Rotary-wing aircraft anti-landing device

Abstract

The invention relates to an anti-landing device (1) for a rotary-wing aircraft comprising: - a base (2); - a mast (3) fixed to the base (2) and extending vertically from the center of said base (2) to obstruct the rotation of the aircraft's rotor blades. The device is notable in that the base (2) is made up of at least one assembly of peripheral beams (4) forming a regular polygon, and radial reinforcing cross members (5). Figure for the abstract: Fig. 1

Description

Title of the invention: Anti-landing device for rotary-wing aircraft Technical field

[0001] The invention relates to the technical field of anti-landing devices for rotary-wing aircraft, such as for example helicopters. Prior art

[0002] Document FR2843417 is known from the prior art, which describes a helicopter anti-landing device comprising a mast formed by the superposition of tubular modules, at the lower end of which a base is fixed.

[0003] The base is in the form of a circular plate provided with holes for anchoring it in a foundation element.

[0004] This device is entirely satisfactory in that it is a question of prohibiting the landing of a rotary-wing aircraft, but its implementation is complex and requires a foundation element for its anchoring to the ground, and the ground anchoring operation as such.

[0005] It also follows that, once the device is installed, its removal also becomes complex. Statement of the invention

[0006] One of the aims of the invention is to overcome the drawbacks of the prior art by proposing an anti-landing device for a rotary-wing aircraft, which is of simple, safe and rational design, while being easy to install and remove.

[0007] For this purpose, an anti-landing device for a rotary-wing aircraft has been developed, comprising: - a base; - a mast fixed to the base and extending vertically from the center of said base to obstruct the rotation of the aircraft blades.

[0008] According to the invention, the base consists of at least one assembly of peripheral beams forming a regular polygon, such as a hexagon or octagon for example, and radial reinforcing crosspieces.

[0009] In this way, the device according to the invention constitutes an anti-landing device for a rotary wing aircraft which is self-stable, that is to say which does not require any anchoring to the ground, nor any addition of ballast elements, such as water, sand or concrete blocks.

[0010] Consequently, its implementation is simplified since it is sufficient to move or assemble the device directly at the location where landing is to be prohibited. of the aircraft, and may be removed or dismantled to allow access.

[0011] According to a particular embodiment, the crosspieces are fixed on one side to the ends of the peripheral beams and, on an opposite side, to a central element to which the mast is fixed.

[0012] This configuration allows for a base independent of the mast, which ensures increased stability.

[0013] According to a particular embodiment, each peripheral beam has a C-shaped section with wings of the C folded towards the center of the base, and the ends of the peripheral beams are folded inwards and fixed to the ends of the corresponding crosspieces.

[0014] Thus, the C-shaped section of the peripheral beams ensures increased bending rigidity in a vertical plane.

[0015] The radial cross members are preferably in the form of an assembly of two C-shaped section beams, positioned back to back and fixed together.

[0016] Here too, the C-shaped section, as well as the doubling of the crosspieces, allows increased rigidity, and also increases the bending resistance of said crosspieces in a vertical plane.

[0017] According to a particular embodiment, the central element comprises a vertical central tube, from which extend radially as many vertical fins as there are crosspieces, the tube being positioned and fixed between two horizontal flanges.

[0018] This configuration allows for solid attachment of the crosspieces to the fins and the mast to the center of the base on an upper flange.

[0019] In order to increase the stability of the base, and to possibly adapt to a difference in level of the ground on which it is placed, the device comprises a plurality of feet adjustable in height and fixed to the ends of the radial crosspieces and to the center of the base.

[0020] In order to keep the center of gravity of the device as low as possible and have optimal stability, the mast is made of composite, which does not require grounding, while the base is made of steel, and preferably galvanized steel to withstand bad weather.

[0021] In order to add a deterrent effect for the pilot to land in the protected area, rods, for example made of composite material, are fixed to a free end of the mast, around the circumference of the mast extending in a radial direction and inclined upwards. Brief description of the drawings

[0022] [Fig-1] is a perspective view of the anti-landing device of an aircraft according to the invention.

[0023] [Fig.2] is a perspective view from above of the base of the device.

[0024] [Fig.3] is a perspective view from below of the base.

[0025] [Fig.4] is a perspective view of the central element of the base.

[0026] [Fig.5] is a view illustrating in detail the peripheral beams and crosspieces of the base.

[0027] [Fig.6] is a view similar to that of [Fig.5], from another point of view, with a part of a sleeper that has been hidden. Detailed description of the invention

[0028] With reference to Figures 1 to 6, the present invention relates to an anti-landing device (1) for a rotary volume aircraft of the helicopter type, which is self-stable, that is to say that it does not require any anchoring to the ground, nor ballast materials so that its installation and uninstallation are facilitated.

[0029] With reference to [Fig.l], the device (1) comprises a ground support base (2) of a generally substantially circular shape, and more particularly in the form of a regular polygon with 6, 8, 10 sides or more.

