"maxinio" standard technology of vehicle manufacturing and operation, no-run take-off and landing electric aircraft (versions), lifting device, turbo-rotary engine (versions), multistep compressor, fan cowling, turbo-rotary engine operation method and method of electric aircraft lifting force creation method

FIELD: transport.

SUBSTANCE: set of invention relates to aircraft engineering. In the first version, no-run take-off and landing electric aircraft contains fuselage (1) with pillars (3) and helical fan in cowlings (2), lifting planes and chassis. Turbo-rotary engines (4) have generator units of the first and the second screws connected by electric circuit with electric motors (12,13) of the first (23) and the second (28) screw respectively of screw fan (11) installed on the front upper pillar (10). In the second version, no-run take-off and landing electric aircraft contains fuselage with upper and lateral pillars with fork at the end. In the fork of front upper pillar (10), turbo-rotary engine (4) with generator units having rotors on shafts of screw fan screws is installed, and in forks of front lateral pillars (48), electric motors (50) driven fans (49) are installed. Invention also covers lifting device, turbo-rotary engine, multistep compressor, fan cowling, turbo-rotary engine operation method and lifting force creation method.

EFFECT: improved flight safety and comfort as well as increased elevating capacity.

14 cl, 15 dwg

I. technical FIELD

The invention relates to the transportation of cargo and passengers, as well as to the production of transport machinery, mainly for the production of aircraft and air transportation, namely to design beaurocracy aircraft, vehicles and engines for them, economically, technologically and environmentally friendly operation through the use of ADEPTS (Single Technology Exploitation and Production of vehicles) in the aviation industry and air transport.

II. PRIOR art

The main disadvantage of aircraft aircraft and helicopter configurations - low safety in operation and a large cost in production, and poor profitability of their operation. Due to it low adjustability of the lifting force by adjusting the horizontal velocity and the associated speed limit regulation mainly at the lower end of a huge flight speeds, such as boarding. Even the landing, the minimum flight speed require specially trevillian and prepared areas, which sharply raises the cost of infrastructure in transportation and eliminates the comfort of such transportation and flights.

Constructive reason for this drawback is the aircraft itself is omonovca with a transverse load-bearing aircraft of planes. Helicopter layout more expensive aircraft in production and uneconomical operation and capacity, and flight speed.

In the helicopter layout comfort air is achieved at the expense of higher costs in the industry and a significant decline in the effectiveness of helicopters in operation.

Understandable dream developers aircraft around the world about the Association of the advantages of the aircraft layout with the comfort of a helicopter. However, practically they have chosen the direction of solving this problem by providing a lifting force vertical takeoff and landing (VTOL) additional lift engines or deviation and separation of the thrust engines with highly increased thrust. Eventually this trend stalled because meager capacity VTOL is inextricably linked with catastrophic increase in the speed of destruction of the bearing area used for takeoff and landing VTOL.

The proposed ETAPE (unified Technology Exploitation and Production Aircraft) not only eliminates the described disadvantages of aircraft and helicopter configurations. It provides the realization of the dream of developers about combining advantages of these serial technologies in one aircraft - electromigrate with more than Desaturate the th increased capacity at reduced 2-4 times the supply of electroanalyt. The author allows the opportunity to both reduce the horizontal speed to optimal, and its increase almost proportionally to the increase in carrying capacity. Despite the fact that comfort electrosolenoid technology is close to perfect.

Aerostatic lift force unfairly limited used in applied aerodynamics, for example in the way that the experiments in the wind tunnel, Pat. Of the Russian Federation No. 2063014, G01M 9/00 for 1996, based on the law of circulation movement. This narrow scope does not reflect the true meaning of this law for the global economy, and this error constructors aircraft complicates the life of the population of the globe, even in industrialized countries, increasing transport costs. And the importance of improving reliability of transport aircraft through the use of the law for the treatment of motion follows from the analysis of statistics of flight disasters resulting from flight accidents, failure of aircraft and lack of time the crew for making the right decisions when an emergency situation due to high speed flight.

The patent of the Russian Federation 2371598, F02K 3/072 2008 known turbopropfan engine with two generators in one gondola from the axial compressor, combustion chamber, turbine and nozzle located along the General flow of air. To the each part of the total free two-stage turbine between the generators rotate in opposite directions and transmits torque to windowancestor through two parallel shafts and two gearboxes.

When any value of the parameters of this engine is its second generator, gearbox and shaft to increase the weight of the engine at approximately 1000 kg. And weight of the aircraft, these pounds will increase further 4,000 kg. Therefore, each engine will increase the weight 5000 kg

Supermotor Klimenko, containing four of the shaft in four rotors, unacceptably inefficient due to the approval of the torque of the compressor and turbine each rotor by reducing the number of turbine blades (see http : //supermot.narod.ru/description_trd.html).

Corporotomy engine according to U.S. Pat. RF 2359140, F02C 6/02, F02K 5/00, F02B 53/06, F01C 1/073 for 2006 contains the compressor and the engine of the two rotors each with internal and external alternating between their rows of blades. The links between the paired rotors complicates the design and increases the weight of the engine and the machine.

The set of supporting planes, known in science and manufactured aircraft, consists of one at least of the wing and two half-planes or one plane tail.

By A.S. USSR №467570, B64C 3/18 for 1984 is known wing of the aircraft, made of plating attached to the power set of spars, ribs and stringers.

The set of supporting planes of an aircraft of canard configuration described in U.S. Pat. Of the Russian Federation No. 2000251, B64C 39/12 C is 1992, consists of two half-planes of monocryl connected by a Central wing with the fuselage, the two half-planes tail and front horizontal tail biplanes schema.

