Aerostat for carrying out transport and / or observation missions on a planet with an atmosphere

Abstract

The present invention relates to an aerostat (1) for carrying out transport and / or observation missions on a planet with an atmosphere, the aerostat comprising: an inflatable body (2) designed to be pressurised by a gas lighter than the atmosphere, a payload (3) configured to have at least one scientific instrument installed on-board, and a solar energy generator (7) arranged between the inflatable body (2) and the payload (3).

Description

Description Title of the invention: Aerostat intended to carry out transport and / or observation missions on a planet with an atmosphere Technical Field

[0001] The present invention relates to an aerostat intended to carry out transport and / or observation missions on a planet with an atmosphere. Prior art

[0002] Aerostats intended to carry out transport and / or observation missions on a planet with an atmosphere are known from the prior art.

[0003] These aerostats generally include a payload which carries components to be transported and / or components intended for observation such as scientific instruments.

[0004] In the space field, aerostats are designed to move through the atmosphere towards a destination where the mission is to be carried out.

[0005] Among the aerostats we know for example the open stratospheric balloons (OSB).

[0006] This type of balloon currently allows flights lasting between 30 and 48 hours.

[0007] Research and development is currently focused on increasing the flight time of these balloons in order to increase the duration of transport or observation missions.

[0008] Along with increasing balloon flight times, it is usually necessary to increase the operating time of the components onboard the payload that require energy.

[0009] Currently, energy is provided by electrical generation means such as batteries or cells. Increasing flight duration would therefore require equipping payloads with a significant number of these electrical generation means making the mass balance and size of the payload incompatible.

[0010] There is therefore a need to provide a power generation system that increases payload life while minimizing the mass and bulk of such payloads. Statement of the invention

[0011] The invention aims in particular to overcome at least one of these drawbacks and relates, according to one aspect, to an aerostat intended to carry out transport and / or observation missions on a planet with an atmosphere. The aerostat comprises an inflatable body designed to be pressurized by a gas lighter than the atmosphere, a payload configured to carry at least one scientific instrument and a solar energy generator arranged between the inflatable body and the payload.

[0012] Thanks to the aerostat according to the invention, it is possible to increase the duration of use of the payload thanks to the use of the solar energy generator. The use of the solar energy generator which allows energy renewal makes it possible to do away with the multiple means of energy generation of the prior art and to minimize the mass and size of the payload.

[0013] Furthermore, the arrangement of the solar power generator between the payload and the inflatable envelope allows the space under the payload to be freed up. This allows components, for example scientific instruments, configured to point towards the ground (at NADIR) not to be disturbed by the presence of a solar generator arranged in this space.

[0014] This also further minimizes the payload footprint as there is no need to use solar array offset elements to exit a shadow cone under the payload.

[0015] This also allows for further reduction of the payload mass which does not require the use of a protective element which would be considered to protect the solar generator arranged under the payload.

[0016] According to other characteristics of the invention, the aerostat of the invention may comprise one or more of the following optional characteristics considered alone or in all technically possible combinations.

[0017] The solar power generator comprises a columnar structure.

[0018] The solar energy generator comprises a plurality of photovoltaic cells disposed on an outer surface of the columnar structure.

[0019] The solar power generator is movable between a first position in which the solar power generator is retracted and a second position in which the solar power generator is deployed.

[0020] The solar power generator includes a plurality of sections, one section of the plurality of sections having a diameter smaller than the diameter of another section of the plurality of sections such that the section can be arranged in the other section when the solar power generator is retracted.

[0021] For example, the columnar structure comprises the plurality of sections when the solar energy generator is deployed.

[0022] For example, the plurality of sections forms the columnar structure when the solar energy generator is deployed.

[0023] The sections are connected to each other by means of removable hinges.

[0024] The solar generator comprises a plurality of side faces, each side face comprising a plurality of photovoltaic panels retractable between the first position in which the photovoltaic panels are grouped and extend horizontally one under the other in horizontal planes, and the second position in which the photovoltaic panels are deployed and extend vertically one under the other in the same vertical plane. The columnar structure comprises the side faces. The side faces form the columnar structure.

[0025] The aerostat includes a rotating device configured to rotate the payload about a vertical axis.

[0026] The photovoltaic cells are arranged around the perimeter of the columnar structure, so that at least part of the photovoltaic cells is always exposed to the sun.

