Cryogenic turbo-electric stol aircraft

FIELD: aviation.

SUBSTANCE: cryogenic turbo-electric STOL aircraft has longitudinal design of triplane with a foreplane, twin-finned H-shape tail unit. The aircraft includes fuselage, wings, wheel landing gear, power plant and variable propulsion system with three different-sized feathering reversible propellers. The foreplane has elevons and panels of all-moving tailplane designed with a capability of differential and inphase turn with reference to the interkeel pitch axis together with propellers from the level attitude downwards and upwards. The power plant, designed using the parallel-serial hybrid technology of the power actuator, is equipped with the left and right electric motors mounted in engine nacelles, gas-turbine engine equipped with forward output shaft for the power take-off to the reduction gearbox of bigger propeller and output shaft for a power take-off, rotationally connected through output and input couplings respectively with the bigger propeller and reversible motor-alternator.

EFFECT: improvement of take-off horizontal thrust/weight ratio and load ratio.

2 dwg

The invention relates to the field of aviation technology and can be used in the design of unmanned and cryogenic turboelectric aircraft longitudinal layout of the Triplane and double circuit with the H-shaped wings, stabilizer which are deviated by the screws in the annular channels to perform short take-off and landing at the aerodrome and deck basing.

Known electroanalyt project "ZEHST" company "EADS", made of carbon fiber, which contains a monoplane with a low wing and end wings, war V-shaped tail, mounted together with an annular channel having a twin pusher propellers rotating in opposite directions, a fuselage, a propulsion unit including two superconducting electric motor mounted on the end of the fuselage and leading twin screws, control system and rechargeable batteries, retractable tricycle wheeled chassis with an auxiliary front foot.

Signs matching the availability of aircraft with low wing and tricycle chassis with an auxiliary front foot. Material for housing electroanalyt project "ZEHST" is carbon fiber, so it will be easy enough. Its main advantages, which will be beneficial in order to dlicate it from conventional aircraft, are powerful aerodynamics, composite design and, of course, light weight airframe. Modified lithium ion polymer batteries electroanalyt will be rechargeable. And the time required for charging, will be the standard time of refueling. At the end of the fuselage together with the annular channel mounted war V-shaped tail. LTO provide two electric motors with twin pusher propellers rotating in opposite directions.

Reasons preventing the task: the first is that electroanalyt project "ZEHST" coupled with the clamping screws in the annular channel at the end of the fuselage, creating only horizontal thrust as when landing, and cruise flight conditions, has a complex scheme of reduction and control motors with independent rotation of the two coaxial pusher screws that predetermines the possibility of operating with concrete runways with a length of 1350 m, and reduces the stability control and safety in the event of failure of one of the motors. The second is that rechargeable lithium-ion battery electroanalyt with the weight (about 35-40%) from the empty weight that highly reduces payload and, as a consequence, reduces the weight of the cottage. The third is that when the flight time of two hours, the range can be up to 1500 km at the height of its flight over 8,500 feet, the Following disadvantage is also underdeveloped V-shaped tail, hence the bad and ground stability and, especially, when the failure of one of the engines on take-off and landing modes, and lack of horizontal thrust. All this limits the possibility of further increased takeoff weight and the weight of rechargeable batteries, as well as increase the horizontal tagavoranist and enforce technology short take-off and landing (KVP).

Known electroanalyt project "Ce-Liner" company "Bauhaus Luftfahrt" (Germany), representing a monoplane with a low-lying unusual shaped wing having end wings outer part of the wing-shaped, the ends of the latter rejected to the engine nacelles mounted on the sides of the fuselage to the horizontal pylons and have motors with closed pulling windowingsystem, contains in the fuselage of the carbon management system and a replaceable rechargeable battery, single tail and tricycle retractable wheel landing gear with a nose auxiliary and main bearings.

