The power plant of the aircraft vertical takeoff and landing |
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IPC classes for russian patent The power plant of the aircraft vertical takeoff and landing (RU 2210524):
B64D27/12 - within, or attached to, wing
 The propulsion system and rotary engine / 2171906
 The main gearbox of the helicopter / 2065381
The invention relates to aircraft and solves the problem of simplification of construction of the main gearbox of the helicopter, improve reliability and extend the service life of his work
 The method of vertical run and forced landing apparatus with soft gazonapolnitel wing / 2205131
The invention relates to the field of aviation
 Apparatus with dynamic maintenance / 2205119
The invention relates to aircraft with vertical takeoff and landing and amphibious vehicles
 Lifting and balancing unit of the aircraft vertical takeoff and landing / 2204505
The invention relates to the field of aviation
 The vehicle with vertical takeoff and landing / 2198113
The invention relates to the field of helicopter industry
The power plant of the aircraft / 2196914
The invention relates to the field of engineering, in particular for aircraft and engines, namely, aircraft
The power plant of the aircraft / 2196913
The invention relates to the field of engineering, in particular for aircraft and engines, namely, aircraft
 Twin-engine multi-role aircraft land and water-based with short and vertical takeoff and landing "ladoga-9 hc" / 2196707
The invention relates to aircraft
 The aircraft vertical takeoff and landing / 2194651
The invention relates to aircraft heavier than air
 Aircraft with gazoturbinnymi engines / 2190560
The invention relates to the field of aviation and, in particular, to aircraft vertical takeoff and landing and can be used when creating
 Vertical takeoff and landing flying vehicle / 2244661
Proposed flying vehicle has fuselage, wings, air flow generators and control system including vertical rudders which are symmetric in profile and are mounted behind wings in way of air flows. Fuselage is provided with two aerodynamic boxes which are longitudinal extensible and have rectangular apertures in outer side face; arranged in each said box are wing and air flow generator. Aerodynamic boxes are provided with reducer mechanism for synchronous transmission of torque from high-speed engines of tubular shafts of aeroturbines. Control system includes vertical and horizontal rudders located in aperture of each aerodynamic box. Wing is provided with slat and flap. Air flow reflector is mounted above wing over entire length at varying angle of attack. Fuselage is provided with vertical tail and horizontal tail and may be provided with landing skis. Each high-speed engine is made in form of shaft-turbine engine. Air flow generators are provided with axial-flow compressors; each compressor is located in rectilinear tube of tubular air ducts near intake unit on shaft secured in bearings. Boxes may be provided with reducer mechanism for synchronous transmission of torque from aeroturbine shafts to shafts of axial-flow compressors. Vertical rudders may be provided with flaps.
 Rotoroplane / 2245824
Proposed rotoroplane has fuselage located between two rotors with wings whose longitudinal axes are located in horizontal planes, wing angle-of-attack control mechanism and engine. Each wing consists of separate thin-profile blades; the profile is symmetrical relative to chord; blades are mounted at spaced relation and are connected into integral wing by means of ribs on which semi-axles are mounted; these axles are received by holes in struts rigidly connected with rotor shaft. Reflecting board-wing is mounted after each rotor in parallel with axis of its shaft on framework secured on tail boom; this board-wing is directed to rotor whose section is made from deformable material. Wing angle-of-attack control mechanism has hub with rings mounted on cylindrical surface of its free end; these rings are connected with tenon on rib of each wing by means of rod. Other part of hub is located in ports of vertical and horizontal slide blocks moved simultaneously with hub relative to axis of shaft of rotor passing inside this hub. End part of rotor shaft is provided with ring for elimination of action of gravity load; this ring is rigidly connected with strut on tubular part of rotor shaft; its cylindrical surface is received by grooves secured on fuselage.
