Abstract
Lift propulsion and stabilizing system and procedure for vertical takeoff and landing aircraft that consists in applying simultaneously and combined as lifters during the initial portion of the climb and at the end of the descent of: a) some fans or electric turbines, EDF, and b) at least one rotor with external blades and/or rotary and/or c) the engine flow directed downwards and/or d) pressure air jets injected on leading edges control fins, and/or e) water jets and/or f) supplemented with aerodynamic lift produced during frontal advance of the aircraft, the stabilization is achieved by the gyroscopic stiffness of the rotor and two or more lifting fans oscillating fins and/or air jets located on two or stabilizers more peripheral points in a plane perpendicular to the vertical axis of the aircraft.
Claims
1. A vertical takeoff and landing aircraft including a fuselage , said fuselage having a central axis, a lenticular wing , said lenticular wing rotatably affixed to a top of said fuselage at said central axis, said lenticular wing including protruding fins and grooves, said lenticular wing rotated by a shaft, said fuselage having a pair of canard fins horizontally attached to a front portion of said fuselage and a pair of stabilizer fins horizontally attached to a rear portion of said fuselage, each of said canard fins having at least one ducted fan passing through said each of said canard fins, each of said stabilizer fins having one or more ducted fans passing through said each of said stabilizer fins, a tail attached vertically to the rear of said fuselage, said tail having a ducted fan.
2. A vertical takeoff and landing aircraft as claimed in claim 1 wherein said shaft is rotated by a power plant selected from the group consisting of a mechanical power plant, a pneumatic power plant and an electrical power plant, said power plant deriving it's power from a power generator selected from the group consisting of flywheels, APU, propeller engines, and batteries.
3. A vertical takeoff and landing aircraft as claimed in claim 1 wherein said lenticular wing comprises a two-bladed rotor rotatably affixed to a top of said fuselage at said central axis.
4. A vertical takeoff and landing aircraft as claimed in claim 3 wherein said two bladed rotor is rigid.
5. A vertical takeoff and landing aircraft as claimed in claim 1 wherein said stabilizer ducted fans are rotatable and tiltable, whereby said stabilizer ducted fans aids in said vertical takeoff and landing aircraft in controlled vertical ascent and descent.
6. A vertical takeoff and landing aircraft as claimed in claim 5 wherein said canard ducted fans include shutters located both above and below said canard ducted fans, said shutters further comprise a plurality of tilting blades.
7. A vertical takeoff and landing aircraft as claimed in claim 6 wherein said stabilizer ducted fans include shutters located both above and below said stabilizer ducted fans, said shutters further comprise a plurality of tilting blades.
Description
BRIEF DESCRIPTION OF THE DRAWINGS
(1) FIG. 1 shows a schematic and a plan view of an aircraft with the system of the invention.
(2) FIGS. 2, 3, 22, 27 and 30 show schematic and elevation views of aircraft with the variants of the invention.
(3) FIGS. 6 and 7A show schematic, partial and cross-section views of rotary wing variants.
(4) FIGS. 3, 15 and 16 show schematic and elevation and partial cross-section views of aircraft variants.
(5) FIGS. 4 and 5 show elevational views of helical wings or fans.
(6) FIGS. 8, 8A, 8B, 8C, 8D, 8E, 8F and 35 show schematic and cross-section views rotor blades or rotary wing.
(7) FIGS. 10 and 10A show variants sections of extendable rotor blades.
(8) FIGS. 11, 13, 17, 18, 19, 20, 21, 22, 23, 28, 28A and 29 show schematic and plan views of variants of aircraft with the system of the invention.
(9) FIGS. 12, 24 and 25 show plan views of variants of rotating wings.
(10) FIG. 14 shows a plan view of upper wings and a rotor.
(11) FIG. 26 shows an elevational view of a rotary wing and related systems.
(12) FIGS. 31, 32 and 33 show a partial and cross-section view of fans variants.
(13) FIG. 34 shows a partial cross-section view of an oscillating fin.