All known bearing plane and sets them to create a lifting force only in high-speed interaction of the apparatus with the air environment. The axial compressor of a gas turbine engine consists of rotating in the stator rotors, each of which contains spaced around the circumference of the sets of blades acting on the air flow passing through the flow channel, each set of impeller blades mounted on the crown of his drive and straightening stator vanes fixed to the motor housing between adjacent rotor disks (http://www.barrens.ru/?p=pecomp).

From the description of the patent of the Russian Federation 2268399, F04C 29/28 in 2006, is known for a built-in rotor of the multistage compressor of the gas turbine engine containing the axial part of the combined rows of blades in the United stages and sections.

The development of the aircraft showed nonoptimality of the axial alignment of the parts compressors with centrifugal.

Amp traction on patent 2344308, F02K 7/04 for 2006 has a hollow hemispherical Radome. The inner surface of the nose portion of the fairing with one, at least, a screen for changing the direction of the ejected stream at about evoprene.

The change of flow direction on the opposite associated with the occurrence of energy loss.

The patent 2375601, F02K 7/04 for 2006, there is a method of operation of the air-jet engine with traction modules pulse detonation combustion, including the mixing of fuel with air and burning the mixture in the cavity, the compressed fuel is evaporated in the heat exchangers. Mix a pair of fuel with air in the mixing chamber for detonation combustion, which serves down their heat engine with electric starter and generator.

The described method associated with an increase in the weight of the engines and apparatus, as it requires for its implementation a special heat engine with a generator.

Developers aircraft aircraft layout all over the world are trying to realize their dream of creating apparatus with a vertical take-off and landing in a blind way - solve the task of unifying the aircraft advantages in capacity and speed with comfort helicopter layout by separating thrust and reject it to perform the functions of lifting force. In the end, they received proved meager capacity of the VTOL YAK-141 and the like, but in addition catastrophically does not allow this construction into operation fantastically high erosion supporting surface rejected from the gas stream.

The closest in technical essence to the claimed unit slice of the wings is a box wing aircraft "Ilya Muromets" (http://aeroplan.boom.ru/shavrov/sh_cont.htm). It consists of upper and lower split on wingspan different extension, connected by a vertical connections. Seven sections of the upper and lower four are made of plating on the power set of the spar on the front edge of the stringer on the rear connected with ribs having a cross-sectional shape of the wing to interact with the air and connected with each other. The fuselage thus rigidly connected to the Central section of each wing.

The closest in technical essence to the claimed turboatomom the engine is turbopropfan engine (TWD) NK-93, consisting of zakuporivanija propfan and gas generator. The gas generator consists of a two-stage axial compressor, ka is a career combustion engines and five-speed turbine, from which the first and second stages transmit torque to the cascade high and low pressure compressor, and the third to the first screw, and the fourth and fifth free stage - the second screw propfan.

The engine has a traditional TWD weight and parameters, as well as unused resources to reduce weight and increase parameters of its work. The closest in technical essence to the claimed compressor is a compressor turborotor motor described in the patent of Russian Federation №2359140. It consists of two counter-rotating rotors - external and internal. Vane crowns the inner rotor is located on the rim of each disk, and alternating with them sets of blades of the outer rotor fixed to the inner surface of the shell is installed by means of bearings on the third shaft of the engine.

The outer and inner rotors of the compressor is connected with the outer and inner rotors of the engine, which significantly increases the weight of the known turborotor engine and limits the scope of it only as a drive gas compressor units.

The closest in technical essence to the claimed is the cowling of the engine NK-93, consisting of a set of ribs mounted on the input guide apparatus and mounted on the external and internal shells.

Under taccom shell is executing the inner surface of its cylindrical and her respective ends of the blades of the screws.

The closest in technical essence to the claimed method works turborotor engine is way ejector gain traction engine of the aircraft, containing the mixture of the ejected gas from the environment into the mixing chamber from the ejection of the mixture in the environment in the direction of motion of the aircraft and the change of flow direction on the opposite in the hollow fairing attached to the motor housing, the mixing chamber and/or the structural elements of the apparatus (see RF patent 2344308, F02K 7/00 for 2006).

The closest in technical essence to the claimed method of creating a lifting force is the method described in patent 2002671, B64C 29/00 (1991)

It consists of the formation of the accelerated fluid flow variable intensity and direction in the direction opposite to the movement above the support surface, while the enhanced stream are formed from two components, the intensity of which change simultaneously or differentially and change the direction of the thrust vector.

III. DISCLOSURE of INVENTIONS

The invention solves the problems of the introduction of a single technology exploitation and production aircraft to improve the operational capabilities of aircraft - electric planes while reducing cost and time in production is the rotary with improved safety and comfort of air travel and flights with the simplification of the infrastructure to handle operations with multiple traffic growth by reducing transportation time and expenses.

The essence of the invention lies in the fact that beaurocracy electroanalyt containing the fuselage with the cockpit and passenger cabin or cargo compartment, a power plant with a thrust reverser on pylons at the front of the fuselage, windowancestor and located in their air flow bearing surface, the air-start installation and control system, fuel, air conditioning and chassis with wheels of trucks on low pressure tires, has mounted on the front side pylons turborotor engines, equipped with generator sets the first and second screws, United electric circuit with the electric motors, respectively, the first and second screw propfan installed on the front upper pylon, and on the fuselage installed blocks slice of the wings on pylons, blocks on the forks of the upper ends of the front and rear pylons through the longitudinal beams or brackets, each corporotomy the engine is made with bestsforum compressor, each shell of windowancestor has a profiled inner surface and provided with upper and lower bearing blocks of sectors, with turbonet the turning engines made by chetyrehbalnoy scheme with the turbine stages of the opposite rotation, at the rear end of the fuselage and on the back of the pylon by means of brackets pivotally mounted handlebars rate and pitch with the possibility of sequential or simultaneous deviation of each wheel in his side.

