Power distribution spacecraft and associated method

Description

[0001] This description relates to the distribution of electrical energy by a spacecraft. It also relates to a method of distributing electrical energy using such a spacecraft. ETAT DE LA TECHNIQUE

[0002] Today, space missions are planned to supply electrical energy to a client vehicle at a point in free space, in orbit or on a celestial body.

[0003] Depending on the mission requirements and the position of the client spacecraft to be supplied with electricity, it is necessary to implement several separate systems in order to bring a solar electrical energy generator to a position of a client spacecraft and supply it with electrical energy. In the case of the most complex missions, it is necessary to provide a launch system intended to bring the solar electrical energy generator into space, an orbit transfer and / or circularization system in space to ensure the transit in space of the solar electrical energy generator and a descent system ensuring the descent of the solar electrical energy generator onto a celestial body.

[0004] For example, in the case of a mission dedicated to the distribution of electrical energy to a client spacecraft located in free space or in orbit, the solar electrical energy generator is loaded onto a spacecraft equipped with an orbit transfer and / or circularization system. The spacecraft, previously placed in Earth orbit, brings the solar electrical energy generator to the client spacecraft. The solar electrical energy generator can then be separated from the orbit transfer and / or circularization system to be connected to the client spacecraft in order to distribute electrical energy until its mission duration is reached, without being able to be used for the purposes of new missions.

[0005] In another example of a mission, the solar electric power generator, also previously placed in Earth orbit, may be intended to distribute electrical energy to a client spacecraft located on a celestial body. For this purpose, the solar electric power generator may be embarked as a payload on a descent system allowing the landing of the solar electric power generator on the celestial body. Once on the ground, the solar electric power generator may be disembarked from the landing system to be connected to the client spacecraft and distribute electrical energy until reaching its mission duration, also without being able to be used for the purposes of new missions.

[0006] In all cases of one-off missions, the solar electric power generators currently in use are intended to carry out missions of distributing electric power to a client spacecraft located at a point in free space, in orbit and / or on a celestial body and cannot be used for other electric power distribution missions. As a result, in existing missions, the operational area covered for the distribution of electric power is limited.

[0007] Furthermore, the use of several separate systems, including a launch system, an orbit transfer and / or circularization system in space, and a descent system, requires the use of high-mass equipment, making such electrical power distribution missions expensive.

[0008] Furthermore, the fuel containers intended for these missions or payloads to be brought to the same customer vehicle to be supplied with electrical energy or on site can be put into Earth orbit by launchers separate from the launcher intended for placing the solar electrical energy generator into Earth orbit. The need for launchers is therefore increased.

[0009] Furthermore, solar electric power generators have the disadvantage of providing a small amount of electrical energy (a few kW) to the customer machine they are intended to power. RESUME

[0010] It is desirable to address at least one of the above drawbacks by providing a spacecraft that can perform multiple electrical power distribution missions during its lifetime.

[0011] It may also be desirable to carry out high-power electrical energy distribution missions.

[0012] It may also be desirable to reduce the cost of electrical power distribution missions.

[0013] It may also be desirable to reduce the need for Earth-orbiting launchers for such missions.

[0014] It may also be desirable to provide spacecraft with electrical power distribution to enable the carriage of payloads.

[0015] To this end, one embodiment provides a spacecraft for distributing electrical energy to client vehicles, the spacecraft comprising: a main structure equipped with an electric thruster, a chemical thruster and a solar generator of electrical energy, with variable geometry, at least one first fuel container intended for the electric thruster, and at least one second fuel container intended for the chemical thruster, and wherein: the spacecraft is modular to removably couple the main structure to the first container to supply fuel to the electric thruster, or to the second container to supply fuel to the chemical thruster, and to removably couple the first container and the second container to each other,the solar electric power generator is configured to be: deployed to distribute electric power to a first client spacecraft located at a first point in free space, in orbit or on a first celestial body, and to move the spacecraft to a second client spacecraft located at a second point in free space, in orbit or on a second celestial body, and retracted to perform docking phases with the first or second client spacecraft in free space or in orbit, as well as landing phases towards a third celestial body and takeoff from the third celestial body for a return to orbit. By "electric thruster" is meant an electric propulsion assembly comprising one or more motor(s).,

[0016] “Chemical propellant” means a chemical propulsion system comprising one or more engines.

