Vector-traction aircraft

Abstract

------ Vector-Tripping Aircraft The present invention relates to a vector-tripping aircraft (1), comprising: a wing in the form of a wing (2); a tail in the form of at least one rear aileron (3) carried by said wing (2); and an engine assembly (4) connected to said wing (2) for thrusting the aircraft (1), characterized in that said engine assembly (4) is disposed in front of said wing (2) and is connected to it by at least one arm (6), and that it comprises at least one turbine (10) configured to create, in operation, a jet of air discharged towards said wing (2) by a steerable nozzle (11). Figure to be published with the abbreviation: Figure 1

Description

Title of the invention: Vector-traction aircraft

[0001] The present invention relates to a vectored traction aircraft.

[0002] To steer in flight, an aircraft uses a set of movable surfaces called control surfaces which act on the air and allow the aircraft to be piloted.

[0003] The removal of control surfaces, implemented on thrust-vectoring aircraft, increases the aircraft's maneuverability and stealth. These aircraft direct the jet stream from a jet engine / turbine in order to steer.

[0004] An improvement has been sought in such rudderless aircraft to increase their control and maneuverability and reduce their weight.

[0005] Aircraft with thrust vectoring, in addition to eliminating control surfaces, improve their performance through the phenomenon of induced lift. Indeed, by positioning the engine assembly in front of the aircraft's wing, an induced lift phenomenon is created, which improves the aircraft's control.

[0006] In addition, this also allows the aircraft to be guided on the ground without having to use landing gear control devices, which allows for a reduction in the mass of the aircraft.

[0007] The present invention relates to a vectored-traction aircraft, comprising: • a wing-like structure; • a fin in the form of at least one rear wing supported by said wing; and • an engine assembly connected to said wing for the traction of the aircraft,

[0008] characterized by the fact that said engine assembly is arranged in front of said wing by being connected to it by at least one arm, and that it comprises at least one turbine configured to create in operation a jet of air discharged towards said wing by a steerable nozzle.

[0009] The steerable nozzle allows the expelled air jet to be directed. By doing so, the aircraft eliminates the need for rudders, thereby reducing the number of mechanical parts. The aircraft is thus lighter, more reliable, and less expensive. This weight reduction is particularly advantageous for a 100% electric aircraft.

[0010] The axis of a turbine can be oriented along a line parallel to the front-rear line of the wing.

[0011] The engine assembly may include two turbines. When the aircraft has two turbines, it is capable of rotating around its longitudinal axis, improving its stealth, when one turbine tilts in one direction and the other in the opposite direction.

[0012] The engine assembly can be arranged in a nacelle by which it is connected to the wing by the arm(s), and which is open at the front and rear in the mounting position.

[0013] The engine assembly can be removable. The removable nature of the engine assembly allows the number of turbines that make up the engine assembly to be changed easily.

[0014] According to a particular embodiment of the aircraft according to the present invention, a turbine consists of a bladed rotor housed in a cylindrical casing, and the nozzle associated with the turbine, mounted to direct the air jet towards the wing of the aircraft, consists of three parts, namely - a first nozzle section consisting of a first ring suitable for being slipped onto and fixed to the turbine housing, and externally bearing: - a support for a first servomotor to control the movements of the nozzle to the right and to the left, and a support for a second servomotor to control the movements of the nozzle upwards and downwards; and - two diametrically opposed pivot link partners, located in a plane perpendicular to the mean plane of the wing; - a second nozzle part consisting of a second ring adapted to be partially slipped onto the first ring in its end region facing the wing in the mounting position and to pivot around an axis perpendicular to the mean plane of the wing in the mounting position, and carrying: - internally, two pivot link partners capable of cooperating with the pivot link partners of the first nozzle section; and - externally, two diametrically opposed pivot joint partners, located in a plane parallel to the mean plane of the wing in the mounting position; and - a third nozzle section consisting of a third ring capable of being partially threaded onto the second ring in its end region facing the wing in the mounting position and bearing: - internally, two pivot link partners capable of cooperating with the pivot link partners carried externally by the second part of the nozzle; and - externally, in a plane parallel to the wing and on one side, a mounting point for a connecting rod of a first connecting rod-crank assembly, the crank of which is fixed to the servomotor controlling the movements of the nozzle to the right and to the left; and, in a plane perpendicular to the wing and in its upper part in the mounting position, a mounting point for a connecting rod of a second connecting rod-crank assembly, the crank of which is fixed to the servomotor for controlling the upward and downward movements of the nozzle.