Rotoroplane / 2245824
Proposed rotoroplane has fuselage located between two rotors with wings whose longitudinal axes are located in horizontal planes, wing angle-of-attack control mechanism and engine. Each wing consists of separate thin-profile blades; the profile is symmetrical relative to chord; blades are mounted at spaced relation and are connected into integral wing by means of ribs on which semi-axles are mounted; these axles are received by holes in struts rigidly connected with rotor shaft. Reflecting board-wing is mounted after each rotor in parallel with axis of its shaft on framework secured on tail boom; this board-wing is directed to rotor whose section is made from deformable material. Wing angle-of-attack control mechanism has hub with rings mounted on cylindrical surface of its free end; these rings are connected with tenon on rib of each wing by means of rod. Other part of hub is located in ports of vertical and horizontal slide blocks moved simultaneously with hub relative to axis of shaft of rotor passing inside this hub. End part of rotor shaft is provided with ring for elimination of action of gravity load; this ring is rigidly connected with strut on tubular part of rotor shaft; its cylindrical surface is received by grooves secured on fuselage.
 Superlight vertical takeoff and landing flying vehicle / 2246427
Proposed flying vehicle includes lifting system made in form of plate-type dome and suspension system made in form of engine mount on which engine, pilot seat, fuel tank and cargo cassette are mounted. Dome skin is made from elastic plate members located in seats of framework for turn under action of counter flow of air. Suspension system is connected with dome by means of suspension unit through extension mechanism consisting of two articulation-and-leverage systems in form of pantographs and kinematically linked with engine. Suspension unit is made in form of cross-piece located between articulations at points of intersection of longer and upper levers of pantographs and connected with them over common axial line. At the top, said cross-piece is articulated with rod rigidly secured in dome framework. During operation of engine, pantographs are folded or extended. Flying vehicle performs translational motion due to deflection of dome by means of hydraulic cylinders mounted in suspension unit at ends of cross-piece and articulated with dome through rods. Oil lines of hydraulic cylinders controlled by pilot are located on longer levers of pantographs. Transversal and longitudinal stability of pantographs is achieved due to availability of stabilization unit located between articulations at points of intersection of longer and shorter levers of pantographs. According to second version, engine is used as vertical stabilization unit which is made in form of cylinder installed on engine mount with piston and upper and lower combustion chambers arranged inside it. Engine piston is connection with extension mechanism.
 Ground situation observation system / 2248307
Proposed system is provided with on-board observation and tracking complex mounted on board of unmanned flying vehicle and provided with command receiver, observation and tracking chamber, image transmitter, microprocessor, altimeter, platformless inertial unit, analog-to-digital converter, formatting unit, data compression unit, two storage units, correlation unit, servo unit and actuators. Correlation unit is used for shaping the signal of correlation function of two images received from storage units and feeding this signal to one of microprocessor inputs for converting this signal to control unit commands of servo unit. Mobile observation and control complex is provided with image receiver for reception of video signal from transmitter via radio channel, portable computer, command transmitter and exposure shaper.
 Vertical takeoff flying vehicle / 2249541
Proposed flying vehicle is made in form of body of revolution at vertical axis. Proposed flying vehicle is provided with axial-flow rotary compressor, engine with fuel and heat-insulated receiver connected with compressor. Flat back bottom of receiver has through holes of small diameter which are inclined to side opposite to takeoff and rotation of compressor rotor-propeller. Receiver is provided with four flaps for closing the holes for creation of trim of flying vehicle. Compressor rotor-propeller takes air in front of flying vehicle and delivers heated air to heat-insulated receiver. Air is expanded into surrounding medium through holes made in receiver bottom used as load-bearing area for flying vehicle surface. For performing horizontal flight, trim shall be formed by means of flaps in the direction of motion.
 Aircraft and method of its operation / 2250181
Proposed aircraft has central cabin 1 located in center of annular wing 3.Located in gap between central cabin and annular wing are several swivel units 101-112 of propulsor. In hovering mode, propulsor units are turned for creating lifting force. In cruise mode, propulsor units are turned for creating direct thrust. Spatial position and motion of aircraft may be controlled by individual or joint control of thrust and angle of turn of propulsor units.
