ES2367501A1 - Sustainer system, propulsor and stabilizer for vertical landing and landing aircraft. (Machine-translation by Google Translate, not legally binding) - Google Patents

Abstract

The supporting, propelling and stabilizing system for vertical take-off and landing aircraft of the invention consists of applying one or more rotors or large fans each with two or more horizontal blades, on, under or inside the fixed-wing aircraft. Rotors are driven by turboshafts, turbofans, turboprops with a mechanical transmission, or hydraulic, pneumatic or electric and the corresponding engines. Using fans, tangential turbines and/or oscillating fins and/or propeller air jets, supporters and/or stabilizers and/or control, placing the horizontal holders in the vicinity of at least one end of the longitudinal axis and the transverse the aircraft. Large fixed fans and fixed blades can be placed inside a duct or their blades can be fitted with an aerodynamic profile at or above the fuselage. (Machine-translation by Google Translate, not legally binding)

Description

Sustaining, propellant and stabilizer system for vertical take-off and landing aircraft.

Field of the Invention

In lift systems, propulsion and stabilization of manned and unmanned aircraft.

State of the art

Airplanes have low lift to low speed, need maximum power, large wings and hyper-sustainers for takeoff and landing, are dangerous for their high speed next to the ground, they use heavy trains of landing, large airports, expensive runways and do not perform the vertical takeoff. The helicopters are slow, expensive, heavy, complex and have little autonomy. VTOL and SVTOL aircraft current, with adjustable nozzles or not, have little security or are unstable and do not efficiently use turbine energy at low altitude and at low speed. All are difficult to control. The invention solves these drawbacks.

Object of the invention

Be able to take off in VTOL and SVTOL mode gathering the advantages of helicopters and airplanes and facilitating the pilotage. Using only part of the great power and support available and simultaneously different systems of lift, stabilization and control.

Be able to fuselar, hunt or hide the blades when external rotors are used.

Use internal counter-rotary rotors, fairings or not with aerodynamic profiles, if you use only one, it will be placed at or near the center of gravity.
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Selectively apply the driving energy to the thrusters and sustainers.

Provide great stability using fans, tangential turbines and / or oscillating fins and / or air jets thrusters, sustainers and / or stabilizers, placing the horizontal sustainers in the vicinity of at least one end of the longitudinal and transverse axis of the aircraft, some stabilizing fins at the exit of the rotors or the application of asymmetric power through several rotors. Compensating fast and efficiently, especially when systems are used electric

Eliminate hypersusters, large wings and heavy and complicated landing gear and its systems.

Fit the adjustable nozzles of the turbines at or below the center of gravity of the aircraft.

Actuate the rotors, fans and mechanical turbines, electrically, hydraulically or pneumatically.

Use turboprops and turbo axles for lift and propulsion.

Use centrifugal or axial fans fairings and oscillating fins as propellers.

Use turbo axles, turbines, mini turbines, Wankel microturbines or motors with powerful magnet generators rare earth permanent at high rpm. The weight of the generator is can reduce to 1/50 of the current one. Electric motors can be used Lightweight

Use very light turbines, similar to those turbo axles, without gears or shafts, with magnet generators Rare earth permanent integrated in the area of compressor.

Control the ship by applying differential energy to two electromagnets of the oscillating fins. More system Simple, fast, efficient and economical than servo systems.

Description of the invention

The sustaining, propelling and stabilizer for vertical take-off and landing aircraft of the invention consists in applying on, under or inside the fixed-wing aircraft one or more rotors or large fans each with two or more horizontal blades, said rotors are driven by turbo axles, turbofan, turbo propellers with a transmission mechanical, or hydraulic, pneumatic or electric and the corresponding engines. Using some fans, turbines tangential and / or oscillating fins and / or air jets thrusters, sustainers and / or stabilizers and / or control, placing horizontal holders in the vicinity of the minus one end of the longitudinal and transverse axis of the aircraft. Generally said stabilizing elements form 90 ° with each other and with the application point of the central rotor or of application of the resulting support forces.

One or two rotors or large fans can be place inside some ducts or fair the rotors with an aerodynamic profile NACA 4412, 2412 or similar, at the height of the fuselage or on it and can be centrifugal or axial These rotors have fins that divert air flow driven to stabilize the aircraft. In case of need to said rotors can be applied full power for five minutes If a single rotor or large fan is used it is placed on, on or under the center of gravity of the aircraft.

The external rotors are of rigid blades or semi-rigid, fixed pitch, simple, folding and retractable. Every rotor with two or more blades, which retract and attach to the fuselage or are introduced partially or totally into a cavity ribbed of the upper part of the same and / or of the wings in the high-wing airplanes, being fuselated or fairing with their surface. You can use and store another rotor in the lower area of the fuselage. Only the outermost ends of the Pallas.

The shovels can be introduced in some cavities in the same way, lacking or fusing its upper or outer face with the surface of the fuselage of the aircraft. Some magnets, springs or some straps can hold them when they are retracted. The strips They hold it at its leading and trailing edge. The shovels can be insert laterally into an external retainer piece The tips of the blades can be tilted down by staying and being held in housings and equally inclined and reinforced of the fuselage. They can also carry on the tips of the blades hooks that are held in fuselage housings. Area The blade housing must be heated.