[0015] Each first part of the nozzle may include, in a plane parallel to the wing in the mounting position, two opposing longitudinal grooves each receiving a transverse bar for the attachment of the turbine associated with the inner wall adjacent to the nacelle or, in the case where several turbines are provided, to the adjacent turbine.

[0016] Advantageously, the wing of the aircraft according to the present invention is a so-called Manta wing.

[0017] The wing advantageously comprises a central main part, two lateral parts capable of pivoting upwards in the mounting position, and two rear fins.

[0018] The aircraft according to the present invention may include a landing gear, a free-moving front wheel and two rear wheels.

[0019] The wing may be surmounted at the front by a cabin section, said cabin section being removable. Without the cabin section, the aircraft can fly autonomously.

[0020] The present invention also relates to a turbine comprising a bladed rotor housed in a cylindrical casing and a nozzle associated with the turbine, said nozzle being made up of three parts, namely - a first nozzle section consisting of a first ring suitable for being slipped onto and fixed to the turbine housing, and externally bearing: - a support for a first servomotor to control the movements of the nozzle to the right and to the left, and a support for a second servomotor to control the movements of the nozzle upwards and downwards; and - two diametrically opposed pivot link partners, located in a vertical plane; - a second nozzle part consisting of a second ring adapted to be partially slipped onto the first ring in its end region facing the air outlet in the mounting position and to pivot around a vertical axis, and bearing: - internally, two pivot link partners capable of cooperating with the pivot link partners of the first nozzle section; and - externally, two diametrically opposed pivot connecting partners, located in a horizontal plane; and - a third nozzle section consisting of a third ring adapted to be partially slipped onto the second ring in its end region facing the air outlet in the mounting position and bearing: - internally, two pivot link partners capable of cooperating with the pivot link partners carried externally by the second part of the nozzle; and - externally, in a horizontal parallel plane and on one side, a fixing point for a connecting rod of a first connecting rod-crank assembly whose crank is fixed on the servomotor controlling the movements of the nozzle to the right and to the left; and, in a vertical plane and in the upper part in the mounting position, a fixing point for a connecting rod of a second connecting rod-crank assembly whose crank is fixed on the servomotor controlling the movements of the nozzle upwards and downwards.

[0021] To better illustrate the object of the present invention, a particular embodiment thereof will be described below, by way of indication and not limitation, with reference to the attached drawing.

[0022] On this drawing: • Fig. 1 is a perspective view of an aircraft according to the present invention oriented with its engine assembly in the foreground and on the left; • [Fig.2] is a perspective view of the aircraft in [Fig.1] oriented with its rear wings forward and to the right; • [Fig.3] is a top view of the aircraft in Figures 1 and 2; • [Fig. 4] is a front view of the aircraft in Figures 1 to 3, assembly side engine ; • [Fig.5] is a view corresponding to [Fig.1], showing the aircraft with its three wheels extended; • [Fig.6] is a front view corresponding to [Fig.4] of the aircraft with its three wheels extended; • [Fig.7] is a rear view, rear wing side, of the aircraft with its three wheels extended; • [Fig.8] is a side view of the aircraft with its wheels extended; • [Fig. 9] is a perspective and side view of the front part of the aircraft with its wheels off; • [Fig. 10] is a view corresponding to [Fig. 1] in exploded perspective; • [Fig. 1 1] is, on a larger scale and in perspective in the orientation of [Fig. 1], a view of the front part of the aircraft showing the aircraft engine assembly in place in its nacelle; • [Fig. 12] is a top perspective view of the front part of the aircraft; • [Fig. 13] is an exploded perspective view of a turbine of the engine assembly and the three parts of its associated nozzle, with the air intake side facing forward and to the left; • [Fig. 14] is a view corresponding to [Fig. 13], with the air outlet side facing forward and to the right; • [Fig. 15] is a view corresponding to [Fig. 13] with the air intake side to the right; • [Fig.16] is a top view of a turbine in straight-line flight position with air blown in the axial direction, the servomotor and the connecting rod-crank assembly being omitted; • [Fig. 17] is a view corresponding to [Fig. 16], with the turbine oriented to blow air onto a side region of the wing; • [Fig. 18] is a perspective view of the turbine in straight-line flight position with air blowing upwards, omitting the servomotor and the connecting rod-crank assembly; • [Fig.19] is a view corresponding to [Fig.18] but with air blowing downwards; • [Fig.20] is a view of the turbine equipped with servomotors and connecting rod-crank assemblies and shown from the right side relative to [Fig. 16]; • [Fig.21] is a view of the turbine equipped with servomotors and connecting rod-crank assemblies and shown in the same position as [Fig.16]; • [Fig.22] is a view corresponding to [Fig.21], but with the mounting sides of the servomotors reversed; • [Fig. 23] is a perspective view corresponding to [Fig. 21]; and • [Fig.24] is a perspective view corresponding to [Fig.22].

