic installation and provide the supply and discharge of working fluid through filters to hydraulic drives: socks of wing consoles, flaperons, stabilizer consoles, rudders, take-off complex - landing devices or fuel refueling rods, the mechanism for turning the front wheel of the chassis or brake flap, emergency or main brake, air intake panels and its protection devices, and the discharge line is also in communication with the liquid cavity of the gas-liquid accumulator, and the hydraulic actuators of the take-off and landing device system and the fuel refueling rods are equipped with emergency sources of compressed gas connected through shuttle valves, characterized in that in each of the hydraulic systems the discharge line of the hydraulic pump is variable performance is connected with the hydraulic drive of the intake panels through a check valve in the line connecting this line with a liquid cavity gas-liquid an accumulator, and in the first hydraulic system, the liquid cavity of the same gas-liquid accumulator is also connected to the emergency brake hydraulic actuator and the output of a manual booster pump introduced into the first hydraulic system, the low pressure cavity of the hydraulic compensator is connected to the suction line of a variable capacity hydraulic pump via a reversible pipeline, and on-board valves for connecting surface hydraulic installations are made and installed with the possibility of removing gas from each hydraulic system, industrial Applicants them and fill with clean oil.  31. The hydraulic system according to claim 30, characterized in that in order to create the required suction pressure when the pump is operating at reduced speeds in conditions of insufficient provision of the required costs, pressure boosting means are introduced with the choice of the appropriate ratio of the areas of the differential piston in the high and low pressure compensation cavities with the accumulator connected via a non-return valve to eliminate pressure drops on the suction of the pump.  32. The hydraulic system according to p. 31, characterized in that the discharge, suction and discharge lines of a variable displacement hydraulic pump in each hydraulic system are connected through filters with hydraulic drives of the front horizontal tail, and the same intake and discharge lines in the first hydraulic system are also connected to the hydraulic drive of the rotary device radar station connections.  33. The pneumatic system of a multi-purpose highly maneuverable supersonic aircraft, containing emergency landing gear, refueling rods, a cockpit opening, closing and sealing system, characterized in that the electropneumatic valve in the compressed nitrogen supply line to the drive cylinders of the landing gear doors and connected in series with electropneumatic valve in the line for supplying compressed nitrogen to the drive cylinders of the chassis racks, mounted on one of the main chassis supports before the rotary connection on the fuselage to the drive cylinders, a cylinder with compressed nitrogen, an electro-pneumatic valve and a shuttle valve connected in series in the compressed nitrogen supply line to the drive cylinder for releasing the fuel refueling rod in flight were introduced, the operational control system for the hinged part of the lamp includes a pneumatic cylinder for opening and closing the hinged part a lantern, a suspension lock that opens at the initial stroke of the cylinder rod when nitrogen is supplied to the pneumatic cavity of the cylinder, when liquid is supplied to the hydraulic cavity from the mechanism p scientific opening, bypass valves of the mechanism for manually opening the lamp before it is locked, kinematic lock for fixing the hinged part of the lamp, gear unit, sealing valve, hose depressurization valve, a nitrogen compressed cylinder connected to a sealing valve, a lamp control valve, a sealing hose and a lamp anti-icing system, one of the pipelines connects the lantern control valve to one of the pneumatic cylinders of the manual opening mechanism of the lantern and the cavity of the pneumohydraulic cylinder, the other pipeline connects the same a crane with a second pneumatic cylinder of the manual opening mechanism of the lantern, with a valve of the manual opening mechanism and with a cavity for closing the pneumatic cylinder.  34. The power supply system of a multi-purpose high-time supersonic aircraft, containing two-channel AC and DC systems, including two integrated drive-generator of alternating current of a stabilized frequency, mounted on remote boxes of engine units of the aircraft power plant engines, rechargeable batteries and emergency DC-AC converters, characterized in that in an alternating current system, each of the generators is equipped with a ballast, protective and transformative equipment, and the converters are equipped with a switching device in case of failure of both generators, the two-channel DC system contains series-connected primary and emergency buses of the central distribution device in each channel and the consumer buses of the first and second levels connected to them in each of the power distribution devices for aircraft and power systems , electronic equipment and weapons systems equipped with switching contactors, while in each central distribution unit The primary bus is connected to one of the three rectifiers, each of which is equipped with a protection device, and is connected to the primary bus of the second central switchgear via a jumper equipped with fuses, and the emergency bus is connected to the corresponding battery, and some consumers are connected to both buses of first-level consumers appropriate switchgear via decoupling diodes.  