The ends of the blades, preferably rigid, they can have small lateral fins inclined in a single address, which forces the blades to address the Marching air when free. The shovels have to have a fixed angle to prevent them from producing resistance or their rotation when they are free This way you don't have to pick up the rotor or the Pallas.

The blades can be flexible with the ends external slightly curved down, so that when the rotor blades are attached to the surface of the fuselage, in an area reinforced

The blades can rotate and be stored between the fuselage and longitudinal plates or bridges on and under said fuselage.

The drive of the rotors and fans can be secure, complement or reinforce with electric motors, hydraulic or pneumatic

Rotor pairs can be used in counter rotation. When the rotors are extended in rotation Increase the separation between the two by a spring. If a single rotor must be compensated with fins, fans or air jets on the steering wheel.

One or more rotors can be used in, over or under the center of gravity of the aircraft or several spaced rotors regularly on the surface of it.

The rotors are coupled to the turbines or engines thrusters using hydraulic or air valves, or with manual, hydraulic, pneumatic or electric clutches and corresponding rpm reducers. If tire is not applied They need a reducer.

The electric motors of the rotors and the fans can clutch automatically when they receive power engines, falling apart if they lose it.

Rotor blades and shafts may be articulated, or be telescopic with sliding or threaded shafts of great length inside some tubular elements and can collect and extend vertically, or they can swing these axes with their articulated ends and attached to the blades by means of a fork and a spring that tends to place the perpendicular blades to these axes when they are collected, being moved by motors, actuators or hammers. The threaded rotors extend to the start the turn in a sustaining sense and retract if they turn on In the opposite direction, this can be done by the wind. To the shovels Telescopic air is applied under pressure or suction inside That is hollow. The shafts of the rotors carry at their ends union with the wedge-shaped blades and when they retract they are introduced each other and in a grooved cavity also wedge the fuselage. The outermost rotor blades are wider than the inner ones. A martinete can introduce it in the cavity.

With gas turbines in, or near the center of gravity, a baffle plate is used to direct the flow of air and exhaust gases down and inwards, also They can apply on the flaps during vertical flight. The turbines with adjustable or vector nozzles are placed and unloaded below the center of gravity of the ship or next to it to compensate the torque created by the turbine suction. This reduces the instability and facilitates stabilization with fans or fins.

A variant uses only turbo axle engines which drive through a hydraulic, pneumatic or electric motors that drive the sustaining rotors or main and / or centrifugal axial or axial shingles propellers To these fairings a nozzle can be added convergent. The turbo axle gases are directed downwards and the Suction is performed from the upper zone, generating a lift additional.

With several rotors the stabilization is achieved using asymmetric power.

Stabilizing and control fans can be pairs of hydraulic, pneumatic or electric fans in series. Oscillating fins can be used. You can also inject air by some grooves from inside the wings or stabilizers on the compensating fin stabilizing the aircraft during the flight vertical. The flap also acts in horizontal flight with the air of the march, being the same control system useful for all the Flight is simple and very useful. Flexible side fins profile the external air flow.

Direct air jets can be used in the minus the tip of a wing, and the nose and / or tail, sent from to at least two different sources through a conduit that is part of the aircraft structure, stringers, ribs and the like, too these ducts will be used to send the engine tire pneumatically operated The air jets are controlled with flow regulating valves.

Fanes or turbines can be axial and centrifugal-axial and can be levitated magnetically and used simultaneously as propellants, stabilizers and / or sustainers. The blades or blades of the fans Centrifugal launch air flow radially and axially, contributing to it the housing or care of them. Shovels they can be flat and parallel with the planes that pass through the axis of turn or may be twisted.

Several pairs of fans can be used fixed thrusters on each side of the fuselage, which may have a slight angle of nose above and / or can rotate 90º around the transverse axis. Its flow can be straightened with fins.

One or more fans or turbines can be placed, fairings or not fairings, on at least one wing, on a fin of a plane type canard or in the stabilizers, the side fans are they can place inclined around the transverse axis and the front around the longitudinal axis to counteract the torque of the main rotor, can also be placed on the horizontal and vertical stabilizer. Stabilizing fins divert the air flow at the outlet of the rotor fans fairings Two fans can be used in rotation and in series fairings within a single conduit, and can be operated by two independent systems and engines.

Stabilizing fans can use a flow variable sustainer to produce stabilization and can reverse the flow to compensate with or without lift.

Rotors or centrifugal fanes fairing they carry a disc and / or a disc in the back area of the blades or propellers cone or semiovoid.

The oscillating fins oscillate around a shaft or a strap under the fuselage and wings, or at the trailing edge of wings and stabilizers and carry a permanent magnet or a portion ferromagnetic alternatively attracted by electromagnets powered by currents or electrical signals from multivibrators or oscillators, varying the intensity or frequency the sustaining or compensating flow power. For better performance they can oscillate lodged in prismatic containers.

Peripheral driven tangential turbines by motors send the air sucked by the side inlets or upper fuselage or wings and expel it down by the exits in the lower zone.