Beaurocracy electroanalyt, which are installed on the front side pylons turborotor motors have a clutch and generator sets of the first and second screws, United electric circuit with the electric motors, respectively, the first and second screw top propfan, and blocks slice of lateral wings windowancestor supplied with fragments of the wing in the area of the gas flow from the nozzle turborotor engines with the temperature close to the temperature of the air environment.

Beaurocracy electroanalyt containing the fuselage with the cockpit and passenger cabin or cargo compartment, a power plant with a thrust reverser on pylons at the front of the fuselage, windowancestor and located in their air flow bearing surface, the air-start installation and control system, fuel, air conditioning and chassis with wheels of trucks on low pressure tires, its fuselage is equipped with front and rear top and side pillars with a fork at the end of each of them, in the front fork upper set corporotomy the motor is tel generator installations with the rotors on the shafts of the screws propfan, and in the forks of the front lateral - fans driven by electric motors, electrically connected with said generator sets turborotor engine with possibility of simultaneous switching on the generator set of the other screw on the ends of forks pylons set the respective ends of the longitudinal beams, each pair of which has a unit slice of the wings, the pie on the top pair, and on the side, straight, and placed them in sets console fragments, while the inner end of the rectilinear fragments block the lateral slice of the wings are placed in the longitudinal groove of the fuselage and the average of them, at least, connected with the power frame of the fuselage.

Block slice wings, containing the United brackets attaching them to the fuselage kits pie or straight-line segments in each wing, located in the air stream of the corresponding propfan, with each slice wing has a total area of the bearing surfaces is equal to the total area of the wing and empennage of an airplane of the same class, the ends of the longitudinal beams fitted with a slice sets of wings with the pie slices is fixed to the front and rear lateral pillars, and p is dolnych beams pie slices at the forks of the upper ends of the front and rear pillars, the height of the unit slice of the wings and the distance between the longitudinal beams is equal to the diameter of the shell corresponding propfan, and the curvature of the bearing surfaces of each piece, the chord cross-section defined by considering the velocity of the air flow propfan at the installation location of the fragment.

Corporotomy engine containing wincounter cowling, guide vanes connected with the front pillar and the gondola gas generator containing the middle and rear supports, a combustion chamber between the compressor and multi-stage turbine, the casing of which is connected to the nozzle, has bessmetrny compressor, the transmission of torque from the corresponding stage of the turbine to the screws and propfan rotors of the compressor is coaxial shafts, and for counter-rotation of the scapula on the crowns of turbine disks installed with a turn angle of 180 degrees, the inner surface of the outer compressor rotor made with confused-diffuser sections and the corresponding angle diffuser sections the ends of the blades.

Corporotomy engine has a first shaft located on the outside of the unit shaft and connecting the outer rotor with the first stage of the turbine and fulfilled the rear section and front, located in the front bearing support, a second shaft inner rotor with the second stage of the turbine, the third shaft of the first stage free turbine with the second screw propfan and fourth internal shaft of the first screw with the second and third steps of the free turbine.

Corporotomy engine containing wincounter cowling, guide vanes connected with the front pillar and the gondola generator, middle and rear support, a combustion chamber between the compressor and multi-stage turbine, the casing of which is connected with the nozzle mounted on the front side pylons turborotor motors have a clutch and generator sets of the first and second screws, United electric circuit with the electric motors, respectively, the first and second screw top propfan.

Corporotomy engine equipped with a two-stage compressor and each stage of it is made of rotary.

Corporotomy engine equipped with a two-stage compressor combined with a rotary compressor low pressure and with the guide apparatus between the shoulder crowns Polivanova the impellers of the compressor high pressure.

Corporotomy engine, in which the fourth and third shafts, connecting screws windowancestor with the appropriate stage of the turbine, where the s additional bearings in the middle part of each of them.

Bessmetrny polystyreny compressor turborotor engine containing successively installed ranks located around the circumference of the sets of blades with alternating rows with radiating ends of the blades with the series converging ends of the blades has an inner rotor mounted on the second shaft preventively disks and spacers, and each section of the outer rotor has confused the location for the castle end of the outer blades of the rotor and diffuser area located against the corresponding shoulder of the crown of the sets of rotor blades of the inner rotor, with front and rear air flow section of the outer rotor are increased in length by an amount sufficient to set up and mount straightener air flow devices, input on the front and output in the rear.

Shell propfan containing the input Kok connected with the outer and inner shells are mounted on the frame of a set of ribs connected with guide vanes mounted on the pylon, is a ring with a confused inner surface from the input end to the plane of arrangement of the front edges of the blades of the first propeller, which fades into the diffuser surface mating with a cylindrical output end, top and bottom with ctor shell provided with a bearing block of sectors with slotted channels between sectors of the block.