 Device for creating lifting force by means of continuously revolving impeller / 2252898
Impeller is mounted at axis parallel to axis of Earth surface. Device is provided with casing mounted near external periphery on side of creating anti-lifting force of impeller having axis parallel to axis of Earth surface. For unbalance between lifting force and anti-lifting force, use may be made of cylindrical wheel with spiral blades which is located in impeller cavity; it may rotate together and concentrically with impeller.
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The invention relates to aviation. The power plant contains two turboshaft engine (TVD), left and right, fixedly mounted on the respective tail beams. The axis of the output nozzle of each theatre directed to the intersection of the corresponding keel with the corresponding elevon. TVD are connected by a transmission with two air screws (top and bottom) of the right and left rotation, mounted on the gearbox in the cutout of the center section above the center of gravity of the aircraft. The gear set by means of two support tubes with the ability to swing in the plane of symmetry of the aircraft. The support pipe of the Central gear are located on one straight line perpendicular to the common axis propellers. One end of each support pipe fixed to the gear housing and the other end through the side of the bearing is fixed on the corresponding tail boom. On one of the tail beams installed drive swing gear kinematically associated with one of the base pipe reducer. The invention is aimed at increasing flight safety, reducing the weight and cost of the aircraft. 6 C.p. f-crystals, 2 Il.
The invention relates to the field of aircraft construction, and specifically Kaleta and landing.
There are various designs of power plants (SU) aircraft vertical takeoff and landing (VTOL).
Known, for example, SU VTOL V-22 "Osprey" firms "bell and Boeing Vertol, USA (see kN. P. Bowers. Aircraft of unconventional schemes. M.: Mir, 1991, 229-230 C., Fig. 11.21), including two engines mounted in nacelles on the wing tips together with two (United with them transmissions) propellers with the possibility of rotation in the vertical plane 98oand transverse shafts, ensure, if necessary, drive the two screws from one engine. For control of VTOL in addition to the usual set of control surfaces in the transmission built machines skew (Autonomous control bias) propellers with controllable pitch that allows you to tilt the thrust vector of the screw in either direction at a fixed position of the engine, and change the thrust of each propeller due to a change in his step.
This construction of the power plant while providing vertical takeoff and landing, as well as sufficient controllability in all modes, however, the complex structure of cross-transmission and screws, respectively, and a complicated control system, have considerable weight and reduced mole could tip over and break.
Closest to the proposed construction of the power plant is SU VTOL on the patent of the Russian Federation 2141432, 64 p 29/00 dated 18.11.98, including two turboshaft engine, connected by a transmission with two propellers. Each of the engines is stationary in the Central part corresponding to the tail beam plane girder scheme and is mounted so that the axis of its output nozzle is directed at the intersection of the corresponding keel with the corresponding elevon, and propellers are made of the same diameter and rotating in different directions. When the atom propellers are installed on the same axis in the cutout of the center section above the center of gravity of the aircraft and placed in the annular channel is arranged to swing in the plane of symmetry of the aircraft, and the swing angle of the annular channel with the air screws is 95-100o.
This embodiment SU allows you to provide a certain level of flight safety VTOL, however, in some cases, when using conventional designs in separate nodes SU, for example in the transmission, reduces the efficiency of the whole SU, in addition, the blowout of the exhaust gases of engines elevons and fins with rudders requires camping in the energy of the exhaust gases by reason of the smallness of the cross sections of jets and excessively high gas velocity.
The task, which is aimed by the invention, is to increase safety VTOL in all flight conditions, increase manageability, and reduced costs of manufacture and operation of the VTOL.
This task is solved with a technical result from the use of the claimed invention to provide increased reliability of the power plant on all flight modes while enhancing the controllability of the power plant and the VTOL, reduce weight, fuel economy and engine life.
