Aerostatic device provided with means for managing descent with active rotary rigid wing

Abstract

The invention relates to an aerostatic device (1) which comprises: - a balloon (100) comprising an envelope (120) intended to be filled with a lighter-than-air gas; - a gondola (200) connected to the balloon (100) and carrying a payload, the gondola being able to be raised in the atmosphere by the balloon (100); and - means for managing the descent (260) following deflation, bursting or automatic or programmed release of the balloon (100) at altitude. The means for managing descent (260) comprise a plurality of motorised rotors (261) controlled by an electronic control module (250) according to data transmitted by sensors on board the gondola (200).

Description

[0001] Aerostatic device equipped with means for managing the descent with active rotating rigid wing

[0002] Technical field

[0003] 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 prevent the formation of hail or to carry out aerial surveillance. It relates in particular to such an aerostatic device equipped with means for managing the descent with a rigid wing.

[0004] Prior art

[0005] Weather balloons, commonly 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 comprehensive picture of atmospheric conditions for use in, for example, weather forecasts.

[0006] Such a weather balloon typically includes:

[0007] - 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, wind direction and velocity 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.

[0008] Such devices may, as disclosed in document CN 107 765 346 A, also include propellers to correct the upward or lateral trajectory of the device, the balloons respectively integrated into said devices providing the permanent technical effect of lift in the air.

[0009] Other types of aerostatic devices are also known, designed 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 cloud particles.

[0010] 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 active particles into the cloud cells such as dust with a strong affinity for water (sodium, calcium, magnesium salts, etc.), refrigerating materials (dry ice, propane, liquid nitrogen) or ice-forming nuclei (silver iodide or copper iodide, etc.).

[0011] 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.

[0012] 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.

[0013] 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.

[0014] Since the payload carried by the nacelle of such an aerostatic device is relatively expensive and fragile, its recovery is generally desired so that it can be reused at least in part.

[0015] 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 canopy connected by straps to the basket and triggered following deflation, bursting or automatic or programmed release of the balloon at altitude.

[0016] Document US 3,614,031 A describes a device for destroying and lowering such a balloon, enabling the payload and its equipment to be recovered 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.

[0017] Due to the turbulence zones encountered by aerostatic devices during their descent, such parachutes unfortunately tend to fold or twist on themselves so that they no longer allow the fall speed to be sufficiently reduced. To combat the disadvantage resulting from the operation of a flexible canopy such as a parachute, other aerostatic devices, such as those described by documents US 4,112,753 A and US 2014 / 137511 A1, comprise passive means with a rigid canopy for managing the descent following a bursting of their respective balloons at altitude. Such known means are, for example, with a rotating rigid canopy or in the shape of a maple seed.Such passive solutions only address the slowing down of the descent of an aerostatic device, after bursting of its aerostatic means without offering control and piloting of said descent as such, said device being able to suffer from strong drifts under the effects of particularly intense horizontal winds within a cloud cell.

[0018] Statement of the invention

[0019] The present invention therefore aims to better secure the sensitive descent phase of such an aerostatic device following the deflation, bursting or automatic or programmed release of the balloon(s) providing the lift effect in the air, in particular allowing better control of a landing site, avoiding no-fly zones and / or areas with high population density.

[0020] The invention proposes for this purpose an aerostatic device comprising:

[0021] - a balloon comprising an envelope intended to be filled with a gas lighter than air;

[0022] - a basket connected to said balloon and carrying a payload, said basket being capable of being raised into the atmosphere by said balloon; and

[0023] - means of managing the descent following deflation, bursting or automatic or programmed release of said balloon at altitude.

[0024] According to the invention, said means for managing the descent following deflation, bursting or automatic or programmed release of said balloon at altitude are of the active rotating rigid wing type.

[0025] 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.

[0026] The use of such an active rigid rotating wing, less sensitive to turbulence possibly encountered in certain areas of the atmosphere, makes it possible to better secure the sensitive descent phase of the aerostatic device by guaranteeing a reduction in the vertical speed of impact with the ground at the time of landing as well as better control of the landing site.

[0027] The invention makes it possible to avoid no-fly zones and / or areas with high population density during the descent of the aerostatic device and considerably limits the risk of deterioration of the payload carried by the nacelle, so as to allow, almost systematically, its reuse for subsequent flights.