(14) FIG. 35 shows a view of a rotor portion of the rotary wing.
(15) FIGS. 36, 37 and 38 show views of propellers or rotor fans.
(16) FIG. 39 shows a variant of a drive assembly of a rotor
(17) FIGS. 40 through 43 show views of complementary electrical supply systems.
(18) FIG. 44 shows a block diagram of an electrical power supply system of rotors motors and fans.
(19) FIG. 45 shows a block diagram with different lift systems.
(20) FIG. 46 shows the lift curves of various systems used in the system of the invention.
MORE DETAILED DESCRIPTION OF THE INVENTION
(21) The invention, FIG. 1 shows the fuselage (1) of the aircraft, the lenticular wing, lifting and rotatable around its axis of symmetry (2d) which carries the protruding fins (2h) and the grooves (2f) and rotates supported and driven by the shaft (3). It uses pairs of stabilizing and lifting fans (9) with the shutters (25) in the canard fins (48) and the stabilizer fins (57) and rotating or tilting turbofans (4d). The rotary wing is mechanical, pneumatic and/or with flywheels, APU, propeller engines, batteries, etc. The rotary wing may be replaced by a two-bladed rotor, preferably rigid.
(22) FIG. 2 shows the fuselage (1) the rotary lifting lenticular wing (2d), the tilting turbofan (4d) pushing the flow downward, the canard fin (48), the oscillating fin (67) which can be propelling, the fan (5) compensates the torque of the rotor, the fans (9) acting in both directions. The arrows show the lift and stabilization forces. It can add a nozzle (15) through which pressurized water is thrown downwards.
(23) FIG. 3 shows the fuselage of the aircraft (1), the shaft (3) of the rotary lenticular wing (2d) with lateral radial fins (54) and covered with the cap-shaped case (88). The airflow is sucked through the upper hole (48b) or radial grooves not shown in the figure, being thrown centrifugally between the case and the rotary wing (2d), exiting at the lower peripheral opening (48c). This wing arrangement can be integrated into a delta wing fuselage or similar. The aerodynamically balanced flap (18) rotated at least 45 about its axis (18a) and directs the flow downward and slightly forward, producing part of the lift. FIG. 4 shows the helical fan or the lifting rotating wing (2d) with the upper fin or leading edge (2h), the lower fin or trailing edge (2g) and the inclined groove or channel (2f) created therebetween. It has horizontal and parallel faces. Can be formed by one or two independent wings or blades.
(24) FIG. 5 shows the helical fan or lifting rotary wing (2d) with the upper blade or leading edge (2h), the lower wing or trailing edge (2g) and the inclined groove or channel (2f) created therebetween. Both wings protrude upward and downward respectively. Can be formed by one or two independent wings or blades.
(25) FIG. 6 shows the portion of the lifting rotary wing (2d) with the upper fin (2h), the lower fin (2g) and the inclined groove (2f). The arrows show the movement of the wing and the air flow through the roof. A fin may be optional.
(26) FIG. 7 shows the portion of the lifting rotary wing (2d) with the inclined groove (2f), with the upper recess (2k) and the bottom (2c). A recess may be optional.
(27) FIG. 7A shows the retracted inclined flange (2h) by the strap (a), which extends and rises when rotating the rotary wing (2d) and pressing the air on the small fin (b). FIG. 8 shows a rotor blade or the rotary wing of the rectangular or oval type (2m) rhomboidal section, that generates the lift by their inclined edges and the high rotation speed. The inclination of the edges depends on the speed of use.
(28) FIG. 8A shows a rotary wing blade of rectangular type, flat-oval convex surfaces (2n) of trapezoidal section, which generates the lift by their inclined edges and the high speed of rotation. This is equal and symmetric to the opposite blade, perpendicular to the plane which separates them. The inclination of the edges depends on the rate of use. The articulated segments (19) rotate around shafts (21) with the strips (23) which tend to keep them elevated. The delayed section is placed horizontally under the action of airflow.
