FR3131904A1 - MIXED-USE ROTARY-WING AIRCRAFT, INCLUDING CARRYING PASSENGERS IN PILOT MODE OR CARRYING LOAD IN DRONE MODE - Google Patents

Abstract

Rotary-wing aircraft, for mixed use, in particular with carrying passengers in piloted mode or carrying loads in drone mode, for versatile applications, comprising:- a core structure (10) with a transfer case (14), an engine (12), - a cockpit (22) and its on-board electronics, - a rotary wing (16) with its rotor (16-1) and blades (16-2) - a tail (18) and its tail rotor (20), and- a skid unit (24) with equipment suitable for the intended application. The invention also covers the container (30) suitable for transporting, assembling and disassembling said aircraft. Figure to be published with abstract: Fig. 2

Description

ROTARY WING AIRCRAFT FOR MIXED USE, IN PARTICULAR CARRYING PASSENGERS IN PILOT MODE OR CARRYING LOAD IN DRONE MODE

The invention relates to a rotary wing aircraft, for mixed use, in particular with carrying passengers in piloted mode or carrying loads in drone mode.

In the aeronautics world, a category of aircraft is classified as VLA, from the Anglo-Saxon trigram “Very Light Aircraft”, very light aircraft. These very light aircraft comply with different rules from those of airplanes, both in the construction itself and in maintenance. This has allowed numerous innovations and access to flight to many new enthusiasts. Constraints remain for this type of classification as for all aircraft, and predominantly, weight. It should be noted that excess weight must always be combated because for the same power developed, the heavier the structure, the more limited the load carried, whether it be passengers or freight or other elements. Furthermore, it is a vicious circle because the heavier the structure, the more power is needed, the more power is needed, the more fuel is needed unless the range of action is limited. So it's always a compromise.

The field concerned by the present invention is a rotary wing aircraft in the very light VLA aircraft category.

A rotary wing aircraft comprises, in known manner, the following main parts:
- a cell, to receive pilots/passengers or to receive the electronic means of autonomous piloting,
- an engine associated with a fuel tank,
- a rotating wing comprising at least two blades, rotating in a substantially horizontal plane, tiltable over a given angular range,
- a first transmission, with a substantially vertical axis of rotation, interposed between the engine and said rotating wing,
- an anti-rotation rotor, rotating in a substantially vertical plane,
- a second transmission, with a substantially horizontal axis of rotation, interposed between said motor and said anti-rotation rotor,
- a tail intended to support the anti-rotation rotor and to keep it away from the rotating wing,
- ground support pads, on which the landed aircraft rests.

The VLA design is identical to that of certified aircraft, but the weight criterion is prohibitive to remain in this flight class and the mass is necessarily more limited, depending on legislation and changes in this legislation. Also, the mass of VLA class aircraft must be limited to allow the carriage of two passengers or the largest possible load in drone mode.

The aircraft according to the present invention consists of providing an architecture common to the two modes, the piloted mode with passenger carrying and the drone mode with load carrying, whether the applications are civil, military, private, commercial. The aim of the present invention is also to allow transport of said rotary wing aircraft to any location of intervention and development from the parking or manufacturing area. However, this location can be very far from the place of residence of said aircraft. In addition, this location can also be modified according to needs. In fact, the aircraft must be able to be dismantled for transfer in a limited volume, therefore at limited costs. The load carrying version applications are numerous, whether in the military field, in the agricultural field for phytosanitary treatments of large areas, for resupplying sites inaccessible otherwise than by air, to name but a few. application examples. The autonomy of the rotary wing aircraft according to the present invention is entirely suitable for local missions and makes it possible to work with a range of around 250 km to give an idea. In addition, in the load carrying version, it is necessary to have means of removable fixing of the load in order to be able to set up a container intended to receive packages, spraying means with the associated tanks, containing the phytosanitary product, surveillance and control cameras, measurement sensors or other weapons in military version, again to name only these applications.

The rotary wing aircraft according to the invention, for mixed use, in particular with carrying passengers in piloted mode or carrying load in drone mode, for versatile applications, comprises:
- a core structure with a drive motor with a motor output shaft,
- a transfer case with a first output and a second output,
- a cockpit and on-board electronics,
- a rotating wing with its rotor and blades,
- a tail and its tail rotor, and
- a skid unit with equipment adapted to the intended application.

