Electrically powered spacecraft and related methods

Abstract

The present invention relates to a spacecraft 1 for supplying electric energy to a client ship 2 located in free space, in orbit and / or on a celestial body, the spacecraft 1 comprising a main structure 10 having an electric thruster 10A, a chemical thruster 10B and a solar electric energy generator 10C, a first fuel container 11 for fuel for the electric thruster 10A and a second fuel container 12 for fuel for the chemical thruster 10B, the spacecraft 1 being such that the main structure 10 can alternatively be connected or separated to the first fuel container 11 or the second fuel container 12, the first fuel container 11 and the second fuel container 12 can be connected to or separated from each other, and the solar electric energy generator 10C is intended to be deployed or stored.

Description

[Technical field]

[0001] The present disclosure relates to the provision of electrical energy by a spacecraft and to a method of providing electrical energy using such a spacecraft. [Background technology]

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

[0003] Depending on the needs of the mission and the location of the client ship that is to be powered, several distinct systems must be implemented to bring the solar electric energy generator to the location of the client ship and to supply it with electrical energy. For the most complex missions, it is necessary to provide a launch system intended to bring the solar electric energy generator into outer space, a space transfer and / or orbital circulation system to ensure the passage of the solar electric energy generator through outer space, and a descent system to ensure the descent of the solar electric energy generator onto the celestial body.

[0004] For example, in the case of a mission dedicated to the supply of electrical energy to a client ship located in free space or in orbit, the solar electric energy generator is installed on board a spacecraft equipped with a transfer and / or orbital circulation system. A spacecraft previously placed in Earth orbit carries the solar electric energy generator to the client ship. The solar electric energy generator can then be separated from the transfer and / or orbital circulation system to be connected to the client ship to supply electrical energy until the mission duration is reached, even though it cannot be utilized for the purposes of the new mission.

[0005] In another example mission, a solar electric energy generator, also placed in Earth orbit, may be intended to supply electrical energy to a client ship placed on a celestial body. For this purpose, the solar electric energy generator may be embedded as an on-board device on a descent system that allows the solar electric energy generator to land on the celestial body. Once on the ground, the solar electric energy generator is lowered from the landing system to be connected to the client ship and can supply electrical energy until the mission period is reached, but also cannot be operated for the purpose of the new mission.

[0006] In all cases of one-off missions, the solar electric energy generators used today are intended to perform missions to supply electric energy to client ships located in free space, in orbit and / or at a point on a celestial body and cannot be used for other electric energy supply missions. As a result, existing missions have limited operational areas to cover for the supply of electric energy.

[0007] Furthermore, the use of several separate systems, notably the launch system, the space transport and / or orbital circulation system and the descent system, makes such electrical energy supply missions costly, without the need for the use of high mass equipment.

[0008] On the other hand, fuel containers planned for these missions, or payloads brought on board or on-site at the same client vessel to supply electrical energy, may be placed into Earth orbit by launchers different from those planned for placing the solar electrical energy generators into Earth orbit, thus increasing the need for launchers.

[0009] Furthermore, solar electric energy generators have the drawback of providing only small amounts of electrical energy (a few kW) to the client vessel that must be powered. [Prior art documents] [Patent documents]

[0010] [Patent Document 1] French Patent No. 2998876 [Patent Document 2] French Patent No. 3024227 Summary of the Invention [Problem to be solved by the invention]

[0011] It would be desirable to overcome at least one of the aforementioned drawbacks by providing a spacecraft capable of performing several electrical energy supply missions during its lifetime.

[0012] It may also be desirable to perform high power electrical energy supply missions.

[0013] It may also be desirable to reduce the cost of electrical energy supply missions.

[0014] It may also be desirable to reduce the need for Earth orbital launchers for such missions.

