Vertical takeoff and landing flying vehicle
 Rotoroplane / 2245824Proposed 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. |
 Vertical takeoff and landing flying vehicle / 2266846Proposed flying vehicle is provided with jet power plant located in center of flat wing round in plan. Power plant includes turbocompressors 13, bypass valves 14, receiver 15, adjusting valves 16 and four-section jet engine used for forming circular radially diverging air jet. Sections 17 of engine are designed for independent control during operation and are separated from one another by receiver. Upper part of body is designed for performing function of wing round in plan. |
 Method of change of aerodynamic characteristics of flying vehicle control surfaces and device for realization of this method / 2272746Proposed method includes bleeding part of preheated gas from gas source followed by delivery of bled gas to control surfaces of rudder, upper and lower surface of flying vehicle elevator. |
 Method for variation of aerodynamic characteristics of flight vehicle and device for its realization / 2274585The device is designed for a flight vehicle having a fuselage, jet engine, fuel system, carrying planes and control sections. The device has a source of offtaken gas, which through sealed lines is connected to the zones of local blowing-out of gas to the boundary layer of air flow on the surfaces the flight vehicle. Each zone of local blowing-out of gas is made on the surface of the carrying plane or fuselage, or control sections with a penetrable porous insert with a cross-sectional area of the ducts in the porous insert within 50 to 60% of the area of the insert proper by 10-15 times less than the distance between the adjacent inserts, a flat rectangular slot for a break of the boundary layer is made before each insert and in parallel with it. |
 Method of change of aerodynamic characteristics of subsonic flying vehicle and device for realization of this method / 2282563Proposed method consists in taking preheated gas from gas source and bringing it to flying vehicle surface followed by blowing-out jet of preheated mixture of air and combustion products of engine plant at subsonic velocity through local blowing-out zones on lower and/or upper surfaces of flying vehicle wing into external incoming air flow. Besides that, air is taken from air intake or from engine plant compressor and is fed over hermetic mains through adjusting members at supersonic velocity through supersonic nozzles which are flat in configuration from leading edge of wing over lower surface in way of wing chord, thus overlapping the subsonic gas jets escaping from local blowing-out zones by high-velocity air flow at Mach number more than 0.7. Device proposed for realization of this method has fuselage, power plant, engine plant, fuel system, wing and control profiles. Engine plant is connected by hermetic lines with local blowing-out zones located on surfaces of wing and control profiles. Mounted on leading edge of wing lower surface are supersonic nozzles whose external surfaces are located at level of wing surface. |
 Transport aircraft / 2287454Proposed aircraft has fuselage, two half-wings, jet engine, vertical and horizontal stabilizers and landing gear. Each half-wing has through passages of rectangular section which are parallel relative to each other along half-wing span. Each through passage has lower passage whose inlet hole is located on lower surface of half-wing; upper passage is narrower as compared with lower passage and its outlet hole is located on upper surface of half-wing. |
 Method to generate thrust (versions) and apparatus to move in fluid medium (versions) / 2374133Set of inventions relates to apparatuses moving in air or water. Proposed apparatus comprises aerodynamic section wheel with top convex surface, fluid medium high-pressure source communicates with high-pressure jet generator arranged above the wing convex surface. Six design versions of proposed apparatus are distinguished for by the design of aforesaid high-pressure jet generator. Method of generating thrust consists in using high-pressure jet generator arranged above the wing convex surface. Five versions of the method are distinguished for by the design of aforesaid high-pressure jet generator. |
 Method to vary hypersonic aircraft aerodynamic characteristics and device to this end / 2383469Device to vary aerodynamic characteristics of hypersonic aircraft comprising airframe, engine, fuel system, planes and control surfaces incorporates bled gas source connected, via sealed pipelines, to permeable porous inserts intended for local gas blow-off into boundary layer of airflow. Cross section area of channels arranged in permeable porous inserts makes 30% to 60% of insert area. Distance between adjacent inserts is 6 to 10 times larger than insert width. Said permeable porous inserts are connected, via sealed pipelines, to low-temperature gas source representing a vortex tube. Proposed method consists in bleeding gas from gas source and feeding it to permeable porous inserts arranged on aircraft surfaces, using above described device, bled gas temperature being other than that of ram airflow. |