The way turborotor engine, including the division in the fan air flow on the threads of the first and second circuit with the acceleration of the flow by covering the screws windowancestor, the compressed air of the first circuit in compressor supply fuel into the combustion chamber and burning it for education accelerated gas stream, the selection of his energy in the turbine to compressor speed and screws propfan from the free turbine, the air flow of the second circuit accelerate through the interaction of a radially moving masses with diffuser inner surface of the shell and the ends of the propfan blades, and the first circuit - with diffuser surface of the outer rotor and the ends of the impeller blades of internal change the direction of their movement on axis, the air compression is performed in the compressor of two combined rotors counter-rotation with the simultaneous creation of a lifting force by the flow of the second circuit in the shells and slice blocks of wings.

The way to create a lifting force of electroanalyt, which convert the energy of the fuel in the engine and move the vehicle with the interaction of the bearing surfaces from the air environment, providing the beginning of the interaction generated by fan motors of air flow bearing what poverhnosti since the beginning of the rotation of the screw and horizontally move electromigrate through consistent communication of air flow it placed in these streams fragments, as for climb to a safe height from the point of touch in the Parking lot during takeoff with the exception of the horizontal movement of the inclusion of each of the reverse mode freezes and/or braking of the wheels of the chassis with the creation of the lifting force in the shells and slice blocks of the wings, when lowering from a safe height in hang mode for extra selected or planned the touch point when planting lifting force of electroanalyt create by means of the blower fan air flows blocks bearing elements of the shells and slice the wings, when you climb safely to the height of the flight level to the lifting force slice of wings from the fan flows is added to the carrying power from the high-speed interaction with the air environment these blocks slice of wings, and when planning to train to the point of tangency to a safe height to reduce the lifting force from the speed of interaction with the air environment through the inclusion of the control of pitch, rate and reverse in the braking mode with automatic relaying of wings in the hover mode is proportional to the speed reduction planning to hang above the touch point, and after hovering above the touch point regulate the magnitude of the lifting force of the engine revolutions and consequently the rate of flow of carrier systems ventilatory flows to control SC is the rate of vertical movement of the touch point.

IV. BRIEF DESCRIPTION of DRAWINGS

1 shows a front view of electroanalyt with turborotor engines on the sides of the pylons and the bearing surfaces, figure 2 is a top view of him, figure 3 - front view along arrow a and figure 4 - rear view of him by the arrow B.

Figure 5 - arrangement of the supporting sectors of the shells of windowancestor, figure 6 - cross-section plane C-C shell figure 5.

7 is a structural diagram turborotor engine, Fig - a fragment of the outer and inner rotors of the compressor with the input and output of a rectifying devices and Fig.9 - scan vane crowns the turbine stages. Reverse thrust conventionally not shown.

Figure 10 is a top view of electroanalyt with turborotor engine on the front pylon and fans on the side, with a sector bearing surfaces on the upper pair of longitudinal beams. Conditionally on the upper pair of lateral beams shown cantilever bearing surface (11), and the lower pair of rectilinear bearing surface of the reinforced bars on the top and bottom beams (Fig).

On Fig, 14 and 15 shows the trajectory of electroanalyt at various stages of the flight and the conditions on the route: in the presence of high-rise buildings on the flight trajectory of the flight, free from them, and in extreme cases, respectively.

V. IMPLEMENTATION of INVENTIONS

Electroanalyt in Fig. 1, 2 comprises a fuselage 1 with turborotor engine 2 installed in front of the front pillars 3 shell 4 windowancestor. At the ends of the sectoral part of the pylons strengthened the ends of the longitudinal beams 5, the rear ends of which are connected with the rear pillars 6 of the respective party. Turborotor the 2 engines have thrust reversers grating 7, and each pair of beams 5 unit installed from the top 8 and bottom 9 slice of wings. On the top of the pylon 10 is wincounter 11, the shaft of the first screw which is connected to the motor 12 and the second screw him with an electric motor 13. Shell 4 windowancestor made with blocks of sectors supporting elements top and bottom with slotted channels 14 between the elements. Each slice wing unit 15 slice of wings mounted on the fuselage by means of brackets 16 or longitudinal beams connected with strengthened by the forks of the upper front and rear pylons (not shown) or at the ends of the sectoral part of the side pylons. The layout of the unit slice of wings mounted on the brackets, is preferred for wide-body electric planes large carrying capacity, as in combination with windowancestor on the front upper pylon number of slice wings are practically unlimited. The combination turborotor engine block slice the wings on the side is the Ylon limits the capacity of the unit due to non-installation of the fragments in the front and the Central zone due to the high temperature of the jet from the nozzle.

On the side of the rear end of the fuselage by means of brackets pivotally mounted handlebars course 17 and on the upper side and the lower side of the ends of the drive pitch 18. Side pylons 3 instead of pie part 19 (3) may be approved for engine nacelle and the upper pole 10 with a fork at the upper end for connection to the ends of the front forks and rear ends of the longitudinal beams. Conventionally not shown handlebars rate and pitch on the rear pylons 6 (figure 4) and the generator set with clutch shafts of the third and fourth.

The elements 20 blocks of the upper and lower sectors of the shell 4 on 5, 6 provided with bearing surfaces, calculated at an arbitrary speed of the air flow entering the engine main modes of engine operation at takeoff and in-flight electroanalyt.

Corporotomy engine 7 consists of a propfan 4 and generator, made of restating compressor 21, the combustion chamber 22 and a five-speed turbine.

The first screw 23 propfan connected to the fourth internal shaft 24 with steps 25, 26 of the turbine and has bearings 27 in the middle part. The second screw 28 is connected to the third shaft 29 with the first stage 30 of the free turbine and has one bearing 31 in the middle. On the second shaft 32 mounted disks 33 of the inner rotor and each disk 33 is connected vane crowns of p is ecstasy 34 and the subsequent 35 speed of the inner rotor of the compressor. Each additional blade crown 34 and 35 completed or connected to the spacer 37 (Fig).