[0028] 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:

[0029] - at least one motorized rotor each connected to said nacelle by a connecting arm; and

[0030] - a flight controller implemented by an electronic control module integrated into said nacelle and configured to: o activate said at least one motorized rotor only at the time, or after the occurrence, of a deflation, bursting or automatic or programmed release of the balloon, and o control the operation of said at least one motorized rotor according to data transmitted by sensors on board said nacelle.

[0031] In order to control the entire descent phase of the device, said flight controller can be configured to activate said at least one motorized rotor at the time of deflation, bursting or automatic or programmed release of said balloon.

[0032] Alternatively and in order to limit energy consumption, said flight controller may be configured to activate said at least one motorized rotor only below a predetermined threshold altitude.

[0033] In this case, to maximize the technical effect induced by the upward thrust delivered by the motorized rotor(s), an aerostatic device according to the invention may comprise a self-righting system in flight so that, upon activation of said at least one motorized rotor, the latter delivers upward thrust.

[0034] To increase tenfold the lifting thrust delivered and / or reduce the intrinsic power and size of the at least one motorized rotor, an aerostatic device according to the invention may comprise a plurality of motorized rotors each delivering lifting thrust, the flight controller being arranged to activate and control each motorized rotor of said plurality.

[0035] In order to control the landing site to avoid no-fly zones and / or areas with high population density, 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.

[0036] In order to prevent certain elements constituting the payload from coming into direct contact with the ground at the time of landing, the motorized rotor(s) 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.

[0037] Generally speaking, said nacelle may include a diffuser designed to diffuse active particles within cloud cells present in the atmosphere so as to ensure their seeding.

[0038] Such a diffuser will, for example, consist of a pyrotechnic torch electrically activated by an electronic control module integrated into said nacelle.

[0039] Brief description of the drawings

[0040] 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:

[0041] - Figure 1 represents a perspective view of a meteorological aerostatic device according to a first embodiment of the invention; - Figure 2 is an enlarged perspective view of the nacelle of the aerostatic device of Figure 1;

[0042] - Figure 3 represents a schematic diagram of the electronic module arranged on the nacelle of Figure 2.

[0043] Detailed description

[0044] Figure 1 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.

[0045] As illustrated in this figure 1, 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.

[0046] 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 to a certain altitude at which the seeding of cloud cells will be carried out.

[0047] 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 100 bursting too early in the atmosphere due to the drop in external pressure with altitude.

[0048] With reference to Figure 2, the nacelle 200 comprises in this case:

[0049] - a support 210; - an active particle diffuser 220;

[0050] - 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;

[0051] - a hollow sleeve 240 onto which the neck 110 of the balloon 100 is securely and tightly fitted (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

[0052] - an electronic control module 250.

[0053] 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.

[0054] 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.

[0055] 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 consisting of 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. This pyrotechnic torch 220 also comprises a trigger, not visible in the figures, advantageously housed in the sealed cylindrical envelope 221 and designed to cause the activation of the pyrotechnic mixture.

[0056] 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 250.

[0057] When activated, causing the active particles it contains to disperse 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.

[0058] 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.

[0059] 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.

[0060] According to other embodiment variants 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.

[0061] 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).

[0062] 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.

[0063] 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.

[0064] 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 a power supply). 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.

[0065] As can be seen in Figure 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.

[0066] As illustrated by figures 1 and 2, the aerostatic device 1 also comprises means for managing its descent 260 which can be activated only following (that is to say, at the time of, or after) a deflation, a bursting or an automatic or programmed release of the balloon at altitude 100.

[0067] Of the active rotating rigid wing type, these means 260 comprise one or more motorized rotors 261 (advantageously four in number arranged in a square of which they constitute the corners as shown in figures 1 and 2) 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. When the means 260 comprise only a single motorized rotor 261, the latter is advantageously arranged at the distal end of a connecting arm to be positioned substantially in the center of the lower part of the nacelle 200 so that the propeller of the rotor does not come into contact with said nacelle 200 or with any other element of the aerostatic device 1 when said single motorized rotor delivers upward thrust.