 Method of generating gas for blowing aircraft surfaces, and steam generator / 2414387Set of inventions relates to aircraft engineering. Steam generator comprises water tank 5, electrically-driven valves 4, 10, check valves 3, throttle 9, jacket 6, tank 2 and safety valve 1. Water flows from tank 5 via opened electrically-driven valve 4, check valve 3 and throttle 9 into jacket 6 to convert into steam. The latter flows via check valve 3 to tank 2 and, via safety valve 1, to jets on aircraft wing 7. Method of generating steam for blowing aircraft wing surface consists in using steam generator. |
 Aircraft aerodynamic flap with stall affecting device / 2428354Invention relates to aircraft engineering. Proposed flap 11 incorporates stall affecting device arranged on flap side edge with wing sections 13 extending along wing span to form air passages for incoming air to pass there through. High-efficiency flap comprises channel extending onto flap side edge through which compressed air may be fed into noise-generating vortex. Stall affecting device comprises compressed air feed device, side edge outlet channel and jointing element. |
 Aircraft wing / 2465172Invention relates to aircraft engineering. Aircraft wing comprises inner bearing carcass, top and bottom envelopments, flap and aileron. Said wing represents a flat plate with thickness equal along the profile and sharpened front tip. The wing has staggered in plan through channels which are covered by top envelopment elements in the form of semicones. Through channels provide airstream portion flowing from bottom wing envelopment onto top envelopment. Envelopment elements in the form of semicones split upper airstream into separate jets. |
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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. |
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Vertical takeoff and landing flying vehicle / 2266846 Proposed flying vehicle is provided with jet power plant located in center of flat wing round in plan. Power plant includes turbocompressors 13, bypass valves 14, receiver 15, adjusting valves 16 and four-section jet engine used for forming circular radially diverging air jet. Sections 17 of engine are designed for independent control during operation and are separated from one another by receiver. Upper part of body is designed for performing function of wing round in plan. |
 Method of landing unmanned aerodynamic flying vehicle / 2278801Prior to flight, electronic guidance equipment is mounted on board and ground landing equipment is placed on landing field. Horizontal flight and landing approach are carried out in aircraft mode with the aid of satellite radio navigational system. At final landing section, self-guidance of flying vehicle on landing field is performed by means of on-board electronic guidance equipment and ground landing equipment with the aid of one algorithms of correlation extremal navigation; soft landing is carried out by killing the kinetic energy of flying vehicle motion. Specific feature of proposed method as compared with known methods consists in decreasing flight speed after beginning of self-guidance of flying vehicle on landing field by means of power plant and aerodynamic control members and increasing angle of attack to critical magnitudes ensuring auto-rotation of flying vehicle at precession relative to direction of speed vector of its translational motion. Then, speed of its vertical motion relative to Earth is reduced by means of aerodynamic control members of flying vehicle to magnitudes ensuring complete killing of kinetic energy and soft landing on landing field. |
 Method of realization of mode of flow over lifting propeller blades and aero-space system with variable-diameter lifting propeller at supersonic flow over blades / 2297949Proposed method is used for forming flow over propeller blades at thickness ratio of 4-6% by increase of rotational speed of lifting propeller to magnitude of tip speed exceeding the sonic speed. Aero-space system includes aircraft stage 1, space stage 2 and alighting column with swivel brackets. Fuselages of stages are interconnected by means of coupling unit 3. Aircraft stage 1 has fuselage, wing 4, high-lift devices, power plant 7 and coaxial propeller. Each blade of coaxial propeller is mounted in hub by means of flexible spar 9 wound on drum which is connected with hub by means of clamp and lag hinge. Fuselage is provided with swivel stops of alighting gear. Space stage 2 has payload container, elevator and rudder. |
 Method of creating lifting force for vertical takeoff flying vehicle / 2305649Proposed method includes suction of air from upper surface of wing by means of impeller of centripetal fan and directing this air flow under lower surface of wing with the aid of centrifugal fan impeller. Air flow formed in radial direction relative to annular wing having asymmetric profile creates lifting force due to difference in pressures on lower and upper surfaces of wing. |