[0023] Referring to Figures 1 to 12, one can see that 1 has designated as a whole an aircraft according to a particular embodiment of the present invention.

[0024] The aircraft 1 comprises a wing in the form of a Manta wing 2, a tail in the form of two rear fins 3 carried by the wing 2 and an engine assembly 4 arranged in front of the wing 2 for the propulsion of the aircraft 1.

[0025] The wing 2 comprises a central part 2a, of large surface area, and two lateral parts 2b capable of being folded upwards in flight position.

[0026] The engine assembly 4 is housed in a nacelle 5 connected to the wing 2 at the front of it by two arms 6. The nacelle 5 has the general shape of a box open at the front and rear when considering its position in place on the aircraft 1, and it is connected to the wing 2 by two lateral arms 6.

[0027] The aircraft 1 comprises a cabin 7 and includes a landing gear 8 and three wheels, namely a front idler wheel 9a and two rear wheels 9b.

[0028] Cabin 7, located in the forward region of wing 2,

[0029] In the example shown, the engine assembly 4 consists of two turbines 10 arranged side by side in the nacelle 5, with their axes oriented along a line parallel to the mean longitudinal line of the wing 2. Each turbine 10 creates a jet of air which, in operation, is discharged towards the wing 2 by means of a steerable nozzle IL

[0030] Figures 13 to 15 are exploded perspective views of a turbine 10 and its associated nozzle 11

[0031] A turbine 10 consists of a bladed rotor 10a housed in a cylindrical casing 10b, the axis of the rotor 10a being coincident with the longitudinal axis of the casing 10b.

[0032] A nozzle 11 associated with a turbine 10 comprises three parts 12, 13 and 14.

[0033] The first part of the nozzle 12 consists of a first ring adapted to be slipped onto the housing 10b of the turbine 10 and fixed thereto, and carrying externally: - a support 15 for a first servomotor 16 for controlling the movements of the nozzle 10 to the right and to the left and a support 17 for a second servomotor 18 for controlling the movements of the nozzle 10 upwards and downwards; and - two pivot link partners 19 diametrically opposed, located in a plane perpendicular to the mean plane of wing 2.

[0034] The ring of this first part of the nozzle 12 has, in a plane parallel to the wing 2 in the mounting position, two opposing longitudinal grooves (20). In the example shown, one groove 20 receives a lateral cross member 22 for the attachment of the turbine 10 associated with the inner wall adjacent to the nacelle 5 and, the other groove 20 receives a central cross member 21 for attachment to the adjacent turbine 10 ([Fig. 11]).

[0035] The second part of the nozzle 13 consists of a second ring adapted to be partially threaded onto the first ring in its end region facing the wing 2 in the mounting position and to pivot about an axis perpendicular to the mean plane of the wing 2 in the mounting position, and carrying: - internally, two pivot link partners 23 capable of cooperating with the pivot link partners 19 of the first part of nozzle 12; and - externally, two diametrically opposed pivot link partners 24, located in a plane parallel to the mean plane of the wing 2 in the mounting position.

[0036] The third part of the nozzle 14, consisting of a third ring adapted to be partially threaded onto the second ring in its end region facing the wing 2 in the mounting position and bearing: - internally, two pivot link partners 25 capable of cooperating with the pivot link partners 24 carried externally by the second part 13 of the nozzle; and - externally, in a plane parallel to wing 2 and on one side, a fixing point 26 of a connecting rod 29 of a first connecting rod-crank assembly 28 whose crank 30 is fixed on the servomotor 16 for controlling the movements of the nozzle to the right and to the left; and, in a plane perpendicular to wing 2 and in the upper part in the mounting position, a fixing point 27 of a connecting rod 32 of a second connecting rod-crank assembly 31 whose crank 33 is fixed on the servomotor 18 for controlling the movements of the nozzle upwards and downwards.