(29) FIG. 8B shows a rotary wing blade of trapezium section (2p), which adds in the back and communicating with the upper edge one or more ducts (6) with flexible flap valves (7) which open for suction of the air flow. FIG. 8C shows a rotary wing blade of a trapezium section (2q), which adds in the back and communicating with the upper edge one or more ducts (6) with flexible flapper valves and angular (8) that open by the suction of the air flow.
(30) FIG. 8D shows a rotor blade or of cross-sectioned rotary wing, of symmetric profile (2i), NACA 0002 or the like, for high speed.
(31) FIG. 8E shows a rotor blade or of rotary wing cross-sectioned of profile (2j) NACA 2202 or the like, for high speed.
(32) FIG. 8F shows a rotary wing blade of Trapezium section (2r) with rotating fin (7a) in the trailing edge ridge that retracts when the air gets front and extends if trailing edge acts of sending the air and producing lift.
(33) FIG. 9 shows two rotors in counter-rotation of trapezoid cross-section and in counter-rotation, and terraced.
(34) FIG. 10 shows the lower blade (2b) attached to the drive shaft with the ratchet (12) abutting with the tooth (11), this is part of the outer shaft (2a), a spring and the action of the ram air keeps it at rest. When the shaft is driven, the upper blade (2a) is delayed and abuts with the opposite ratchet (12). Can be used with rotors and fans.
(35) FIG. 10A shows the lower blade (2a) forming part of the external shaft and the ratchet (11), at rest this ratchet abuts with the upper blade (2b) attached to the inner and driver shaft. When the shaft is driven, the lower blade (2a) is delayed and abuts on the opposite end of the ratchet (11). Can be used with rotors and fans.
(36) FIG. 11 shows the fuselage of the aircraft (1), the rotary oval wing (2t) with blades (2u) extending automatically by centrifugal force, pulling the spring (13) in the housing (14), the turbofan (4a) with deflecting blades integrated into the cowl, the front or lower (17) and the upper or rear (19) driven by actuators (20), the stabilizing fans and/or lifters (9d) on the canard fins (48) and stabilizer (57). By conduit (87) air is blown from the turbines and the one stored on the control and stabilization fins (5b, 5c and 5d), the flap (18f) and the elevator (18e) and counteracts the torque of the rotary wing during the vertical flight.
(37) FIG. 12 shows a rotary oval wing (2t) with fins (2f) and grooves (2h). This type of wing is positioned longitudinally above the fuselage of the aircraft.
(38) FIG. 13 shows the fuselage of the aircraft (1), the turbofan (4a), the lenticular rotor (2d): the main, two on the canard fins, two on the wings and two on the stabilizers, that rotate in opposite direction to the main providing horizontal stabilization. The wings are part of the fixed airfoil (2s) in front of the main rotary wing. All rotors maintain its plane of rotation and stability with minimal resistance because they are integrated in the wings or flaps of the aircraft. They are used as flywheels.
(39) FIG. 14 shows the aircraft fuselage (1) delta wing type, the rotor blades (2) superposed and housed in the wings (47) and the stabilizing fans (9).
(40) FIG. 15 shows the fuselage (1) of an aircraft type flying saucer with its rotary wings in the shape spherical caps (2d) in counter rotation on both sides of the fuselage, which adopts the lenticular-annular shape with the hollow central zone to let circulate the air stream created by the fins and grooves (2h and 2f) of the rotary wing. The wings are driven by the turbine (4), the shaft or propeller shaft (34) and the set or gearbox (31). The stabilization is effected with the fans (9 and 9a) and/or the air jets (59) and heading control with the fin (5f).
(41) FIG. 16 shows the fuselage (1b) of an aircraft flying saucer type with rotary wings in the shape spherical caps (2d) in counter rotation with radial blades (54a and 54b), the fuselage (1c) of semi-oval shape is placed in the lower zone and are mechanically driven by the turbine (4). The stability is controlled with air jets. The arrows show the air inlet and centrifugal and axially launch.