The outer rotor is made of circular sections, each of which has confused plot 38 to position the blade set and diffuser section 39 for engagement with a radially floating part of the air flow. Front length 40 and 41 of the rear section is increased by an amount sufficient for installation and fastening of the rectifying devices 42, 43. The lower ends of the blades of these machines are connected respectively with the front 44 and 45 rear section of the first outer shaft 44 of the outer rotor (Fig).

For the opposite direction of rotation of each stage vane crowns have blades that are installed by 180 degrees (figure 9): the blades on the turbine disks in stages 2, 4 and 5 are installed with angle plus 180 degrees relative to the angle setting them on the crowns of steps 1 and 3.

Works corporotomy engine "Maxino as follows.

Since the beginning of the rotation of the screws 23, 28 of the engine 2 and/or windowancestor 11 their impact on air creates an air stream and exit the shell and the entrance to it. When this part of her stream is divided into streams of the first and second contours. In turbojet engines of any known composition both stream is converted to directed horizontally t the se. And the thrust of the plane, standing in front of the Parking pads, and the lifting force is equal to zero, since transversely located wing its not blown by the thread of the screw. The lift force appears with the beginning of the horizontal movement of the aircraft and small safe for the device and loads it speeds it remains insufficient for flight, i.e. it is much less than the takeoff weight of the apparatus. Enough to take off it is only at extremely high speeds, dangerous for the system and the environment, and to ensure its aircraft layout can only on the maximum engine operating conditions one or four of the ships. Naturally, to get used to that dB is almost impossible and unacceptable. And getting rid of them developers aircraft not found for more than a century, their production and operation. And as zealously continued the marked non-use of redundant resource - air flow entering the first and second circuit known engines. In the compressor of the first path of the air stream is compressed by rotation of the transfer of energy from the blades to the flow and the loss of part of its each guide device. But these losses are not as obvious as the doomed aircraft layout on eposredstvennoe control lifting force by adjusting the horizontal speed.

Included in the confused part of the shell air flow enters the slit 14 (6) block bearing elements 20. Direct the jet of elements along the cracks between them, this thread creates a lifting force on each of them, which is summarized in sectors and shells in the part of the total lifting force of electroanalyt.

Passed through the shell and receiving the acceleration from the screw thread, direct the jet of the sequence of each fragment block 8, 9, or 15 slice of wings, creates a lifting force on each of them. Since the total area of each slice of the wing is equal to the sum of the bearing surfaces transversely spaced aircraft wing and tail surfaces, the total area of the blocks 15 a fragment of the wing exceeds the area of the bearing surfaces of the airplane of the same class in a number of times equal to the number of slice wings electroanalyt. Shown in figure 1 the layout, it is at least 8 and, accordingly, when the aircraft speed HBS the VA their lifting power electroanalyt will be 8 times more. And the flow rate from the screws, and especially the jet from the nozzle, are many times greater than the flight speed of the aircraft. Hence, the total lifting force his will exceed 9-10 times the power of similar characteristics of the plane even without power rings of windowancestor. And a significant improvement in the conversion of the air flow in the first circuit further increases the total lift force of electroanalyt.

The exception of guide vanes of the design of the rotors of the compressor not only reduces the length of the engine by almost a meter and a significant weight. After passing through the first flow path through a rectifying device 42 (Fig) consistently exposed blades of the inner rotor mounted on the rims of the disks 33, 34 and 35. Radial drop these blades to cone sections 39 air masses get their axial displacement. Immediately following the teachings of the energy from the blades of the speed of the inner rotor to flow under the influence of the blades counter-moving blades of the outer rotor installed on confused sections 38 of each stage. The inner ends of the blades of the rotor have a lower circumferential speed and to the same centrifugal force is directed to the root ends of the stage and profiling spacers 37 are not appropriate. However, the effectiveness of the counter-effects of l is patok flow significantly increases the efficiency restating compressor 21 in compressing the air. The arrangement of the blades on the turbine disks of the first 45 and third stage 30 (Fig.9) provides clockwise rotation, and the second 36, 25 fourth and fifth 26 degrees counterclockwise.

It can be assumed that the effectiveness of the reciprocal transfer of energy in bestform the compressor 21 from the shoulder blades of his air flow will increase so that in nine speed rotary compressor, the compression ratio can reach up to 12-14 atmospheres instead 10.8 V two stage with fourteen steps.

And increase the compression ratio at the output of the rectifying device 43 of the compressor before the combustion chamber 22 increases the kinetic energy of the gas stream from the camera and, accordingly, the torque at each stage of the turbine. The consequence is an increase in the flow rate of the first and second paths, and consequently the lifting force and thrust electroanalyt. The fuselage electroanalyt figure 10, 11 and 12 is supplied with front pylons 48 strengthened by the forks of late, have corporotomy engine with 4 generating units of windowancestor on the top and the fan 49 motor 50 on the shaft of the fan on the side pylons. Block a pie slice of the wings 15 is mounted on the longitudinal beams 5, the ends of which are connected to the ends of the forks of the upper front 48 and rear pylons 6.

Generator installation is key propfan turborotor engine (not shown) electrically connected with the electric motors 50 simultaneous reciprocal switching them. The optimal layout of electroanalyt is a layout with a set of console rectilinear fragments 51 (figure 10, 11). For lower-speed electric planes local airlines acceptable layout with block rectilinear fragments 52, mounted on longitudinal beams by means of rods 53 (figure 10, 12).