 Flying vehicle-convertiplane-amphibian (versions) / 2312795According to first version, proposed flying vehicle has star-shaped wings which are spaced apart in each crossing vertical planes at even number of rays. Mounted on tips of wings in engine nacelles are power plants forming rigid structure in each crossing plane. Wings are provided with adaptive control surfaces for activation of them according to required modes of operation of power plants and counteraction to external disturbing factors in accordance with objective synergetic laws of unity of adaptation and control processes. Lower parts of engine nacelles have extension displacement-type alighting gears of changeable volume for retraction into internal cavities of engine nacelles. According to second version, flying vehicle is provided with even number of detachable aerodynamic wings of optimal aspect ratio. Their outer panels are secured on fuselage in between planes of star-shaped wings, thus forming different aerodynamic configurations. According to third version, each power plant of flying vehicle is provided with at least two coaxially independent drives with air screws in thrust ring. Each alighting gear may be made in form of folding corrugated cylinder and sphere. Interior of this cylinder is divided into two cavities by elastic transversal partition fitted with reducer valve. Envelope of sphere may be retracted into end cavity of cylinder. Its end face is provided with swivel tabs of fairing. Alighting gears may be provided with splittable doors with inflated ballonets secured in their cavities. |
 Tail unit / 2313474Proposed tail unit includes streamlined planes located in lower section of fuselage and rotating around axes perpendicular to helicopter longitudinal axis passing through " point of application of lifting force + helicopter CG + point of securing the tail unit to fuselage". For horizontal motion of flying vehicle from steady vertical hovered flight position, bearing is mounted at point of attachment of tail unit to fuselage in such way that free rotation of tail unit around helicopter longitudinal axis is ensured. Respective turn of streamlined planes of tail unit shall exclude spontaneous rotation of tail unit around longitudinal axis for forming the horizontal force for horizontal motion. |
 Portable air-based optical visual monitoring complex / 2320519Proposed complex includes remotely piloted flying vehicle and ground control terminal for information processing. Ground terminal is provided with processor with monitor, autonomous navigational system equipped with radio range-finder, barometer and antenna module with compass mounted on swivel unit and provided with drive, transceiver and control channel antenna. Flying vehicle has fuselage, flight support system, transceiving equipment and video information collection system. Mounted on fuselage are screw propeller, servo actuators for control of heading and pitching, emergency parachute landing system and radio beacon. Onboard flight support system is provided with processor, sensors, automatic return system phase meter and servo actuators. Sensors include micromechanical three-dimensional angular velocity and acceleration pickups, three-dimensional electronic compass, optical horizon sensor mounted on fuselage external surface and two barometers located in instrumentation compartment of fuselage; one barometer is connected with Pitot tube. Onboard transceiving equipment includes video signal transmitter with antenna and additional onboard range-finder and additional antenna for receiving the control signals. Video information collection system has two TV video cameras: observation camera and monitoring cameras. Proposed complex makes it possible to extend range of functioning due to use of aircraft-type self-contained platform at simultaneous low requirements to operator's qualification in pilotage. |
 Flying source / 2365522Invention relates to aircraft engineering and can be used in designing new flight vehicles. Proposed flight vehicle consists of dome-shaped compartment, partition, power plant, reduction gear, rotor, vertical shaft, bearing support, coil and three bearing wheels. A build-up ring-like wing has its fixed wing attached power plant, right below aforesaid partition ceiling. The said build-up movable wing is integrated with the rotor. Note that it has its ribs rigidly fixed to the hub and articulated with rotor blades. |
 Computer-controlled aircraft take-off, piloting and landing complex / 2376203Proposed complex, apart from computer-controlled aircraft (CCA), comprises one or several remote control boards of pilot in command, one or several airfields and one or several useful load remote control boards, all above listed components being integrated by common info field. There can be used also air-traffic-control service with communication system that incorporates air traffic control hardware. Said useful load can represent photo- and video cameras, containers with medicines, items of mail, mobile communication hardware, atmosphere contamination pickups etc. Proposed complex allows operating traditional CCA in whatever zones, on whatever airfields and in airports equipped with air traffic control hardware. It helps relay service info to not only CCA pilot in command but to other CCAs and dispatchers, and transmit flight zone underlaying surface image and other data from onboard useful load to useful load remote control boards, as well as reveal conflict aircraft and avoid them in both automatic and semi-automatic operating conditions. It allows also CCA space flight training. |
FIELD: heavier-than-air flying vehicles.