[0017] By "retracted to allow movement of the spacecraft to another client spacecraft" we mean that the movement includes, among other things, docking phases on the other client spacecraft and descent phases.

[0018] Such a spacecraft has the advantage of combining several functions in a single spacecraft, namely: launching the spacecraft into space from a celestial body using the chemical propellant, transferring and / or circularizing the craft into space, as well as distributing electrical energy to the client craft to which it is brought, and distributing electrical energy to the client craft using the solar electrical energy generator.

[0019] By "removably coupled" is meant, for example, a first element mechanically detached from a second element to be mechanically attached to a third element. The intermediate state between the detachment and the attachment of the first element corresponds to a transient state in which the first element is mechanically detached from the second element and the third element.

[0020] The combination of these functions allows the distribution of electrical energy at any point to client devices located at different points in free space, in orbit and / or on a celestial body.

[0021] Thus, such a spacecraft can be designed to successively carry out several missions of distributing electrical energy to client vehicles located in free space, in orbit or on a celestial body, and this autonomously.

[0022] For example, such a spacecraft may perform a first mission of distributing electrical energy in free space or in orbit to a first client spacecraft before performing a second mission of distributing electrical energy on a celestial body to a second client spacecraft. The invention is of course not limited to this example mission and may be used in any combination of missions exploitable by the invention, for example, a first mission of distributing electrical energy to a client spacecraft located on a celestial body such as the Moon, followed by a second mission of distributing electrical energy to another client spacecraft located on another celestial body.

[0023] The main structure comprising the electric thruster, the chemical thruster and the variable geometry solar electric power generator form an integrated functional unit.

[0024] However, it may be possible to provide that the electric thruster can be decoupled from the main structure for replacement.

[0025] Client vehicles can be, for example, inhabited infrastructures, production infrastructures, research infrastructures (microgravity), computing centers, heavy assembly equipment.

[0026] It will be understood that the chemical propellant allows the landing and placing in orbit of the main structure on or from a celestial body other than Earth.

[0027] It will be understood that the electric thruster allows the transit in free space or in orbit of the main structure.

[0028] A celestial body is a body distinct from Earth and with a ground such as a planet, a moon or an asteroid.

[0029] The chemical propellant can be a monopropellant or a dipropellant.

[0030] The fuel contained in the first container is preferably monopropellant or dipropellant.

[0031] Preferably, the electric thruster may be a grid ion engine thruster or a Hall current thruster.

[0032] The fuel of the electric thruster is preferably an inert gas, even more preferably a monatomic gas such as Xenon, Argon or Krypton. According to one embodiment, the solar electric energy generator comprises flexible photovoltaic cells configured to be wound and unwound around the same axis.

[0033] According to one embodiment, the variable geometry solar electric energy generator comprises at least two flexible photovoltaic cells or canvas which can be folded and unfolded relative to the same axis.

[0034] Documents FR 2 998 876 and FR 3 024 227 describe the use of such flexible photovoltaic cells or flexible fabrics. As described in these documents, such a flexible fabric can be rolled up or unrolled using a deployable structure or device as described in these documents. For this purpose, the deployable structure or device and its method, if applicable, can be associated with the present spacecraft. Document US2012000575 A1 discloses a transfer of electrical energy between two spacecraft. Document US2019248515 A1 discloses a modular spacecraft according to the art of the art.

[0035] In this description, the term "rolled up" means a retracted state and the term unrolled means an extended state.

[0036] According to one embodiment, the spacecraft comprises a carrier structure for carrying a payload, the carrier structure being configured to be coupled and decoupled to the first container and the second container.

[0037] According to one embodiment, the solar electrical energy generator is equipped with a means of transferring electrical energy by wire and / or by short distance waves and / or by laser.

