WO2018156041A4

WO2018156041A4 - Propulsion system and vertical take-off and landing aircraft

Info

Publication number: WO2018156041A4
Application number: PCT/RO2018/050001
Authority: WO
Inventors: Liviu Grigorian Giurca
Original assignee: Liviu Grigorian Giurca
Priority date: 2017-02-22
Filing date: 2018-01-31
Publication date: 2018-11-22
Also published as: WO2018156041A3; WO2018156041A2; RO132763A2

Abstract

The present invention relates to a propulsion system and vertical take-off and landing (VTOL) aircraft. A VTOL aircraft (100) uses a modular propulsion system (101) containing three multiple propellers (102, 103) and (104). The multiple propeller (102) is of fixed type and is included in a fuselage (105), at its front side, inside a cavity (106). The exhaust port 108 is controlled by means some louvers (109), which are oriented vertically in takeoff and landing, directing the air jet in downward, and which are inclined during transition directing the air jet in the rear. During forward flight the cavity (106) is closed by a cover (110) on the upper surface and by the louvers (109) on the lower surface. The fuselage (105) is of the type of that used by the airliners having a shape which can be considered substantially cylindrical. On the fuselage (105) are fixed side by side two wings (111).

Claims

AMENDED CLAIMS

received by the International Bureau on 03 October 2018 (03.10.2018)

[Claim 1] [Propulsion system for aircraft, of the type of these acted electrically wherein a multiple propeller (151), with thrust amplifier, contains at least two ducted fans (151), containing a rotor (152) acted by an electric motor (153) fixed in a duct (154), having some walls with an aerodynamic shape, and

several ducted fans (154) arranged in line are fixed between them by means some connected bridges (155), forming together a ducted block (166), and

each ducted fan (151) is surrounded partially at some distance by an external duct (157), having also some walls with aerodynamic shape, and

the external ducts (157) are merging forming together a surrounding ring (158) which is rigidly fixed with the duct block (156) by means some ribs (159), and

the surrounding ring (158) is offset axially from the ducted block (156) so that to obtain a Venturi effect, respectively a depression, when the ducted fans (151) are operated, respectively a parallel air flow with the air flow produced by the rotor (152), which amplify the initial flow, and

at its lower side, each ducted fan (151) has a deflector (161) which induces a swirl jet of the air produced by the rotor (152) with certain rotation speed, and

the deflectors 160 of two neighbor ducted fans (151) are built so that the neighbor air flows have contrary rotation motions, and

the electrical motors (153) are supplied with electricity from a battery pack embarked on an aircraft (1), and

the battery pack and the electrical motors (153) are supplied intermittently by an infrastructure (43) mounted on the ground which is included in a transport system (41), supplying in motion with electrical energy by contact at least one electric flying aircraft.]

[Claim 2] [Propulsion system as in the claim 1 wherein the swirl jet produced by the ducted fans (151) mixed with the air flow sucked from the ducts (154), amplifies the suction effect, respectively increases the air flow produced by the multiple propeller (150).

[Claim 3] [Propulsion system as in the claim 2 wherein the deflector (160)

contains a numbers of lamellas (161), bent through the interior side, having preferably a triangular shape and inclined so that to obtain a swirl jet of the air produced by the rotor (152) with certain rotation speed and another number of lamellas (162), intercalated with the lamellas (161), which are bent through the exterior side, having preferably a triangular shape and are inclined to obtain a swirl jet of the additional air passing between each ducted fan (151) and its external duct (157).

[Propulsion system as in the claim 2 wherein a deflector (182) is built in form of twisted lobs (183), producing the air swirl which lives a ducted fan (181).

[Propulsion system as in the claim 1 wherein the multiple propeller can be fixed in a cavity which communicate with the exterior side by two ports.

[Propulsion system as in the claim 1 wherein each multiple propeller (150) has a longitudinal axis (163) contained in the longitudinal median plane of the multiple propeller (150), along which can be mounted some supporting and driving cranks, and the multiple propeller (150) can be rotated after the longitudinal axis (163).