Signs matching - the presence of the rear nacelle with pulling windowingsystem creating only Horiz is Stalnoy cravings, contains management system that distributes charging batteries electroanalyt "Ce-Liner" between the two motors with pulling propellers, providing speeds of up to 750 km/h on the flight altitude of more than 8500 m and at the distances up to 1700 km, single tail and tricycle retractable wheeled chassis with nose auxiliary support. The minimum charge time of the batteries will be two hours, so for a quick turnaround of operations of the battery will be their currency. In this case, 16 standard LD3 containers with lithium-ion batteries can be replaced in 30-minute time data processing.

Reasons preventing the task: the first is that the rear of the accommodation on the end and sides of the fuselage with a single tail plumage of the two engine nacelles with motors and pulling closed windowingsystem determines structurally complex wing of unusual form, is made in the transverse plane of the C-shaped configuration with a complex mechanization and steering surfaces of the wing - elevons, which complicates the design and longitudinal controllability; the second is that the diameters pulling windowancestor is limited by the size zakuporennyh annular fairing and this consequently limits the horizontal tagavoranist; the third is that what a field-replaceable lithium-ion battery electroanalyt Ce-Liner with a capacity of 190 people, who will be 30 tons heavier Airbus A320, this significantly reduces the payload and, therefore, reduces the weight returns; the fourth is that takeoff thrust pulling windowancestor is provided only in the horizontal direction, and the lack of change in the vertical plane of the direction of the thrust vector of these windowancestor and, as a consequence, the possibility of reducing the landing speed to be ensured in the implementation of technology KVP, this electroanalyt Ce-Liner can't, which significantly reduces the security and, in particular, creates complexity longitudinal and lateral control with wing-shaped, especially on takeoff and landing flight modes, when this wing vector its thrust is not balanced. All this limits the possibility of further increased takeoff weight and the weight of replaceable batteries, and increase the horizontal tagavoranist and execution technology KVP.

Closest to the proposed invention is a multi-purpose cryogenic convertiplane [1] (Russia) made on a longitudinal diagram of the Triplane with canard war the H-shaped wings mounted to consoles of nizkoraspolozhennym the wing in spaced beams, has a glider made of composite carbon fiber with smooth mate flows wing and fuselage, power plant, located on the aft pylon, transmitting power through the main gearbox and shafts of the transmission on the screws in the annular channels located in the nose and aft fuselage, providing horizontal and appropriate deflection of the vertical rod, retractable tricycle wheeled chassis with nose auxiliary support.

Signs matching the three bearing surfaces of the longitudinal scheme Triplane: the canards (GIP), the swept wing having a variable sweep beading and spaced beams war H-shaped tail, console tselnopovorotnogo stabilizer (LTP) which have the screws in the annular channels. Wing beading, fuselage and H-shaped plumage combined into a single structural force trenbolone scheme, spaced beams which, along with fuel for jet fuel tanks in the wing, equipped for liquefied natural gas cryogenic fuel tanks. Annular channels with pulling screws associated with engines synchronizing shaft and located in the forward fuselage, and on consoles LTP mounted on the sides of the aft pylon, provide horizontal thrust and the appropriate deviation, rst the x at the angle of 90° or 35° from the horizontal position vertical or inclined traction when performing vertical take-off/landing or technology KVP.

Reasons preventing the task: the first is that the diameters mikelevich pulling screws in rotary annular channels is limited by the height of the racks, especially the main chassis and as a consequence, this limits the runway traction-orogennoi and, in particular, when performing technology KVP rejected with screws at an angle of 35°, while ensuring the tipping angle φ=12° determines the extension rack height chassis 6-8%; the second is that the power unit (SU), including two gas-turbine engine (GTE), posted to the main gearbox and shafts of the transmission in the rear part of the fuselage and on the sides of the aft pylon, are from the last to the bow and the top of the fuselage. It is, thus, highly increases drag and reduces the useful scope of the LTP and its carrying capacity, but also because of the presence of the aft pylon with the main gear, a rear pusher propeller at the end of the fuselage and, especially, on the axis of symmetry. All this limits the possibility of further increase in takeoff weight of weight and payload, as well as increase the horizontal tagavoranist when performing technology KVP.