[0038] Optionally, the wired electrical power transfer means can be connected to the client craft using a robotic arm or manually by an astronaut.

[0039] According to one embodiment, the main structure comprises at least a third fuel container for the chemical propellant to enable the spacecraft to return to orbit from a celestial body.

[0040] The at least one third container forms a fuel reserve allowing the spacecraft to take off again from the celestial body.

[0041] Such a third container can be attached to the main structure and coupled to the spacecraft to supply fuel to the chemical propellant to ensure the spacecraft is put into orbit from the celestial body.

[0042] Of course, the fuel contained in this third container is preferably monopropellant or dipropellant.

[0043] According to one embodiment, the main structure comprises docking means configured to couple the spacecraft to a client craft.

[0044] Such docking means allow the spacecraft to be stabilized at the client craft to facilitate the distribution of electrical power to a client craft located in orbit or in free space.

[0045] According to one embodiment, the main structure comprises landing means configured to enable the spacecraft to land on a celestial body. According to one embodiment, the spacecraft comprises fuel transfer means for refueling the spacecraft.

[0046] For example, a refueling cargo ship could be provided to refuel the spacecraft using fuel transfer means.

[0047] Such means of refueling can be formed by connectors and distribution conduits.

[0048] Such fuel transfer means may be provided to refuel the spacecraft with fuel for chemical propulsion or electric propulsion. Embodiments may also relate to a method for distributing electrical energy to at least one client craft (2) located at a point in free space, in orbit or on a celestial body, using a spacecraft as defined above, comprising a step of transiting the spacecraft previously placed in orbit, to a client craft located in free space, in orbit or on another celestial body, using the electric thruster and the solar electrical energy generator deployed after the spacecraft has been placed in orbit.

[0049] According to one embodiment, the method comprises steps of: docking the spacecraft with a client craft located in free space or in orbit; and distributing the electrical energy produced by the solar electrical energy generator to the client craft.

[0050] According to one embodiment, the method comprises steps of: placing the spacecraft into orbit around the celestial body; retracting the solar electric power generator; decoupling the first container from the main structure; coupling the main structure to the second container; decoupling the first container from the second container; landing the spacecraft on the ground of the celestial body; deploying the solar electric power generator; and distributing the electric power generated by the solar electric power generator to a client spacecraft on the celestial body.

[0051] According to one embodiment, the spacecraft comprises the previously defined carrier structure carrying a payload, in this case, the method comprises a step of unloading the main structure on site of the client craft or to supply the client craft with supplies.

[0052] The supporting structure is advantageously arranged between the first container and the second container.

[0053] According to one embodiment, in the case of a continuation of a mission to distribute electrical energy to another client spacecraft, the method comprises steps of: retracting the solar electrical energy generator; filling the second container or alternatively coupling the at least one third container to the main structure to supply fuel to the chemical propellant; and takeoff to bring the spacecraft into orbit around the celestial body.

[0054] According to one embodiment, the method comprises steps of: decoupling a third container from the main structure; refueling, in orbit or in free space, for the electric thruster and the chemical thruster, and transit of the spacecraft to a client craft.

[0055] The refueling step may consist of refueling the first container and / or the second container with fuel or alternatively, equipping the spacecraft with another first container and another second container pre-filled with fuel. It will be understood that in the case of refueling the first container and / or second container, the latter will have been previously recovered.

[0056] According to other characteristics of this second embodiment, the method comprises a step of transiting the spacecraft to another client craft located in free space, in orbit or on a celestial body using at least the electric thruster and using the solar electric energy generator deployed after its placement in orbit.