Fans engines and peripheral turbines they can be reversible, producing and storing current or tire during descent.

Fans and rotors bearings can also Be air or magnetic.

Electric generators of permanent rare earth magnets, iron boron neodymium, cobalt samarium or the like, air-cooled, rotating at high speeds of turbines, miniturbines, Wankel engines, etc. are used. applying them directly to them, or through a small reduction in rpm: The generated high frequency current is rectified and applied to oscillating fins and DC, or low frequency AC motors through an inverter. The weight of the generator can be reduced to 1/50. Rotors and fans can be applied with multiple brushless electric motors. Its use reduces the necessary energy, noise and emission of pollutants. Electric motors must also use permanent earth magnets
rare

You can use Wankel engines or turbines, mini turbines, etc. Light gas for exclusive current use electric, which do not use reduction gears or external shafts, the which can carry a large alternator whose rotor of permanent rare earth magnets is supportive and rotates with the compressor, with the stator secured by uprights to a bushing fixed or to the turbine housing. Due to their low weight they can be used only on vertical flight.

During takeoff and landing you can add electrical or pneumatic energy and that of the accumulators, fuel cells or supercapacitors applying it to engines electric or complementary tires that reinforce the motors of the main rotors and the fans. A gearbox facilitates the sum of the energies of the different axes or motors before applying it to the shafts of the rotors and fans. If the rotors main sustainers are powered by electric motors, they It will add that energy directly to them. Accumulators They will be quick download.

Gyros detect the change in attitude with respect to the horizontal and heading, generating signals that they act on electric motors driving the fans, fins and flight controls There may be a gyro for each engine or fan.

The best solutions are: a) Use of engines Wankel or simple and light miniturbines, microturbines or turbo axes with powerful permanent magnet generators, integrated or not, to drive rotors, oscillating fins and / or electric fans, b) Use of turboprops setting the propeller propeller pitch a zero during vertical flight, c) Using the hydraulic system of a turbo shaft to drive the rotor during vertical flight and a fan centrifugal axial fairing or propeller propeller for flight horizontal and d) Use of the mechanical transmission of a turbo shaft for drive the rotor during vertical flight and the centrifugal axial fan fairing or propeller propeller for horizontal flight.

An additional system can be used consisting of turbofan, in which the fan of the turbine shaft through a clutch during flight vertical.

The legs can be a buffer strips flexible and fixed, curved backwards and sustainers, which They can be retractable and carry wheels at their ends.

The changes of support mode of the rotors as provided by the wings overlap and is made gently, avoiding sudden changes in attitude.

In the ascent you can use a cable electric umbilical attached to ground or a swivel arm which feeds the aircraft to a certain height or to a certain extent speed, disconnecting later. For long flights it can ascend and even descend helped by a helicopter power supply and an electric cable. You can also raise the aircraft using a platform up to a starting height of the flight. All this saves fuel and gives security, especially in the takeoffs that is when it presents greater weight.

On long flights another aircraft can be used or nurse helicopter that refills fuel once it has risen the aircraft that makes the flight. They can also be done intermediate refueling along these flights.

The rotor has a brake that facilitates Enter it, once stopped, in your accommodation.

The aircraft can use only four wings reduced and / or low rope, two canard and two later in stabilizer positions, so that the rotor flow has little opposition. In compensation the lower area of the fuselage can be flat.

On the rise you can use a liquefied and isolated gas thermally, such as nitrogen, which drives turbines or pneumatic motors, which in turn move generators electric This system is economical and does not need bottles heavy

Fans blinds and fairings rotors they are powered by motors, open with internal flow and close with the air of the march and some springs. They can also be operated automatically, they open with the internal flow and close with the air of the March. Blinds can be used to stabilize the aircraft with respect to its transverse axis.

To improve lift offs and landings will be made with plane fuselage ships approved at wind with a positive angle of attack.

Brief description of the drawings

Figure 1 shows a schematic view and in perspective of an aircraft with the system of the invention.

Figures 2 and 6, 7 and 32 show views schematized and elevation of variants of the aircraft of the invention.

Figures 3, 26 and 27 show views schematized and in elevation and partially sectioned variants of aircraft

Figures 4, 5,18 to 25 and 38 are seen in plant of variants of the aircraft.

Figures 9, 10, 10A, 10B and 10C show cross-sectional views of semi-detached blades or introduced into a portion of fuselage.

Figure 11 shows a sectional view of a fuselage and rotor portion.

Figure 12 shows a partially view sectioned by a propellant fan.

Figure 13 shows a schematic view and cross section of a wing or stabilizer portion and a control fin.

Figures 8, 14 and 41 show views schematized and partially sectioned double device fan.

Figure 15 shows a schematic view and partially sectioned of a rotor and the drive pinions of the movement.

Figures 16 and 17 show elevation views and partial rotor variants.

Figures 28, 33 and 42 show views Schematized of partially sectioned fuselages.

Figures 29 and 30 show front views of fuselages with oscillating fin variants.

Figure 31 shows a view of a wing sectioned with oscillating fins.

