ROTARY-WING AERODYNE WITH PARACHUTE

Abstract

A rotary-wing aerodyne includes a motor, a structure supporting at least one passenger seat, and a rotor arranged above the structure and linked to the motor by a hollow transmission shaft. The transmission shaft is movable in rotation relative to the structure. The aerodyne also includes a hollow mast attached to the structure and extending through the transmission shaft, and a parachute arranged above the rotor. The parachute is attached to the mast and linked to the structure by means of a suspension element passing through the mast. The suspension element is produced from a multi-strand steel cord with a tensile strength of greater than 150 daN/mm.sup.2.

Claims

1. A rotary-wing aerodyne, the said aerodyne comprising: a motor; a structure supporting at least one passenger seat; a rotor arranged above the said structure and linked to the motor by a hollow transmission shaft, the transmission shaft being movable in rotation in relation to the structure; a hollow mast attached to the structure and extending through the transmission shaft; and a parachute arranged above the rotor, the parachute being attached to the mast and linked to the structure by means of a suspension element passing through the mast; wherein said suspension element is produced from a multi-strand steel cable with a tensile strength of greater than 150 daN/mm.sup.2.

2. The aerodyne according to claim 1, wherein the said cable has a flexibility enabling it to be curved over a radius of less than or equal to 10 times the diameter thereof without reaching the bending elastic limit thereof.

3. The aerodyne according to claim 1, wherein said cable has a tensile breaking strength of more than 10 times the maximum authorized weight of said aerodyne even though a cross-section of said cable is reduced by 95%.

4. The aerodyne according to claim 1, wherein said parachute incorporates an extractor, said extractor being manually controlled from a cockpit of the aerodyne.

5. The aerodyne according to claim 4, wherein said extractor is controlled by a ripcord passing through said mast.

6. The aerodyne according to claim 4, wherein said extractor is controlled by an electrical switch, said electrical switch being connected to said cockpit by at least one electric wire passing through said mast.

7. The aerodyne according to claim 4, wherein said extractor is controlled by wireless transmission means.

8. The aerodyne according to claim 1, wherein said parachute incorporates an extractor, said extractor being controlled automatically when certain abnormal parameters are detected.

9. The aerodyne according to claim 8, wherein said extractor is achieved by a mechanical percussion device configured such as to ensure the extraction of said parachute when the rotor has a lateral acceleration greater than a threshold value.

10. The aerodyne according to claim 8, wherein said extractor is achieved by a switch-controlled electro-mechanical device configured such as to ensure the extraction of said parachute when said rotor has a lateral acceleration greater than a threshold value.

11. The aerodyne according to claim 8, wherein said extractor is achieved by an electronic device configured such as to ensure the extraction of said parachute when said aerodyne has an angular acceleration greater than a threshold value.

12. The aerodyne according to claim 1, wherein said suspension cable is attached to said structure by at least two attachment tethers connected to two different attachment points of said structure.

Description

BRIEF DESCRIPTION OF THE FIGURES

[0037] The method for implementing the disclosed embodiments and their advantages will become more apparent from the following disclosure of the embodiment, given by way of a non-limiting example, supported by the attached figures in which FIGS. 1 to 3 represent:

[0038] FIG. 1: a side view of an aerodyne supported by a parachute according to one embodiment;

[0039] FIG. 2: a schematic representation in cross section of the aerodyne of FIG. 1; and

[0040] FIG. 3: a schematic representation in partial cross section of the transmission column of the aerodyne of FIG. 1.

DETAILED DESCRIPTION

[0041] FIGS. 1 to 3 illustrate an aerodyne 10 comprising a metal tubular structure 11 supporting at least one passenger seat as well as a motor 35. The motor 35 drives in rotation a rotor 14, arranged above the structure 11, by means of a transmission shaft 13. The lift of the aerodyne 10 is produced by two blades 12 attached to the rotor 14.

[0042] The movement of the aerodyne 10 is produced by changing the orientation of the blades 12 by means of a swash plate 15 arranged around the transmission shaft 13 between the rotor 14 and the structure 11. The aerodyne 10 includes a cockpit 40 provided with a joystick suitable for changing the orientation of the swash plate 15 in order to control the movements of the aerodyne 10.

