Aerostatic device equipped with means for managing the descent with rigid wing

Abstract

The invention relates to an aerostatic device (1) comprising:- a balloon (100) comprising an envelope (120) intended to be filled with a gas lighter than air;- a nacelle (200) connected to said balloon (100) and carrying a payload, said nacelle being capable of being raised into the atmosphere by said balloon (100); and- means for managing the descent (260) following the deflation, bursting or automatic or programmed release of said balloon (100) at altitude;characterized in that said means for managing the descent (260) comprise a rigid wing (261) secured to said nacelle (200; 200'; 200''). Figure to be published with the abstract: Fig. 2

Description

Title of the invention: Aerostatic device equipped with means for managing the descent with rigid wing Technical field

[0001] The present invention relates generally to the field of aerostatic devices used for example to collect data on the atmosphere at different altitudes, to seed cloud cells in order to avoid the formation of hail or to carry out aerial surveillance. It particularly targets such an aerostatic device equipped with means of managing the descent with rigid wings. Prior art

[0002] Meteorological aerostatic devices generally referred to as "weather balloons" are commonly used in conjunction with other ground-based instruments, such as radars, satellites and weather stations to obtain a complete picture of atmospheric conditions for the purpose of, for example, weather forecasts.

[0003] Such a weather balloon typically comprises - a balloon itself generally made of an elastically deformable material and comprising an envelope intended to be filled with a gas lighter than air such as hydrogen or helium; and - a basket connected to said balloon, for example by means of a rope, and carrying a payload conventionally consisting of a “radio-sonde” grouping together several sensors for measuring and recording certain characteristics of the atmosphere (such as pressure, temperature, humidity, direction and velocity of the wind and / or the molecular concentrations of various gases such as ozone), a radio transmitter continuously transmitting the data from the sensors to a ground station, as well as a radar reflector allowing the determination of the trajectory of the balloon.

[0004] Other types of aerostatic devices are also known for ensuring the seeding of cloud cells in order to intervene on the microphysical processes linked to the exchanges between the different phases of water in the cloud (vapor, liquid, ice) and thus on the distribution and size of the particles in the cloud.

[0005] Commonly referred to as “Cloud Seeding”, this seeding aims to disrupt the microphysical balances within cloud cells to accelerate the growth of certain droplets or their transformation into ice crystals by introducing into the cloud cells active particles such as dust having a strong affinity for water (sodium salts, calcium, magnesium, etc.), refrigerating materials (dry ice, propane, liquid nitrogen) or ice cores (silver iodide or copper iodide, etc.).

[0006] The use of silver iodide particles with a crystalline structure similar to that of ice is often preferred for its high effectiveness from -5°C in small quantities.

[0007] Having a structure relatively close to that of a weather balloon, such an aerostatic seeding device, described in particular in document FR 3 051 098 A1, conventionally comprises a nacelle connected to a balloon and carrying a diffuser designed to diffuse active particles within cloud cells present in the atmosphere so as to ensure their seeding.

[0008] This diffuser is for example constituted by a pyrotechnic torch, generally comprising a cylindrical envelope containing active particles and a pyrotechnic mixture allowing the combustion of such a torch and finally the dispersion of the active particles in the atmosphere. Such a torch also comprises a trigger intended to cause the activation of said mixture and which can be electrically actuated by a control card according to atmospheric data collected by sensors integrated into the nacelle.

[0009] The payload carried by the nacelle of such an aerostatic device being relatively expensive and fragile, its recovery is generally desired so that it can be reused at least in part.

[0010] In order to limit their speed of fall in the air so as to avoid deterioration of their payload, these aerostatic devices can be equipped with a parachute comprising a flexible wing connected by straps to the basket and triggered following deflation, bursting or automatic or programmed release of the balloon at altitude.

[0011] Document US 3,614,031 A describes a device for destroying and lowering such a balloon, making it possible to recover the payload and its equipment using means capable of destroying a portion of the balloon and inverting it. This allows the gas initially contained in the balloon to escape so as to cause a controlled descent of the balloon until the moment of its deflation, when a parachute then takes over and provides the means for recovering the payload.