[0027] The columnar structure is cylindrical or polygonal. Brief description of the drawings

[0028] [Fig. 1] Figure 1 illustrates an aerostat according to one embodiment of the invention, in flight, comprising a solar generator in the deployed position.

[0029] [Fig. 2] Figure 2 illustrates the aerostat according to one embodiment of the invention comprising the solar generator in the retracted position.

[0030] [Fig. 3] Figure 3 illustrates the aerostat comprising a solar generator of the aerostat according to one embodiment of the invention.

[0031] [Fig. 4] Figure 4 illustrates the aerostat comprising the solar generator according to one embodiment of the invention.

[0032] [Fig. 5] Figure 5 illustrates the aerostat comprising the solar generator according to one embodiment of the invention.

[0033] [Fig. 6] Figure 6 illustrates a deployment / retraction mechanism of the solar generator according to one embodiment of the invention.

[0034] [Fig. 7] Figure 7 illustrates a solar generator according to another embodiment in the deployed position.

[0035] [Fig. 8] Figure 8 illustrates the solar generator according to the other embodiment in the deployed position.

[0036] [Fig. 9] Figure 9 illustrates a deployment / retraction mechanism of the solar generator according to one embodiment of the invention.

[0037] [Fig. 10] Figure 10 illustrates the deployment / retraction mechanism of the solar generator according to one embodiment of the invention.

[0038] [Fig. 11] Figure 11 illustrates the solar generator according to the other embodiment in the retracted position. Description of the embodiments

[0039] Other characteristics and advantages of the invention will appear on reading the non-limiting description which follows and the appended figures which schematically illustrate several embodiments of the aerostat according to the invention.

[0040] For the sake of simplification, identical elements are identified by identical reference signs throughout the figures.

[0041] In the following description and in the claims, the terms "horizontal", "vertical", "upper", "lower", etc. will be used without limitation and with reference to the drawings in order to facilitate the description.

[0042] Figure 1 illustrates an aerostat 1 intended to carry out transport and / or observation missions on a planet with an atmosphere according to this presentation.

[0043] The aerostat 1 comprises an inflatable body 2 designed to be filled with a gas lighter than the atmosphere. In other words, the inflatable body 2 is intended to contain a gas lighter than the gas present in the planet's atmosphere, such as helium for example. The gas lighter than the gas present in the atmosphere allows the inflatable body to move in the atmosphere. For example, the inflatable body can be designed to be pressurized by a gas lighter than the atmosphere.

[0044] The inflatable body is configured to move between a surface of the planet with an atmosphere and a predetermined altitude in the atmosphere, for example the stratosphere. For this purpose the inflatable body can be configured to store a quantity of gas at a pressure such that it can move at the predetermined altitude.

[0045] By planetary surface we mean any surface of the planet such as water (seas, oceans) or land (such as glaciers for example).

[0046] Aerostat 1 may be a stratospheric balloon, for example an open stratospheric balloon or any other balloon suitable for carrying out transport and / or observation missions on a planet with an atmosphere.

[0047] For example, inflatable body 2 has a water drop shape.

[0048] For example, the inflatable body comprises at its base at least two gas discharge sleeves 24, 24'. The sleeves make it possible to balance the atmospheric pressure and the pressure of the gas present in the inflatable body 2.

[0049] The aerostat 1 according to the invention comprises a payload 3.

[0050] For example, payload 3 is configured to carry one or more scientific instrument(s), for example measuring instruments, for example instruments for measuring atmospheric properties. These various components also require energy to operate. For example, payload 3 is a scientific pod intended to carry out observation missions.

[0051] For example, the payload can carry one or more telescopes, for example to carry out astronomy measurements.

[0052] For example, payload 3 may include four feet 32, 33, 34, 36 (Figure 2). Feet 32, 33, 34, 36 prevent payload 3 from crashing upon return to the ground after the mission is completed.

[0053] In the present disclosure, the payload 3 is arranged under the inflatable body 2.

[0054] By the expression "arranged under the inflatable body" is meant that the payload 3 is intended to be arranged under the surface of the inflatable body 2 arranged opposite the surface of the planet when the aerostat is put into operation and raised into the atmosphere.

[0055] For example, payload 3 is connected to inflatable body 2.