[0068] In the configuration illustrated in FIG. 2, each of the four motorized rotors 261, arranged at the distal end of a respective connecting arm 262, comprises a rotating propeller 261 A driven by a corresponding motor (not visible) housed in a hollow body 261 B provided at this distal end of the connecting arm 262.

[0069] Each rotary propeller 261 A comprises a central hub and several blades extending radially from this central hub and the number of which is advantageously between two and five.

[0070] The set of at least one motorized rotors 261 is sized (in terms of power, dimensions, electrical consumption) to deliver an upward thrust intended mainly to oppose gravity in order to slow the fall speed of the aerostatic device 1 and orient its trajectory back to the ground to control the landing site, after deflation, bursting or automatic or programmed release of the balloon at altitude 100. Such an aerostatic device 1 must be as compact and light as possible in an application such as seeding a cloud cell. The lift and elevation in the air of the aerostatic device are solely induced by the balloon 100. They are in no case provided by the activation of said one or more motorized rotors 261, as would be the case with the high-power motorized rotors of a drone devoid of aerostatic means.The means for managing the descent 260 of an aerostatic device 1 according to the invention can thus be sized to deliver sufficient thrust to mainly oppose gravity and orient the trajectory back to the ground. They must, however, deliver a power greater than the rotors of the system previously mentioned in connection with document CN 107 765 346 A, according to which the elevation is provided by the activation of a set of eight rotors of small dimensions and motorized two by two by four low-power motors, the balloon compensating for the weight of the disclosed device, the latter becoming neutral or stationary in the absence of the activation of said motors.Furthermore, although said document CN 107 765 346 A mentions being able to manage the descent of the aerostatic device by means of said eight motorized rotors, without removing the lift provided by the balloon, the reader will not find any technical teaching within the document likely to propose such a functionality. According to the invention, in connection with the example illustrated by Figure 2, the central hub and the blades of each rotary propeller 261 A are preferably molded in a single piece from a thermoplastic polymer.

[0071] According to alternative embodiments not shown, each motorized rotor 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.

[0072] Again with reference to Figure 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 activate the motorized rotor(s) 261 only following (that is to say, at the time of, or after) an automatic or programmed deflation, bursting or release of the balloon 100 at altitude. Said flight controller 264 is further configured to control the operation of each of said at least one motorized rotors 261 as a function of data transmitted by sensors on board 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.

[0073] In order to control the entire descent phase of the device, the flight controller 264 may be configured to activate the motorized rotor(s) 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. Alternatively and in order to limit energy consumption, the flight controller 264 may be configured to activate the motorized rotor(s) 261 only below a predetermined threshold altitude. In such a case, the aerostatic device 1 may advantageously be equipped with a self-righting system in flight not shown in the figures.Such a system will then advantageously be designed so that, upon activation of the motorized rotors 261 by the flight controller 264, said motorized rotor(s) 261 deliver an upward thrust mainly opposing gravity, that is to say a thrust mainly vertical and oriented from the ground towards the sky. Such a self-righting system may advantageously consist of a counterweight located below the center of gravity of the nacelle 200 of the aerostatic device 1, when the upper surface of said nacelle 200 cooperates with a balloon 100.Such a counterweight may also be configured to compensate for the torque exerted by the weight of the body of the torch 220 advantageously emptied of any active substance and its support 212 on the nacelle 200, preventing any tilting of said nacelle 200, after the deflation, bursting or release of said balloon, if the motorized rotor(s) 261 are not activated immediately during said deflation, bursting or release. Under the action of such a self-righting system, the nacelle 200 can recover or maintain a “nominal” attitude, that is to say substantially horizontal, as described during the ascending phase of the aerostatic device 1 prior to the bursting or release of said balloon 100.Alternatively or additionally, such a self-righting system may comprise a flap, the proximal part of which is rotatably mounted along an axis parallel to the edge of the flat attachment portion 211 of the support 210, opposite the edge cooperating with the body of the torch 220. Such an arrangement of such a movable flap allows the latter to describe a first “inactive” configuration according to which the flap is oriented substantially in a vertical position (distal part oriented towards the ground) during the ascent of the aerostatic device 1. On the other hand, when said device 1 begins a descent (under the effect of a burst or a release of the balloon 100), said flap straightens to occupy an “active” configuration, that is to say according to which said flap is substantially in the plane of the support 210 (i.e. substantially horizontally when the attitude of said support 210 is horizontal).As a result, said flap increases the bearing surface of said support 210, opposing the torque exerted by the weight of the body of the torch 220 (advantageously emptied of any active substance) and its support 212 on the nacelle 200, preventing any tilting of said nacelle 200. Such a flap or flaps may form, together with the nacelle 200, the equivalent of a propeller with possibly variable pitch, capable of autorotating, thus controlling the speed and direction of fall.Whatever its arrangement, such a self-righting system is however optional, the motorized rotor(s) 261 being able to be configured to, under the control of the flight controller 264, right itself or by itself the attitude of the nacelle 200 during the descent of the aerostatic device 1, so that said nacelle 200 recovers the attitude that it occupied substantially during the ascent of the aerostatic device 1 under the effect of the balloon 100 and / or an attitude allowing said device to head towards a target landing site.