Figures 34 through 36 show plan views of different variants of oscillating fins.

Figure 37 shows a schematic view and in perspective of an aircraft with a fin system variant oscillating

Figure 39 shows a plan view of a fan variant

Figure 40 shows an elevation view of the fan of figure 30.

Figure 43 shows a view of a wing sectioned with tangential turbines.

Figures 44, 45 and 46 show views Schematized variants of special turbines with generators incorporated.

Figure 47 shows a block diagram of an electrical system that feeds rotors, fans, turbines and fin electromagnets.

More detailed description of the invention

The invention, figure 1, shows the fuselage (1) of the aircraft in vertical flight, the blades (2), the rotor shaft external (3) of the sliding or telescopic type, the turbofan (4), the double tail fan (5), the wing (47) and the canard fins (48). The major arrow shows the rotor's bearing force and the small wings of the double supportive and stabilizing fans (9 and 9a), to stabilize it is sufficient to apply them in only two points, the other fans are used when used as sustainers. The Blades are flexible and their ends (72) slightly curved towards Below, it shows the optional housing (43).

Figure 2 shows the fuselage (1) of the aircraft, blades (2), extended external upper rotor shaft (3). The turbines (4a) with the adjustable nozzle (58), under the center of gravity, they suck the air from the upper area through the duct (62) with the valve (63) open by a spring, it closes at the advance the plane at a certain speed. The rotors are in counter rotation, the tail (5) is optional.

Figure 3 shows the fuselage (1) of the aircraft, the outer rotor blades (2) retracted and fuselated in upper area of the fuselage of the aircraft, the turbofan (4) and the tail rotor (5), the external rotor shaft (3) sliding vertically with an actuator or motor and gears (21), the shaft of the rotor rotates further inside the tubular housing (22) and It is supported by bearings. The rotor shaft (3) rotates using the drive shaft from the turbine and gears (2. 3).

Figure 4 shows the aircraft (1), the axis of the upper external rotor (3), its blades (2) and those of the optional rotor under the fuselage (2a), the twin centrifugal-axial propeller fans (10), the double supporting fans and stabilizers (9), the four minialas in positions of the stabilizer (57) and in the canard fins (48) outside the circle of the rotors. You can use little rope wings in the central area. The driving fans or turbines are placed outside the central zone. The lower area of the fuselage can be
flat.

Figure 5 shows the aircraft (1) canard type, the external rotor shaft (3), centrifugal axial fans propellers (10), horizontal compensating oscillating fins (71) on a wing and tail (71a). Fanes and fins are used in two 90º points with the main rotor. Show the blades (2) in a Superior accommodation of the wings of a high wing aircraft. Shovels of dashed lines can be those of a four-bladed rotor.

Figure 6 shows the fuselage (1) of the Aircraft, blades (2), external rotor shaft (3) type tilting, the fork shaft (8), the tail rotor (5), the outflow of turbines (4a) under the center of gravity hits the inclined plate (64) driven by the hammer (65) and deflects the flow down and inwards, it can suction the air from the upper area through the duct (62) to the open the valve gate (63), a spring closes it and closes when the plane advances at a certain speed.

Figure 7 shows the fuselage (1) of a aircraft, extended blades (2), external rotor shaft (3), the turboprop (4b) the rotor joints and blades (8 and 8a), the tail fan (5a), double stabilizer fan (9), tail (53) with a double stabilizer fan (9b) and the blade housing retracted, marked with dashed line.

Figure 8 shows the double axial fan (9) with their blades (46) in counter-rotation with common engines (56 and 56a), the pinions (28) and their axes of action (29), the motors are They clutch when receiving power. Fanes can be independent each. The blind (25) operated with an actuator also opens automatically with the air of the fans and closes with that of the March and the action of some docks. Use the flexible fins (25a) In the lower face. Bearings not shown. This system of gears can be used on rotors placed above and below the fuselage, both external rotors would extend or move towards the outside driven by the pinions (28) and shafts (29).

Figure 9 shows the blade (2) housed in the reinforced upper or lower area of the fuselage (la), attracted and held by the fixed magnet (50) and its ferromagnetic section (51). Add the flexible seal (76).

Figure 10 shows the blade (2) housed in the reinforced upper or lower external area of the fuselage (1b), subject by the protruding lateral seal (77). The end of the shovel is inclined laterally so that the air of the march presses it into the retainer (77). To do this you must turn the shovel in Wrong Way.

Figure 10A shows the blade (2) attached to the fuselage (1) and retained, of its leading edge and exit, with the Straps (38 and 38a).

Figure 10B shows the blade (2), the inclined housing (92) reinforced on the fuselage (1) where the inclined tip (93) of the attached blade (2) is housed.

Figure 10C shows the shovel (2) attached, the inclined housing (92) reinforced on the fuselage (1) where the inclined tip (93) of the blade is housed.

Figure 11 shows the end of the rotor external (3) with the wedge (14) which is introduced into the channel of sloping walls (15) of the fuselage (1) forcing it to retract to address in the longitudinal slit thereof. This is valid for a single rotor. If you use two rotors the external one is wider and the Internal is introduced deeper.