Operate electroanalyt, adjusting the lifting force of the engine speed during all phases of flight with a separation from his touch point in the Parking lot or by lowering on extra selected or planned touch point.

The ability to create a lifting force without horizontal movement, a multiple increase of the total area of the bearing surfaces with the exception of use for takeoff takeoff mode engines, with the exception of the impact of human factors to aviation security and flight significantly increase the carriers ' capabilities and ensure the competitiveness of United technologies exploitation and production of vehicles.

The ability to create and control the lifting force of the engine revolutions provides the use for the beginning of the flight and the completion of any loose from the buildings ground settlements square, squares, intersections, vacant lots, parcels, streets, and history enterprises and roofs of industrial and residential buildings,stadiums and other sports facilities, the shores and waters of the rivers and lakes.

Operate electroanalyt as follows.

Example 1

Start a fully loaded electroanalyt requires maximum lifting force. Stalling his Parking pads or brake wheels, run corporotomy engine 2 and include electric motors 12, 13 propfan 11. With the first revolutions of the screws air flow from the blades create a gradually increasing lifting force as the output of the engine at idling speed. Depending on the type of space in which to fly electrostimulator, the pilot determines the piloting technique to control the lifting force. If the trajectory of the upcoming horizontal movement there are obstacles (Fig - tower transmission lines, communication, pipes enterprises and so on), the pilot includes reverse thrust and increases the speed of the motors and/or fans to such, on which the lifting power unit 15 slice the wings will exceed the takeoff weight of electroanalyt and will tear off its wheels from the touch point in the Parking lot. As repeatedly increased the total area of the blocks 8, 9 and 15 slice of the wings provides a separation of electroanalyt from the Parking lot at the speed of 0.3-0.4 nominal rejected the thrust reverser to be insignificant and, accordingly, the rate moved the I back - it will not be more pedestrian-step. This speed provides the set of height-shift back full control of the process to set safe altitude (l). It reverse off and electroanalyt begins to set the horizontal speed at altitude. To exit to a safe height, he emerges with increasing horizontal speed to such, which become effective aerodynamic handlebars course 17 and pitch 18. After that, the pilot puts electroanalyt mode cabrerana at the speed required to perform the flight task or exit flight level. As well as in flight at FL lift force is created fan blower units 8, 9 and 15 slice of wings and shells 4 windowancestor 11, to which is added their carrying power from the high-speed interaction with the atmosphere, cruising mode electric planes at the speed of the engine below the cruising mode airplane of the same class. This provides a significant increase engine life and efficiency of air transportation.

When approaching the destination electroanalyt plans from the top of the echelon to a safe height in the direction to the target touch point. In certain previous flights or experience of the pilot point of the trajectory of the flight at a safe altitude include reverse thrust, rudders course 7, pitch 18 in the braking mode, only reverse or only controls the rate of speed reduction of electroanalyt to hang over the next touch point. After you hang the engine revolutions regulate the speed of vertical descent at touch point with a short-term increase in turnover to ensure a soft touch with a speed of 0.3-0.15 m/sec.

Example 2

Create a start lifting force, variable speed motors, perform described in example 1. In the absence of the horizontal moving direction of tall obstacles after separation electroanalyt from the touch point in the Parking lot at the same time he gains a safe altitude and the speed of horizontal movement. At this altitude the engine revolutions increase to achieve the height and speed required for the continuation of the flight planned route. At the end of flight or approach to planning the touch point planning electroanalyt performs with rudders course 17 and pitch 18 in the braking mode. The pilot selects the beginning of the planning of the calculation of the horizontal velocities approaching the touch point and the reduction in the height, with full control of the process on the actual approximation and reduction. If there is a noticeable deviation reduction or approximation include short-term reverse thrust mode tarmogen who I am. And when slowing down one of these options adjust the landing, turning off wheels from braking mode (Fig).

Example 3

The beginning of the flight performed as described in examples 1 and 2.

When the occurrence of an emergency situation during the flight, the pilot determines whether it is abnormal or emergency. In case of emergency he urgently eliminates dangerous flight parameters - altitude and horizontal speed. This includes reverse thrust, rudders course 17 and pitch 18 in the braking mode and translates electroanalyt in steep planning to a safe height and at the same time when this selects the point of the forced touch. At a safe altitude, continuing the approach to the selected touch point, controls the transition flight mode hangs above the selected touch point. And after you hang the pilot adjusts the lowering of the touch point speed of the motor(s) to the soft touch. After touching the crew determines the degree of complexity of the failure of systems electroanalyt and, if possible, corrects the problem, or call the specialists to eliminate failure. And after a fault completes flight on the base or on the route (Fig).

Option BNPP with turborotor engine on the front of the upper pole 10 has better features maximum capacity with minimum power is voorujennoi.

The difference between this electroanalyt described, except for the location Trott is running generator set with rotors on the shafts of the screws windowancestor this Trott, and in the forks of the front side of the pylons 48 installed windowancestor 49 from the motor 50. The electric circuit from the generator set to the motor side windowancestor performed with simultaneous switching of the generator set one screw to install the other screw. The bearing surfaces are made of the sector bearing surfaces 15 on the upper pair of longitudinal beams 52 and straightforward or console 51 of the bearing surfaces on the side.

The similarity of the technical results of the described variants of BNPP clearly follows from similar sets of features of their structures and functions:

- conversion of mechanical energy Trott into electrical energy for conversion in which the kinetic energy of the air flow, creating a lifting force is not associated with the horizontal speed;

- longitudinal location of the bearing surfaces.