[0056] For example, the aerostat 1 may comprise a connecting means configured to connect the payload 3 and the inflatable body 2.

[0057] For example, the connecting means comprises or is at least one flight chain 4, for example two flight chains.

[0058] According to an embodiment illustrated in Figure 3, the connecting means may comprise two flight chains 4, 4'.

[0059] For example, the inflatable body 2 may be attached to a first end portion 40 of the flight chain 4 and the payload 3 may be attached to a second end portion 400 of the flight chain 4.

[0060] For example, the first end portion 40 of the flight chain 4 is opposite the second end portion 400 of the flight chain 4.

[0061] The aerostat may include pyrotechnic separators 5. The pyrotechnic separators may, for example, make it possible to separate, for example at the end of the mission, the inflatable body 2 from the flight chain 4.

[0062] The pyrotechnic separators 5 are intended to separate the payload 3 from the inflatable body 2 once the mission is completed. This allows the payload 3 to be recovered at the end of the mission and to be able to reuse it.

[0063] The pyrotechnic separators 5 can be attached to the flight chain 4. For example, the pyrotechnic separators are arranged between the inflatable body 2 and the payload 4.

[0064] The aerostat 1 may include at least one parachute intended to slow the return of the payload 3 to the ground.

[0065] Said at least one parachute can be attached to the flight chain 4. For example, said at least one parachute can be arranged between the inflatable body 2 and the payload 3, under the pyrotechnic separators 5.

[0066] By under the pyrotechnic separators, it is meant that said at least one parachute can be arranged under the pyrotechnic separators 5 when the aerostat 1 is in flight.

[0067] For example, the aerostat includes one or more parachute(s), for example two or three parachutes.

[0068] The aerostat 1 may comprise an auxiliary inflatable body 10. The auxiliary inflatable body 10 is configured to initiate the flight of the aerostat into the atmosphere.

[0069] The auxiliary inflatable body 10 is for example configured to lift the payload by one or a few meters, for example 1 or 2 meters to prevent the payload 3 from being dragged on the ground during takeoff.

[0070] For example, the auxiliary inflatable body 10 may be attached to the flight chain 4. For example, the auxiliary inflatable body may be arranged between the inflatable body 2 and the payload 3. For example, the auxiliary inflatable body may be arranged under said at least one parachute.

[0071] The aerostat according to the invention comprises a solar energy generator 7 also called a solar generator 7.

[0072] The solar energy generator 7 comprises a plurality of photovoltaic cells.

[0073] The solar energy generator 7 is intended to generate energy necessary for the operation of the scientific instrument(s) on board the payload 3.

[0074] The solar generator allows for renewable energy generation, which increases energy production and increases the useful life of the payload.

[0075] In the present disclosure, the solar energy generator 7 is arranged between the inflatable body 2 and the payload 3.

[0076] In the present disclosure, the solar energy generator 7 is arranged between the inflatable body 2 and the payload 3 only.

[0077] The photovoltaic cells of the solar generator are thus arranged between the inflatable body 2 and the payload 3, for example the photovoltaic cells of the aerostat are only between the inflatable body 2 and the payload 3. For example, the photovoltaic cells of the aerostat are arranged between the inflatable body 2 and the payload 3 only.

[0078] The aerostat 1 may comprise conversion means intended to convert the solar energy generated by the solar generator 7 into electrical energy. The conversion means may comprise one or more converter(s) intended to convert the solar energy generated by the solar generator 7 into electrical energy.

[0079] The conversion means(s) may for example be supported by payload 3.

[0080] For example, the inflatable body 2 may be attached to the first end portion of the flight chain 4, the payload 3 may be attached to the second end portion of the flight chain 4, and the solar generator may be arranged between the inflatable body 2 and the payload 3.

[0081] The arrangement of the solar energy generator between the inflatable body 2 and the payload 3 also makes it possible not to hinder the measurements of scientific instruments intended to point at the nadir (i.e. towards the ground). This latter behavior can be observed when solar generators are arranged under the payload.

[0082] Furthermore, this allows the payload to have stable behavior during takeoff and landing by avoiding, for example, propeller effects which could set the payload into rotation if the solar generator were arranged on the sides of the payload, for example in such a case when the solar generator is inclined relative to the payload.

[0083] This also further minimizes the payload footprint as there is no need to use solar array offset elements to exit a shadow cone under the payload.