[Propulsion system as in the claim 1 wherein each multiple propeller (150) has a transversal axes (164), contained in the transversal median plane of the multiple propeller (150), along which can be mounted some supporting and driving cranks, and the multiple propeller (150) can be rotated after the transversal axes (164).

[Propulsion system as in the claim 2 wherein a multiple propeller (200) with thrust amplifier contains a number of parallel rows (201) of ducted fans (202), and in this case the ducted fans (202) from a row (201) intertwine with the ducted fans (202) of the neighbor row (201).

[Aircraft with vertical takeoff and landing as in the claim 1 wherein an aircraft (1) with vertical takeoff and landing contains a modular propulsion system (2) which comprises two multiple propeller groups (3), respectively (4), mounted at the extremities of a fuselage (5), one group (3), at the front and the other group (4), located at the rear of the aircraft (1).

[Aircraft as in the claim 9 wherein the front group (3) contains a multiple propeller (6) of the simple type containing and a number of adjacent ducted fans (7) aligned with an axis which is perpendicular on the longitudinal median plane of the fuselage (5) and which are rigidly mounted with two cranks (8) which can be rotated on two brackets (9) connected with the fuselage (5), containing also the bearings of the crank (8), and

each crank (8) passes through its bracket (9) and is rigidly connected at the external side with an multiple propeller (10) of the type with thrust amplifier, mounted in console, which can have different configurations, and

the simple multiple propeller (6) and the two multiple propellers (10) with thrust amplifier can be rotated together, and the simple multiple propeller (6) is rotated in the position with ducted fan central axes in horizontal plane, it becomes included in a enclosure (13) of the fuselage (5), and in this position a trot (14), having a cylindrical shape, can be operated to cover the air entry of the ducted fans (7) of the simple multiple propeller (6), and

the simple multiple propeller (6) and (10) can be rotated together by at least an actuator according to the flying operation procedure.]

[Claim 11] [Aircraft as in the claim 9 wherein the rear multiple propeller group (4) contains a multiple propeller (15), with thrust amplifier, mounted in a central position, the multiple propeller (15) with thrust amplifier including a number of adjacent ducted fans (16) aligned with an axis which is perpendicular on the longitudinal median plane of the aircraft fuselage (5), and

the multiple propeller (15) with thrust amplifier located in the central position is rigidly mounted with two cranks (18) which can be rotated on two brackets (19) connected with the fuselage (5), containing also the bearings of the crank (18), and inside the brackets 19 are mounted some actuators used to rotate the multiple propeller (15), and each crank (18) passes through its bracket (19) and is rigidly connected at the external side with a multiple propeller (20) of the type with thrust amplifier, mounted in console, which can have different configuration, and

all the rear multiple propellers (15), respectively (20) can be rotated together by the actuators according to the flying operation procedure.] [Claim 12] [Aircraft as in the claim 9 wherein the fuselage (5) of the aircraft (1) has an aerodynamic shape, respectively an upper surface (23) located in such manner as the multiple propeller (15) with thrust amplifier will create a suction effect on the upper surface (23) when the multiple propeller (15) has the ducted fan axes in horizontal plane, respectively during the forward flight, and this increases the lift of the aircraft (1), and

in forward flight the aircraft (1) uses the lift created by two main wings (24) fixed side by side on the fuselage (5) and the lift produced by the aerodynamic shape of the fuselage (5), which also work as wing, and each main wing (24) comprises a fixed wing (25) which is rigidly fixed on the fuselage (5), and a mobile wing (26), which can be folded along the fuselage (5) during takeoff and landing or can be extended during transition and forward flight, and

the two multiple propellers (10) with thrust amplifier are located so that in the forward flight directs the pressured air under the wings (24), and the two multiple propellers (20) with thrust amplifier are located so that in the forward flight aspirate the air existent above the wings (24).] [Claim 13] [Aircraft as in the claim 12 wherein all the ducted fans (7), (11), (16) and (24) are acted by electric motors and the energy necessary to supply the electric motors is furnished by a battery pack, the propulsion being pure electric, and

the battery pack can contain electrical batteries, ultracapacitors or a combination of batteries with ultracapacitors.]