[0057] Embodiments may also relate to a spacecraft for distributing electrical energy to client vehicles at points in free space, in orbit and / or on a celestial body, the spacecraft comprising: a main structure equipped with an electric thruster, a chemical thruster and a variable geometry solar electric energy generator, at least one first fuel container for the electric thruster, at least one second fuel container for the chemical thruster, the spacecraft being modular in order to couple: the main structure alternately to the at least one first container for supplying fuel to the electric thruster or to the at least one second container for supplying fuel to the chemical thruster, the at least one first container and the at least one second container being able to be coupled / decoupled from each other,the variable geometry solar electric power generator being intended to be: deployed to ensure the distribution of electric power to a client spacecraft located at a point in free space, in orbit or on a celestial body, and to move the spacecraft towards another client spacecraft located at another point in free space, in orbit or on another celestial body, retracted to carry out docking phases in free space or in orbit, as well as landing phases towards a celestial body and take-off from a celestial body for a return to orbit.,

[0058] According to one embodiment, the variable geometry solar electric energy generator comprises flexible photovoltaic cells which can be wound and unwound around the same axis.

[0059] According to one embodiment, the solar electrical energy generator is equipped with a means of transferring electrical energy by wire and / or by short distance waves and / or by laser.

[0060] According to one embodiment, the spacecraft comprises a carrier structure for carrying a payload, the carrier structure being designed to be coupled / decoupled to the at least one first container and to the at least one second container.

[0061] According to one embodiment, the main structure comprises at least a third fuel container intended for the chemical propellant to ensure the ascent into orbit of the spacecraft from a celestial body.

[0062] According to one embodiment, the main structure comprises docking means for coupling the spacecraft to the client craft.

[0063] According to one embodiment, the main structure comprises landing means for ensuring the landing of the spacecraft on a celestial body. According to one embodiment, the spacecraft comprises fuel transfer means for ensuring the refueling of the spacecraft.

[0064] Embodiments may also relate to a method for distributing electrical energy to client vehicles at points located in free space, in orbit and / or on a celestial body to at least one client vehicle using a spacecraft as defined above, the spacecraft being previously placed in orbit, the method comprising a step of transiting the spacecraft to a client vehicle located in free space, in orbit or on a celestial body using at least the electric thruster and using the solar electrical energy generator deployed after it has been placed in orbit.

[0065] According to one embodiment, in the case of a client spacecraft in free space or in orbit, the method comprises: a step of docking the spacecraft with the client spacecraft; a step of distributing the electrical energy produced by the solar electrical energy generator to the client spacecraft.

[0066] According to one embodiment, in the case of a client spacecraft on a celestial body, the method comprises: a step of placing the spacecraft into orbit around the celestial body; a step of retracting the solar electric power generator; a step of decoupling the first container from the main structure; a step of coupling the main structure to the second container; a step of decoupling the first container from the second container; a step of landing the spacecraft on the ground of the celestial body; and a step of deploying the solar electric power generator; a step of distributing the electric power generated by the solar electric power generator.

[0067] According to one embodiment, in the case of a continuation of a mission to distribute electrical energy to another client spacecraft, the method comprises: a step of retracting the solar electrical energy generator; a step of filling the second container or alternatively a step of coupling the at least one third container to the main structure for supplying fuel to the chemical propellant; a takeoff step to bring the spacecraft into orbit around the celestial body.

[0068] According to one embodiment, the method comprises: when the spacecraft is equipped with at least one third container, a step of decoupling the at least one third container from the main structure; a step of refueling in orbit or in free space with fuel for the electric thruster and the chemical thruster of the spacecraft, and a step of transiting the spacecraft to another client craft.