SUBSTANCE: proposed flying vehicle is provided with jet power plant located in center of flat wing round in plan. Power plant includes turbocompressors 13, bypass valves 14, receiver 15, adjusting valves 16 and four-section jet engine used for forming circular radially diverging air jet. Sections 17 of engine are designed for independent control during operation and are separated from one another by receiver. Upper part of body is designed for performing function of wing round in plan.
EFFECT: enhanced economical efficiency and reliability.
3 cl, 4 dwg
The technical field to which the invention relates.
The invention relates to the field of aviation aircraft (LA) are heavier than air and, in particular, to LA vertical takeoff and landing.
The level of technology.
Famous LA vertical takeoff and landing rotorcraft Ka-22 [1, str]. He has two pulling screw 2 bearing screw (LC) and high mounted wing. HB used to generate the lifting force and control ventorrillo hover and low speeds, and the wing and flight feathers are used for the same purposes at high speeds.
| The power plant ventorrillo | 2 CCD D - 25 VK |
| Power plant capacity | 2×4050 kW |
| Empty weight ventorrillo | 25,84 t |
| Maximum takeoff weight | 42.5 t |
| Load | 16.5 t |
| The weight returns | 0,4 |
The way to create a lifting force (vertical takeoff and landing) and the horizontal thrust of the air-jet, when the thrust is created by dropping the air at a speed that is greater than the flow velocity, which may not provide greater lifting force. The presence of bearing screws and mechanical transmission complicates and aggravates the intercept is uccio, that reduces the weight returns.
Famous aircraft of the vertical take-off and landing Harrier GR.1 [1, str, table] who:
| Power plant | 1 turbofan engines (lift-cruise) |
| Takeoff weight | a 7.62 t (vertical take off) |
| The empty weight of the aircraft | of 5.53 t |
| Load | 2.09 tons |
| The weight returns | 0,26 |
The way to create lift and thrust air-breathing that can not provide a large lifting force and the weight returns.
Famous LA vertical take-off and landing of the helicopter MI-8 [1, str, table] who:
| Power plant | 2 GTE TV2 - 117 |
| Power plant capacity | 2×1100 kW |
| Empty weight | 7,07 t |
| Maximum takeoff weight | 12 t |
| Load | 4,93 t |
| The weight returns | 0,41 |
Helicopter uniaxial systems [1, str, paragraph 1] is NV and tail rotor that creates a hazard in the operation and impairs economic characteristics (the cost of the steering screws are 8-15% of the total m is snasti engines). The helicopter has a complex and heavy mechanical transmission, which reduces the weight returns [1, str, Fig.3].
The way to create a lifting force of the air-jet, which may not provide greater lifting force and the weight returns.
Lift and thrust for horizontal flight creates HB that does not provide the necessary reliability LA when the power failure or the carrier system in flight.
As the prototype is set to the helicopter MI-8.
The essence of the invention.