[0037] In order to maintain the airflow passing through the turbine 10, the diameter of the housing 10b corresponds to the diameter of the ring of the third part of the nozzle 14 on the air outlet side.

[0038] Figures 16 to 19 and 20 to 22 show the movement of the second and third parts of nozzle 13 and 14.

[0039] The servomotor 16 is associated with the connecting rod-crank assembly 28, the connecting rod 29 of which is connected to the third part of the nozzle 14 via the attachment point 26.

[0040] The servomotor 18 is associated with the connecting rod-crank assembly 31, the connecting rod 32 of which is connected to the third part of the nozzle 14 via the attachment point 27.

[0041] When the servomotor 16 drives the crank 30 to rotate clockwise, the connecting rod 29 is pulled towards the turbine body 10. In doing so, the connecting rod 29 pulls on the attachment point 26, which causes the second part of the nozzle 13 to rotate to the left by rotation around the pivot joint formed by the partners 19 and 23. Conversely, when the servomotor 16 drives the crank 30 to rotate counterclockwise, the second part of the nozzle 13 is caused to rotate to the right.

[0042] When the servomotor 18 drives the crank 33 to rotate clockwise, the connecting rod 32 is pulled towards the turbine body 10. In doing so, the connecting rod 32 pulls on the attachment point 27, which causes the third nozzle section 14 to rotate upwards by rotation around the pivot joint formed by the partners 24 and 25. Conversely, when the servomotor 18 drives the crank 33 to rotate counterclockwise, the third nozzle section 14 is caused to rotate downwards.

[0043] In Figures 21 and 23, the servomotor 16 is mounted on the left side of the turbine and the servomotor 18 on the right. This arrangement can be reversed, as shown in Figures 21 and 23. Figures 22 and 24, where servomotor 16 is mounted on the right and servomotor 18 on the left.

[0044] In operation, it is therefore possible to direct the flow exiting the turbines 10 by orienting the nozzles 11, each nozzle moving synchronously with the other. For example, when the nozzles 11 are oriented to the right, the aircraft 1 is driven to the right. When the nozzles 11 are oriented downwards, the aircraft is driven downwards.

[0045] Furthermore, when the aircraft is on the ground, it is possible to guide the aircraft to the right or to the left by the orientation of the airflow from the turbines 10. This allows only one idler wheel 9a to be at the front of the aircraft 1, which then does not need another mechanism for guiding the aircraft 1 on the ground, thus saving weight by the absence of such a mechanism.

[0046] Reference figures

[0047] 1 Aircraft

[0048] 2 Wing

[0049] 2a Central part of the wing

[0050] 2b Lateral part of the wing

[0051] 3 Rear wing

[0052] 4 Engine assembly

[0053] 5 Gondola

[0054] 6 Arms

[0055] 7 Cabin

[0056] 8 Landing gear

[0057] 9a Front idler wheel

[0058] 9b Rear wheel

[0059] 10 Turbine

[0060] 10a Bladed rotor

[0061] 10b Carter

[0062] 11 Nozzle

[0063] 12 First part of nozzle

[0064] 13 Second part of nozzle

[0065] 14 Third part of nozzle

[0066] 15 First servomotor support

[0067] 16 First servomotor (left-right movement)

[0068] 17 Second servomotor support

[0069] 18 Second servomotor (up-down movement)

[0070] 19 External pivot connecting partner on nozzle part 12

[0071] 20 Groove

[0072] 21 Central cross member

[0073] 22 Lateral cross member

[0074] 23 Internal pivot connecting partner on nozzle part 13

[0075] 24 External pivot connecting partner on nozzle part 13

[0076] 25 Internal pivot linking partner on nozzle part 14

[0077] 26 Fixing point for connecting rod of the connecting rod-crank assembly at the first servomotor 16 (right-left)

[0078] 27 Fixing point for connecting rod of the connecting rod-crank assembly at the first servomotor 18 (up-down)