[0012] Due to the turbulence zones encountered by aerostatic devices during their descent, such parachutes unfortunately have a tendency to fold or twist on themselves so that they no longer allow the fall speed to be sufficiently reduced. Statement of the invention

[0013] The present invention therefore aims to better secure the sensitive descent phase of a such meteorological aerostatic device.

[0014] For this purpose, it proposes a meteorological aerostatic device comprising: - a balloon comprising an envelope intended to be filled with a gas lighter than air; - a basket connected to said balloon and carrying a payload, said basket being capable of being raised into the atmosphere by said balloon; and - means of managing the descent following deflation, bursting or automatic or programmed release of said balloon at altitude.

[0015] According to the invention, said descent management means comprise a rigid wing secured to said nacelle.

[0016] The term "rigid wing" must here be interpreted in its aeronautical definition as a wing whose curvature is not affected by the surrounding air (unlike a "flexible wing" such as a parachute or a sail) but which can nevertheless undergo a certain deformation in bending and torsion.

[0017] The use of such a rigid wing, less sensitive to turbulence possibly encountered in certain zones of the atmosphere, makes it possible to better secure the sensitive phase of descent of the aerostatic device by guaranteeing a reduction in the vertical speed of impact with the ground at the time of landing.

[0018] The invention thus considerably limits the risk of deterioration of the payload carried by the nacelle, so as to allow, almost systematically, its reuse for subsequent flights.

[0019] In order to reduce as much as possible the vertical speed of impact with the ground at the time of landing, said means for managing the descent are preferably of the rigid rotating wing type.

[0020] According to a first preferred embodiment offering in particular better control of the landing zone, said means for managing the descent, of the active rotating rigid wing type, comprise: - a plurality of motorized rotors extending along the same mean plane and connected to said nacelle by connecting arms; and - a flight controller configured to control the operation of each of said motorized rotors based on data transmitted by sensors on board said nacelle.

[0021] In order to control the entire descent phase of the device, said flight controller is advantageously configured to activate said motorized rotors at the time of deflation, bursting or automatic or programmed release of said balloon.

[0022] In order to control the landing site to avoid no-fly zones and / or high population density zones, said flight controller is preferably coupled to a geo-positioning information receiver on board said nacelle, this flight controller being further configured to ensure the automated return of said aerostatic device to its take-off point or to a predetermined landing site.

[0023] In order to prevent certain elements constituting the payload from coming into direct contact with the ground at the time of landing, said motorized rotors are advantageously extended in the lower part by support legs intended to come to rest on the ground at the time of landing of said device.

[0024] According to a second, more economical embodiment of the invention, said descent management means, of the passive rotating rigid wing type, comprise at least one self-rotating propeller secured to said nacelle and comprise several blades.

[0025] In order to guarantee optimal braking of the device during the descent phase, the diameter of said at least one propeller is advantageously greater than or equal to 20 centimeters.

[0026] In order to facilitate the ascent phase of the aerostatic device by limiting the drag generated by the self-rotating propeller, the blades of said at least one propeller are preferably foldable and configured to unfold automatically at the time of deflation, bursting or automatic or programmed release of said balloon.

[0027] In order to limit the rotation of said nacelle during the descent of the aerostatic device, said at least one propeller is advantageously mounted to rotate freely on a mast fixed to said nacelle.

[0028] In order to limit the vibrations generated while increasing the lift generated, the descent management means preferably comprise two superimposed counter-rotating propellers mounted to rotate freely on the same said mast.

[0029] Alternatively, said descent management means may be of the fixed rigid wing type. According to a third preferred embodiment of the invention, these means thus comprise two coplanar wings fixed to said nacelle and arranged symmetrically.

[0030] In order to limit the pitching of the device during the descent phase, these latter descent management means may also advantageously comprise a tail unit provided with at least one pitch stabilizing surface extending parallel to the plane of said wings.

[0031] Generally speaking, said nacelle may comprise a diffuser designed to diffuse active particles within cloud cells present in the atmosphere so as to ensure their seeding.