[Claim 14] [Aircraft as in the claim 12 wherein the energy necessary to supply the electric motors is delivered by a hybrid unit which can have different configurations containing mainly at least a power unit and a battery pack.

[Claim 15] {Aircraft as in the claim 12 wherein in operation, during takeoff and landing from a limited space, the mobile wings (26) are folded through the rear of the aircraft (1), and the foot-print of the aircraft (1) has a minimum extension, and concomitantly the front group (3) and the rear group (4) generate air flows directed vertically, downward, and when the aircraft (1) has a certain altitude, the mobile wings (26) are extended to obtain the maximum lift in forward flight, and

during transition from the vertical lift to forward flight the group (3) and (4) are acted in an inclined position and this generate a horizontal speed to the aircraft (1), and

as much as the horizontal speed of the aircraft (1) increase, due to horizontal component of the thrust force, the lift is taken over by the wings (24), and

at the end of the transition stage, the operation of the ducted fans (7) is stopped and the ducted fans (7) gradually enter inside the enclosure (13), and when the speed of the aircraft (1) increases sufficiently, the group (3) and (4), are rotated in the position when the air flows are directed horizontally, the lift is taken over totally by the wings (24), and in this position the trot (14) is closed, the ducted fan (7) are out of operation and the aerodynamic shape of the aircraft (1) is improved concomitantly with the drug reduction, and

due to the position of the multiple propellers (10), respectively (20), the wings (24) operate as blowing wings which increase the lift of the aircraft (1).]

[Claim 16] [Aircraft as in the claim 12 wherein the control of the aircraft (1) is achieved by positioning of the group (3) and (4), as well as controlling the rotation speed of different ducted fans in different area of the aircraft (1), and when some control parts are damaged, the aircraft (1) can glide with the help of the wings (24) and land like a normal airplane on a airport runway, using some wheels.

[Claim 17] [Aircraft with vertical takeoff and landing as in the claim 1 wherein an aircraft (70) with vertical take off and landing uses a modular propulsion system (83) which contains five multiple propellers (71), (72), (73), (74) and (75) with thrust amplifier, and the aircraft uses a fuselage (76) similar with that used by the current airliners, having an external shape which can be considered as substantially cylindrical, and

the multiple propellers (71) is of fixed type and is included in the fuselage (76), located in the front side, inside a cavity (77), which communicates with the upper surface of the aircraft (70) by means an intake port (78) and which communicate with the lower surface of the aircraft (70) by means an exhaust port (79), and

the intake and the exhaust ports (78) and (79) are closed during the forward flight by two covers (80), one in the upper position and the other in the lower position, and

side by side of the fuselage (76) are fixed two fixed wings (81), and two multiple propellers (72) and (73) of the rotating type are mounted in the front of wings (81), and

two multiple propellers (74) and (75) are also of the rotating type and are mounted on two struts (82) fixed on the fuselage (76) at the rear side, and

the struts (82) are distanced from the fuselage (76) so that the air flows generated by the multiple propellers (72) and (74) do not interfere with the air flows generated by the multiple propellers (74) and (75).]

[Claim 18] [Aircraft as in the claim 17 wherein the necessary electrical energy used to supply the multiple propellers (71), (72), (73), (74) and (75) is delivered by a hybrid system which employs two turbo-generators (84), mounted on the fuselage (76) at its rear side.