[0030] A mast (3), for example made of composite material, is fixed to the center of the base (2) and extends vertically over a height of between 3 and 5 m, for example 4 m, and with a diameter of between 8 and 15 cm, for example 12 cm, in order to prevent the aircraft from landing. In particular, if the aircraft attempted to land near the device (1) according to the invention, the blades of the aircraft would strike the mast (3) which would cause an accident. Based on this principle, the aircraft does not approach the device (1).

[0031] Of course, depending on the surface area of ​​the area to be protected, several devices (1) according to the invention can be regularly positioned.

[0032] With reference to Figures 2 and 3, the base (2) is preferably made of steel, advantageously galvanized to resist bad weather, and is made up of at least one assembly of peripheral beams (4) forming the regular polygon, and radial reinforcing crosspieces (5), fixed, on one side to the ends of the peripheral beams (4) and, on an opposite side, to a central element (6) of the base (2). It may be envisaged that the crosspieces (5) are fixed directly to the lower part of the mast (3), which then acts as the central element. For example, the base has a diameter of approximately 3 m, with peripheral beams (4) of a length of approximately 110-115 cm, and radial crosspieces of a length of approximately 130 cm.

[0033] With reference to [Fig.4], the central element (6) comprises a vertical central tube (6a) from which extend radially as many vertical fins (6b) as there are crosspieces (5). The tube (6a) is bounded on either side by flanges (6c, 6d), of which a lower flange (6c) rests against the ground and an upper flange (6d) which receives the mast (3). The whole thing is preferably welded.

[0034] Each peripheral beam (4) has a C-shaped section, thus defining a vertical main body, a lower flange (4a) and an upper flange (4b), folded towards the center of the base (2), and this in order to improve the bending resistance of the beam in a vertical plane.

[0035] The ends of the peripheral beams (4) are folded inwards so as to define two cheeks (4c) which are fixed, in particular by bolting, to the ends of the corresponding crosspieces (5).

[0036] The radial crosspieces (5) are, for their part, preferably in the form of an assembly of two beams also of C-shaped section, positioned back to back and fixed together.

[0037] In particular, and with reference to Figures 5 and 6, the two beams fixed together to form a radial cross member (5) are bolted together at the ends. The bolting of the ends is common with that which makes it possible to fix the end of the cross member (5) to the peripheral beams (4), as well as with that which makes it possible to fix the cross member (5) to the central element (6). In particular, each vertical fin (6b) of the central element (6) is positioned between two beams of a cross member (5), and the bolting fixes the assembly.

[0038] In order to ensure maximum stability of the base (2), and to adapt to differences in ground level, the device (1) comprises a plurality of feet (7) adjustable in height, see [Fig.3], fixed to the ends of the radial crosspieces (5) and to the center of the base (2), in particular to the lower flange (6c) of the central element (6).

[0039] The mast (3) is fixed, in particular bolted, to the upper flange (6d) of the central element (6) and comprises, at an upper free end, rods (8) which are fixed around the circumference of the mast (3), and which extend in an upwardly inclined radial direction, for example with a length of between 30 and 50 centimeters, and acting as a deterrent for the pilot of the aircraft. These rods (8) are for example made of composite materials.

[0040] All bolts used are preferably non-removable bolts to make it difficult for an unauthorized person to uninstall them.

[0041] It is clear from the above that the invention provides an anti-landing device (1) for a rotary wing aircraft, which is self-stable and which can be installed and uninstalled easily.

Claims

Claims

1. Anti-landing device (1) for a rotary wing aircraft comprising: - a base (2); - a mast (3) fixed to the base (2) and extending vertically from the center of said base (2) to prevent the rotation of the blades of the aircraft; characterized in that it is self-stable, and the base (2) is made up of at least one assembly of peripheral beams (4) forming a regular polygon, and radial reinforcing crosspieces (5).

2. Device (1) according to claim 1, characterized in that the crosspieces (5) are fixed on one side to the ends of the peripheral beams (4), and on an opposite side, to a central element (6) to which the mast (3) is fixed.

3. Device (1) according to claim 2, characterized in that each peripheral beam (4) has a C-shaped section with wings (4a, 4b) of the C folded towards the center of the base (2), and the ends of the peripheral beams (4) are folded inwards and fixed to the ends of the corresponding crosspieces (5).

4. Device (1) according to one of the preceding claims, characterized in that the radial crosspieces (5) are in the form of an assembly of two beams of C-shaped section, positioned back to back and fixed together.

5. Device (1) according to claim 2, characterized in that the central element (6) comprises a central vertical tube (6a) from which extend radially as many vertical fins (6b) as crosspieces (5), the tube (6a) being positioned and fixed between two horizontal flanges (6c, 6d).

6. Device (1) according to one of the preceding claims, characterized in that it comprises a plurality of feet (7) adjustable in height and fixed to the ends of the radial crosspieces (5) and to the center of the base (2).

7. Device (1) according to claim 1, characterized in that the mast (3) is made of composite.

8. Device (1) according to one of the preceding claims, characterized in that rods (8) are fixed to a free end of the mast (3), around the circumference of the mast (3) extending in a radial and upwardly inclined direction.

9. Device (1) according to claim 8, characterized in that the rods (8) are made of composite material.

10. Device (1) according to one of the preceding claims, characterized in that the base (2) is made of galvanized steel.

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