[0032] Such a diffuser will for example consist of an activatable pyrotechnic torch electrically by an electronic control module integrated into said nacelle. Brief description of the drawings

[0033] The description of the invention will now be continued by the detailed description of several exemplary embodiments, given below for illustrative but non-limiting purposes, with reference to the appended drawings, in which: - [Fig.l] represents a perspective view of a meteorological aerostatic device according to a first embodiment of the invention; - [Fig.2] is an enlarged perspective view of the nacelle of the aerostatic device of [Fig.l]; - [Fig.3] represents a schematic diagram of the electronic module arranged on the nacelle of [Fig.2]; - [Fig.4] is an enlarged perspective view of the nacelle of an aerostatic device according to a second embodiment of the invention, the blades of which occupy their unfolded configuration; - [Fig.5] represents an enlarged perspective view of the nacelle of the aerostatic device of [Fig.4] whose blades occupy their folded configuration; and - [Fig.6] is an enlarged perspective view of the nacelle of an aerostatic device according to a third embodiment of the invention. Description of the embodiments

[0034] [Fig.l] represents a meteorological aerostatic device 1 according to a first embodiment of the invention, intended to ensure the seeding of cloud cells in order to intervene on the microphysical processes linked to the exchanges between the different phases of water in the cloud (vapor, liquid, ice) and thus on the distribution and size of the particles of the cloud.

[0035] As illustrated in this [Fig.l], the aerostatic device 1 comprises a balloon 100 advantageously made of an elastically deformable material (such as rubber, latex, neoprene, chlorophene or even polyethylene) and comprising an inlet neck 110 and an envelope 120 intended to be filled with a gas lighter than air such as hydrogen or helium.

[0036] This aerostatic device 1 also comprises at least one nacelle 200 connected to the balloon 100 and carrying a payload, this nacelle 200 being capable of being raised into the atmosphere by said balloon in the inflated state up to a certain altitude at which the seeding of cloud cells will be carried out.

[0037] According to alternative embodiments, the balloon 100 could be made of a non-elastically deformable material such as aluminum so as to make it more airtight. Particularly relevant for aerostatic devices intended to exceed the troposphere, such a conformation nevertheless requires great precision concerning the inflation pressure in order to avoid the balloon bursting too early in the atmosphere due to the drop in external pressure with altitude.

[0038] With reference to [Fig.2], the nacelle 200 comprises in this case - a 210 support; - an active particle diffuser 220; - an inflation connector end piece 230 designed to be connected in a sealed manner to a complementary end piece of an external inflation device not shown so as to ensure the inflation of the balloon 100; - a hollow sleeve 240 on which the neck 110 of the balloon 100 is fitted securely and in a sealed manner (for example via a plastic clamp), this sleeve 240 being in fluid communication with the inflation connector end piece 230 and being provided with an internal non-return valve preventing the deflation of this balloon 100 during the separation between the complementary end piece of the inflation device and the connector end piece 240; and - an electronic control module 250.

[0039] Advantageously made from a cut and folded sheet of metal, the support 210 comprises a first flat attachment portion 211 having for example a rectangular shape and against which the electronic control module 250 is fixed.

[0040] This support 210 also comprises a second curved attachment portion 212 fixedly supporting the diffuser 220 via embedding clips 213 and which is connected to the first flat portion 211 by a connecting portion 214.

[0041] The diffuser is in this case constituted by a pyrotechnic torch 220 comprising a sealed cylindrical envelope 221 containing active particles having a strong affinity for water and advantageously constituted by ice-forming nuclei such as silver iodide or copper iodide and preferably in the form of powders or crystals. This cylindrical envelope 221 also contains a pyrotechnic mixture, also referred to as an explosive charge, and making it possible to ensure the combustion of the torch 220 and the dispersion of the active particles.

[0042] This pyrotechnic torch 220 also comprises a trigger, not visible in the figures, advantageously housed in the sealed cylindrical casing 221 and designed to cause the activation of the pyrotechnic mixture.

[0043] This trigger is for example constituted by an igniter capable of generating sufficient heat to trigger the combustion of a priming composition making it possible to cause the activation of the pyrotechnic mixture of the torch 220. It can advantageously be actuated by means of an electrical signal emitted by the electronic module 250 and transmitted by an electrical cable 222 electrically connected by one of its ends to this trigger and the other end of which is provided with a connector which is connected to a complementary connector provided on this electronic module. tronic 250.