(42) FIG. 17 shows the fuselage (1) of the delta wing aircraft with two rotating helical wings (2d) integrated, each with two independent blades and in counter rotation to eliminate torque, the optional rotor blade (2), the turbines (4a) with integrated deflecting fins and fans (9d) and air jets (59 and 59a) stabilizing and lifters. The rotor blades are attached to the fuselage in level flight when the rotor is lowered.
(43) FIG. 18 shows an aircraft with eight flywheel rotors (2d) integrated into the longitudinal wings (81) on the stabilizer and on the sides of the fuselage (1) driven by the flow of the turbine (4) through conduits (23) and turbofans (4a).
(44) FIG. 19 shows the fuselage (1) of an aircraft of the type of four fix wings, two front fixed wings (48a) and two rear (57a) with two oval or flat-oval canvesas rotary wings (2t) in counter rotation between the four wings. It produces the lift with the inclination of the edges of each of the two blades in which are divided or with extendable blades, fins, recesses or slots are not shown. Add the turbofan (4) and fans (9d).
(45) FIG. 20 shows the fuselage (1) of an aircraft with two front wings (48a) and two rear (57a), gas turbine (4). Carrying on and under the fuselage and rotors and at the tips of the wings. Enlarged is sown a cross-section of the special blade of the fuselage rotors. The front propeller blades carry an internal counterweight (86) in a blade and in the other lateral fins (71) or transverse (72). The rear propeller has one of the blades of smaller dimensions offset by counterweights (86) and are aerodynamically with greater surface or angle of attack. The cross-section AA shows a cross-section typical of fuselage, with the flat base. The rotors can be replaced by rotating wings.
(46) FIG. 21 shows the fuselage (1) of an aircraft with two front wings (48a) and two rear (57a), gas turbines (4) carrying on and under the fuselage and the oval elements (22b) the protruding oval elements by the leading edge and trailing edge of the wings, where are attached or inserted rotors (2). The more external rotors are stabilizers.
(47) FIG. 22 shows an aircraft with front and rear wings (48a and 57a), carrying on and under the fuselage (1) and the rotors and wings (2), oval elements (22a, 22b). gas turbines (4), rotated 90 driven by the rod and piston of the cylinder (4p) and the pressurized air delayed by the valves (4v). The more external rotors are stabilizers.
(48) FIG. 23 shows an aircraft with front and rear wings (48a and 57a), gas turbines (4), carrying attached or introduced longitudinally above and below the fuselage (1), wings and stringers (22) the rotors (2). The more external rotors are stabilizers. FIG. 24 shows the rotating wing (2d) with extendable blades or vanes (2v) which extend when actuated the rotor rotating the pinion (26) and with this the sliding or linear pinions (28). Reversing or reducing the speed of the pinion the blades retract. The more external rotors are stabilizers.
(49) FIG. 25 shows the rotary wing, of the type flywheel (2d) driven by the GPU air (50) and/or turbofan (4) and the duct (23) on the peripheral fins (29).
(50) FIG. 26 shows the rotary wings (2d) in counter rotation, with extendable blades (2v and 2u), driven by the gas turbine (4), the electric motor (32), the additional flywheel (40) driven by the APU (60a) or pneumatic of the ground installation (84a) which drive the turbine (45a) through the gear (55a). The flywheel can be filled and emptied with the water pump (41) and the electro-valve (42), the water is discharged at high speed downwards. The ground cart (50) and the electrical connection to the ground installation (84) on the ground drive the electric motor (32a) which accelerates the flywheel (40a) and from this is fed the electric motor (32b) which drives the shafts (3) via the gearbox (31). Displays optional clutches (31a, 31b and 52). From the tubular structure (44), pneumatic group (46) and compressed air cylinders (43) compressed air is sent to the turbine (45) to mechanically actuate the rotary wing. The compressed air is sent through the pipe (33) to push the water stored in a reservoir or in the flywheels chamber, throwing abroad by the nozzles (15) of the FIG. 2.