This result is achieved in that in the known power plant of the aircraft vertical takeoff and landing, including two turboshaft engine, left and right, fixed in the Central parts of the respective tail beams so that the axis of the output nozzle of each engine is directed to the intersection of the corresponding keel with the corresponding elevon, and United the two transmissions with two air screws (top and bottom) of the right and left rotation, mounted on the same axis in the cutout of the center section above the center of gravity of the aircraft and placed in the annular channel, made with vozmozhno by means of two supporting tubes can be rotated in the tail beams, thus the output shaft turboshaft engines (TVD) have the same direction of rotation, and a transmission connecting the output shafts of theater with a Central gear, contain clutch, angular gears and intermediate shafts, mounted on bearings in said support tubes; two of the support pipe of the Central gear unit having a housing, are located on one straight line perpendicular to the common axis propellers and hull, and are directed in opposite directions, with one end of each support pipe fixed to the housing perpendicular to its axis, and the other end through the side of the bearing is fixed on the corresponding tail boom, in addition, in the case set gear shaft lower air screw and bevel wheel mounted on the Central shaft of the upper propeller, and shaft-gear connected with a Central shaft with two internal bearings and, in addition, the gear shaft and the Central shaft is connected to the housing, each with upper and lower bearings, while the Central gear also includes left and right bevel gears which are in engagement with the shaft, gears and bevel wheel and ustanovleno Central gear coaxial propellers; on one of the tail beams installed drive swing Central gear kinematically associated with one of the support tubes of the Central gear; clutch made of inertial and transmitting torque from the corresponding TVD transmission only after they reach working speed; clutch made manageable, for example hydrodynamic providing disabling transmissions from theater during start up, shut down any theater or failure and idling and the transmission of torque from one operating theatre to the second to accelerate its launch; on the exhaust nozzles TVD installed ejectors.
Introduction to the design of the power plant additional units, a special implementation of existing and additional components, as well as their particular placement, help to improve safety by facilitating and accelerating run any engine in flight, as well as to improve the controllability of the aircraft due to the increase blown lengths of the elevons and fins with rudders, to provide fuel economy and service life of engines by providing opportunities off of one of them cruising in level flight, reduce weight and cost sa the unique take-off and landing elements of the power plant; - Fig.2 shows the kinematic diagram of the transmission of the power plant VTOL.
The proposed power plant of the aircraft vertical jacks and landing contains two turboshaft engine (TVD): left 1 and right 2, fixedly mounted in the Central parts of the respective left 3 and right 4 tail beams so that each axis of the output nozzle 5 and 6 of the corresponding TVD 1 and 2 are directed to the intersection of the corresponding fin 7 and 8 with the corresponding elevon 9 and 10, and United the two transmissions 11 and 12 with two propellers (upper 13 and lower 14) of the right and left rotation mounted on the same axis in the cutout of the center section 15 above the center of gravity of the aircraft and placed in the annular canapés 16, is arranged to swing in the plane of symmetry of the aircraft.
Propellers 13 and 14 placed on the Central gear 17 defined by the two support tubes (left 18 and right 19) can be rotated in the tail beams 3 and 4, when the atom output shafts 20 and 21 turboshaft engines 1 and 2 have the same direction of rotation and the transmission 11 and 12, connecting the output shafts 20 and 21 TVD 1 and 2 with a Central gear 17, contain clutch 22 and 23, for example, inertial type, uguestbook support tubes 18 and 19.
Two of the support pipe 18 and 19 of the Central gear 17 with the housing 32, are located on one straight line perpendicular to the common axis of rotors 13, 14 and the housing 32 and are directed in opposite directions, with one end of each support pipe 18 and 19 fixed to the housing 32 perpendicular to its axis, and the other end through the side of the bearings 33 and 34 fixed to the corresponding tail boom 3 and 4.
In addition, the housing 32 is set gear shaft 35 of the lower propeller 14 and bevel wheel 36 mounted on the Central shaft 37 of the upper air screw 13, and the gear shaft 35 is connected with a Central shaft 37 by means of two internal bearings 38 and 39 and, in addition, the gear shaft 35 and the Central shaft 37 is connected to the housing 32, each using the top 40 and bottom 41 of the bearings. This provides the possibility of simultaneous rotation of both propellers 13 and 14 in different directions, and the transmission of thrust propellers 13 and 14 on the housing 32 and through the support pipe 18 and 19 on the design of the VTOL.