[0069] Other characteristics and advantages will appear on reading the following non-limiting description and the attached figures which schematically illustrate several embodiments. There figure 1 represents a schematic view of a spacecraft according to an embodiment equipped with a main structure, a first container, a structure carrying a payload and a second container, and mounted on a launcher for its placement in Earth orbit. The figure 2 represents the spacecraft placed in Earth orbit. The figure 3 represents the spacecraft in a stage of retraction of its solar electric power generator which it is carrying in preparation for landing on a celestial body. figure 4 represents the spacecraft in a stage of decoupling the main structure from the first container and its coupling to the second container in preparation for its landing on the celestial body. figure 5 represents a step of decoupling the first container from the payload in preparation for its landing on the celestial body. figure 6 represents a step of reorientation of the spacecraft in preparation for its landing on the celestial body. The figure 7 represents a descent stage of the spacecraft for its landing on the ground of the celestial body. The figure 8 represents steps of unloading the spacecraft and distributing the electrical energy supplied by the solar electric power generator to a client spacecraft. The figure 9 represents stages of launching the spacecraft into orbit from the ground of the celestial body. The figure 10 represents steps to refuel the spacecraft before sending it to another customer spacecraft. figure 11 represents steps for refueling the spacecraft before sending it to another customer spacecraft according to an alternative embodiment. The figure 12 is an enlarged isometric view of the main structure of the spacecraft including a solar electric power generator in the retracted position, according to one embodiment. figure 13 is an enlarged view of the main structure of the spacecraft showing the solar electric power generator in the deployed position, according to one embodiment. figure 14 is a top view of the main structure of the spacecraft and the solar electric power generator in the deployed position, according to one embodiment. figure 15 is an enlarged top view of the main structure of the spacecraft shown in figure 14 . There figure 16 is an enlarged view from below of the main structure of the spacecraft shown in figure 14 .

[0070] To the figure 1 , a spacecraft 1 is shown for distributing electrical energy to client craft 2 at points located in free space, in orbit and / or on a celestial body.

[0071] The spacecraft 1 comprises a main structure 10, at least a first fuel container 11, a payload-carrying structure 13 and at least a second fuel container 12 stacked and arranged in a single launcher 3.

[0072] Thus, the placing of spacecraft 1 into Earth orbit may require the needs of a single launcher 3.

[0073] The main structure 10 is equipped with the thrusters, namely an electric thruster 10A and a chemical thruster 10B.

[0074] Furthermore, the main structure 10 is equipped with a solar generator 10C of electrical energy forming an integral part of the main structure 10.

[0075] The first container 11 forms a fuel tank intended for electric propulsion. The fuel of the first container 11 may be an inert gas, preferably such as Xenon, argon or Krypton.

[0076] The second container 12 forms a fuel tank intended for chemical propulsion. The fuel of the second container 12 may be a monopropellant or a dipropellant, liquid and / or solid.

[0077] The supporting structure 13 is intended for carrying a payload intended for the client machine 2 or for the site of this client machine 2.

[0078] In particular, Spacecraft 1 has a modular configuration so that it can adapt to the needs of several consecutive missions.

[0079] In this case, the supporting structure 13, the first container 11 and the second container 12 form a logistics stack and can be coupled or decoupled from each other.

[0080] The main structure 10 can alternatively be coupled / decoupled to the first container 11 or to the second container 12.

[0081] The arrangement of the supporting structure 13 disposed between the first container 11 and the second container 12 has the advantage of allowing the main structure 10 to be supplied with fuel for electric propulsion or for chemical propulsion.

[0082] Of course, the main structure 10 is equipped with a control unit allowing the transit of the spacecraft 1 and to enable these maneuvers.

[0083] When the main structure 10 is coupled to the first container 11, it allows the supply of fuel to the electric propellant 10A, whereas when it is coupled to the second container 12, it allows the supply of fuel to the chemical propellant 10B.

[0084] The control unit is configured to ensure the coupling and decoupling of the main structure 10 to one of the containers 11, 12 according to the mission requirements. In an initial configuration intended for placing the spacecraft 1 in Earth orbit, the main structure 10 is coupled to the first container 11 for the power supply of the electric propulsion, in order to allow transit in space once in Earth orbit.

[0085] The 10C solar array is variable geometry. In other words, it is designed to be deployed or retracted depending on mission needs.

[0086] In particular, the solar generator 10C is intended to be deployed to provide electrical power distribution to a client spacecraft 2 located at a point in free space, in orbit or on a celestial body, and retracted to enable the movement of the spacecraft 1 to another client spacecraft 2 located at another point in free space, in orbit or on another celestial body.

[0087] The 10C solar array may include flexible photovoltaic cells or a flexible web of photovoltaic cells that can be rolled and unrolled around a single axis, so that the unrolled cells cover a large area of ​​solar radiation. Thus, such photovoltaic cells can significantly increase the electrical energy production and distribution capacity of such a spacecraft 1.