(51) FIG. 27 shows an aircraft with the axis (3) of a rotor consisting of two extended independent blades (2a and 2b) extended, driven by the flywheel (40) complementary, which rotates counter to the rotor and is attached thereto by the speed reducer (55a). The turbine (4) drives the flow over the wing flap (18c).
(52) FIG. 28 shows an aircraft with two blade rotor (2a) wide and independent routed backwards by the action of the ram air, rotating around the shaft (3). The blades are formed longitudinally with aerodynamic profile, as shown by the leading edge (89). FIG. 28A shows the fuselage of the aircraft (1), the turbofan (4) and the two-bladed rotors (2a) independent, which rotate around the shafts (3a) and are routed backwards by the action of the ram air. They are mounted along the fuselage and of the four wings (48a and 57a), above and below them.
(53) FIG. 29 shows the fuselage of the aircraft (1), the helical or lenticular wing (2d) and its shaft (3). Add the fans stabilizers and/or lifters (9) on the stabilizer fins (57) and on the front wing forming the airfoil (2s) for the rotary wing. The wing can be driven mechanically or pushing air with inclined nozzles from the wing or front profile and impacting on peripheral fins.
(54) FIG. 30 shows the fuselage of the aircraft (1), the lenticular rotary wing (2d). Add the fan (5) that counteracts the torque of the rotary wing and stabilizes the course and the rotating fans (9d) propelling the aircraft, gas turbines (4), the small deflecting wings (80) and the stabilizing and/or lifting fans (9) on the front wing that forms the airfoil (2s) and fins (57). The profile (2s) is supported by the upright (2p).
(55) FIG. 31 shows the fan (9) and in the upper zone the shutter formed by the tilting blades (25) around the eccentric shaft (25a) which opens automatically with the fan flow and closed by the ram air which impact on the fins of less surface in which divides the shaft, the stops (25b) hold them horizontally when closed. In the lower zone are placed flexible or rigid fins (25c) and tilt-able by the rotational shaft (25d) at an edge which likewise open to the flow of the fan and close with the ram air. The support struts are not shown.
(56) FIG. 32 shows a wing or fin with the fan (9) sucking air automatically by opening the upper tilting and eccentric fin (25). In the lower zone has the fins (25c) that open to the flow of the fan air and close with the ram air.
(57) FIG. 33 shows the fin (48), the motor (24), the rotary wing fan (2d) and the flexible or rigid and tilting fins (25c).
(58) FIG. 34 shows on a wing or fin (48) oscillating fin (67) retracted by the action of the ram air, the electromagnet (68) that actuates it during the vertical flight, dashed lines, and the spring (27) that places it vertically with the aircraft is static.
(59) FIG. 35 shows the fan or rotor (2), which on extending automatically drags and opens the two halves of the gate (69) that rotate around the shafts (70).
(60) FIG. 36 shows a propeller with a few extensions (71) on one of the blades and the counterweight (86) on the opposite. The blade with the extension (71) acts as a weather vane.
(61) FIG. 37 shows a propeller with a small transverse fin (72) on one blade and the counterweight (86) on the opposite. The flap with the fin(72) acts as a weather vane
(62) FIG. 38 shows a propeller that has a blade (73) shorter, with the counterweight (86) and a larger angle of attack. Reducing this can become bladed propeller. The longest blade acts as a weather vane.
(63) FIG. 39 shows the upper blades (2) and the lower (2z) the rotor shafts (3) in counter rotation, longitudinally striated and sliding together, reduce gears (31), the main shaft (30) and the reduced speed (55) when the clutch is operated (49), the electric motor (32a) drives the outer rotor and through the gears the internal and also the supplementary electric motor of reinforcement and security (32). May be added in the lower area (32a), dashed lines to drive the internal rotor. The rotor blades are attached to the fuselage in the mode of horizontally advance, compressing a spring between them. The section (38) of the outer shaft is wedge-shaped for insertion into the housing of the same shape of the fuselage (1). If they are wings remain separated and perpendicular wings to the fuselage. At rest the actuator (35) presses on a section of the eccentric rotary wing shaft directing these and/or grooves and fins with the longitudinal axis of the aircraft. The air turbine (45) driven with compressed air bottles and hollow structure, etc. drives the inner shaft (3) of the rotor. The optional spring separates the rotors from each other during rotation thereof, an actuator compress and joins both wings or blades forming a single wing during flight. During climb the aircraft adopts a rise angle of the nose down to advance horizontally to the horizontally the rotating wings, and longer still, stay positive angle. to advance horizontally to the rotating wings and fixed now, left with positive angle. An actuator not shown raises and lowers the rotors.