This invention is directed to providing a cost-effective, reliable, simple and safe in operation, with high weight efficiency, compact aircraft, capable of vertical takeoff and landing, still "hang" in the air, move along and rotate about any axis.
The aircraft has an aerodynamic scheme "flying saucer". Side view (Fig 1) has the form of a plate. View in plan (figure 2) is a circle. The upper part of the airframe flat round plays the role of a wing (propulsion). In the centre of the wing is a jet power plant, including turbochargers, bypass valves, receiver, control valves and four circular jet engine (SCRD), forming a circular radiating air-jet stream (CRWRC).
Turboc mpressor and four circular jet engine separated from each other by the receiver.
The change in the value of the lifting force of the aircraft is carried out by simultaneous control of all four sections of a jet engine.
The change in the vector direction of the lifting force of the aircraft is carried out by counter-control pairs of oppositely located sections of a jet engine.
The lift force of the aircraft is formed by the difference in static pressure of the atmospheric air acting on the aircraft at the bottom, and static pressure in a circular radiating air-jet acting on the aircraft from above.
Improving the reliability of the aircraft is derived from the following factors:
1. Power turbine of the gas turbine engine and transmission helicopter replaced the receiver system of pneumatic valves and pipelines. Compressed air from any turbocharger sent to the receiver, can get to any section four circular jet engine (cross-redundancy).
2. Autonomous (independent) work of turbochargers and sections four circular jet engine, divided by the receiver, allows a controlled descent and landing failure of any turbocharger or any section four rogovicnogo of the engine;
3. There is no bearing screw, therefore, no torque reaction. There is no need for steering screw. The absence of transmission, main rotor, tail beam and tail rotor makes the aircraft is compact, simple and safe in operation, increases the weight impact of the aircraft.
List of figures.
Figure 1. Aerodynamic design of the aircraft (side view). Shows a circular radiating air-jet stream (11) and air flow (12).
Figure 2. Aerodynamic design of the aircraft (the plan). Shows a circular radiating air-jet stream (11).
Figure 3. Structural diagram of the reactive power of the installation.
Figure 4. Shows the relative locations of major components and assemblies of the reactive power of the installation.
Information confirming the possibility of carrying out the invention.
The composition of the reactive power of the installation (figure 3) consists of:
Turbochargers (13), are used to compress atmospheric air.
Bypass valves (14), used for pneumatic communication turbochargers operating in normal mode, with the receiver, and to connect the turbo to the atmosphere at the idle state, at the time of launch and during an emergency condition turbochargers.
The receiver (15), the employee DL the accumulation compressed by the turbochargers air and feeding it to the four-section of a circular jet engine, and marching to the engine (if installed on the aircraft) via a regulating valve.
Regulating valve (16)that serve to regulate the flow of compressed air from the receiver to the four sections of the circular jet engine (as well as propulsion engine)operating in a normal mode, and to isolate them from the receiver when an alarm condition.
Four circular jet engine, which is used for forming a circular radiating air-jet consists of four independent sections (17).
Section four circular jet engine comprising a combustion chamber and a jet nozzle. serves to form radiating air-jet in the sector of 90 degrees.
Main engine (18) (installed if needed)that serves to create additional longitudinal thrust.
Reactive power unit is placed in the center of a flat circular wing under the casing of the power unit (9) 1, 2, hosts the inlets (5, 6, 7, 8) figure 2 turbochargers.
The mutual location of major components and assemblies of the reactive power of the installation is shown in figure 4. Four sections (17), forming a four-section of a circular jet engine, separated from each other by bridges (19). Above re Accame posted by turbochargers (13). In the center of the jet propulsion installed receiver (15) with bypass system (14) and control (16) air valves.
In the initial state, the bypass valve (14) figure 3 connects the cavity of the compressed air of the turbocharger (13) with the atmosphere. Regulating valve (16) connects the receiver chamber (15) with the section of the jet engine. Jet propulsion is not working. On aircraft top and bottom acts atmospheric pressure. The differential pressure and the lifting force is equal to zero.