[0088] We will now describe an example of successive missions implementing the spacecraft, according to one embodiment, to enable the distribution of electrical energy to client craft at points in free space, in orbit or on a celestial body.

[0089] The configuration of the figure 1 represents a spacecraft 1 arranged in a launcher 3 for its placement in Earth orbit from a launch site.

[0090] The spacecraft 1 as described above forms a stack that can fit in a single launcher 3. The second container 12 of the spacecraft 1 is coupled to a base 30 of the launcher 3 for the stable maintenance of the spacecraft 1 during its phase of placing in Earth orbit.

[0091] To the figure 2 , spacecraft 1 is shown in Earth orbit where it has been detached from the base 30 of launcher 3 and separated from launcher 3.

[0092] Once placed in Earth orbit, the 10C solar array can be deployed.

[0093] A step of transferring the spacecraft 1 to a client craft 2 can then be initiated using electric propulsion powered by the electrical energy provided by the deployed solar generator 10C and by the fuel from the first container 11 to which the main structure 10 is coupled.

[0094] In a configuration of a first mission intended to distribute electrical energy to a first client machine 2 (cf. figure 8 ) in free space or in orbit, docking means may be provided to couple the spacecraft 1 to the client craft 2.

[0095] The 10C solar generator is equipped with a means of transferring electrical energy by wire and / or short-distance waves and / or laser and can, once deployed, distribute electrical energy to the client machine 2.

[0096] It can be expected that during the docking phase the 10C solar generator will be retracted and deployed once this phase is completed.

[0097] Spacecraft 1 can then carry out an electrical energy distribution mission following the one it has just completed.

[0098] In this case, it can be directed towards a celestial body such as the Moon on which a second client 2 device is placed on the ground.

[0099] In this case, spacecraft 1 is first put into orbit around the celestial body containing the second client spacecraft 2.

[0100] Then, as illustrated by the figure 3 , the 10C solar electric power generator is retracted to prepare for the landing phase of spacecraft 1 on the ground of the celestial body.

[0101] For this purpose, the spacecraft comprises landing means configured to ensure the landing phase. For example, the spacecraft comprises landing gear 16 (cf. figure 6 ).

[0102] As represented in the figure 4 , the main structure 10 is then decoupled from the first container 11 and it is controlled to allow its coupling to the second container 12. Then, the first container 11 can be decoupled from the second container 12 ( figure 5 ). The spacecraft 1 thus modulated comprises the carrying structure 13 of the payload coupled to the second container 12. It is suitable for carrying out a landing phase of the spacecraft 1 on the ground of the celestial body since it now allows the use of chemical propulsion.

[0103] There figure 6 illustrates the reorientation of spacecraft 1 in orbit to prepare for its exit from orbit and landing on the celestial body and the figure 7 illustrates the landing phase of spacecraft 1 on the celestial body.

[0104] Spacecraft 1 illustrated by the figures 6 And 7 includes landing gear 16 in the open position.

[0105] As represented in the figure 8 , once on the ground, the spacecraft 1 can be unloaded from the second container 12 and from the supporting structure 13 comprising the payload to the site where the client craft 2 is located.

[0106] The 10C solar power generator can then be deployed for the distribution of electrical power to the client machine 2.

[0107] Spacecraft 1 can again carry out an electrical power distribution mission following the one it has just completed.

[0108] For example, it can be directed towards another celestial body on which a third client craft 2 is placed on the ground.

[0109] For this, the 10C solar generator is first retracted.

[0110] At least one third container 14 is provided which can be attached to the main structure 10 or can be supplied from the site on which the second client machine 2 is located.

[0111] There figure 9 illustrates the placing into orbit of the spacecraft 1 from the ground of the celestial body comprising the second client craft 2. When placing the spacecraft into orbit, the landing gear 16 closes in the retracted position. The main structure 10 previously separated from the supporting structure 13 and the second container 12 can then receive the third container 14 comprising a fuel for chemical propulsion.