[0044] When activated, causing the dispersion of the active particles it contains within cloud cells in the atmosphere, this pyrotechnic torch 220 generates a flame projecting from the top of its cylindrical envelope 221. It will be noted that the support 210 is preferably shaped so that the relative positioning between the pyrotechnic torch 220 and the sleeve 230 receiving the neck of the balloon 100 causes this flame to lick the junction zone between the neck 110 and the envelope 120 of this balloon 100 so as to cause it to burst and the aerostatic device 1 to descend.

[0045] According to alternative embodiments not shown, the diffuser 220 could be constituted by a device other than a pyrotechnic torch such as a spray or an aerosol making it possible to ensure progressive and possibly controlled diffusion.

[0046] According to alternative embodiments not shown, the balloon 100 could be associated with a deflation device, for example of the pyrotechnic type, controlled by the electronic module 250 and activated automatically after activation of the diffuser 220 in order to cause the deflation of this balloon 100.

[0047] According to other variant embodiments not shown, the balloon 100 could be mounted on a second dedicated support attached to the rest of the nacelle 200 by electromagnets controlled by the electronic module 250 so that their power supply is cut off after activation of the diffuser 220 in order to cause the release of this balloon 100.

[0048] The bursting, deflation or release of the balloon 100 causing the device 1 to descend may also not be carried out automatically following the triggering of the diffuser 220 but programmed to take place before or after this event when certain conditions are met (for example, when it is not desired to unnecessarily diffuse, before returning to the ground, the active particles when the seeding conditions have not been satisfied or in order to allow seeding from above of cloud cells during the return to the ground of the aerostatic device 1).

[0049] Presented for example in the form of an electronic printed circuit board commonly designated by the acronym PCB (acronym in English for the expression “Printed Circuit Board”), the electronic module 250 comprises, with reference to [Fig. 3], a processing unit 251 provided with at least one computer or microprocessor and configured to cause the activation of the diffuser 220 in response to a triggering event corresponding for example to the lapse of a predetermined time since the takeoff of the aerostatic device 1 or to the reaching of thresholds predetermined by one or more parameters (such as for example the altitude, the rate of climb of the aerostatic device 1, the humidity level, the temperature and / or the pressure) measured by sensors 252, 253, 254 integrated into this module 250.

[0050] The electronic module 250 may further comprise a non-volatile memory 255 intended to store the data collected by the sensor(s) 252, 253, 254.

[0051] The term "non-volatile memory" should be understood as a computer memory whose technology retains its data in the absence of an electrical power supply (unlike a "volatile memory" whose data is lost in the absence of such an electrical power supply).

[0052] The main non-volatile memories currently available are electrically writable such as EPROM technology (acronym for "Erasable Programmable Read-Only Memory") or electrically writable and erasable such as EEPROM technology (acronym for "Electrically-Erasable Programmable Read-Only Memory), flash, SSD (acronym for "Solid-State Drive"), etc.

[0053] As can be seen in [Fig.2], the inflation connector end piece 230 and the hollow sleeve 240 are assembled to each other in a sealed manner, for example by screwing, and in such a way as to sandwich the flat attachment portion 211 of the support 210 and the electronic module 250 in which superimposed, non-visible orifices are provided, allowing fluid communication between these two elements 230, 240.

[0054] As illustrated by figures 1 and 2, the aerostatic device 1 also comprises means for managing its descent 260 following deflation, bursting or automatic or programmed release of the balloon at altitude 100.

[0055] Of the active rotating rigid wing type, these means 260 comprise a plurality of motorized rotors 261 (advantageously four arranged in a square of which they constitute the corners) preferably extending along the same mean plane and connected to an element of the nacelle 200 (in this case, to the flat attachment portion 211 of the support 210) by connecting arms 262.

[0056] Each of these motorized rotors 261, arranged at the distal end of a respective connecting arm 262, comprises a rotary propeller 261A driven by a corresponding motor (not visible) housed in a hollow body 26IB provided at this distal end of the connecting arm 262.

[0057] Each rotary propeller 261A comprises a central hub as well as several blades extending radially from this central hub and the number of which is advantageously between two and five.

[0058] The central hub and the blades of each rotary propeller 261A are preferably molded in one piece from a thermoplastic polymer.

[0059] According to alternative embodiments not shown, these motorized rotors 261 can be extended in the lower part by support legs intended to come to rest on the ground at the time of landing of the aerostatic device 1, so as to prevent the electronic module 250 from coming into direct contact with the ground.