[0079] 28 Connecting rod-crank assembly associated with servomotor 16

[0080] 29 Connecting rod of assembly 28

[0081] 30 Crank of assembly 28

[0082] 31 Connecting rod-crank assembly associated with the servomotor 18

[0083] 32 Connecting rod of assembly 31

[0084] 33 Crank of assembly 31

Claims

Demands

1. - Vector-pitch aircraft (1) comprising: • a wing in the form of a wing (2); • a tail in the form of at least one tail fin (3) carried by said wing (2); and • an engine assembly (4) connected to said wing (2) for the propulsion of the aircraft (1), characterized in that said engine assembly (4) is disposed in front of said wing (2) by being connected to it by at least one arm (6), and that it comprises at least one turbine (10) configured to create in operation a jet of air discharged towards said wing (2) by a steerable nozzle (11).

2. - Aircraft (1) according to claim 1, characterized in that the axis of a turbine (10) is oriented along a line parallel to the front-rear line of the wing (2).

3. - Aircraft (1) according to any one of claims 1 and 2, characterized in that the engine assembly (4) comprises two turbines (10).

4. - Aircraft (1) according to any one of claims 1 to 3, characterized in that the engine assembly (4) is arranged in a nacelle (5) by which it is connected to the wing (2) by the arm or arms (6), and which is open at the front and rear in the mounting position.

5. - Aircraft (1) according to any one of claims 1 to 4, characterized in that the engine assembly (4) is removable.

6. - Aircraft (1) according to any one of claims 1 to 5, characterized in that a turbine (10) is constituted by a bladed rotor (10a) housed in a cylindrical casing (10b) and that the nozzle (11) associated with the turbine (10), mounted to direct the air jet towards the wing (2) of the aircraft (1), is made up of three parts, namely a first nozzle section (12) consisting of a first ring adapted to be slipped onto the turbine housing (10b) and fixed thereto, and externally carrying: a support (15) for a first servomotor (16) for controlling the movements of the nozzle (10) to the right and to the left, and a support (17) for a second servomotor (18) for controlling the movements of the nozzle (10) upwards and downwards; and two pivot link partners (19) diametrically opposed, located in a plane perpendicular to the mean plane of the wing (2); a second nozzle part (13) consisting of a second ring adapted to be partially threaded onto the first ring in its end region facing the wing (2) in the mounting position and to pivot about an axis perpendicular to the mean plane of the wing (2) in the mounting position, and carrying: internally, two pivot link partners (23) capable of cooperating with the pivot link partners (19) of the first nozzle part (12); and Externally, two diametrically opposed pivot joint partners (24), situated in a plane parallel to the mean plane of the wing (2) in the mounting position; and a third nozzle portion (14) consisting of a third ring adapted to be partially threaded onto the second ring in its end region facing the wing (2) in the mounting position and carrying: internally, two pivot joint partners (25) adapted to cooperate with the pivot joint partners (24) carried externally by the second nozzle portion (13); and externally, in a plane parallel to the wing (2) and on one side, a mounting point (26) for a connecting rod (29) of a first connecting rod-crank assembly (28), the crank of which (30) is fixed to the servomotor (16) for controlling the nozzle movements to the right and to the left; and, in a plane perpendicular to the wing (2) and in its upper part in the mounting position, a point fixing (27) of a connecting rod (32) of a second connecting rod-crank assembly (31) whose crank (33) is fixed on the servomotor (18) for controlling the movements of the nozzle upwards and downwards.

7. - Aircraft (1) according to claims 4 and 6 taken in combination, characterized in that each first part of nozzle (12) has, in a plane parallel to the wing (2) in mounting position, two opposing longitudinal grooves (20) each receiving a transverse bar (21, 22) for the attachment of the turbine (10) associated with the inner wall adjacent to the nacelle (5) or, in the case where several turbines (10) are provided, to the adjacent turbine (10).

8. - Aircraft (1) according to any one of claims 1 to 7, characterized in that the wing (2) comprises a central main part (2a), two lateral parts (2b) capable of pivoting upwards in the mounting position, and two rear fins (3).

9. - Aircraft (1) according to any one of claims 1 to 8, characterized in that it comprises a landing gear (8), a free-moving nose wheel (9a) and two tail wheels (9b).

10. - Aircraft (1) according to any one of claims 1 to 9, characterized in that the wing (2) is, at the front, surmounted by a cabin part (7), said cabin part (7) being removable.

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