This rotary wing aircraft has a monolithic core structure.

The core structure is more particularly made of composite materials based on carbon fibers and includes housings laterally, capable of receiving the fuel tanks, necessary for powering the drive motor.

The rotary wing aircraft according to the invention comprises a skid unit connected to the core structure by quick releases.

More particularly, the tail comprises a connecting flange and the core structure comprises a fixing flange capable of cooperating with said connecting flange.

According to another characteristic, the core structure comprises a cradle intended to receive the drive motor.

According to a specific architectural characteristic, the engine output transmission shaft, the transfer case with its first output towards the rotary wing and its other output towards the tail rotor, are in the same plane.

According to another very important characteristic, an alignment of the transfer case motor and the transmission shaft towards the tail rotor is provided, this leading to high compactness, better reliability, improved efficiency, limitation of mechanical losses and less wear on parts, in particular.

In drone mode, the controls are electric and in passenger transport mode, the controls are manual.

The invention also covers a container for a rotary wing aircraft according to the present invention. This container includes a framework with reception means for receiving the different units of said aircraft:
- core structure with drive motor and transfer case,
- tail and tail rotor,
- skid unit, and
- sail blades.

This container has six sides:
- a lower face,
- an upper face,
- two front and rear faces, with at least one of them mounted articulated relative to the lower face, and
- two side faces.

The upper face is supported by vertical uprights, each comprising two upper and lower coaxial profiles, mounted telescopically relative to each other.

This container is also equipped with a maneuvering hoist, mounted on a beam, movable relative to said upper face.

According to a particular embodiment, the walls are made up of a sandwich, notably a honeycomb core and light alloy skins.

The rotary wing aircraft according to the present invention is now described using examples that are purely illustrative and in no way limiting the scope of the invention, and from the appended drawings, drawings in which the different figures represent:

represents a schematic perspective view of the rotary wing aircraft according to the present invention, in drone version, with load carrying.

represents an exploded schematic view of the different constituent parts of the rotary wing aircraft of the .

represents a view of a transport container of the rotary wing aircraft, according to the present invention, before its installation in said container.

represents a view of a transport container of the rotary wing aircraft, according to the present invention, with the aircraft disassembled and in the transport position.

represents a view of the transmission kinematics with its alignment.

The rotary wing aircraft according to the present invention is now described with reference to Figures 1 or 2, indifferently.

The rotary wing aircraft according to the present invention comprises a core structure 10, a drive motor 12, with a transfer case 14, a rotary wing 16 and its controls, a tail 18, a tail rotor 20 and its controls , a cockpit 22 and a skid unit 24.

The core of structure 10 visible on the , is made of monolithic composite material. This core structure is monolithic and accommodates all the components of the aircraft. The front and the rear are considered with respect to the direction of flight symbolized by the arrow F. This core of monolithic structure 10, comprises a front housing 10-1 intended to receive a cradle 12-1 itself adapted to receive the drive motor 12. A central housing 10-2 receives the transfer case 14. On the sides of the core structure, open side housings 10-3, in this case 4 side housings in the embodiment shown, are intended to receive fuel tanks, intended to supply the drive motor 12. At the rear, the core structure 10 comprises an extension 10-4 with a substantially hollow cylindrical end, with a fixing flange 10-5 . Structural reinforcements 10-6 are arranged laterally.

The drive motor 12 is attached to the core structure and held by the cradle 12-1. This drive motor 12 comprises an output transmission shaft 12-3 which is connected to the transfer case 14. It is supplied with fuel from the fuel tanks 12-2, this in a known manner. The engine is an internal combustion engine of a type known, in particular under the registered trademarks “ROTAX” or “D-Motor”, in order to provide and distribute the mechanical power necessary for the rotating wing 16 and the tail rotor 20 to ensure rotation.

The transfer case 14 receives the output transmission shaft 12-3 of the engine 12 and includes sets of bevel and stepped gears as well as two outputs, a first output 14-1 towards the rotating wing 16 and the other 14-2 towards the tail rotor 20. This allows, from a common rotation speed of the output transmission shaft 12-3 of the drive motor 12, to obtain a constant ratio of the differentiated rotation speeds of the rotary wing 16 and rotation of the tail rotor 20.