[0060] Again with reference to [Fig. 3], the means for managing the descent 260 of the aerostatic device 1 also comprise a flight controller 264 advantageously arranged on the electronic module 250 and provided with at least one computer or microprocessor (dedicated or constituted by that of the processing unit 251) configured to control the operation of each of the motorized rotors 261 as a function of data transmitted by sensors embedded on this module 250 such as conventionally a gyroscope 265, an accelerometer 266 and a magnetometer 267, so as to maintain the stability and control of the aerostatic device 1 during its descent.

[0061] The flight controller 264 is advantageously configured to activate the motorized rotors 261 at the time of deflation, bursting or automatic or programmed release of the balloon 100 so as to manage the descent of the aerostatic device 1.

[0062] Alternatively and in order to limit energy consumption, the flight controller 264 may be configured to activate the motorized rotors 261 only below a predetermined threshold altitude. In such a case, the aerostatic device 1 will advantageously be equipped with a self-righting system in flight.

[0063] This flight controller 264 is advantageously coupled to a geo-positioning information receiver 268 on board the electronic module 250 of the nacelle 200 and making it possible to determine the position of the aerostatic device 1 in a local or global positioning reference frame.

[0064] This geo-positioning information receiver 268 is preferably a receiver using the GPS satellite positioning system (acronym in English for the expression "Global Positioning System") which picks up the radio signals transmitted by at least four satellites of this GPS system and can, by calculating the propagation times of these signals between the satellites and itself, know its distance from them and, by trilateration, determine with an accuracy of a few meters, the position of the vehicle placed in visibility of the satellites.

[0065] Alternatively, the geopositioning receiver 268 may use a satellite positioning system other than GPS, such as for example the EGNOS system (acronym in English for the expression “European Geostationary Navigation Overlay System”), the GLONASS system (acronym in English for the expression “Global Navigation Satellite System”) or the GALILEO system.

[0066] According to other variants or in addition, the geo-positioning receiver 268 may comprise an inertial unit generally comprising three gyrometers and three accelerometers.

[0067] Thanks to the presence of such a geo-positioning information receiver 268, the Flight controller 264 may advantageously be configured to ensure the automated return of the aerostatic device 1 to its take-off point or to a predetermined landing site whose geographical coordinates are stored in a non-volatile memory such as 255.

[0068] In order to provide electrical power to the electronic module 250 and the motorized rotors 261, the nacelle 200 comprises an electrical energy source 269 advantageously in the form of at least one pre-charged battery (for example of the lithium-polymer type due to its high power-to-weight ratio) preferably installed on this module 250.

[0069] According to alternative embodiments not shown, this source of electrical energy 269 may be in the form of photovoltaic cells covering, for example, part of the support 210.

[0070] According to other variant embodiments and in order to limit the electrical consumption so as to optimize the mass of the energy source carried by the nacelle 200, the flight controller 264 can be configured to activate the motorized rotors 261 only during part of the descent phase of the device 1, for example when its altitude or its speed reaches a predetermined threshold.

[0071] Figures 4 and 5 illustrate a second embodiment of an aerostatic device 1' according to the invention.

[0072] In the following and in these figures 4 and 5, the same references have been kept for the elements identical to the first embodiment and a prime has been added for the similar elements.

[0073] The aerostatic device 1' is similar to the device 1 described previously, with the notable exception of the means for managing its descent 270 of the passive rotating rigid wing type.

[0074] These means for managing the descent 270 comprise a self-rotating propeller 271 secured to an element of the nacelle 200' and comprising several blades 271A (in this case two aligned blades) the number of which is advantageously between two and five.

[0075] For reasons of simplicity and manufacturing cost, the proximal ends of the blades 271A of this self-rotating propeller 271 are advantageously rigidly fixed to an element of the nacelle 200' (in this case, to the flat attachment portion 211 of the support 210), so that the entire nacelle 200' is driven in rotation on itself during the descent of the aerostatic device 1'.

[0076] It will be understood that the descent of this aerostatic device 1' maintains the rotation of this self-rotating propeller 271 generating lift resulting in a reduction in the descent speed.

[0077] In order to limit the additional mass generated by the self-rotating propeller 271 of so that the lift it generates is sufficient to significantly reduce the descent speed of the aerostatic device 1', this propeller 271 will preferably be made of a low density and high stiffness material such as for example beech, balsa, expanded polystyrene or even impact polystyrene.