[Claim 19] [Aircraft as in the claim 17 wherein in operation, during takeoff and landing, all the five multiple propellers (71), (72), (73), (74) and (75) generate air flows directed downward, respectively in vertical direction, and

during transition from the vertical flight to the forward flight the multiple propellers (72), (73), (74) and (75) are acted in inclined position and this induces a horizontal speed to the aircraft (70), and as much as the horizontal speed of the aircraft (70) increases, due to horizontal component of the thrust force developed by the multiple propellers (72), (73), (74) and (75) , the lift is taken over partially by the wings (81), and

at the end of the transition stage, the operation of the multiple propeller (71) is stopped and the cavity (77) is sealed by closing the covers (80), which improves the aerodynamics of the aircraft (70) in the forward flight, and

when the speed of the aircraft (70) increases sufficiently, the multiple propellers (72), (73), (74) and (75) are rotated in the position when the air flows are directed horizontally and the lift is taken over totally by the wings (81).]

[Claim 20] [Aircraft with vertical takeoff and landing as in the claim 1 wherein an aircraft (100) with vertical take off and landing uses a modular propulsion system (101) which contains containing three multiple propellers (102), (103) and (104) with thrust amplifier, and

the multiple propeller (102) is of fixed type and is included in a fuselage (105), at its front side, inside a cavity (106), located in the front of the aircraft (100), and the cavity (106) contains an intake port (107), which communicate with upper surface of the aircraft (100) and an exhaust port (108), which communicate with lower surface of the aircraft (100), and

the exhaust port (108) is controlled by means some louvers (109), which are oriented vertically in takeoff and landing, directing the air flow in downward, and which are inclined during transition directing the air flow in the rear, and during forward flight the cavity (106) is closed by a cover (110) on the upper surface and by the louvers (109) on the lower surface, and the fuselage (105) is of the type of that used by the airliners having a shape which can be considered substantially cylindrical, and

on the fuselage (105) are fixed side by side two wings (111), fixed, and the multiple propellers (103) and (104), of the rotating type, are mounted on the fuselage (105) behind the wings (111) and are acted by some actuators.]

[Claim 21] [Aircraft as in the claim 20 wherein in operation, during takeoff and landing, all the three multiple propellers (102), (103) and (104) generate air flows directed downward, respectively in vertical direction, and

during transition from the vertical flight to the forward flight the multiple propellers (103) and (104) are acted in inclined position and the louvers (109) incline so that to deviate the air flow behind to induces a horizontal speed to the aircraft (100), and

as much as the horizontal speed of the aircraft (100) increase, due to horizontal component of the thrust force developed by the multiple propellers (102), (103) and (104), the lift is taken over partially by the wings (111), and

at the end of the transition stage, the operation of the multiple propeller (102) is stopped and the cavity (106) is sealed by closing the cover

(110) and the louvers (109), which improves the aerodynamics of the aircraft (100) in the forward flight, and

when the speed of the aircraft (100) increases sufficiently, the multiple propellers (102) and (103) are rotated in the position when the air flows are directed horizontally and the lift is taken over totally by the wings

(111) .]

[Claim 22] [Aircraft as in the claim 20 wherein the necessary electrical energy used to supply the multiple propellers (102), (103) and (104) is delivered by a hybrid system which employs two turbo-generators

(112) , mounted on the wings (111).

[Claim 23] [Aircraft as in the claim 21 wherein an aircraft (130) uses a fuselage

(131) which has an enlargement (132) around the fixed multiple propellers (102), to solve the storage capacity of the aircraft (130).