Figure 12 shows the double propeller fan centrifugal-axial (10), can be supportive and / or stabilizer, its shafts (11), the fairing (12), the convergent nozzle (13) and the blades (46) flat and parallel with the passing planes by the axis of rotation, they may be twisted, add the discs baffles (89) and the optional cone or semiovoid (91).

Figure 13 shows the wing or stabilizer (17), through whose inner groove (16) air is injected onto the fin compensator (18) rotating around the axis (19), compensating the aircraft during vertical flight, the fin is divided by the axis (19) in two asymmetric sections, which helps to deflect the air jet to me or another side of it. The fin acts on horizontal flight over the air of the march. Flexible fins (20 and 20a) allow aerodynamically profiling the air flow external

Figure 14 shows the centrifugal axial fans doubles (9) with the deflector discs (89) with their blades (46) in counter rotation, driven simultaneously by motors electric (24 and 24a) and clutches (61 and 61a), blinds (25) operated with actuators or hammers (26), brackets and bearings (27), the pinion assembly (28) and its shafts (29). I dont know Show some bearings. Fanes can be independent each.

Figure 15 shows the axes of the external rotors (3) in rotation, grooved and longitudinally sliding between them, driven by the pinions (31), the main shaft (30) and speed reducer (55) when the clutch is operated ( 49) and also by the complementary electric motor for reinforcement or safety (32) and its clutch and rpm reducer (61b). The rotors extend with the actuator (35) and the rod (34), mainly related to the external rotor which, when extended, extends the spring (36) separating the rotors from each other for greater safety. Bearings not shown. (35) could be an electric motor or pneumatic driven turbine-
mind.

Figure 16 shows an external rotor (3) of shovels (2) extensible, telescopic and hollow and its outer section (40), extend with pressurized air and retract by suction.

Figure 17 shows an external rotor (3), the blade ends (2), preferably rigid, which may have small side wings inclined in a single direction (41 and 41a), which forces the blades to address, when they remain free, with the air of the march shown by the arrow. They can use only the upper or lower fins.

Figures 18 through 21 show aircraft (1), with pairs of centrifugal main internal rotors in counter-rotation (54) and in the center of gravity, with fins stabilizers in its lower zone, propellers (4) and fans double sustainers and optional stabilizers (9 and 9a) in counter rotation. If a fan fails, the power of the fan is increased adjacent. The rotors can be axial. The front fans (73) from figure 21 they retract and hide in the fuselage during the flight horizontal. The system is similar to the one used in the F-35 but uses centrifugal axes in or on the center of gravity and add stabilizing fans.

Figure 22 shows the aircraft (1), the pairs of internal centrifugal or axial rotors in counter rotation (54), with stabilizing fins, propellers (4) and the thrusters (4a) typical for orientable nozzles and for flip flops or flaps, direct air jets stabilizers (59 and 59a), placed in the vicinity of the minus one end of the longitudinal and transverse axis of the aircraft.

Figures 23 through 25 show the aircraft (1), with three or four pairs of centrifugal internal rotors or axial in counter rotation (54) with stabilizing fins, not shown in the figure, and propellers (4) and propellers (4a) typical for orientable nozzles and for fins or tilting flaps of the flow. The rotors can be axial.

In the aircraft of Figures 18 to 25, stabilization is also achieved by varying the lift by means of stabilizing fins in the flow of
air.

Figure 26 shows the aircraft (1), the couple of main internal centrifugal rotors (54) with the deflector discs (89)., their shafts (3), the thrusters (4), the fan optional stabilizer (5), the drive shaft (30), the box gears (31) and stabilizing fins (59) which are actuated by the motors (60) divert the air flow. The rotors can be axial and be driven by drive shafts or motors totally independent.

Figure 27 shows the aircraft (1), the axles of the rotors (3) and the transmitting shaft portion (30), the pair of centrifugal-axial rotors (54) and both aerodynamic profile fairings (48) of the rotors. Instead of deflector discs the fixed deflector wall (90) is used. A rotor is at the height of the fuselage and the other in the upper area of the ship forming a high wing supported by the uprights (43).

Figure 28 shows the fuselage (the), the flippers (67) oscillating around the axes (74) attracted alternatively their arms opposite by electromagnets (68). The fins are stored in accommodation (69), sections of strokes. I dont know show the actuators.

Figure 29 shows the fuselage (la) and the oscillating fins (67) adapted to the flat and inclined sides of a special fuselage. The arrows indicate the flow input of air.

Figure 30 shows the fuselage (la) and the oscillating fins (67) adapted adjacent to the flat bottom of a special fuselage

Figure 31 shows the wing (47), the fins (67) oscillating around the axes (74), attracted alternatively by electromagnets (68). They may be stabilizers, sustainers and propellers. Fins too they can rotate around a support strap and retract by attaching to the intrados during the horizontal flight, they can remain attached to the wing with actuators, magnets, suction on the inner face or having slightly tilted the trailing edge outwards. The fin (67b) is applied to the trailing edge, (75 and 75a) being membranes elastic or foam rubber padding that fuse the fin with the to.