[0084] This also allows for further reduction of the payload mass which does not require the use of a protective element which would be considered to protect the solar generator arranged under the payload.

[0085] Furthermore, the aerostat 1 may comprise a plurality of connectors for connecting the components of the solar generator 7 configured to generate energy to the components on board the payload 3 which require energy.

[0086] In the present disclosure, the solar generator 7 may comprise a columnar structure 72.

[0087] The columnar structure allows at least a portion of these photovoltaic cells to always be exposed to the sun. This configuration allows, for example, the photovoltaic cells to be arranged around the perimeter of the columnar structure, for example over 360°, so that at least a portion of these photovoltaic cells is always exposed to the sun. Thus, it is no longer necessary to provide a device intended to allow the rotation of the solar generator so as to expose the solar cells to the Sun. This makes it possible to simplify and lighten the aerostat.

[0088] For example, the solar generator 7 may comprise a single columnar structure 72, i.e., a single columnar structure.

[0089] For example, the columnar structure ni is a hollow column.

[0090] We hear that the columnar structure 72 is hollow.

[0091] For example, solar array 7 may be configured to extend around flight string 4.

[0092] For example, at least a portion of the flight chain 4 may be arranged in the hollow of the columnar structure 72.

[0093] For example, the columnar structure 72 can be cylindrical or polygonal.

[0094] The solar energy generator 7 may comprise a plurality of photovoltaic cells 74.

[0095] The photovoltaic cells 72 allow energy to be generated in a renewable manner, which makes it possible to increase energy production and increase the useful life of the components that can be carried in the payload 3.

[0096] For example, the photovoltaic cells 74 may be arranged on all or part of an external surface of the columnar structure 72.

[0097] The external surface of the columnar structure is understood to mean the surface intended to face the sun when the aerostat 1 is in flight. The external surface of the columnar structure 72 is understood to mean the surface opposite the surface forming the hollow of the columnar structure 72.

[0098] This arrangement provides adequate exposure of the photovoltaic cells to the sun.

[0099] For example, the plurality of photovoltaic cells 74 are disposed over the entire outer surface of the columnar structure 72.

[0100] According to one embodiment, the plurality of photovoltaic cells can be attached to the outer surface of the columnar structure by encapsulating the photovoltaic cells in a material of the columnar structure.

[0101] For example, the columnar structure may include a canvas material.

[0102] For example, encapsulation may be achieved using a resin, preferably one designed to withstand the atmospheric environment.

[0103] The number of photovoltaic cells can be chosen according to the energy requirement. The greater the energy requirement, the greater the number of photovoltaic cells must be.

[0104] For example, the size of the surface of the solar generator on which the plurality of photovoltaic cells are arranged can be chosen according to the energy requirement.

[0105] Dimension is understood to mean an area of ​​the external surface of the columnar structure on which the photovoltaic cells can be arranged.

[0106] For example, the aerostat may comprise a first solar generator 7 whose columnar structure has a surface of a first dimension and at least one other solar generator whose columnar structure has a surface of another dimension.

[0107] For example, the surface dimension of said at least one other solar generator may be less than or greater than the surface dimension of the first solar generator.

[0108] For example, the plurality of photovoltaic cells may be arranged over the entire external surface of the columnar structures so that the number of photovoltaic cells is a function of the available external surface of the columnar structure, on which they are fixed.

[0109] For example, the first solar generator may be replaced by a second solar generator having a larger size than the first solar generator and comprising a greater number of photovoltaic cells than the first solar generator, depending on the energy requirement.

[0110] For example, the dimension of the surface of said at least one other solar generator may be equal to the dimension of the surface of the first solar generator.

[0111] In this example, the number of solar cells in the second solar generator may be less or more than that of the first generator.

[0112] For example, the number of solar cells in the second solar generator is greater than that of the first generator. The first solar generator can be replaced by the second solar generator depending on the energy requirement.

[0113] In another example, the aerostat may comprise a single solar generator 7. In this example, the surface area of ​​the columnar structure 72 of the solar generator may be modular.

[0114] Modular surface means a surface whose dimension can be increased or reduced. For example, the dimension of the surface of the solar generator on which the plurality of photovoltaic cells are arranged can be modulated according to the energy requirement. Dimension means an area of ​​the external surface of the columnar structure on which the photovoltaic cells can be arranged.