The invention solves the problem in the above well-known multi-purpose cryogenic convertiplane significant increased what I takeoff horizontal tagavoranist and increased takeoff weight and the weight returns, simplifying the design and reducing the mass of the glider due to the exclusion of control roll deflection of the ailerons to the wing and the tail beam with a vertical pylon, main gearbox and shafts of the transmission, improving lateral and directional stability and ease of handling in roll and pitch.

Distinctive features of the present invention from the above well-known multi-purpose cryogenic convertiplane closest to him, are the existence of what he made on double circuit with short fuselage-nacelle and the ability to change propulsion system in flight configuration as the plane with three different-sized feathered-reversible screws for the landing flight modes, and in the plane with two - or single-screw propulsion system for cruise flight, and back, which along with two smaller screws it is supplied along the plane of symmetry on minilevel transverse axis tail nacelle with large four-bladed propeller, the first of which have the same direction of rotation between itself and the opposite with the latter, with the aim of reducing losses for balancing while providing high load-bearing properties and smaller size and simple mechanization of bearing surfaces with the possibility of the membrane of its release/cleaning by mentioning is the existence of the canards are equipped with elevons, as mentioned wing - megalochari and outer flaps, but also to provide transverse and longitudinal balancing management mentioned plumage includes console whole-rotating stabilizer with the ability according to their differential and common-mode rotation relative minilevel transverse axis together with the smaller screws from the horizontal position downward and upward respectively from 0° to -35° and 0° to +15°, with the aim of increasing the effective lengthening of the wing along with the reduction of the inductive resistance of the end portion of the wing, made with a positive angle +12° transverse V, have in-plane negative twist the end parts of the wing tips with the bent back ends of the lower surface of the latter sloped at an angle of 45° with smoothly formed a rounding bottom and a relatively sharp edge at the top, which reduces the intensity of the vortex behind the wing in the air stream emerging from under the lower surface of the wing relatively rounded in the plane of the unbent end of its respective sickle in terms of the ending, the power plant, made by parallel-serial hybrid technology power drive, equipped with the left and right electric motors mounted in the respective nacelle on the ribs of the respective ring is s channels, gas turbine engine equipped with front output shaft for PTO on the gearbox larger screw and the output shaft for PTO, rotationally connected through output and input clutch, respectively, with a large screw and a motor-generator, is made reversible, and having a drive system including the electric motor and rechargeable batteries, there are input and output electromagnetic clutch that provides remote control of the engagement/disengagement, respectively, of the output shaft of the gearbox larger screw to the shaft of the motor-generator and shaft four-bladed pusher larger screw.