[0074] A flight controller 264 according to the invention 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.

[0075] 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.

[0076] 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. According to other variants or in addition, the geopositioning receiver 268 may comprise an inertial unit generally comprising three gyrometers and three accelerometers.

[0077] Thanks to the presence of such a geopositioning information receiver 268, the flight controller 264 can be advantageously configured to ensure the automated return of the aerostatic device 1 to its takeoff point or to a predetermined landing site whose geographical coordinates are stored in a non-volatile memory such as 255.

[0078] 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 precharged battery (for example of the lithium-polymer type due to its high power-to-weight ratio) preferably installed on this module 250.

[0079] 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.

[0080] According to other embodiment variants 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 rotor(s) 261 only during a part of the descent phase of the device 1, for example when its altitude or its speed reaches a predetermined threshold. Such a flight controller 264 can also temporarily configure the or one of said motorized rotors 261 so that the latter describes an autorotation during the descent of the aerostatic device 1, the motor of such a rotor transforming into a generator capable of recharging an electric battery, for example.Alternatively or additionally, the invention provides that the flight controller 264 can also control the propeller pitch of the or one of the motorized rotors 621, during the descent of the aerostatic device 1, when the arrangement of said rotor allows it, to act on the upward thrust delivered by said rotor. 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 devices for seeding cloud cells or clouds 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) 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 deflation, bursting or automatic or programmed release of said balloon (100) at altitude; characterized in that said means for managing the descent (260) are of the active rotating rigid wing type.

2. Aerostatic device (1) according to claim 1, for which the descent management means (260) comprise: - at least one motorized rotor (261) each connected to said nacelle (200) by a connecting arm (262); and - a flight controller (264) implemented by an electronic control module (250) integrated into said nacelle (200) and configured to: o activate said at least one motorized rotor (261) only at the time, or after the occurrence, of a deflation, a bursting or an automatic or programmed release of the balloon (100), and o control the operation of said at least one motorized rotor (261) according to data transmitted by on-board sensors (265, 266, 267) on said nacelle (200).

3. Aerostatic device (1) according to claim 2, characterized in that said flight controller (264) is configured to activate said at least one motorized rotor (261) at the time of deflation, bursting or automatic or programmed release of said balloon (100).

4. Aerostatic device (1) according to claim 1 or 2, wherein the flight controller (264) is configured to activate said at least one motorized rotor (261) only below a predetermined threshold altitude.

5. Aerostatic device (1) according to claim 3, comprising a self-righting system in flight so that, upon activation of said at least one motorized rotor (261), the latter delivers upward thrust.

6. Aerostatic device (1) according to any one of claims 2 to 5, comprising a plurality of motorized rotors (261) each delivering an upward thrust, the flight controller (264) being arranged to activate and control each motorized rotor (261) of said plurality.

7. Aerostatic device (1) according to one of claims 1 to 6, 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.

8. Aerostatic device (1) according to one of claims 1 to 7, characterized in that the motorized rotor(s) (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).

9. Aerostatic device (1) according to one of claims 1 to 8, characterized in that said nacelle (200) comprises a diffuser (220) provided for diffusing active particles within cloud cells present in the atmosphere so as to ensure their seeding.

10. Aerostatic device (1) according to claim 9, characterized in that said diffuser is constituted by a pyrotechnic torch (220) electrically activatable by the electronic control module (250) integrated into said nacelle (200).

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