[0115] An example is illustrated in Figure 3. In this example, the solar generator 7 may comprise a plurality of sections (72a, 72b, 72c, 72d, 72e, 72f).

[0116] The sections (72a,...,72f) can extend under each other and each have a cylindrical or polygonal section.

[0117] Each section may comprise a plurality of photovoltaic cells fixed to the external surface of the columnar structure, for example by encapsulating the photovoltaic cells in a material, for example fabric, of the columnar structure.

[0118] The plurality of sections (72a,...,72f) forms the surface of the columnar structure 72.

[0119] For example, each section is connected to an adjacent section in a removable manner.

[0120] For example, the sections (72a,...,72f) are connected to each other by means of a removable connection.

[0121] For example, the sections (72a,...,72f) are connected to each other by means of removable hinges.

[0122] In the example shown in Figure 3, the columnar structure may comprise six sections (72a, ..., 72f) connected to each other in a removable manner.

[0123] The removable connection makes it possible to modulate the dimension of the photovoltaic surface, for example by removing one or more sections (72a,...,72f) from the columnar structure or by adding one or more sections (72a,...,72f) to the columnar structure 72, on which the photovoltaic cells are arranged, for example depending on the energy requirement. It is thus also possible to repair damaged sections.

[0124] Another example of a solar generator 7 is illustrated in Figures 7 and 8. In this example, the solar generator 7 comprises a plurality of side faces (75a, ..., 75h).

[0125] A side face is understood to mean a side face of the solar generator, for example a side face of the columnar structure.

[0126] The side faces (75a,...,75h) can be independent of each other, that is to say they are not connected to each other.

[0127] The side faces form the columnar structure 72. For example, the side faces (75a, ..., 75h) are arranged so as to form the columnar structure 72.

[0128] Each of the side faces comprises a plurality of solar panels 750. Each solar panel 750 comprises a plurality of photovoltaic cells 7500. The photovoltaic cells may be fixed to the side faces forming the columnar structure, for example encapsulated, for example in a fabric material of the side faces forming the columnar structure.

[0129] Because the side faces (75a,...,75h) can be independent of each other, it is possible to remove or add one or more faces (75a,...,75h) depending on the energy requirement. In the example illustrated, the solar generator 7 comprises eight side faces (75a,...,75h). The columnar structure can thus have an octagonal shape.

[0130] The solar generator 7 could comprise more or fewer side faces such as for example four side faces or six side faces.

[0131] The solar panels 750 of each of the side faces can be connected to each other in a removable manner, for example by removable connections, for example by removable hinges 60. A hinge can have a first movable part on which a first solar panel is intended to be fixed and a second movable part on which a second adjacent solar panel is intended to be fixed. The hinge may comprise a shaft connecting the first and second movable parts and allows the movable parts to move by rotation around the shaft.

[0132] For example, two adjacent 750 photovoltaic panels can be connected to each other using two removable hinges.

[0133] This makes it easy to remove or add one or more photovoltaic panels to each of the side faces. The removable connection makes it possible to modulate the size of the photovoltaic surface, for example by removing one or more photovoltaic panels from each of the side faces or by adding one or more photovoltaic panels to each of the side faces, on which the photovoltaic cells are arranged, for example depending on the energy requirement. It is also possible to repair damaged photovoltaic panels.

[0134] In the example shown, each side face (75a, ..., 75h) comprises six photovoltaic panels 750. Each face could comprise more or fewer photovoltaic panels, for example four panels or six photovoltaic panels.

[0135] Furthermore, in the illustrated example, each photovoltaic panel 750 comprises a plurality of photovoltaic cells 7500, for example fifteen photovoltaic cells. The invention is not limited to this number of photovoltaic cells and each of the photovoltaic panels may comprise more or fewer photovoltaic cells.

[0136] In the present disclosure, the solar energy generator 7 can be movable between a first position in which the solar energy generator is retracted, called the storage position (figure 2) and a second position in which the solar energy generator is deployed, called the use position (figure 1).

[0137] For example, the solar power generator 7 may be movable relative to the payload 3, for example when the solar generator is attached to the payload 3.

[0138] When retracted, the solar energy generator 7 has a minimum of bulk, necessary in particular during the take-off, ascent and descent phases of the aerostat.