Due to the presence of these symptoms, allowing to perform cryogenic turboelectric plane KVP by the longitudinal layout of the Triplane, structurally-power double-girder design and concept of the tandem arrangement of different-sized screws (TRV) according to scheme 1+2, which creates the possibility of relatively cheap to double the horizontal tagavoranist and ensure conversion of its flight configuration as the plane with three different-sized feathered-reversible screws for the landing flight modes, and in the plane with two - or single-screw propulsion system for cruise flight, but back. P is given, aerodynamic longitudinal scheme of Triplane, including GIP, swept wing having a variable sweep beading and spaced beams war H-shaped tail, the LTP which is mounted on minilevel transverse axis, are pushing smaller screws in the annular channels. At this end of the wing, made with a positive angle+12° transverse V with edge lines, each of which is made with bent back ends having transverse plane of the lower surface is angled at 45° with smooth rounded bottom and a relatively sharp edge at the top, repelling the flow of air coming in the vortex flow from below the lower surface of the wing relative to the rounded end in terms of the corresponding sickle in terms of wingtips. In hybrid SU during cruise flight the increase in generation capacity for power supply, when the drop charging lithium-ion polymer rechargeable battery will decrease to 25% of its maximum, the control system will automatically turn off the output clutch pull more screw from his gear, install the blades into the feathered position and will include GTE rear of the engine nacelle, which will rotate through the gear larger screw motor-generator that provides charging the battery the Directors in the flight configuration of the two aircraft. Hybrid SU, executed by a parallel-serial technology actuator equipped with left and right mikeletegi engine nacelles with electric motors mounted in the annular channels, rotationally associated with the corresponding smaller screws, but tail nacelle larger screw, which, along with a CCD, having a bottom air inlet and containing on the front output shaft for selection of runway capacity gearbox larger screw output shaft of the latter, rotationally connected across the output and the input clutch, respectively, with a large screw and a motor-generator, is made reversible, and has a drive system that includes all of the motors, rechargeable batteries, the power Converter with a control unit of the power transmission connecting and disconnecting the motor and GTE, co-generating power and procedure of recharging batteries from the engine-generator, but the joint work of the CCD with the latter having a motor-electric motor, or independent of his work only on one shaft larger screw, but independent work in a distributed transmission nominal capacity and on the shaft of the electric motor-generator having the mode generator and shaft pull more in the NTA, set when the clutch shaft with the output shaft of the gearbox last in the directional position so that one and the other pair of opposite blades are respectively perpendicular to and along the middle line of consoles tselnopovorotnogo stabilizer. The presence of these features will help greatly reduce the acoustic signature hybrid SU and to provide transverse and longitudinal controllability, respectively, of the differential and common-mode rotation consoles LTP together with the smaller screws in the annular channels and the deployment of hybrid SU in Maikelawi tail will provide easier control of electric drives, but will due to the removal of the screws to the tail of the aircraft to achieve a low noise level in the cabin. It will also help to improve the safety and use GTD smaller in its cross-section, which will ensure the reduction of the midsection of the tail engine nacelle and the width of the rear fairing with the exhaust pipe. While pushing two smaller screws in the swivel ring channels and its pulling more screw mounted on the axis of symmetry in the rear of the nacelle, mounted in maskilim space H-shaped tail, which will greatly reduce the weight of the glider, to increase the payload to increase the weight returns, as well as transport and toplivno the efficiency.

The present invention cryogenic turboelectric plane (CTAs) and the options for its use when performing KVP is shown in Fig. 1 and 2.

In Fig. 1 on the General side view depicted CTAs with GIP and swept wings with variable sweep beading and spaced beams war H-shaped tail, the LTP which are pushing the smaller screws in the annular channel, rejected, down on the corner -35° in the flight configuration of the aircraft with trehvaltsovoj propulsion system on runway modes KVP.

In Fig. 2 on the General top view depicts CTAs with GIP and low profile wing with variable sweep beading and spaced beams war H-shaped tail, the LTP which are pushing the smaller screws in the annular channels that create horizontal thrust in flight configuration of the aircraft with a twin-screw digitalno system at cruise flight modes with the set pulling a large screw in the feathered position.

Cryogenic turboelectric plane KVP (and execution TRV-X1+2) made on structural force girder scheme and concept longitudinal schematic of the Triplane and shown in Fig. 1 and 2, includes a fuselage-nacelle 1 and a low wing 2 having ahead of it flows 3 variable sweep smoothly PE ehteshami in megalofonou part of the wing 2, combining the fuselage-nacelle 1 and wing 2 flows 3 into a single smoothly formed structure (see Fig. 2). In front of the wing 2 in the forward portion 4 of the fuselage-nacelle 1 is mounted GIP 6 with throughout the span provided with 7 mode the flaps and elevators. Posted beams 5 connect the wing war 2 the H-shaped tail unit 8 having the rudders 9. Console DSP 10 N-shaped tail unit 8 mounted on minilevel transverse axis (Fig. 1 and 2 is not shown), provided with a pushing smaller screws 11 decline in the annular channel 12, having a range of rotation from -35° to +15°. Swept wing 2, equipped megalochari and outer flaps 13 has an end portion 14 of the wing with aerodynamic projection 15 on the leading edge of the wing 2, is made with a positive angle +12° transverse V with tip 16, each of which is made with bent back ends 17, having in the transverse plane of the lower surface is angled at 45°, with smooth rounded bottom and a relatively sharp edge at the top, repelling the air flow, coming in a vortex flow from under the lower wing surface 2 relative to the rounded end in terms of the corresponding sickle in terms of its ends 16. The outer part of the wing 2, located on the outer sides of the spaced beams 5, the imp is tive deviating up and folding for easy placement on the deck (hangar) and the possibility of operating on aircraft carriers, also, Parking in the formulation of generating energy and recharging lithium-ion polymer rechargeable battery (Fig.1 and 2 is not shown).