[0078] In order to ensure sufficient braking of the aerostatic device 1' after the dispersion of the active particles contained in the diffuser 220, the diameter of this propeller 271 will advantageously be greater than or equal to 20 centimeters and preferably between 30 and 40 centimeters.

[0079] As illustrated by [Fig.5] and in order to facilitate the ascent phase of the aerostatic device 1' by limiting the drag generated by the self-rotating propeller 271, the blades 271A of the latter are advantageously foldable around an axis (for example parallel to their axis of rotation as shown in this [Fig.5]); these blades 271A being configured to unfold automatically at the time of deflation, bursting or automatic or programmed release of the balloon 100 so as to manage the descent of the aerostatic device 1'.

[0080] According to alternative embodiments not shown, the self-rotating propeller 271 can also be mounted to rotate freely on a mast fixed to an element of the nacelle 200' (for example to the support 210) so as to limit the rotation of this nacelle 200' during the descent of the aerostatic device 1'.

[0081] According to other embodiment variants not shown and with the aim of limiting the vibrations generated while increasing the lift generated, the descent management means 270 may comprise two superimposed counter-rotating propellers such as 271 mounted to rotate freely on the same mast fixed to an element of the nacelle 200'.

[0082] According to other variant embodiments not shown, the self-rotating propeller 271 can also be mounted integral with another element of the nacelle 200 such as for example the casing 221 of its diffuser 220.

[0083] Since the means for managing the descent of such an aerostatic device 1' are not motorized, the energy requirements of this device 1' prove to be significantly lower than those of the device 1. The source of electrical energy providing the electrical power supply to the aerostatic device 1' can thus be simply constituted by one or more pre-charged capacitors, which makes it possible to significantly reduce the mass and the cost price of this device 1'.

[0084] In order to facilitate the recovery of the nacelle 200' after its landing, the location of which depends on the intensity and direction of the relative winds that it will have encountered during its descent, the aerostatic device 1' will advantageously comprise a geo-positioning receiver coupled with means for transmitting radio signals transmitting the position of this nacelle 200' on a private mobile radio network operating for example on a frequency between 3 and 30 kHz.

[0085] [Fig.6] illustrates a third embodiment of an aerostatic device 1” according to the invention.

[0086] In the following and in this [Fig.6], the same references have been kept for the elements identical to the first embodiment and a double prime has been added for the similar elements.

[0087] The aerostatic device 1” is similar to the device 1 described previously, with the notable exception of the means for managing its descent 280 of the fixed rigid wing type.

[0088] These means for managing the descent 280 comprise two coplanar wings 281 fixed to an element of the nacelle 200” (in this case to the envelope 221 of the diffuser 220) and arranged symmetrically.

[0089] It will be understood that the lift generated by these wings 281 during the descent of the aerostatic device 1” will cause this device 1” to glide, substantially limiting the vertical component of its fall speed.

[0090] These means for managing its descent 280 also advantageously comprise a tailplane 282 provided with at least one pitch stabilizing surface 282A extending parallel to the plane of the wings 281.

[0091] In order to limit the additional mass generated by this fixed wing so that the lift it generates is sufficient to significantly reduce the descent speed of the device 1”, the wings 281 and the empennage 282 will preferably be made from a low-density, high-stiffness material such as, for example, beech, balsa, expanded polystyrene or even impact-resistant polystyrene.

[0092] The means for managing the descent of such an aerostatic device 1” not being motorized, the energy requirements of this device 1” turn out to be significantly lower than those of the device 1.

[0093] Thus and as indicated previously with reference to the device 1', the source of electrical energy ensuring the electrical power supply of the aerostatic device 1” can also be simply constituted by one or more pre-charged capacitors, which makes it possible to significantly reduce the mass and the cost price of this device 1”.

[0094] In order to facilitate the recovery of the nacelle 200'' after its landing, the location of which depends on the intensity and direction of the relative winds that it will have encountered during its descent, the aerostatic device 1” will advantageously comprise, as indicated previously with reference to the device 1', a geopositioning receiver coupled to means for transmitting radio signals transmitting the position of this nacelle 200” on a private mobile radio network.