[0139] For example, the solar generator 7 can be arranged, for example in its entirety, as close as possible to the payload 3.

[0140] When deployed, the solar array 7 may extend around a first portion of the flight chain.

[0141] For example, the solar power generator 7 may extend around the first portion of the flight chain 4 and at least one other portion of the flight chain 4.

[0142] In the example illustrated in Figures 3 to 5, the solar generator 7 may comprise the section 70a comprising for example a first end portion 70 of the solar generator 7.

[0143] For example, the first end portion 70 of the solar generator 7 can be fixed to the payload 3. For example, the first end portion 70 of the solar generator 7 is fixed to an upper part 30 of the payload 3.

[0144] The upper part of the payload 3 is understood to mean the part of the payload proximal to the inflatable body 2 when the payload 3 is connected to the inflatable body 2, for example by means of the flight chain 4.

[0145] The solar generator 7 may comprise another section 70f comprising a second end portion 700 of the solar generator 7.

[0146] For example, the second end portion 700 may be free.

[0147] The first end portion 70 of the solar generator is opposite the second end portion 700 of the solar generator 7.

[0148] For example, the section 72a of the columnar structure 72 comprising for example the free end 700 of the solar generator has a diameter smaller than the diameter of the other section 72f of the columnar structure 72 comprising for example the end 70 of the solar generator fixed to the payload 3.

[0149] This configuration allows section 72a to be integrated into the other section 72f of the columnar structure 72. Thus the solar generator 7 can be retracted.

[0150] For example, the columnar structure ni can comprise the plurality of sections of which the section 72a comprises for example the free end 700 of the solar generator and the other section 72f comprises the end 70 fixed to the payload 3.

[0151] For example, each section of the plurality of sections 72a 72f has a diameter increasing from the section 72a comprising for example the free end 700 of the solar generator to the other section 72f comprising the end 70 fixed to the payload.

[0152] This configuration allows the sections 72a, ..., 72f forming the columnar structure to be able to integrate into each other in the retracted position of the solar generator.

[0153] In the example illustrated in Figures 3 to 5, the columnar structure may comprise six sections 72a, ..., 72f of increasing diameter, the sections being configured to integrate into each other in the retracted position of the solar generator. When the surface of the columnar structure is modular, the number of section(s) may be modified by adding or removing one or more section(s).

[0154] The aerostat may comprise a retraction / deployment device 8 configured to cause the retraction / deployment of the solar generator 7.

[0155] For example, the retraction / deployment device 8 is configured to retract / deploy the columnar structure 72.

[0156] For example, the retraction / deployment device 8 may be configured to move from a deployed position to a retracted position so as to drive the solar generator 7 from the deployed position to the retracted position, and to move from a retracted position to a deployed position so as to drive the solar generator 7 from the retracted position to the deployed position.

[0157] For example, the retraction / deployment device 8 may be configured to drive the section 72a of the columnar structure comprising the free end of the columnar structure, for example so as to drive the other sections.

[0158] For example, driving the section 72a of the columnar structure comprising the free end portion 700 of the columnar structure 72 drives some of the other sections 72b, 72e of the columnar structure nor in movement so as to allow the deployment or retraction of the solar generator 7.

[0159] For example, driving the section 72a, comprising the free end portion 700 of the columnar structure 72, drives some of the other sections 72b, ..., 72e so that they integrate into each other in the section 72f of the columnar structure attached to the payload 3. This makes it possible to retract the solar generator 7.

[0160] For example, the section 72a of the columnar structure comprising the free end portion 700 of the columnar structure 72 drives some of the other sections 72b, 72e so that they deploy outside the section 72f of the columnar structure attached to the payload 3. This makes it possible to retract the solar generator 7.

[0161] For example, the retraction / deployment device 8 may comprise a first end portion 800 attached to the section 72a of the columnar structure comprising the free end 700 of the columnar structure 72.

[0162] For example, the retraction / deployment device 8 may include a second end portion 80 attached to the payload 3.

[0163] For example, the retraction / deployment device 8 is arranged in the hollow of the columnar structure 72.

[0164] For example, the columnar structure 72 of the solar generator extends around the retraction / deployment device 8.

[0165] As illustrated in Figures 3 to 6, the retraction / deployment device 8 may be a pantograph.