[0112] The main structure 10 can then be supplied with fuel for chemical propulsion to enable the take-off of spacecraft 1 and its placement in orbit around the celestial body from which it takes off.

[0113] There figure 10 illustrates the preparation of spacecraft 1 for its continuation of its mission of distributing electrical energy to the destination of a third client spacecraft 2.

[0114] Once in orbit as previously described, the third container 14 is separated from the main structure 10. Then, the solar generator 10C is deployed. Finally, the main structure 10 can be coupled to another first container 11 of a new logistics stack planned for the next mission or alternatively fuel transfer means can ensure the refueling of the first container 11 and the second container 12 previously recovered.

[0115] The new logistics stack may be similar to the initial configuration, namely: a first container 11, a second container 12 and a supporting structure 13 arranged between the two containers 11, 12. Then the newly formed spacecraft 1 may be driven towards the third client craft 2 on the second celestial body according to the steps previously described.

[0116] In one embodiment illustrated by the figure 11 , the main structure 10 can be coupled to another first container 11 of fuel intended for the electric thruster only, intended for the following mission. A step of transferring the spacecraft 1 to a client craft 2 can then be initiated using the electric propulsion powered by the electrical energy provided by the deployed solar generator 10C and by the fuel of the first container 11 to which the main structure 10 is coupled.

[0117] THE figures 12 à 16 are views of the main structure 10 according to one embodiment.

[0118] There figure 12 represents the main structure 10 in orbit, in which the variable geometry solar power generator 10C is retracted. In the embodiment illustrated by the figure 12 , the 10C solar generator of electrical energy comprises two canvases each formed of one or more flexible photovoltaic cells, and which are each wound around the same axis.

[0119] The main structure 10 comprises the electric thruster or electric propulsion assembly comprising a plurality of electric motors 10A.

[0120] The main structure 10 comprises the electric thruster or chemical propulsion assembly comprising a plurality of chemical engines 10B.

[0121] The main structure 10 comprises a mooring and fuel transfer system 18 configured to provide coupling / decoupling between the main structure 10 and the fuel containers 11, 12, 14 in order to provide fuel transfer.

[0122] In the embodiment illustrated by the figure 12 , the landing gear is retracted to the stowed position (not visible).

[0123] There figure 13 illustrates the main structure 10 on the ground, for example placed on the ground of a celestial body in which the solar generator 10C of variable geometry electric energy is deployed.

[0124] In the embodiment illustrated by the figures 13 à 16 , the 10C solar electric power generator comprises two flexible photovoltaic cell canvases which are each unrolled.

[0125] The landing gear 16 is deployed, that is to say in the open position to ensure the landing of the main structure 10 and its maintenance on the ground of a celestial body (such as the Moon).

[0126] THE figures 14 et 15 are top views of the main structure 10 with the variable geometry solar power generator 10C deployed.

[0127] In the embodiment illustrated by the figures 12, 13 And 16 , the main structure 10 comprises an electric thruster comprising several electric motors 10A forming an electric propulsion assembly. The main structure 10 comprises an electric thruster comprising the chemical motors 10B forming a chemical propulsion assembly.

[0128] As illustrated by the figure 15 , the main structure 10 may comprise a rotating orientation device 20 for driving the solar generator 10C of electrical energy in rotation around a vertical or longitudinal axis A. For example, the rotating device 20 is configured to drive the rotation of the winding of photovoltaic cells through 360° around the longitudinal or vertical axis A.

[0129] The rotating device allows the position of the sun to be tracked and the photovoltaic cells to be oriented towards the sun.

[0130] In the embodiments illustrated by the figures 12 à 16 , the spacecraft includes an optional energy dissipation device. For example, the energy dissipation device includes two radiators 22', 22" which each extend over one half of the surface area of ​​the main structure 10 so as to provide the largest available surface area around the main structure 10.

[0131] Obviously, the present description is not limited to the examples which have just been described and numerous adjustments can be made to these examples without departing from the scope of the appended claims.