With this Central gear 17 has also left 42 and right 43 bevel gears which are in engagement with the shaft-gear 35 and the bevel wheel 36 and mounted on noviciate rod coaxial propellers 13 and 14, rigidly mounted on the support tubes 18 and 19 of the Central gear 17 coaxial propellers 13 and 14, and on one of the tail beams, such as on the left 3, a drive swing arm 44 of the Central gear 17, kinematically associated with the supporting tube 18 of the Central gear 17.
Clutch 22 and 23 made, for example, inertial and transmitting torque from the corresponding TVD 1 and 2 of the transmission 11, 12 only after it reaches operating speed. Clutch 22 and 23 can also be made manageable, such as hydrodynamic, ensures disconnection of the transmission 11, 12 from TVD 1 and 2 during start up, shut down any theater 1 or 2 (including its failure) and at idle, and the transmission of torque from one operating theatre 1 or 2 second to accelerate its launch.
To reduce the temperature of the exhaust gases and increase blown lengths of these modes 9 and 10 and rudders 45 and 46 on the exhaust nozzles 5 and 6 theatre 1 and 2 installed ejectors 47 and 48, intended for pre-mixing of exhaust gases with atmospheric air and cooling.
The proposed power plant VTOL is operated as follows.
When you start turboshaft engines 1 and 2 of their output shafts 20 and oresti rotation. This makes it easier to run turboshaft engines 1, 2, and provides the minimum time exit the preset mode. After the automatic inclusion of the inertial clutch 22 and 23 TVD 1 and 2 begin to rotate propellers 13 and 14 in different directions, ensuring asked the pilot rod. This coaxial arrangement of the bearings 28, 29, 30, 31 intermediate shafts 26 and 27 and the side bearings 33 and 34 of the support tubes 18 and 19 provides independent control of thrust propellers 13, 14 and the change in the vector direction of their thrust by rotation of the Central gear 17, which facilitates control of the VTOL.
In the case of a typical shutdown or failure of one turboshaft engines 1 or 2 its output shaft 20 or 21 stops and inertial clutch 22 or 23 automatically terminates the kinematic connection of the output shaft 20 or 21 of this staying turboshaft engine 1 or 2 with the air screws 13, 14, and both the air screw 13, 14 will rotate one working turboshaft engine 2 or 1.
Thus, the presence of inertia of the clutch 22, 23 increases the reliability of the power plant and provides the possibility of horizontal flight in economy mode, and save the resource space. In this case, the advantages of the SU with the inertial execution of the clutches 22, 23 will be added the possibility of promotion already working turboshaft engine 1 or 2 other 2 (or 1) to accelerate its launch.
Pre-mixed with air ejectors 47 and 48 output nozzles 5 and 6 gas turbine engines 1, 2 and chilled them jet exhaust 49 and 50 fanned long root pieces corresponding to these modes 9 and 10 and the fins 7 and 8 with rudders 45 and 46, providing more effective control of VTOL pitch, roll, and direction of takeoff and landing by shifting the same controls as in horizontal flight, which can significantly simplify the management process and training him.
The use of the invention allows to: 1. To enhance safety by improving the reliability of the power plant, facilitate and speed up the implementation of any of the engines in flight. 2. To standardize the engine and thereby improve the maintainability of the power plant VTOL Yes through the use of engines of the same type with the same direction of rotation of the output shafts. 3. To provide fuel economy and engine life due to p is to Reduce the weight and cost of the aircraft by providing applicability in the design of the fins, rudders and elevons conventional structural aluminum alloys by reducing the temperature of the exhaust gases flowing out of ejectors engines. 5. To improve the controllability of the aircraft due to the increase in size of the cross section of the jet of exhaust gases, cooling fins with rudders and elevons. 6. To simplify the management process VTOL and training him.
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