Trott transmission of rotation from the turbine stages of the screws 23, 28 and propfan rotors of the compressor and the counter-rotation by shafts and turbine blades mounted on each subsequent stage of the turbine 45, 30 and after which it a pair of disks by 180 degrees (Fig.9).

VI. INDUSTRIAL APPLICABILITY

Described in this application and the applications 2010100721, 2010119884 layout of aircraft and methods for their exploitation illustrate only a part of the technical result and benefits of unified technology exploitation and production of aircraft - electric planes. And even though these benefits - guaranteed security electrocatalytic beaurocracy airline and flight with reduced costs of production and operation, with reduced range of devices and in industry, and in operation is enough to prove the industrial applicability of ETAPE.

In ETAPLE very important factor is increased by an order of capacity, compared with the aircraft layout. As well as an increased capacity electrosolenoid layout possible with a simultaneous decrease in 2-4 times the supply of electroanalyt, then for any manufacturer of aircraft and helicopters, the more interest in the production of these expensive production uneconomical and dangerous in operation of the apparatus will disappear by itself. And for carriers unlimited possibilities in traffic to impossible for planes comfort also exclude any choice between ETAPE and aircraft-helicopter technology. This follows from the fact that PL is the venues for takeoff and landing electric planes can be used the area around the city: the intersections of streets and squares or designated areas on the outskirts, evenly spaced on the periphery of cities, suburbs, villages.

The combination of the layout of electroanalyt composite wings in ventilator flow provides a manifold increase in the total bearing area, which in turn provides a lifting force greater takeoff weight electroanalyt already on the engine rpm below the nominal mode of engine operation. And this immediately eliminates two problems with aircraft technology: no operation takeoff decibels, as necessary, in the selection and arrangement of huge areas of the country airfields with runways, taxi-ways and lighting equipment on them.

Aircraft long-haul layout class TU-154, BOEING ERB AC not connected with four engines on a supporting plane. In electrocatalytic builds their capacity can provide one engine. Safety rules have to put two engines in electrosolenoid layout. Accordingly, when the weight of one engine of this class 2500 kg weight reduction of electroanalyt by reducing the number of engines from four to two is 2500×2×4=20000 kg this technical effect of the claimed electrosolenoid arrangement, the weight of each of the two engines is reduced by the weight of six to nine drives the compressor. Accordingly, the weight of electrosmog the ETA on 50×9×4=1800 kg In sum, the relief of electroanalyt will be 20000+1800=21800 kg, respectively, this value will increase the capacity electrosolenoid layout.

As well as electroaparatna technology fits perfectly into the infrastructure of cities, ETAPE turns into reality the implementation of what was previously considered unattainable principle of air "from the front door to entrance". That means savings in transport costs and time and, consequently, increasing consumer services of air carriers.

Thus, repeatedly proven industrial applicability of ETAPE in the aviation and transportation, as well as similar applications in engine building, automotive and transport, shipbuilding and possibly in rail transport will certainly determine the translation of these industries on ETAPE.

1. Beaurocracy electroanalyt containing the fuselage (1) cab and passenger or cargo compartment, with pylons (3) in the front part of the fuselage and windowingsystem in the shells (2), the bearing surface and the control system, fuel, air conditioning and chassis with wheels of trucks on low pressure tires, characterized in that mounted on the front side pylons (3) turborotor engines (4) have a generating set of the first and second screws, United electric is a chain with electric motors (12, 13), respectively, of the first (23) and second (28) screws propfan (11)mounted on the front upper pylon (10), and on the front side (3) and rear (6) piers, beams (5) fuselage mounted bearing plane of the top row (8) and the bottom number (9), the supporting surface (15) on the forks of the upper ends of the front (10) and the rear pylons with the longitudinal beams or brackets (16), each corporotomy engine (4) is made with composite rotors counter-rotating compressor 21), each shell (2, 14) propfan provided with bearing surfaces (18, 19) of the upper and lower sectors (20) shells, with turborotor engines made by chetyrehbalnoy scheme with the turbine stages of the opposite rotation, and at the rear end of the fuselage and the rear pylons (6) by means of brackets pivotally mounted handlebars rate (17) and pitch (18) with sequential or simultaneous deviation of each wheel in his side.

2. Beaurocracy electroanalyt according to claim 1, characterized in that mounted on the front side pylons (3) turborotor engines (4) have a clutch with generator sets the first and second screws, United with electric motors (12, 13) respectively of the first (23) of the screw and the second screw (28) upper propfan (11), and a series of bearing surfaces (8, 9) of the side art is the NOC have a bearing plane in the zone of gas flow from the nozzle turborotor engines with temperature, close to the air temperature.

3. Beaurocracy electroanalyt containing the fuselage (1) cab and passenger or cargo compartment, with pylons (3) in the front part of the fuselage and windowingsystem (2), the bearing surface and the control system, fuel, air conditioning and chassis with wheels of trucks on low pressure tires, characterized in that the fuselage it is equipped with top and side pillars with a fork at the end of each of them, in the front fork top (10) installed corporotomy engine (4) with generator sets, with the rotors on the shafts of the screws propfan, and in the forks of the front side (48- the fans (49) with the drive of each of them from electric motors (50)electrically connected with said generator sets turborotor engine with possibility of simultaneous switching on of the generator set of the other screw on the ends of forks pylons set the respective ends of the longitudinal beams (5), each pair of which has a bearing plane, pie (15) on the top pair, and side - straight (52) or placed them in sets of cantilever bearing planes (51), while the inner end of each bearing plane placed in the longitudinal groove of the fuselage and the average of them, at least, is connected with the power frame.