35. The power supply system according to clause 34, wherein each of the drive-generator is made with approximately doubled power and is equipped with a new generation of solid-state ballasts, ballasts, and converters, and the DC system is equipped with three control relays with input and output NC contacts, four trip relays with NC contacts and silicon power planar diodes installed in each central switchgear between the primary and emergency with buses, while one of the rectifiers is connected to the jumper between the primary buses of the central distribution devices in the area between the low-inertia fuses located on the side of each primary bus with respect to the direct resistance of each of the power diodes in the central distribution and rectifier devices to the resistance of each of the low-inertia fuses more than 3 fuses, control relay windings are connected in series with the corresponding rectifier protection devices her, and the input opening contacts of each of the control relays are connected in series with the input opening contacts of the other control relay in the power supply circuit of the windings of the disconnecting relays, the opening contacts of which are included in the power supply circuit of the switching contacts of the consumer busbars of the second level in the power distribution devices of electronic equipment and weapons systems, each of the power distribution devices for aircraft and power systems, electronic equipment and weapons systems, the power bus will consume The first level switch is connected to the emergency bus of one of the central distribution devices, and the second-level power supply bus is connected to the primary bus of another central distribution device, while the system is equipped with means for connecting a ground-based power source with the ability to visually monitor all parameters and the state of the system by means of information display in the cockpit.  36. Lighting equipment of a multi-purpose highly maneuverable supersonic aircraft, containing means of external and internal lighting with means of their power supply, switching on, off and adjustment, including: parking lights located at the ends of the wing consoles and one of the dorsal fins, landing and taxiing lights mounted on a rack the front landing gear, cab lighting and instruments installed in them, characterized in that it further comprises retractable headlights for illumination of the aircraft a fuel operator and his external means of fuel delivery during refueling, a fuel receiver illuminator at the end of a retractable fuel refueling rod, illuminators of the aircraft’s internal compartments with means for turning them on and off during ground handling, means for illuminating inscriptions on control panels having transparent panels with these inscriptions located above means of illumination.  37. The air conditioning system on a multi-purpose highly maneuverable supersonic aircraft, containing a system for regulating the pressure, temperature and humidity in the cockpit, a ventilation system for the costumes of crew members, a system for blowing glazing of the cockpit lantern and a system for boosting and cooling equipment, and including means for taking compressed air from compressors of turbojet engines of an aircraft power plant, its cooling with outside air and fuel, and adjustable expansion with decreasing temperature s, as well as a regulated discharge of exhaust air overboard, regulation of the flow rate, temperature and humidity of the supplied air, characterized in that the exhaust air pressure limiter, air-air and fuel-air heat exchangers, dehumidifiers and a turbo-cooler with a loading fan included in the air the air intake channel is installed in one of the tail beams of the fuselage, and the air intake pipe for pressurization of the accumulator is connected to the section of the highway oh azhdaemogo air between the heat exchanger and having air bleed pipe flow regulator to boost missile equipment and equipment installed in predkabinnom zakabinnogo compartments and fuselage - to the plot line of the cooled air before connecting to it place the hot air line, also equipped with a flow regulator.  38. The system according to clause 37, wherein the hot air main is equipped with a network pressure regulator and connected to the cooled air main by three pipelines in sections in front of the air-air heat exchanger, between the heat exchangers and between the fuel-air heat exchanger and the turbo-cooler, in the main of hot air between its sections connected to the inlet and outlet of the fuel-air heat exchanger an additional damper is installed to control the flow of hot air, in the system we have two parallel-connected turbo-coolers of different cooling capacities, connected at the inlet through an electro-pneumatic valve controlled by a signal of the cooled air pressure, introduced devices for reconfiguring the flow regulator in the air intake pipe to boost equipment to increase the flow rate when the system is used to heat the crew cabs, a device for charging equipment with high-speed air pressure head, including a recessed retractable air intake connected to the equipment boost line and equipped with th drive, controlled by signals of temperature in highways, flight speed and air pressure before cooling turbines.  39. A liquid cooling system for equipment of a multi-purpose highly maneuverable supersonic aircraft, comprising means for supplying a cooling liquid and heat removal means, characterized in that a gear pump is installed therein, included in a closed circulation circuit of a cooling liquid, a fuel-liquid heat exchanger installed in a closed circulation circuit is installed in fuel supply tank, a mesh filter is installed in the system to clean the coolant from mechanical impurities and a broad tank to ensure cavitation-free operation of the pump, the pressurized cavity of the tank is equipped with a safety valve to prevent it from being re-pressurized and is in communication with the pressurization system through a non-return valve that prevents liquid from entering the pressurization system at negative overloads, the system contains a coolant flow sensor and a temperature sensor for informing about the reliability of reliable cooling.  