Claims

1. A spacecraft (1) for distributing electrical energy to client crafts (2), the spacecraft (1) comprising: a main structure (10) equipped with an electric thruster (10A), a chemical thruster (10B) and a solar electrical energy generator (10C), with variable geometry, at least one first fuel container (11) intended for the electric thruster (10A), and at least one second fuel container (12) intended for the chemical thruster (10B), and in which: the spacecraft (1) is modular to removably couple the main structure (10) alternately to the first container (11) for supplying fuel to the electric thruster (10A), or to the second container (12) for supplying fuel to the chemical thruster (10B), and to removably couple the first container (11) and the second container (12) to each other, the solar electrical energy generator (10C) is configured to be: deployed to distribute the electrical energy to a first client craft (2) located at a first point in the free space, in orbit or on a first celestial body, and to displace the spacecraft (1) to a second craft client (2) located at a second point in the free space, in orbit or on a second celestial body, and retracted to carry out mooring phases with the first or second client craft in the free space or in orbit, as well as phases of landing towards a third celestial body and taking-off from the third celestial body for a return to orbit.

2. The spacecraft (1) according to claim 1, wherein the solar electrical energy generator (10C) comprises flexible photovoltaic cells configured to be wound and unwound about a same axis.

3. The spacecraft (1) according to any one of claims 1 and 2, wherein the solar electrical energy generator (10C) is equipped with a means of transferring electrical energy by wire and / or by short distance waves and / or by laser.

4. The spacecraft (1) according to any one of claims 1 to 3, comprising a supporting structure (13) for carrying a payload, the supporting structure (13) being configured to be coupled and decoupled from the first container (11) and the second container (12).

5. The spacecraft (1) according to any one of claims 1 to 4, wherein the main structure (10) comprises at least one third fuel container (14) intended for the chemical thruster (10B) to allow the spacecraft (1) to go back into orbit from a celestial body.

6. The spacecraft (1) according to any one of claims 1 to 5, wherein the main structure (10) comprises docking means configured to couple the spacecraft (1) to a client craft (2).

7. The spacecraft (1) according to any one of claims 1 to 6, wherein the main structure (10) comprises landing means (16) configured to allow the spacecraft (1) to land on a celestial body.

8. The spacecraft (1) according to any one of claims 1 to 7, comprising fuel transfer means to ensure the refueling of the spacecraft (1).

9. A method for distributing electrical energy to at least one client craft (2) located at a point in the free space, in orbit or on a celestial body, using a spacecraft (1) according to any one of claims 1 to 8, comprising a step of transiting the spacecraft (1) previously placed in orbit, towards a client craft (2) located in the free space, in orbit or on a celestial body, by using the electric thruster (10A) and the solar electrical energy generator (10C) deployed after the spacecraft is placed into orbit.

10. The method according to claim 9, comprising steps of: docking the spacecraft (1) to a client craft (2) located in the free space or in orbit; and distributing the electrical energy produced by the solar electrical energy generator (10C) to the client craft (2).

11. The method according to any one of claims 9 and 10, comprising steps of: placing the spacecraft (1) into orbit around a celestial body; retracting the solar electrical energy generator (10C); decoupling the first container (11) from the main structure (10); coupling the main structure (10) to the second container (12); decoupling the first container (11) from the second container (12); landing the spacecraft (1) on the ground of the celestial body; deploying the solar electrical energy generator (10C); and distributing the electrical energy generated by the solar electrical energy generator (10C) to a client craft (2) on the celestial body.

12. The method according to any one of claims 9 to 11, wherein, in the case of a continuation of the mission of distributing electrical energy to another client craft, the method comprises steps of: retracting the solar electrical energy generator (10C); filling the second container (12), or alternatively coupling at least one third container (14) to the main structure (10) to supply fuel to the chemical thruster (10B); and taking-off to bring the spacecraft (1) into orbit around the celestial body.

13. The method according to any one of claims 9 to 12, comprising steps of: decoupling a third container (14) from the main structure (10); a refueling step, in orbit or in the free space, for the electric thruster (10A) and the chemical thruster (10B); and a step of transit of the spacecraft (1) to a client craft (2).