Figure 32 shows the aircraft (1) and the oscillating fins (67, 67a, 67b and 67c). They can be formed by several sections as shown with dashed lines.

Figure 33 shows the aircraft (1) with the oscillating fin (67), rotating around the axis (74) and driven by the electromagnet (68).

Figure 34 shows the fin (67) actuated by the electromagnet (68), which can be placed in the optional position (68a), the axis of rotation (74) and the ferromagnetic part (75).

Figure 35 shows the fin (67) actuated by the electromagnet (68) that attracts the ferromagnetic joint (76) around the axis of rotation (74).

Figure 36 shows the fin (67) actuated by the electromagnet (68) that attracts the ferromagnetic part (75) flexing the strap (77).

Figure 37 shows the aircraft (1), the fins oscillators (67a, 67b, 67c and 67d) at rest or propelling horizontally, the wings (47), canard fins (48) and the turbofan (4).

Figure 38 shows the aircraft (1), the fans double centrifugal thrusters, sustainers and stabilizers (10), supportive double fans or rotors and stabilizers (9), stabilizer (57) and canard fins (48). The wings when not using rotor can also be in the zone central.

Figure 39 shows the propeller (46) of the Fanes, its peripheral ring (70), pulleys (71) and electric motors actuators (56d).

Figure 40 shows the peripheral rings of the propellers (70) of the fans, pulleys (71) and electric motors actuators (56d).

Figure 41 shows the centrifugal axial fans doubles (9) with the deflector discs (89) .with their blades (46) in counter rotation, driven simultaneously by motors independent electric (24) and clutches (61) supports and bearings (27).

Figure 42 shows the fuselage (1) with the peripheral tangential turbines (84), driven by motors (85), which suck the air through the upper inlets (86) and push it down through the exits (87).

Figure 43 shows the wing (47) with two tangential turbines (84) powered by engines (85).

Figure 44 shows the miniturbine or microturbine (60), with permanent earth magnet rotor rare (69) in the area of the compressor and the stator (70) or winding attached to the housing by means of uprights or fixed blades.

Figure 45 shows the miniturbine or microturbine (60), the rotor with several permanent magnet stages Rare earth (69a) in the compressor area, and the stator (70a) attached to the housing by uprights.

Figure 46 shows the miniturbine or microturbine (60), with permanent rare earth magnets (69b) in the compressor and the stator (70b) around it.

The previous miniturbines or microturbines do not use reduction gears or external shafts.

Figure 47 shows the turbine, miniturbine or microturbine (60), which drives the generator (78) between approximately 10,000 to 200,000 rpm, whose alternating current is sent to the rectifier (62) which sends the obtained direct current to the bar (63 ). The generators (78a, 78b and 78c) send the current to the rectifiers (62a, 62b and 62c) and once rectified they are applied to the direct current bars (63a, 63b and 63c). As an example some propellers or fans are shown whose bars (63, 63a, 63b, and 63c) feed the motors (32, 24a, 24b and 24c) of the external rotor (3), internal rotor (54), internal rotor (54b) fairing with the aerodynamic profile (48) and the fans (9 and 10) through the corresponding frequency inverters (65, 65a, 65b and 65c) operated by the gyro or control signals. Those who use several engines can use a planetary gear system to drive the rotor or fan. The Wankel engine (79), the pneumatic or nitrogen driven motor (80), the battery (81), the fuel cell (82) and the supercapacitors (83) feed the rod (63c) through the semiconductors (66 ), and from the bar (63c) through the frequency inverters (65e and 65f) to the motors (85) of the tangential turbines (84) and to the electromagnets of the oscillatory fins (67) Each fan uses at least one motor and each motor can be powered by other frequency inverters if the power fails
principal.

Claims (67)