40. A life support system for the crew of a multi-purpose, highly maneuverable supersonic aircraft, comprising an onboard oxygen system, a chair oxygen supply system, an onboard supply of gaseous oxygen, high-altitude equipment for pilots, ventilation equipment and air conditioning and air pressure control systems, including protective helmets, oxygen masks, high-altitude compensating anti-overload and ventilated suits, characterized in that it is configured to provide during the entire flight at altitudes up to the practical ceiling of the flight of the aircraft in pressurized cabins, in depressurized cabins at intermediate heights, briefly during depressurization of the cockpit at heights from intermediate to practical ceiling using a set of oxygen equipment as an emergency means of supplying crew oxygen with the process lowering to a safe height, briefly at heights to a practical ceiling when ejecting with automatic by switching to the oxygen supply from the oxygen equipment block of the chair, oxygen cylinders are connected through oxygen devices to oxygen masks and to the chambers of the tension device of the high-compensating suit by means of an oxygen valve, an oxygen reducer, a pressure switch, and a flow regulator, and the low-pressure cavity of the oxygen device is connected to with a feed indicator housing, a protective helmet is made with the possibility of protecting the head from injuries when striking the structure and both ore cabin and eye protection from exposure to sunlight and projection rays, as well as noise attenuation and installation of the telephone and loringophon, the high-altitude compensating suit has a compensating tension device and a built-in ventilation system in which the input is connected to the air supply line to the cabin and the output to the cabin itself , an anti-loading suit made of nylon fabric is made with the possibility of crimping the front wall of the abdomen and muscle groups of the lower limbs of a crew member to prevent the movement of blood to the lower parts of the body and improvement of blood supply to the upper parts of the body under the action of overloads while protecting the internal organs from displacement and stretching, and the suit is equipped with an inflatable chamber made of rubberized fabric fastened to the power shell on the inside of the front wall of the belt, the system is equipped with special swimming trunks for each crew member with an urinal and valve on the output tube made with a tip for connection with a drain tube, which is led overboard the aircraft and is equipped with a suction ejector connected to the main combustion air conditioning system, in each of the booths installed panel with a set of flexible containers with different pasty food.  41. The emergency exit system of a multi-purpose highly maneuverable supersonic aircraft containing a control system for the hinged part of the lantern and an ejection system, including two ejection seats; emergency reset system of the hinged part of the lamp; unlocking system for shooting mechanisms of seats; forced bailout system; an ejection blocking system, the ejection system including a parachute launch mechanism, an overhead rescue system with a parachute, a stabilization system with a stabilizing parachute, emergency stock with an automatic beacon, food stock, alarm and medication equipment, pilot equipment as part of a height-compensating suit or high-altitude marine rescue kit, a protective helmet and a set of oxygen equipment, and is configured to emergency escape the crew and the aircraft in the entire range of altitudes and flight speeds, characterized in that it provides means for emergency dumping of the hinged part of the lantern from the handrail of the seat by electric and mechanical lines; means of autonomous dumping of the hinged part of the lamp from the handle in the front or rear cabins along a mechanical line; unlocking the firing mechanism in the rear cockpit with a halyard and backup pyromechanical system, and in the front cockpit with electric and backup pyromechanical systems; means for ensuring consistent ejection of crew members from the rear and front cabins when pulling the ejection handrails of both seats simultaneously; means of independent ejection of a crew member from the front cockpit in the event of a failure of the ejection system of the rear cockpit chair; protective covers to prevent unintentional actuation of the emergency reset system of the hinged part of the lamp, while in the closed position the hinged part of the lamp is held by a suspension lock, two pins on the arc of the front part of the lamp, stops on the sub-light frame and rollers in the lamp rollback rails so that when opening it, the hinged part together with the suspension lock moves back to the exit from the pins, stops and rollers with subsequent rotation, directed towards the hinged part of the front profile shelf profile is the herme with a teasing surface, to which the hose for sealing the hinged part of the lantern adjoins, the front glass of the hinged part of the lantern is attached to the front arc and the middle arc by means of the lavsan tape and the flat ramrod, the rear glass of the hinged part is attached to the middle arc and the rear bracket also by means of the mylar ribbon and the flat ramrod, To shade the dashboard of the rear cab from direct external lighting, a protective visor is installed, and a transparent protective deflector is installed outside the visor, the lamp is equipped with an alcohol rotivoobledinitelnoy system in which the alcohol feed compressed nitrogen is provided by a command from the front of the cab.  42. The system according to paragraph 41, wherein the means of emergency escape are configured to reduce the time of emergency exit by 0.5 s and the size of the surface of the glare shield to the rear cab.