[0095] According to other embodiment variants not shown, the wings 281 can be each equipped with a torsion device or an aileron controlled by a flight controller and allowing their lift to be modulated so as to allow the descent of the aerostatic device 1 to be controlled.

[0096] It may also be provided that these wings 281 have variable geometry so as to further adjust their lift during the descent phase.

[0097] Many other variants are also possible and it will be recalled in this respect that the invention is not limited to the embodiments described and shown, but also encompasses all the variants of execution within the reach of those skilled in the art. It will be specified in particular that the invention is not limited to aerostatic seeding devices but that it can also be implemented to manage the descent of all types of aerostatic devices, such as for example weather balloons or aerial surveillance devices.

Claims

Claims

1. Aerostatic device (1; 1'; 1”) comprising: - a balloon (100) comprising an envelope (120) intended to be filled with a gas lighter than air; - a nacelle (200; 200'; 200”) connected to said balloon (100) and carrying a payload, said nacelle being capable of being raised into the atmosphere by said balloon (100); and - means for managing the descent (260; 270; 280) following the deflation, bursting or automatic or programmed release of said balloon (100) at altitude; characterized in that said means for managing the descent (260; 270; 280) comprise a rigid wing (261; 271; 281) secured to said nacelle (200; 200'; 200”).

2. Aerostatic device (1; 1') according to claim 1, characterized in that said descent management means (260; 270) are of the rotating rigid wing type.

3. Aerostatic device (1) according to claim 2, characterized in that said descent management means (260), of the active rotating rigid wing type, comprise: - a plurality of motorized rotors (261) connected to said nacelle (200) by connecting arms (262); and - a flight controller (264) configured to control the operation of each of said motorized rotors (261) as a function of data transmitted by on-board sensors (265, 266, 267) on said nacelle (200).

4. Aerostatic device (1) according to claim 3, characterized in that said flight controller (264) is configured to activate said motorized rotors (261) at the time of deflation, bursting or automatic or programmed release of said balloon (100).

5. Aerostatic device (1) according to one of claims 3 or 4, characterized in that said flight controller (264) is coupled to a geo-positioning information receiver (268) on board said nacelle (200), this flight controller (264) being further configured to ensure the automated return of said aerostatic device (1) to its take-off point or to a predetermined landing site.

6. Aerostatic device (1) according to one of claims 3 to 5, characterized in that said motorized rotors (261) are extended in the lower part by support legs intended to come to rest on the ground at the time of landing of said device (1).

7. Aerostatic device (1') according to claim 2, characterized in that said descent management means (270), of the passive rotating rigid wing type, comprise at least one self-rotating propeller (271) integral with said nacelle and comprising several blades (271 A).

8. Aerostatic device (1') according to claim 7, characterized in that the diameter of said at least one propeller (271) is greater than or equal to 20 centimeters.

9. Aerostatic device (1') according to one of claims 7 or 8, characterized in that the blades (271 A) of said at least one propeller (271) are foldable and configured to unfold automatically at the time of deflation, bursting or automatic or programmed release of said balloon (100).

10. Aerostatic device (1') according to one of claims 7 to 9, characterized in that said at least one propeller (271) is mounted to rotate freely on a mast fixed to said nacelle (200').

11. Aerostatic device (1') according to claim 10, characterized in that said descent management means (280) comprise two said superimposed counter-rotating propellers mounted to rotate freely on the same said mast.

12. Aerostatic device (1”) according to claim 1, characterized in that said descent management means (280), of the fixed rigid wing type, comprise two coplanar wings (281) fixed to said nacelle (200”) and arranged symmetrically.

13. Aerostatic device (1”) according to claim 12, characterized in that said descent management means (280) also comprise a tail unit (282) provided with at least one pitch stabilizing surface extending parallel to the plane of said wings (281).

14. Aerostatic device (1; 1'; 1”) according to one of claims 1 to 13, characterized in that said nacelle (200; 200'; 200”) comprises a diffuser (220) provided for diffusing active particles within cloud cells present in the atmosphere so as to ensure their seeding.

15. Aerostatic device (1; 1'; 1”) according to claim 14, characterized in that said diffuser is constituted by a pyrotechnic torch (220) electrically activatable by an electronic control module (250) integrated into said nacelle (200; 200'; 200”).

Images