(64) FIG. 40 shows the aircraft (1c) electrically powered by the power cable (76) from the helicopter or aircraft (1a). The latter can be a ground vehicle.
(65) FIG. 41 shows the aircraft (1b) electrically supplied with electrical cables (76) through the slip rings or hooks with brushes (74) which slide on the power cables (75) supported between the posts (81 and 82).
(66) FIG. 42 shows the aircraft (1b) electrically supplied with the cable (76) supported by an arm rotable about the tower (77).
(67) FIG. 43 shows the aircraft (1b) electrically supplied with the cable (76), which is supported by a captive balloon (78) attached or anchored to the floor by the cable (79). The aircraft of FIG. 40 to the 43 is disconnected when reaching certain speed.
(68) FIG. 44 shows the turbine or impeller or microturbine o turbo-shaft (60), which drives the generator (78) between approximately 10,000 to 200,000 RPM, the AC is sent to the rectifier (62) which applies the DC obtained to the bar (63), (60) also can represent a GPU or APU. The generators (78a and 78b) send the current to the rectifiers (62a and 62b) and once rectified to DC bars (63a and 63b). As an example are shown some fans whose bars (63, 63a, 63b, and 63c) feed the motor (32) of the rotary lenticular wing (2d) by the variable speed or frequency controllers (65), to the motors (24a, 24b and 24c) of the fairing fans (9a, 9b and 9c) and through the corresponding frequency or speed controllers (65a, 65b and 65c) and to the inverter (65f) which feeds the electromagnet (68) which drives the oscillating fin (67), controlled by the control signals or by stabilizing of the gyroscopes, accelerometers and/or GPS processed or controlled by the microprocessor or controller (61). The compressed air cylinder (80a) is also used to drive the turbine (80) and this the rotary wing. When several motors are used a system can use several gears which act on a common shaft or rotor to drive the fan. Can be used AC or DC motors. The battery (81), the fuel cell (82) and ultracapacitors or supercapacitors (83) feeds the bar (63c) through the semiconductor (66). Ultracapacitors additionally feed the laser gun (84) and the microwave gun (85). Each fan uses one engine and each engine can be fed from other speed or frequency controllers if mains power fails. The rotary wing (2d) is driven mechanically by the APU or by the gas turbine (4), mechanically or electrically with the flywheel (40) via the gear (55a) driven in turn by the GPU (50) and the APU. The rotary wing (2d) can be replaced by a blade rotor. The gas turbine can be replaced by a turbo-shaft engine, turboprop or motor with a large engine power/weight ratio.
(69) FIG. 45 shows a block diagram with different power supplies used in the lift and its use in rotary wings, rotors and fans. It is sown also the lift effected with the flow of the propulsion engines and APUs. One wing represents the aerodynamic lift during horizontal flight.
(70) FIG. 46 shows the different curves of lift during takeoff and initial climb, when gas turbines involved, one or more rotors similar to the one used with helicopters, propellers or electrical fans with battery-powered motors, generators, ultracapacitors, fuel cells, etc. and the aerodynamic lift. All systems can operate simultaneously or only some of them. If the climb is vertical the aerodynamic lift is initiated later at the same time than the horizontal displacement. The lift diagram for the descend is similar to the previous, but with lower values. Aircraft carrying external rotors will used preferably narrow wings and fuselages and the flat bottom area to increase the lifting surface.