1. Sustaining, propelling and stabilizer for vertical take-off and landing aircraft, which it consists of applying on, under or inside the aircraft of fixed wings one or more rotors or large fans each with two or more horizontal blades, said rotors are driven by turbo axles, turbofan or turbo propellers with a mechanical transmission, or either hydraulic, pneumatic or electric and the corresponding engines, using fans and / or oscillating fins and / or ones air jets propellants, sustainers and / or stabilizers and / or of control, placing horizontal holders in the proximities of at least one end of the longitudinal axis and of the Transversal of the aircraft. 2. System according to claim 1, characterized in that one or two rotors or fanes are placed inside some ducts or are shielded with a NACA 4412, 2412 or similar aerodynamic profile, in the central area of the fuselage and / or thereon, fins at the exit of the ducts stabilize the aircraft. 3. System according to claim 1, characterized in that the rotors are external, of fixed pitch blades, simple, folding and retractable, each rotor with two or more blades, which when retracted are partially or totally inserted into a groove in its upper area , being the external ones that are greater fuseladas or fairing with its surface. 4. System according to claim 1, 2 and 3, characterized by using a single rotor or a large fan on or under the center of gravity of the aircraft. 5. System according to claim 1, 2 and 3, characterized by placing a pair of rotors or large fans in, on or under the center of gravity of the aircraft. 6. System according to claim 1, 2 and 3, characterized by using pairs of rotors in rotation. 7 System according to claims 1 and 3, characterized in that the blades are attached or inserted into a grooved cavity in the wings of wing-type aircraft
high. System according to claims 1 and 3, characterized in that the two, three or four outermost blades of the rotors are attached to the upper area of the fuselage and / or in the wings of high wing type aircraft. 9. System according to claims 1 and 3, characterized in that the blades are rigid and are inserted into an external retainer piece laterally. 10. System according to claims 1 and 3, characterized in that the blades have their ends inclined downwardly staying and being held in equally inclined and reinforced housings of the fuselage. 11. System according to claims 1 and 3, characterized in that the axes of the rotors are collected and extended vertically and slide or threaded telescopically into tubular elements. 12. System according to claim 1 and 3, characterized in that the axes of the rotors are collected and extended by tilting and have their ends articulated and joined to the blades by means of a fork and a spring that tends to place the blades perpendicular to said axis. 13. System according to claims 1 and 3, characterized in that the axes of the rotors carry at their connecting ends with the wedge-shaped blades and when they are retracted they are introduced to each other and into a ribbed cavity equally in the wedge of the fuselage. 14. System according to claims 1 and 3, characterized by using two or more rotors, with the wider external rotor blades. 15. System according to claim 1, characterized by using several rotors which are regularly spaced on the surface of the aircraft and placed at different heights. 16. System according to claim 1, characterized in that the rotors are coupled to the turbines or propellant motors using hydraulic or air valves. 17. System according to claim 1, characterized in that the rotors are coupled to the turbines or propeller motors using hydraulic, pneumatic or electric clutches and the corresponding rpm reducers. 18. System according to claim 1, characterized in that the rotors are coupled to the turbines or propeller motors using manual clutches. 19. System according to claims 1 and 10, characterized in that the rotors in counter rotation when extended increase the separation between them by means of a spring. 20. System according to claims 1 and 3, characterized in that the blades are telescopic, actuated by pressure and air suction inside them. 21. System according to claims 1 and 3, characterized in that the ends of the blades, preferably rigid, have small lateral fins inclined in a single direction, which forces the blades to be directed with the air of the march when the blades are free, the blades they must have a fixed angle to avoid producing resistance or turning when they are free. 22. System according to claim 1, characterized by using an external rotor in the upper area and another in the lower one of the fuselage. 23. System according to claims 1 and 3, characterized in that the blades are introduced into cavities with the same shape, lacking or fusing its upper or outer face with the surface of the fuselage of the aircraft. 24. System according to claims 1 and 3, characterized in that only the outermost ends of the blades are inserted in some housings of the fuselage and magnets, springs or straps hold them when they are retracted. 25. System according to claims 1 and 3, characterized in that the blades are attached to the fuselage and are retained by their leading and trailing edges with two strips. 26. System according to claim 1, characterized by using one or more fairings or non-fairings supporting and / or stabilizers in at least one wing, in a fin of a canard-type aircraft or in the tail and / or in the stabilizers. 27. System according to claim 1, characterized by using pairs of counter-rotating series fairs inside a single duct in each of the wings, on the fins of a canard-type aircraft and on the horizontal and vertical stabilizer, operated by two systems and independent engines. 28. System according to claim 1, characterized by using thrusters, sustainers and / or axial stabilizers. 29. System according to claim 1, characterized by using propellant, sustaining and / or centrifugal axial stabilizers. 30. System according to claim 1, characterized by using pairs of propellant, sustaining and / or magnetically levitated stabilizers. 31. System according to claim 1, characterized in that the flanges of the wings or sides are inclined around the transverse axis of the plane and those of the canard or front wings around its longitudinal axis. 32. System according to claim 1, characterized in that the fans are retractable. 33. System according to claim 1, characterized in that several pairs of fixed drive fans are used on each side of the fuselage, which have a slight nose angle above. 34. System according to claim 1, characterized in that several pairs of driving, supporting and stabilizing fans are used, which rotate 90 ° with respect to the transverse axis of the aircraft. 35. System according to claim 29, characterized in that converging nozzles and a cone in the central area are added to the fairings of the centrifugal axial fans. 36. System according to claim 1, characterized in that the centrifuged rotors or centrifugal fans carry a disc and / or a cone or semiovoid in the rear area of the blades or propellers. 37. System according to claim 1 characterized in that the actuation of the fans and rotors is reinforced with electric or pneumatic motors. 