5. Corporotomy engine containing wincounter cowling, guide vanes connected with the front pillar and the gondola gas generator containing the middle and rear supports, a combustion chamber between the compressor and multi-stage turbine, the casing of which is connected to the nozzle, characterized in that the transmission of torque from the corresponding stage of the turbine screws (23, 28) and propfan rotors of the compressor is sudestada coaxial shafts, as for counter-rotation of the rotor blades on the crowns of turbine disks installed with a turn of the installation of 180°, the inner surface of the channel of the outer compressor rotor made with confused-diffuser sections and the corresponding angle diffuser sections the ends of the blades.

6. Corporotomy engine according to claim 5, characterized in that the first motor shaft, located on the outside of the unit shaft and connecting the outer rotor with the first stage (45) turbine made from the rear section (44) and the front beneath the bearing in the front leg, the second shaft (32) - inner rotor with the second step (36) of the turbine, the third shaft (29) - the first step (30) of the free turbine with the second screw (28) propfan and fourth internal shaft (24) - the first screw (23) with the second (25) and third (26) the speed of the free turbine.

7. Corporotomy engine according to claim 5, characterized in that the compressor it is made of two stage and each stage of it is made with a combined counter-rotating rotors.

8. Corporotomy engine according to claim 5, characterized in that the compressor it is made of a two-stage combined with the low-pressure compressor with the guide apparatus between the vane crowns the iterative impellers of the compressor high pressure.

9. Corporotomy engine according to claim 5, otlichalis the same time, that fourth (24) and third (29) shafts, connecting screws windowancestor with the appropriate stage of the turbine, equipped with additional bearings (27, 31) in the middle part of each of them.

10. Corporotomy engine containing wincounter cowling, guide vanes connected with the front pillar and the gondola gas generator containing the middle and rear supports, a combustion chamber between the compressor and multi-stage turbine, the casing of which is connected to the nozzle, characterized in that the transmission of torque from the corresponding stage of the turbine screws (23, 28) and propfan rotors of the compressor is coaxial shafts, and for counter-rotation of the rotor blades on the crowns of turbine disks installed with a turn of the installation of 180°, the inner surface of the channel of the outer compressor rotor made with confused-diffuser sections and the corresponding angle diffuser sections ends the blades.

11. Polystyreny compressor turborotor engine containing successively installed ranks located around the circumference of the sets of blades and alternating rows with radiating ends of the blades with the series converging ends of the blades, characterized in that it is made with offset rotors counter-rotation, for which the internal rotor you Olsen installed on the second shaft (32) preventively disk (33) and spacers (37), and each section of the outer rotor has a confused plot (38) for accommodating the locking end of the outer blades of the rotor and diffuser section (39)that is located against the corresponding shoulder of the crown of the sets of rotor blades of the inner rotor, with the front (40) and rear (41) air flow section of the outer rotor are increased in length by an amount sufficient to set up and mount straightener air flow devices, input (42) on the front and the output (43) on the back.

12. Shell propfan containing the input guiding device, the ends of the radial guiding pillars which are connected with the outer and inner membranes at the periphery and a support with a cook in the centre, a shell mounted on the frame of a set of ribs connected with guide vanes mounted on the pylon, wherein the shell is made with a confused inner surface (46) from the input end to the plane of arrangement of the front edges of the blades of the first propeller, which fades into the diffuser surface (47), coupled with the cylinder on the output end, with the upper and lower sector of the shell provided with bearing surfaces with slotted channels 14).

13. The way turborotor engine, including the division in the fan air flow on the threads of the first and second is on contours with acceleration thread screws vintagetelevision, the compression of air in the primary circuit in the compressor (21), a supply of fuel into the combustion chamber and burning it for education accelerated air flow, the selection of his energy in the turbine to compressor speed and screws propfan from the free turbine, characterized in that the second air flow path through the interaction of a radially moving masses of air flow from the diffuser inner surface (47) of the shell and the ends of the propfan blades, and the first circuit - diffuser surface (39) of the outer sections of the rotor and the ends of the impeller blades of internal change the direction of their movement on the axis, the air compression is performed in the compressor of two combined rotors counter-rotation with the simultaneous creation of a lifting force by the flow of the second circuit in the shells and bearing devices.

14. The way to create a lifting force of electroanalyt containing formation accelerated air flow variable intensity directed in the direction opposite to the direction of movement of electroanalyt, and regulating the intensity of these flows, characterized in that provide the beginning of the interaction generated by the fan air flow with the bearing surfaces since the beginning of the rotation of the screw and regardless of horizontal movement of the electron is of rozavlea through consistent communication of air flow bearing planes to climb to a safe height from the point of touch in the Parking lot during takeoff or lowering from a safe height for extra selected or planned point of tangency with the exception of horizontal movement, which create a lifting force by means of blower bearing surfaces (8, 9, or 15), and when set from a safe height to the height of the flight level to the lifting force mentioned carrier planes from the fan flows is added to the carrying power from the high-speed interaction with the air, and in the planning of flight level to a safe, extra or standard, reduce the lifting force from the high-speed interaction of the bearing device with the air through the inclusion of the control rate (17) and pitch (18) in the braking mode, the change is thrust engines reverse and reduce the speed, and the speed reduced to hang above the touch point and after hovering above the touch point adjust the lifting force of the engine revolutions and the speed of the fan flow to control the speed of vertical movement of the touch point.