The rotating wing 16 comprises in a known manner a rotor 16-1, in this case a rotor 16-1 receiving two blades 16-2 in the embodiment presented. This rotor 16-1 also comprises, in a known manner, the different bearings, bearings, axes, rings and linkages for controlling the incidence of the blades, the inclination of the rotor towards the front or rear, and/or towards the right or left sides to provide elevation, descent, left or right turns as well as hovering. These different commands, which are not the subject of the present invention, are grouped under the common reference 16-2. Electric motors ensure, in the drone variant presented, the movements of these different controls 16-2 instead of manual controls in a piloted version.

The tail rotor 20 is connected to the output 14-2 of the transfer case 14 by a transmission shaft 20-1. The tail rotor 20 comprises two blades 20-2 and an angle gear 20-3 in order to be able to rotate the blades 20-2 of the tail rotor 20 in a plane parallel to the direction of flight F. A linkage of control 20-4 ensures the modification of the incidence of the blades, in a known manner, to increase or decrease the anti-rotation torque, depending on the flight parameters and the parameters of the rotating wing.

The tail 18 is connected to the core structure 10 by a connecting flange 18-1 intended to cooperate, for example by means of a bayonet assembly, with the fixing flange 10-5 of the extension 10-4 with a substantially hollow cylindrical end of the heart of monolithic structure 10. The tail 18 is therefore removable. The profile of the tail 18 is perfectly matched geometrically to that of the extension 10-4 in order to ensure continuity of the exterior surface and a connection to the flange 10-5. The tail 18 includes access hatches 18-5 and other wing appendages 18-6 depending on aerodynamic needs. The tail 18 receives in its interior volume, the transmission shaft 20-1 of the tail rotor 20. The tail 18 receives at its free end, opposite the end which carries the connecting flange 18-1, the rotor of tail 20 and its angle gear 20-3.

The cockpit 22 is shown for the drone variant as indicated, that is to say minimalist, housing the control organs and the on-board electronics, not shown. This cockpit 22 is of aerodynamic shape to limit drag and of solidity adapted to the use and in particular ensuring resistance to impacts from volatiles, for example or impacts from munitions in the case of military application. The cockpit 22 constitutes a protective casing.

Note that the particular architecture of the aircraft according to the present invention is arranged so that the output transmission shaft 12-3 of the engine 12, the transfer case 14 with its first output 14-1 towards the rotating wing 16 and its other outlet 14-2 towards the tail rotor 20 are in the same plane. Note that the motor shaft 12-3, the transfer case 14 with its output 14-2 and the shaft 20-1 are perfectly aligned, see . This alignment leads to certain advantages because it provides high compactness, better reliability, improved efficiency, limitation of mechanical losses and less wear of the parts, these advantages not being limiting. Thus vibrations are also partly limited by this alignment, which is important to maintain perfect integrity of the structure without the need to provide specific reinforcements, synonymous with additional weight and degraded performance.

According to the present invention, the rotary wing aircraft has multiple applications. In known manner, it is necessary to provide a skid unit 24 to rest on the ground. By pads we mean rigid pads intended to rest on the ground but also floating pads to rest on a liquid surface for certain applications. In the case of the present invention, the shoe unit 24 comprises connection means 24-1 with the core structure 10 so as to make it removable. These connection means 24-1 are quick attaches. This skate unit, according to the particularity of the present invention, includes on-board components 24-2, linked to the application. In this case, to cite a first example of application, non-limiting and purely exemplifying, if it is an application for aerial phytosanitary treatment, the skid unit 24 comprises a housing intended to receive a reservoir storage of said phytosanitary product, spray booms, means for pumping and pressurizing said phytosanitary product to diffuse it through said booms. In a second example, no more restrictive than the first, the skate unit 24 includes a box intended to receive a load. This trunk may include in-flight opening/closing means to ensure in-flight release of the contents of said trunk.

Thus, we see that the rotary wing aircraft according to the invention comprises four units:
- the core structure 10 with its transfer case 14, its drive motor 12 and its rotor 16-1 as well as the cockpit 22 and its on-board electronics,
- the 16-2 blades of the rotary wing
- the tail 18 and its tail rotor 20
- the skid unit 24 with its equipment adapted to the intended application.