Hybrid SU, executed by a parallel-serial technology actuator equipped with left and right mikeletegi the nacelle 18 with electric motors mounted in the annular channel 12, rotationally associated with the respective pushing smaller screws 11 and a tail nacelle 19 pull larger screw 20, which, along with a CCD having front and on the lower part of the air vent 21, contains on the front output shaft of the CCD for the selection of runway capacity gearbox larger screw 20, the output shaft of the latter rotationally connected across the output and the input clutch, respectively, with a large screw 20 and the motor-generator, made reversible. The drive system includes all motors, rechargeable batteries, energy Converter with a control unit of the power transmission connecting and disconnecting the motor and GTE, co-generating power and procedure of recharging batteries from the generator (Fig.1 and 2 is not shown). In hybrid SU cryogenic CCD made for the selection of runway capacity with the front of the conclusions of the shaft, is installed along the square is Scoti symmetry on minilevel transverse axis with maximum ease of maintenance and operation in the rear of the nacelle. Three smaller screws 11 in two rotary annular channels 12 and one four-bladed larger screw 19 is made feathered-reversible and rigid mounting of carbon and fiberglass blades and the ability to change the angle of installation. Turn consoles LTP 10 together with the smaller screws 11 in the annular channel 12 is carried out by means of Electromechanical actuators, and the production and cleaning of a wheeled chassis, a control elevons 7 and the flaps 13, deviation and folding the outer parts of the wing 2 is also electrically (Fig.1 and 2 is not shown). Tricycle retractable wheel landing gear, the nose bearing with the wheel 22, is removed in the front recess of the fuselage-nacelle 1, the main side supports with wheels 23 in compartments spaced beams 5, provided with a bottom leaves, closing the gap.

The real achievement of profitability and high fuel efficiency may include, in particular, and use in hybrid SU turbine engines cryogenic modifications, only with regard to the use of liquefied natural gas (LNG). It should be recognized that girder aerodynamic design CTAs, and determines as the technical ability and simplicity of design combined with cryogenic fuel tanks. Such convertible CTAs can have a separate fuel system (ar is as standard - for jet fuel, other - cryogenic LNG). Cryogenic fuel tanks for LNG, basic and centering, can be located, respectively, in two spaced beams 5 and the fins 8 and mounted near the engines of the SU. The combination of midship fuel tank with mid-section spaced beams 5, and the combination of the supporting ribs mikelevich annular channels 12 and GCHQ 10 total girder aerodynamic scheme, will allow you to locate cryogenic fuel tanks outside the fuselage-nacelle 1 almost without increasing aerodynamic drag and additional strengthening of the wing 2. Short cryogenic fuel tracks in SU are light-weight and low thermal insulation. Remote from the fuselage-nacelle 1 cryogenic SU and fuel system significantly increase the reliability, explosion and fire safety. With two separate fuel systems for jet fuel in the wing and LNG in spaced beams) CTAs will be able to refuel with gas, make a flight in the airport where no equipment for its production and storage, and to fly on jet fuel. All this helps to improve safety and to achieve high fuel efficiency that make CTAs LNG more cost-effective and profitable.