[0166] In the example illustrated in Figures 7 to 11, a plurality of photovoltaic panels 750 on each of the faces is retractable between the first position of the solar generator, i.e. the position in which the generator is retracted, in which the photovoltaic panels 750 are grouped and extend horizontally one under the other in horizontal planes P (Figure 11), and the second position of the solar generator, i.e. the position in which the generator is deployed, in in which the photovoltaic panels are deployed and extend vertically under each other in the same vertical plane V so that the plurality of faces forms the columnar structure 72 (figure 7).

[0167] For example, the photovoltaic panels 750 of each of the faces are retractable, for example each panel is retractable, between the first position of the solar generator, i.e. the position in which the generator is retracted, in which the photovoltaic panels 750 are grouped and extend horizontally one under the other in horizontal planes P (figure 11), and the second position of the solar generator, i.e. the position in which the generator is deployed, in which the photovoltaic panels 72 are deployed and extend vertically one under the other in the same vertical plane V so that the plurality of faces forms the columnar structure 72 (figure 7).

[0168] By grouped photovoltaic panels, we mean that the photovoltaic panels are grouped together one under the other, stacked one under the other, so as to have the minimum possible space requirement. In this configuration, the photovoltaic panels are grouped together in their entirety near the payload support 3. This configuration, called the storage position, is particularly advantageous during takeoff of the aerostat because it reduces the risk of impact with the operators working around the aerostat during its takeoff.

[0169] By deployed photovoltaic panels we mean that the photovoltaic panels extend below each other in the same vertical plane "V".

[0170] According to this configuration, the lateral faces, each comprising a plurality of photovoltaic panels, form the columnar structure 72.

[0171] When the surface of the columnar structure is modular, the number of side faces and / or the number of solar panels can be modified by adding or removing one or more side faces and / or solar panels.

[0172] The electrical energy produced by exposing the photovoltaic cells to the sun during the day is discharged into batteries of the payload components at night. For this purpose, the aerostat includes electromechanical interconnections configured to routed the electrical energy produced by the photovoltaic panels to the devices requiring energy from the payload. For example, the aerostat may include electrical cables for carrying electrical energy from the photovoltaic panels to the batteries on board the payload (not shown). The electrical cables are routed from the photovoltaic panels to the payload. The electrical cables may be flexible so as not to hinder the retraction and deployment of the photovoltaic panels. For example, the electrical cables are made of silicone. This embodiment with the retractable photovoltaic panels facilitates the electrical connection between the photovoltaic panels.

[0173] The retraction / deployment device 8 configured to cause the retraction / deployment of the solar generator 7 as previously described may also be used to deploy and retract the solar generator 7 according to the present example.

[0174] The difference lies in the fact that the retraction / deployment device 8 further comprises a first ring 850 fixed to the first end portion 800 of the device and a second ring 85 fixed to the second end portion 80 of the device (Figures 9 and 10). Each of the faces, for example each end of the faces, is fixed to both rings. For example, for each face, one of the panels 750, forming the first end of each lateral face, is fixed to the first end portion 800 of the retraction / deployment device 8 via the first ring 850 and another of the panels, forming the second end of each lateral face, is fixed to the second end portion 80 of the retraction / deployment device 8 via the second ring 85.

[0175] For example, the retraction / deployment device 8 may be configured to drive the panel, forming the first end of each side face, attached to the first end portion 800.

[0176] For example, driving said panel 750 drives the other panels 750 of each side face in movement so as to allow the deployment or retraction of the solar generator 7.

[0177] The dimensions of the first crown 850 and the second crown 85 can be chosen according to the number of side faces used to form the columnar structure.

[0178] The aerostat 1 may comprise a control device 9 (not visible) for the solar energy generator 7. The control device 9 is configured to allow the solar generator 7 to be remotely switched from the deployed position to the retracted position, and vice versa.

[0179] In the examples described above, the surface area of ​​the columnar structure 72 of the solar generator can be modulated according to the energy requirement. The solar generator 7 can also be deployed, for example by means of the retraction / deployment device 8, according to the energy requirement. For example, the control device 9 can be configured to trigger the transition of the solar generator 7 from the retracted position to the deployed position so that the solar generator 7 is deployed in part or in full according to the energy requirement.