The rotary wing aircraft according to the present invention is composed of dismountable units in particular the tail 18 since it is sufficient to uncouple this tail 18 from the core structure 10 and disconnect, to the right of the outlet 14-2 of the transfer case 14, the transmission shaft 20-1 driving the tail rotor. The mechanical connection can be a splined shaft and a splined tube, in a well-known manner. Likewise, the shoe unit 24 can be easily uncoupled from the core structure 10 by dismantling the quick releases. In addition to easy access, easy servicing and maintenance, the rotary wing aircraft according to the present invention can be transported in a restricted volume in the event of missions in remote territories, more particularly in the volume of a container of standardized dimensions.

The present invention therefore also relates to a transport container 30 intended to receive a rotary wing aircraft, in particular that of the present invention. We refer to the and 4 which represent this transport container 30. This transport container 30 according to the present invention allows the transport of the different units of the rotary wing aircraft according to the present invention but also to ensure the assemblies / disassembly of these different units, constituting a workshop, particularly for commissioning in places with little equipment. In addition, the transport container 30 according to the present invention comprises an architecture making it of a very limited weight, which allows travel over long distances by air means, without the weight increasing the financial cost and/or land or air transport options

The transport container 30 according to the present invention is of parallelepiped shape, with a front face 30-1, a rear face 30-2, an upper face 30-3, a lower face 30-4 and two side faces 30-5 and 30-6. A framework 32 ensures mechanical rigidity. This framework 32 comprises tubular elements 34 along the 4 edges of the upper 30-3 and lower 30-4 faces and in the middle part, made of light alloy. The tubular elements 34 of these faces are braced by vertical uprights 36, 6 in number, arranged at each intersection, also in light alloy. Each vertical upright 36 comprises two coaxial profiles upper 36-1 and lower 36-2, mounted telescopically relative to each other, in this case the upper profile 36-1 being able to slide in the lower profile 36- 2. The upper profiles 36-1 are integral with the tubular elements 34 of the upper face 30-3 and the lower profiles 36-2 are integral with the tubular elements 34 of the lower face 30-4. The upper face 30-3 can therefore be lifted relative to the lower face. Locking means with disengageable notches, for example, maintain the desired spacing.

The transport container comprises panels 40 attached to the frame 32. These panels are advantageously, in the mode chosen, made of composite material of the sandwich type with a honeycomb core and skins made of light metal alloy sheet . Such panels are very rigid and at the same time very light in weight. The front 30-1 and rear 30-2 faces are mounted, for at least one of them, pivoting relative to the lower face 30-4 so as to be able to open said front and rear faces and to make them rest on the ground. Thus, the front faces 30-1 and rear faces 30-2 are positioned in the plane of the lower face to form a clean floor of great length allowing assembly work in any area, even on natural terrain.

Advantageously, the upper face 30-3 comprises a maneuvering hoist 42, mounted on a beam 44 movable relative to said upper face 30-3, under said upper face, along the front/rear axis of the container. The operating hoist 42 can be moved in translation on said beam, therefore transversely in relation to the front/rear axis. This maneuvering hoist 42 makes it possible to move the different constituent units of the rotary wing aircraft according to the present invention both for assembly and for dismantling, in any location, even isolated. Even if the parts are of reduced weight, the number of constituent parts being limited, the weight of each of them is greater than the capacities of the operators, especially when the aim is to be able to act with a small number of operators. In addition, the dimensions of the container are adapted just to the dimensions of the rooms and the peripheral space for moving the servants is very limited.

The rotary wing aircraft according to the present invention is arranged in a particular manner in the container to gain compactness. The blades are removed from the main rotor. The tail 18 is dismantled, the shoe unit 24 as well. In the container, reception means are also provided to receive the different units:
- core structure 10 with drive motor 12 and transfer case 14,
- tail 18 and tail rotor 20
- skid unit 24
- blades 16-2 of wing 16.

The installation of the rotary wing aircraft according to the present invention is carried out in the manner shown on the more particularly. The disassembled blades are advantageously placed in a side receptacle, in the lower part. The tail 18 and its tail rotor are also placed in a suitable cradle, laterally, on the opposite side of the blades. The core structure assembly with its motor, its transfer case, its motor and its rotor is placed on a sliding cradle on the lower face in the middle part. The shoe unit 24 is placed above the central frame and rests on lateral supports 38 attached to the side faces, thus the rotor is positioned in the free space under the shoes with an essential gain in compactness. Restrictions are provided by any means, this not being the very essence of the invention and which can be adapted without inventive effort.