[Claim 24] [Aircraft with vertical takeoff and landing as in the claim 1 wherein an aircraft (300), with vertical take off and landing and of the flying wing type, uses a modular propulsion system (301) which contains two multiple propellers with thrust amplifier one in the front (302) and the other in the rear (303) of the aircraft (300), and

the aircraft (300) uses a central fuselage (304) and some fixing wings

(305) which are a prolongation of the fuselage (304), and

the front multiple propeller (302) is of the fixed type and is included in a cavity (306), containing an intake port (307), which communicate with upper surface of the aircraft (300) and an exhaust port (308), which communicate with lower surface of the aircraft (300), and the longitudinal axis of the front multiple propeller (302) is included in the longitudinal median plane of the aircraft (300), and

the exhaust port (308) is controlled by means some louvers (309), which are oriented vertically in takeoff and landing, directing the air flow downward, and which are inclined during transition, directing the air flow in the rear, and

the rear multiple propeller (303) is of the rotating type and is mounted so that its longitudinal axis to be perpendicular on the longitudinal median plane of the aircraft (300), and

the rear multiple propeller (303) is rigidly mounted with two cranks (311) which can be rotated on two brackets (312) connected with the fuselage (304), containing also the bearings of the cranks (311), and inside the brackets (312) are mounted some actuators used to rotate the multiple propeller (303), and

the rear multiple propeller (303) can be rotated as a function of the flight phase, and

the fuselage (304) has an aerodynamic shape, respectively an upper surface located in so manner that when the rear multiple propeller (303) has the ducted fans with there axis in horizontal position, it is produced a fort suction effect, respectively an important depression on the upper surface, which generates an increased lift of the aircraft (300).]

[Claim 25] [Aircraft as in the claim 24 wherein in operation, during takeoff and landing the two multiple propellers (302) and (303) and generate air flows directed downward, respectively in vertical direction, and during transition from the vertical flight to the forward flight the multiple propellers (303) is acted in inclined position, the louvers (309) incline also to deviate the air flow behind, and this induces a horizontal speed to the aircraft (300), and as much as the horizontal speed of the aircraft (300) increase, due to horizontal component of the thrust force developed by the multiple propellers (302) and (303), the lift is taken over partially by the wings (305), and

at the end of the transition stage, the operation of the multiple propeller (302) is stopped and the cavity (306) is sealed by closing the cover (310) and the louvers (309), which improves the aerodynamics of the aircraft (300) in the forward flight, and

when the speed of the aircraft (300) increases sufficiently, the multiple propeller (303) is rotated in the position when the air flow is directed horizontally and the lift is taken over totally by the wings (305) and by the fuselage (304).]

[Claim 26] [Aircraft as in the claim 25 wherein an aircraft (330), with vertical take off and landing, of the flying wing type, uses a modular propulsion system (331) which contains three multiple propellers with thrust amplifier, two in the front, of the fixed type (332), and a third (303), in the rear, of the rotating, and

the front multiple propellers (332) are located symmetrically reported to the longitudinal median plane of the aircraft (330).]

[Claim 27] [Aircraft as in the claim 1 wherein an aircraft (400), with vertical take off and landing, of the flying wing type, uses a modular propulsion system (401) which contains two multiple propellers with thrust amplifier, one in the front, of the fixed type (402) and the other in the rear of the rotating type (303), and

the front multiple propeller (402), having a shape substantially trapezoidal, comprises two rows (403) of ducted fans, and

the front multiple propeller (402), is located in a cavity (404) of the fuselage and has an intake port which communicates with the upper surface and an exhaust port which communicates with the lower surface of the aircraft (400), and

during forward flight the intake port is closed by a cover and the exhaust port by some louvers as in previous examples, and

the longitudinal median plane of the aircraft (400) divides the front multiple propeller (402) in two symmetrical portions.]

[Claim 28] [Aircraft with vertical takeoff and landing as in the claim 1 wherein an aircraft (350) with vertical take off and landing uses a modular propulsion system (351) which contains a fixed multiple propeller