38. System according to claim 1 characterized in that by means of a gearbox, the energy of the shafts or motors is added and applied to the shafts of the rotors or fans. 39. System according to claim 1, characterized in that the aircraft use stabilization and control devices consisting of grooves or ducts in the wings or stabilizers by which the air jets are blown onto the control fins compensating the aircraft during vertical travel , carrying flexible lateral fins that outline the external air flow. 40. System according to claim 1, characterized in that the stabilizing and control air jets, direct or not, are sent by ducts that are part of the structure of the aircraft, stringers, ribs and the like, and are placed on at least the tip from a wing, and from the nose and / or tail, these ducts will also be used to send the tire of the pneumatically driven motors. 41. System according to claim 1, characterized in that the stabilizing and control fins divert air flow at the outlet of the fanes of the fairings rotors. 42. System according to claim 1, characterized in that at take-off and landing it adds electrical energy from the accumulators to the complementary electric motors of the engines of the rotors and fanes of the aircraft. 43. System according to claim 1, characterized in that during the take-off and landing of the aircraft the pneumatic energy is added to that of the pneumatic motors of the sustaining rotors. 44. System according to claim 1, characterized in that the turbofan engines use a fan that becomes independent from the turbine shaft by means of a
clutch during vertical flight. 45. System according to claim 1, characterized in that only turbo-axle engines are used which drive, by means of a hydraulic, pneumatic or electric system, the motors that drive the main or main rotors and / or the axial propeller or centrifugal axial fans and the electromagnets of the oscillating fins , the exhaust gases are directed downwards and the suction is made from the upper zone, generating an additional lift. 46. System according to claim 1, characterized by using turbines, miniturbines, microturbines or Wankel engines, for the exclusive use of the electric power of the aircraft, which have an integrated generator whose rotor formed by permanent rare earth magnets is integral and rotates with the compressor, having the stator secured by means of uprights to a fixed bushing or to the Wankel engine housing, turbine, miniturbine or microturbine. 47. System according to claim 1, characterized by applying the electric energy by means of electric generators driven by turbines or pneumatic motors and these in turn with pressurized air or liquefied gas stored in thermally insulated containers. 48. System according to claim 1, characterized in that during the take-off and landing the electrical energy of generators, accumulators, fuel cells or supercapacitors is added, applying it to complementary electric motors that reinforce the motors of the fans and rotors. 49. System according to claim 1, characterized in that the turbines are close to the center of gravity and by means of the flap or a deflector plate the flow of air and exhaust gases is directed downwards and inwards during the vertical flight. 50. System according to claim 1, characterized in that the turbines carry adjustable or vector nozzles below the center of gravity of the aircraft or slightly separated from the center of gravity to compensate for the torque created by the suction of the turbine, which directly discharge the flow down. 51. System according to claim 1, characterized in that the legs of the train have wheels and flexible and fixed damping strips, curved backwards. 52. System according to claim 1, characterized in that the oscillating fins oscillate around an axis or strip under the fuselage and wings or at the exit edge of wings and stabilizers and carry a permanent magnet or a ferromagnetic portion which is alternately attracted by Electromagnets fed by currents or electrical signals from multivibrators or oscillators, varying the intensity or frequency is achieved to vary the power of the sustaining or compensating flow, the fins are introduced or attached to the fuselage or wings. 53. System according to claim 1, characterized by using peripheral tangential turbines which, driven by motors, send the air sucked by the side or upper entrances of the fuselage or wings and propel it downwards through the exits in the lower zone. 54. System according to claim 1, characterized in that the fairings fans and rotors are covered with blinds, which are opened by means of motors or actuators and are also closed by means of springs. 55. System according to claim 1, characterized in that the fanes and fairings rotors are automatically covered, open with the internal flow and close with the air of the march and springs. 56. System according to claim 1, characterized in that the bearings of fans and rotors are air or magnetic. 57. System according to claim 1, characterized in that the blades of the centrifugal axial fans or rotors are flat and parallel with the planes passing through the axis of rotation. 58. System according to claim 1, characterized in that the blades of the fans are twisted. 59. System according to claim 1, characterized in that the fans carry a ring or peripheral ring held between pulleys driven by electric motors. 60. System according to claim 1, characterized in that the aircraft uses only four small wings, with small rope and / or in positions of the stabilizer and canard fins, and the fuselage with at least its lower flat area. 61. System according to claim 1, characterized in that the electrical energy is applied in the ascent by means of an electric cable connected to ground or to a rotating arm which feeds the aircraft to a certain height or a certain speed, subsequently disconnecting. 62. System according to claim 1, characterized by using a platform to raise the aircraft to a flight start height. 63. System according to claim 1, characterized in that the energy is generated using a thermally insulated liquefied gas in the ascent in a container which is allowed to drive out of pneumatic motors and these to electric generators. 64. System according to claim 1, characterized by ascending and descending the aircraft aided by a feeder helicopter and an electric cable. 65. System according to claim 1, characterized by being the engines of the fans and reversible tangential turbines and producing and storing current and / or pneumatic in the descent. 66. System according to claim 1, characterized in that the electric power is generated by electric generators of permanent rare earth magnets, neodymium boron iron, cobalt samarium or the like, air-cooled that rotate at high speeds of turbines, miniturbines or microturbines, or Wankel motors applying them directly to them, or through a small reduction in rpm, the high frequency of the generated alternating current is rectified and applied to oscillating fins and DC motors, or low frequency AC motors through In an inverter, the current from the accumulators, supercapacitors and fuel cells is applied to the direct current bars and from these to the inverters that feed the electromagnets, rotor motors and complementary fans, the DC motors are fed directly. 67. System according to claim 1, characterized by using gyroscopes to stabilize or control heading and horizontability. 68. System according to claim 1, characterized by using a gyroscope for each motor or stabilizing electromagnet.