Management of hybrid kites KVP provided General (modifies silalahi) by changing the pitch of the smaller screws 11 in two rotary annular channels 12 and one larger screw 20, as well as the deviation of the tail surfaces of the elevons 7 GIP 6, rudders 9 and consoles DSP 10, working together with smaller screws 11. When landing flight modes lifting force created by the wing 2 and GIP 6, the horizontal pull - trehvaltsovoj propulsion system - two smaller screws 11 together with a large screw 20, in cruising flight wing 2 and GIP 6, horizontal pull, two - or single-screw propulsion system, respectively, the two smaller screws 11 or one large screw 20. On take-off and landing flight modes CTES in the creation of horizontal thrust, pushing his smaller screws 11 that have the same direction of rotation between itself and the opposite with pulling a large screw 20 and located in the tail, provide, without creating additional turbulence, a more even flow of the wing 2 and fuselage-nacelle 1, but rather increase the efficiency trehvaltsovoj propulsion system. During the transition from trehvaltsovoj propulsion system in a twin or single screw propulsion system and if there is a moment of pitch (M_z), he sultry deflection of the elevons 7 GIP 6, creating, working ahead of the wing 2, parrying force. After installing consoles LTP 10 with smaller screws 11 to a horizontal position along the lines of their horizontal thrust is in moznosti cruise. When performing technology short takeoff with trehvaltsovoj propulsion system console DSP 10 installed in an intermediate position -15° to achieve together with the horizontal thrust of a larger screw 20 maximum acceleration during the takeoff with simultaneous automatic deflection of the flap 7 and 13 at maximum angle for maximum lifting force GIP 6 and the wing 2, equipped with advanced and automatic accelerated phase deviation together with smaller screws 11 in the annular channels 12 down on the angle from -15° to -35° to achieve the two components of thrust in forward and vertical lifting.

Thus, CTAs with structural force double circuit having techventure propulsion system, war H-shaped tail split beams, is a hybrid aircraft longitudinal schematic Triplane with GTE for LNG and a reversible electric motor-generator. Three-bladed feathering-reversible push the screws in the annular channels, creating a horizontal and a corresponding deviation down an inclined rod, provide the necessary control points and reducing the distance when performing technology KVP. And GIP are located on the front of the wing and creates extra lift and unload it, and that predopredelyaetsya high pull of the trigger-hybrid capability SOO easy to implement and the implementation of technology KVP. The latter is very important for the deck base and, particularly, hybrid kites, as it provides a short take off and landing on the deck of the ship (it is enough 120-180 m) at the takeoff of tagavoranist not less than 0.7.

It is now known that structural force girder scheme, and especially in the aircraft longitudinal layout Triplane, provides maximum unloading the wing and fuselage-nacelle from the action of aerodynamic and mass forces, and the aircraft techventure propellers mounted and, especially, in maskilim space H-shaped tail that they are sustainable and manageable and, therefore, they are suitable for further engineering applications. Therefore, further studies on the formation of a hybrid kites and BTAS using the above-mentioned advantages, will allow them to understand their wider family.

Ultimately wide performance standards for hybrid next-generation aircraft will undoubtedly lead to the creation and development of hybrid kites providing really high technical and economic results that compete with the company "Volva Volare" (USA), which produces a similar hybrid electroanalyt mod. GT4. Weigh the empty plane from carbon 1175 kg, on Board can carry five people or 542 kg payload to a range of 1850 km When this limit is Naya takeoff weight Volva Volare GT4 is 1717 kg

The most important in modern conditions for these goals is the development of commercial CTAs with take-off weight 3400 kg for the transport of 8 persons with a total range of up to 2380 km in the implementation of technology KVP. To weigh an empty kites, made of carbon, will be no more 2290 kg when the weight of the batteries 1180 kg In its hybrid SU, comprising two electric motors with smaller screws with a diameter of 2.2 m and one D with a larger diameter 3,11 m (including the last one reversible electric motor-generator) total peak power of 600 kW and nominal - 330 kW, has a generator GTE (MC-150), which if necessary can provide an additional 117 kW (160 HP). Under favorable weather conditions, lithium-polymer battery that will allow CTAs is 0.8 to fly a distance of 1020 km at a cruising speed of 560 km/H. However, when the drop charging up to 25% of the maximum value will be included GTE and will be in flight, the rotating motor-generator, fuel batteries. Fuel his tank when running the DPC capacity is 110 kg of fuel, which is equivalent to an additional 1360 km Therefore, when performing KVP and having fuel on the flight time of 0.5 h, and even with the operation of the generator GTE, fuel efficiency for CTAs to 0.8 in the range of 1360 km is very impressive and will make 10,11 g/pass.-km (or 6,07 l per 100 km flight).