(352) , located in the front of a fuselage (353), considered as having flattened shape, and

the fixed multiple propeller (352), is located in a cavity of the fuselage

(353) and has an intake port which communicates with an upper surface (356) of the aircraft (350) and an external port which communicates with the lower surface of the aircraft (350), and

the fixed multiple propeller (352) has the longitudinal axes contained in the longitudinal median plane of the fuselage (353), and

during forward flight the intake port is closed by a cover and the exhaust port by some louvers, and

the modular propulsion system (351) contains at the rear side of the aircraft (350) two multiple propellers (354) of the rotating type, mounted symmetrically on a rear bracket (355) fixed in console on the fuselage (353), and

the two rotating multiple propellers (354) have the longitudinal axes perpendicularly on the longitudinal median plane of the fuselage (353), and are acted together by an actuator contained in the rear bracket (355) as a function of the flight phase, and

the fuselage (353) has an aerodynamic shape, respectively the upper surface (356) is located in so manner that when the rear multiple propellers (354) have the ducted fans with there axis in horizontal position, it is produced a fort suction effect, respectively an important depression on the upper surface (356), which generates an increased lift of the aircraft (350), and

to achieve the lift during forward flight, the aircraft (350) uses some main wings (357), fixed in the middle zone of the fuselage (353), side by side, and

each main wing (357) comprises a fixed wing (358) rigidly fixed on the fuselage (353), and a mobile wing (359) which can be folded in vertical position during vertical takeoff and landing or can be extended during transition and forward flight.]

[Claim 29] [Aircraft with vertical takeoff and landing as in the claim 28 wherein an aircraft (380) with vertical take off and landing having a flattened fuselage (381) uses a modular propulsion system (382) which contains four multiple propellers with thrust amplifier, two in the front (383), of the fixed type and two in the rear (354), of the rotating type, and the two front multiple propellers (383) are symmetrically located reported to the longitudinal medium plane of the aircraft (380).

[Claim 30] [Aircraft with vertical takeoff and landing as in the claim 1 wherein an aircraft (450) with vertical take off and landing having a flattened fuselage (451) uses a modular propulsion system (452) which contains three multiple propellers with thrust amplifier, one in the front (453) of fixed type and two in the rear (354) of the rotating type, and

the fixed multiple propeller (453), is located in a cavity of the fuselage (451) and has an intake port which communicates with an upper surface of the aircraft (450) and an external port which communicates with the lower surface of the aircraft (450), and

the front multiple propeller (453) contains at least two rows (455) of ducted fans and has a shape substantially trapezoidal, and

the longitudinal medium plane of the aircraft (450) divides the front multiple propeller (453) in two symmetrical portions.]

[Claim 31] [Aircraft as in the claim 1 wherein the aircraft can takeoff and land from and on water due to the natural buoyancy of the fuselage.

[Claim 34] [System as in the claim 1 wherein the infrastructure (43) comprises two metallic floors (51), having an undefined length, each being made from a metallic lattice (52), and

each metallic floor (51) is designed to supply with one phase of the electrical current, and is suspended over the ground by means some pillars (53), and

between the two metallic floors (51) are mounted some nonconducting rods (54), serving to reinforce the structure, and

a side of metallic floor (51) can be prolonged with a concave structure (55), supported by a nonconducting rail (56), fixed also on the pillars (53), and

the concave structure (55) is made like a network of nonconducting curved wires, located perpendicularly on the rail (56), and

the rail (56) can be extended with some panels (58) across the length of the infrastructure (43), and the panel 58 can be made from graphen or other light materials, being mounted inclined through exterior to evacuate the water from rain or the snow, and

the panels 58 can contain some halls to evacuate the water and the snow, or can be achieved as a lattice.]

[Claim 36] [Aircraft as in the claim 1 wherein an aircraft (40) uses a complementary way of charging from the infrastructure (43) by means an electric energy collector (42).

[Claim 37] [Aircraft as in the claim 36 wherein the electric energy collector (42) uses two telescopic arms (44) rotatable mounted on two bearings (45) fixed underneath the fuselage (5), and the two telescopic arms (44) are rigidified by a front cross member

(46), and a rear cross member (47), used for reinforcement, and inside of each telescopic arm (44) is mounted a power supply cable, of not conducting type, making connection between a metallic contactor (48), having an curved shape, located at the end of the telescopic arm (44), and the electrical power supply system, located inside the fuselage (5), which make the distribution of the electrical energy to different electrical devices, and

the metallic contactor (48) has some elasticity, and

each power supply cable is designed to supply with one phase of the electrical current, and

the electric energy collector (42) is acted by a telescopic actuator (49) fixed with one of its ends inside a cavity (50) of the fuselage (5) and with the other end on the front cross member (46), respectively in the middle zone.]