[0180] In the example illustrated in Figures 3 to 5, the control device 9 can be configured so that the retraction / deployment device drives certain sections in the deployed position only, for example. In the example illustrated in Figures 7 to 11, the control device 9 can be configured so that the retraction / deployment device drives certain photovoltaic panels in the deployed position only, for example.

[0181] The aerostat may comprise a rotating device 11 configured to drive the payload 3 in rotation about a vertical axis “A”, passing for example through a center of the payload 3. For example, the rotating device 11 is configured to drive the payload 3 in rotation through 360° about the vertical axis “A”. The rotation is illustrated in FIG. 1 by the arrows F.

[0182] The expression “vertical” will be used without limitation in reference to Figure 1.

[0183] According to the present disclosure, the rotating device 11 is configured to orient the payload 3 towards a chosen direction, for example observation. The rotation of the payload 3 can cause the rotation of the solar generator 7 when the solar generator is attached to the payload.

[0184] Alternatively, the aerostat may be devoid of a rotating device 11. In this case, an uncontrolled rotation of the payload 3 will cause a rotation of the solar energy generator 7, the shape of which may, for example, make it possible to maintain the illumination of the photovoltaic cells 74, for example in the presence of the columnar structure 72.

[0185] In operation, the aerostat 1 initially placed on a surface of the earth is raised into the atmosphere by means of the inflatable body filled with gas lighter than the gas of the atmosphere.

[0186] Take-off can, for example, be initiated by means of the auxiliary balloon 10 previously filled with gas lighter than the atmospheric gas.

[0187] During takeoff and as the aerostat ascends to altitude, the solar energy generator 7 is in the retracted position (Figure 2). The retracted position is maintained throughout the aerostat's ascent into the atmosphere, until arrival at the desired mission location.

[0188] The deployment of the solar generator can be triggered using the control device, for example.

[0189] The solar generator 7 can be rotated by rotating the payload 3 by means of the rotation device 11.

[0190] A few minutes before the end of the mission, the solar generator can be retracted using the steering device, for example.

[0191] The payload 3 and the solar generator 7 can be separated from the inflatable body 2 by means of the operation of the pyrotechnic separators 5. The payload 3 and the solar energy generator 7 can begin their return to the ground, for example by means of said at least one parachute.

Claims

Claims

1. Aerostat (1) intended to carry out transport and / or observation missions on a planet with an atmosphere, the aerostat comprising: an inflatable body (2) designed to be pressurized by a gas lighter than the atmosphere, a payload (3) configured to carry at least one scientific instrument, a solar energy generator (7) arranged between the inflatable body (2) and the payload (3).

2. Aerostat (1) according to claim 1 wherein the solar energy generator (7) comprises a columnar structure (72).

3. Aerostat (1) according to the preceding claim in which the solar energy generator (7) comprises a plurality of photovoltaic cells (74) arranged on an external surface of the columnar structure (72).

4. An aerostat (1) according to any preceding claim wherein the solar power generator (7) is movable between a first position in which the solar power generator (7) is retracted and a second position in which the solar power generator (7) is deployed.

5. An aerostat (1) according to claim 4 in combination with claim 2 wherein the solar energy generator (7) comprises a plurality of sections, one section (72a) of the plurality of sections having a diameter smaller than the diameter of another section (72f) of the plurality of sections such that the section (72a) can be arranged in the other section (72f) when the solar energy generator is retracted, the columnar structure comprising the plurality of sections when the solar energy generator (7) is deployed.

6. Aerostat (1) according to the preceding claim wherein the section (72a) comprises a first end portion (70) of the solar energy generator (7), the first end portion (70) being fixed to the payload (3) and the other section (72f) comprising a second end portion (700) of the solar energy generator (7), the second end portion (700) being free.

7. Aerostat (1) according to claim 4 in combination with claim 2 wherein the solar generator (7) comprises a plurality of lateral faces (75a,...,75h), each lateral face comprising a plurality of photovoltaic panels (750) retractable between the first position in which the photovoltaic panels (750) are grouped and extend horizontally one under the other in horizontal planes (P), and the second position in which the photovoltaic panels (750) are deployed and extend vertically one under the other in the same vertical plane (V) so that the columnar structure comprises the lateral faces (750).

8. Aerostat (1) according to any one of the preceding claims wherein the aerostat (1) comprises a rotating device (11) configured to drive the payload (3) in rotation about a vertical axis (A).

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