[0043] The transmission shaft 13 is a hollow metal part wherewithin a mast 30 is inserted. The mast 30 is attached to the structure 11 and the transmission shaft 13 is movable in rotation around the mast 30. The rotor 14 as well as the swash plate 15 have a central recess wherewithin the mast 30 is inserted. The mast 30 thus extends above the rotor 14 in such a way as to attach a parachute 16 securely to the structure 11.

[0044] More specifically, the parachute 16 is incorporated into a housing 31 incorporating the canopy 42 of the parachute 16 as well as the shrouds 41 thereof and the elements for extracting the parachute 16 from the housing 31. As illustrated in FIG. 1, when the parachute 16 is deployed the shrouds 41 connect different points of the canopy 42 to a suspension cable 17. The form of the parachute 16 can vary without departing from the contemplated embodiments. For example, the parachute 16 can comprise a plurality of canopies 42.

[0045] The suspension cable 17 passes through the mast 30 in order to be secured to the structure 11 of the aerodyne 10. The suspension cable 17 can be secured to the structure 11 in using any known means. FIGS. 2 and 3 illustrate an embodiment wherein the suspension cable 17 is secured by a shackle 32 around the suspension cable 17. The shackle 32 is connected to two attachment tethers 20, 21 connected to two different attachment points of the structure 11. A first attachment tether 20 is secured around a tube of the structure 11 close to the motor 35. A second attachment tether 21 is secured around a tube of the structure 11 close to the floor of the aerodyne 10.

[0046] The suspension cable 17 is an essential element of the contemplated embodiments because it makes it possible to withstand the deterioration of the blades 12, the mast 30 and/or the transmission shaft 13. To do this, the suspension cable 17 is produced from a multi strand steel cable with a tensile strength of greater than 150 daN/mm.sup.2. Preferably, the suspension cable 17 has a flexibility enabling it to be curved over a radius of less than or equal to 10 times the diameter thereof without reaching the bending elastic limit thereof. Preferably, the suspension cables 17 has a tensile breaking strength of more than 10 times the maximum authorized weight of said aerodyne when a cross-section of said cable 17 is reduced by 95%. For example, a hoisting cable with a cross-section of 20 mm can be used.

[0047] The elements for extracting the parachute 16 from the housing 31 include an extractor 18, for example a fuze, and a trigger mechanism of the extractor 18. The trigger mechanism can be mechanical, electrical or electronic. For example, as illustrated in FIGS. 2 and 3, the trigger mechanism can be produced by a ripcord 19 passing through said mast 30. The cross-section of the ripcord 19 is far smaller than that of the suspension cables 17 because the ripcord 19 can be cut without impairment after the opening of the parachute 17. Typically, the cross-section of the ripcord 19 can be in the order of 1 or 2 mm. The said ripcord 19 makes it possible to ensure manual control of the opening of the parachute 16 from the cockpit 40.

[0048] As a variant, manual control of the opening of the parachute 16 can be achieved by an electrical switch by means of an electric wire passing through the mast 30. As a variant, manual control can be achieved by means of wireless transmission. A wireless transmitter is then arranged within the cockpit 40 and a receiver is arranged at the parachute 16.

[0049] Moreover, the opening of the parachute 16 can also be controlled automatically when certain abnormal parameters are detected. The automatic triggering can be achieved by a mechanical percussion device configured such as to ensure the extraction of the parachute 16 when the rotor 14 has a lateral acceleration greater than a threshold value. To that end, a gyroscopic sensor is incorporated into the trigger mechanism. As a variant, the automatic triggering can be achieved by a switch-controlled electro-mechanical device configured such as to ensure the extraction of the parachute 16 when the rotor 14 has a lateral acceleration greater than a threshold value. As a variant, the automatic triggering can be achieved by an electronic device configured such as to ensure the extraction of the parachute 16 when the aerodyne 10 has an angular acceleration greater than a threshold value. To that end, a gyroscopic sensor is incorporated into the structure of the aerodyne 10.

[0050] When the trigger and/or extractor incorporate one or more electric accumulators involved in the operation thereof, the cockpit 40 includes a charge indicator of the accumulators.

[0051] Preferably, the aerodyne 10 incorporates two means of triggering the parachute 16, a manual control operated by the pilot and an automatic control if the pilot is unable to manually trigger the extraction of the parachute 16.

[0052] The contemplated embodiments thus make it possible to ensure greater passenger safety by means of a parachute 16 resistant to the significant damage that could occur between the parachute 16 and the structure 11.