[Claim 38] [Aircraft as in the claim 37 wherein in operation the electric energy collector (42) is tilted with some angle and extended so that to allow the contact between each metallic connector (48) and the corresponding metallic floors (51), achieving the in-flight transmission of the electrical energy to the aircraft (40), and

this electrical energy is used partially to supply the electric motors of the ducted fans and partially to recharge the battery pack of the aircraft (40), and

to maintain a constant distance between the infrastructure (43) and the aircraft (40), and simultaneously to maintain the aircraft (40) on the same path as the infrastructure (43), the navigation system of the aircraft (40) is of autonomous type and uses a sensor system and emitters located on both the infrastructure (43) and the aircraft (40), connected with a global positioning system, and when is detected a damage of the supply system or when the external conditions, respectively when the distance between the aircraft (40) and the infrastructure (43) cannot be maintained, the aircraft (40) is forced to increase the altitude and moves away from the infrastructure (43) and in this case the electric energy collector (42) is retracted in the initial position and the aircraft (40) can be operated also by the pilot as an independent vehicle.]

[Claim 39] [Aircraft as in the claim 38 wherein when between the aircraft (40) and the panels (50) there is a distance among 3 and 12 m, the aircraft (40) operates with ground effect, compressing the existent air between the wings (24) and the panels (58).

[Aircraft as in the claim 38 wherein if the aircraft (40) is a pure electric vehicle its propulsion system is of dual type because can use the energy from the battery pack or from infrastructure (43).

[Aircraft as in the claim 38 wherein if the aircraft (40) is a hybrid electric vehicle its propulsion system is of triple type because can use the energy from the power unit, from infrastructure (43) or from the battery pack, and

the aircraft (40) with hybrid propulsion system which use also the infrastructure (43), can has a reduced size battery pack, which ensures the independent operation of the aircraft (40) for several minutes in emergency cases when the hybrid system is damaged, ensuring the redundancy of the system.]

[System as in the claim 34 wherein a big number of aircraft (40) can simultaneously use the infrastructure (43) for the same direction of flight and an autonomous navigation system maintain a safe distance between two successive aircraft (40).

[System as in the claim 42 wherein if the infrastructure (43) covers a vast territory it can be used to achieve an efficient transport on this territory and near the cities the aircraft (40) leaves the infrastructure (43) and lands in the destination area.

[Claim System as in the claim 42 wherein if the infrastructure (43) is fragmented, it can be used to charge in motion the aircraft (40) with electric energy without to be stopped when it finishes its energy.

[System as in the claim 42 wherein the infrastructure (43) can be doubled with a parallel structure used for the other direction of travel, located to secured distances, the two parallel infrastructures (43) forming together an aerial freeway.

STATEMENT UNDER ARTICLE 19 (1 )

Inventor opinion is that the claims 32 alone is not new (see International Search Report) but the combination of claims 1 and 32 resulting as CLAIM 1 is new and also induces the unity of invention.

Inventor opinion is that the claim 32 will be cancelled and several dependent claims must to change the dependency to keep the unity of invention. Also the dependent claims 33 and 35 will be cancelled as consequence of the International Search Report.

New statement:

1. The claims 1 and 32 are unified and the content is changed.

2. The claims 32, 33 and 35 are cancelled.

3. The dependency (preamble) of the claims 5, 6, 7, 9, 17, 20, 24, 27, 28, 30, 31, 34, 36 is changed but the content remains unchanged.

4. There are no modifications of the description or of the drawings.