When you start a turbocharger (13) figure 3 air from the atmosphere through the air vent (5, 6, 7, 8) 1, 2 enters the turbocharger, compressed and through the bypass valve (14) figure 3 emitted into the atmosphere. After the release of the turbocharger on the operating mode bypass valve directs compressed air into the receiver (15). From the receiver the compressed air through the control valve (16) is in section four circular jet engine (17). In the combustion chamber of the chemical energy of the fuel components is converted into heat, and a jet nozzle into the kinetic energy of the jet stream. Each section of the four-section of a circular jet engine forms a radiating air-jet stream in the sector of 90 degrees. When all four sections are formed in a circular radiating in the hot-jet stream (11) 1, 2, which, spreading over the flat round wing blows air flow (12) figure 1-creating a low pressure above the wing of the aircraft. On aircraft below applies atmospheric pressure and above the pressure in a circular radiating air-jet. As a result of pressure differential produces a lifting force.
When an emergency condition of the turbocharger (13) bypass valve (14) cuts faulty turbocharger from the receiver and connects the cavity of the compressed air of the turbocharger with the atmosphere.
If the alarm status section (17) four-section of a circular jet engine regulating valve (16) cuts off the faulty section from the receiver (15), stopping the flow of compressed air from the receiver.
Control of the aircraft is provided by four circular jet engine and gas-dynamic control surfaces (1, 2, 3, 4) figure 2.
Managing the work of the four sections of the circular jet engine, it is possible to change the parameters of the jet at the nozzle exit, thus altering the magnitude of the lifting force. Depending on the mode the expiration of the jet vector lifting force may vary not only in magnitude but also in direction.
Vertical control of the aircraft is changing the lifting force by the synchronous control of all four sections of the circular jet engine.
Pitch control is effected by changing the lifting force in the longitudinal sector of the circular wing by antiphase control longitudinal sections SCRD with the inclination of the vertical axis LA and, as a result, the longitudinal component of the thrust.
The control roll is carried out by changing the lifting force in the lateral sectors of the circular wing by antiphase control side sections SCRD with the inclination of the vertical axis LA and, as a consequence, there is a lateral component of thrust.
The control yaw is to create aerodynamic forces gas-dynamic control surfaces (GDR) by simultaneous rotation in the same direction.
Control of longitudinal movement of LA is a longitudinal thrust, which occurs when the tilt of the vertical axis LA (see pitch Control)and anti-phase deviation of the GDR. When anti-phase deviation of the GDR (4, 3) figure 2 arises longitudinal thrust in the same direction, in opposite phase deviation of the GDR (1, 2) occurs thrust in the opposite direction.
Depending on the destination LA it can be installed propulsion jet engines to create a large longitudinal thrust.
Control lateral movement of LA is the lateral thrust, which occurs when the slope of the ve the vertical axis LA (see Control roll)and anti-phase deviation of the GDR. When anti-phase deviation of the GDR (1, 4) occurs thrust, directed to one side, while the opposite phase deviation of the GDR (2, 3) occurs thrust directed in the opposite direction.
Bibliographic information sources.
[1] - aviation. The encyclopedia. Editor Gpicview. Scientific publishing house "Great Russian encyclopedia". Central Aerohydrodynamic Institute named after Professor N.E. Zhukovsky. Moscow 1994.
1. Flying machine heavier than air vertical takeoff and landing jet power plant, characterized in that the reactive power unit placed in the center of a flat circular in plan wing includes turbochargers, bypass valves, receiver, control valves and four-section jet engine intended for the formation of a circular radiating an air jet, the sections of which are intended for independent control during operation.
2. Aerial apparatus according to claim 1, characterized in that the turbochargers and sections of the engine of the power unit are separated from each other by the receiver.
3. Aerial apparatus according to claim 1, characterized in that the upper part of the body is designed to perform the function of a flat circular in plan of the wing.