The aircraft according to the present invention has a simple design while being easy to implement and very versatile. Indeed, the cockpit can be modified by providing manual controls in place of the drone's electric motor controls and two seats for carrying the pilot and co-pilot or passenger or operator. The constituent elements remain the same. The size and weight are completely acceptable for transport by land, sea or air and in particular by hoisting as close as possible to the work areas when this proves necessary. The missions are very versatile, almost immediately bringing back a skate unit adapted to the mission. The rotary wing aircraft according to the present invention is produced by molding entirely in carbon fibers and inserts in a light alloy as resistant as titanium. The structural core 10 in particular is made of composite materials based on carbon fibers in order to produce a lightweight element having strong mechanical properties since it receives all of the elements of the aircraft which are connected to said core. Mechanical parts can be obtained from machined titanium, particularly for transmissions which are usually heavy. The engine itself can be standard but can also be developed to deliver increased power, making the rotary wing aircraft according to the present invention even more efficient, particularly for military applications. The weight of the aircraft is in fact very limited, allowing a greater payload and very interesting flight performance.

Claims (15)

Rotary wing aircraft, for mixed use, in particular with passenger transport in piloted mode or load transport in drone mode, for versatile applications, including:
- a core structure (10) with a drive motor (12) with a motor output transmission shaft (12-3),
- a transfer case (14) with a first output (14-1) and a second output (14-2),
- a cockpit (22) and its on-board electronics,
- a rotating wing (16) with its rotor (16-1) and blades (16-2),
- a tail (18) and its tail rotor (20), and
- a skate unit (24) for resting on the ground or on a liquid surface. Rotary wing aircraft according to claim 1, characterized in that the core structure (10) is monolithic. Rotary wing aircraft according to claim 1 or 2, characterized in that the core structure (10) is made of composite materials based on carbon fibers. Rotary wing aircraft according to any one of the preceding claims, characterized in that the core structure (10) comprises housings laterally, capable of receiving the fuel tanks necessary for powering the drive motor (12). Rotary wing aircraft according to any one of the preceding claims, characterized in that the skid unit (24) is connected to the core structure (10) by quick releases. Rotary wing aircraft according to any one of the preceding claims, characterized in that the tail (18) comprises a connecting flange (18-1) and the core structure (10) comprises a fixing flange (10-5) capable of cooperating with said connecting flange (18-1). Rotary wing aircraft according to any one of the preceding claims, characterized in that the core structure (10) comprises a cradle (12-1) intended to receive the drive motor (12). Rotary wing aircraft according to any one of the preceding claims, characterized in that the output transmission shaft (12-3) of the engine (12), the transfer case (14) with its first output (14-1) towards the rotating wing (16) and its other outlet (14-2) towards the tail rotor (20) are in the same plane. Rotary wing aircraft according to any one of the preceding claims, characterized in that, in drone mode, the aircraft includes electrical controls. Rotary wing aircraft according to any one of claims 1 to 8, characterized in that, in passenger carrying mode, the aircraft includes manual controls. Container (30) for a rotary wing aircraft according to any one of claims 1 to 10, characterized in that it comprises a frame (32) with receiving means for receiving different units of said aircraft:
- core structure (10) with drive motor (12) and transfer case (14),
- tail (18) and tail rotor (20)
- shoe unit (24), and
- blades (16-2) of the sail (16). Container (30) for rotary wing aircraft according to claim 11, characterized in that it comprises six faces:
- a lower face (30-4)
- an upper face (30-3)
- two front (30-1) and rear (30-2) faces, with at least one of them mounted articulated relative to the lower face (30-4), and
- two side faces (30-5) and (30-6) Container (30) for rotary wing aircraft according to claim 12, characterized in that the upper face (30-3) is supported by vertical uprights (36), each comprising two upper (36-1) and lower coaxial profiles (36-1). 36-2), mounted telescopically relative to each other. Container (30) for rotary wing aircraft according to claim 12 or 13, characterized in that it comprises a maneuvering hoist (42), mounted on a beam (44), movable relative to said upper face (30-3 ). Container (30) for rotary wing aircraft according to any one of claims 12, 13 or 14, characterized in that the walls (30-1; 30-6) consist of a sandwich, honeycomb core and light alloy skins.