An important feature when the change-parallel hybrid technology actuator and concepts TRV-X1+2 in CTAs, providing qualitative growth of consumer properties, is that it is scalable and allows along with commercial CTAs-0,8 create and lungs, mid-range CTAs with Seating capacity of 30 and 48 people, developed on the platform of the aircraft girder schemes respectively su-80 and MiG-110. This CTES-3,0 can have three motor peak power 1440 kW (nominal D 792 kW) each and cryogenic CCD LNG type RK-65 EOF (power 1100 HP) with smaller screws with a diameter of 2.2 m and one pulling a large screw diameter of 3.9 m

You can learn and medium CTAs-11,0 on the basis of the Yak-44, made by girder with three electric motors peak/nominal power 4540/2500 kW each and cryogenic CCD LNG mod. TV7-SF with smaller and one large screws respectively with a diameter of 3.65 and 6.5 m, providing technology KVP takeoff weight of 42.6 t, will allow, with the criterion: useful load range, equal 32725 t-km (Ce-Liner 32300 t-km), to implement high technical and economic results that compete with Bauhaus Luftfahrt" (Germany), mastering electroanalyt Ce-Liner.

Cryogenic turboelectric aircraft short takeoff and landing made by the longitudinal scheme Triplane with canard war the H-shaped wings, see nirvanam to consoles low-lying wing in spaced beams, has a glider made of composite carbon fiber with smooth mate flows wing and fuselage, power plant, located on the aft pylon, transmitting power through the main gearbox and shafts of the transmission on the screws in the annular channels located in the nose and aft fuselage, providing horizontal and their corresponding deviations of the vertical rod, retractable tricycle wheeled chassis with nose auxiliary support, characterized in that it is double-girder scheme with a short fuselage-nacelle and the ability to change propulsion system in flight configuration as the plane with three different-sized feathered-reversible screws for the landing flight modes, and in the plane with two - or single-screw propulsion system for cruise flight, and back, which along with two smaller screws it is supplied along the plane of symmetry on minilevel transverse axis tail nacelle with large four-bladed propeller, the first of which have the same direction of rotation between itself and the opposite with the latter, with the aim of reducing losses for balancing while providing high load-bearing properties and smaller size and simple mechanization of bearing surfaces with the possibility of the membrane of its release/cleaning-mentioned front the horizontal stabilizer is equipped with elevons, as mentioned wing - megalochari and outer flaps, but also to provide transverse and longitudinal balancing management mentioned plumage includes console tselnopovorotnogo stabilizer with the ability according to their differential and common-mode rotation relative minilevel transverse axis together with the smaller screws from the horizontal position downward and upward respectively from 0° to -35° and 0° to +15°, with the aim of increasing the effective lengthening of the wing along with the reduction of the inductive resistance of the end portion of the wing, made with a positive angle +12° transverse V, have in-plane negative twist the end parts of the wing tips with the bent back ends of the lower surface of the latter sloped at an angle of 45° with smoothly formed a rounding bottom and a relatively sharp edge at the top, which reduces the intensity of the vortex behind the wing in the air flow coming out from under the lower surface of the wing relatively rounded in the plane of the unbent end of its respective sickle in terms of the ending, the power plant, made by parallel-serial hybrid technology power drive, equipped with the left and right electric motors mounted in the respective nacelle on the ribs of the respective calcev the x channel, gas turbine engine equipped with front output shaft for PTO on the gearbox larger screw and the output shaft for PTO, rotationally connected through output and input clutch, respectively, with a large screw and a motor-generator, is made reversible, and having a drive system including the electric motor and rechargeable batteries, there are input and output electromagnetic clutch that provides remote control of the engagement/disengagement, respectively, of the output shaft of the gearbox larger screw to the shaft of the motor-generator and shaft four-bladed pusher larger screw.