[0015] It may also be desirable to provide a spacecraft for supplying electrical energy that allows it to carry payload. [Means for solving the problem]

[0016] To this end, an embodiment provides a spacecraft for supplying electrical energy to a client vessel, the spacecraft comprising a main structure with an electric thruster, a chemical thruster and a solar electric energy generator with a variable geometry, at least one first fuel canister for the electric thruster and at least one second fuel canister for the chemical thruster, the spacecraft being adapted to removably couple the main structure to the first fuel canister for fueling the electric thruster or alternatively to removably couple the main structure to the second fuel canister for fueling the chemical thruster, the spacecraft being adapted to removably couple the first fuel canister and the second fuel canister. The present invention proposes a spacecraft that is modular, with a solar electric energy generator and a storage container detachably connected to each other, and that is configured to be deployed to supply electric energy to a first client ship located at a first point in free space, in orbit or on a first celestial body and to displace the spacecraft to a second client ship located at a second point in free space, in orbit or on a second celestial body, and to be stored in order to perform a mooring phase with the first client ship or the second client ship in free space or in orbit, as well as a landing phase towards a third celestial body and a take-off phase from the third celestial body for returning to orbit.

[0017] The term "electric thruster" means an electric propulsion unit that includes one or more motors.

[0018] The term "chemical thruster" means a chemical propulsion unit that includes one or more motors.

[0019] The term "retracted to allow a displacement of the spacecraft towards another client craft" means that the displacement includes, among other things, the mooring phase and the descent phase on the other client craft.

[0020] Such a spacecraft has the advantage of combining several functions in the same spacecraft: the launch of the spacecraft from a celestial body into space using chemical thrusters, the transportation and / or circulation of the craft in space and the supply of electrical energy to the client vessel which brings it in, and the supply of electrical energy to the client vessel using solar electrical energy generators.

[0021] The term "removably coupling" refers, for example, to a first element being mechanically detached from a second element to be mechanically attached to a third element. An intermediate state between the detachment and attachment of the first element corresponds to a transitional state in which the first element is mechanically detached from the second element and the third element.

[0022] The combination of these capabilities allows the supply of electrical energy at any point to client vessels located at different points in free space, in orbit and / or on celestial bodies.

[0023] Such a spacecraft can therefore be planned to carry out several missions in succession, autonomously supplying electrical energy to client craft located in free space, in orbit or on celestial bodies.

[0024] For example, such a spacecraft may perform a first mission to supply electrical energy in free space or in orbit to a first client vessel before performing a second mission to supply electrical energy on a celestial body to a second client vessel. The invention is naturally not limited to this mission example and may be used with any combination of missions available according to the invention, such as a first mission to supply electrical energy to a client vessel located on a celestial body, such as the Moon, followed by a second mission to supply electrical energy to another client vessel located on another celestial body.

[0025] The main structure, comprising the electric thrusters, the chemical thrusters and the solar electric energy generators with variable geometry, forms an integrated functional assembly.

[0026] Nonetheless, provision can be made for the electric thrusters to be separated from the main structure for replacement.

[0027] Client vessels may be, for example, residential infrastructure, production infrastructure, research infrastructure (microgravity), computing centers, heavy assembly means.

[0028] It will be appreciated that chemical thrusters may enable the main structure to be landed on a celestial body other than Earth, or to be placed into orbit from a celestial body.

[0029] It will be appreciated that the electric thrusters enable the main structure to pass in free space or in orbit.

[0030] Celestial body refers to a celestial body other than the Earth that has a terrestrial surface, such as a planet, moon, or asteroid.

[0031] The chemical thruster may be a monopropellant or a multipropellant thruster.

[0032] The fuel contained within the first fuel container is preferably monopropellant or polypropellant.

[0033] Preferably, the electric thruster may be a gridded ion motor thruster or a Hall current thruster.

[0034] The fuel for an electric thruster is preferably an inert gas, more preferably a monatomic gas such as xenon, argon or krypton.

[0035] According to one embodiment, a solar electric energy generator comprises flexible photovoltaic cells configured to be wound and unwound about the same axis.

[0036] According to one embodiment, a solar electric energy generator with variable geometry comprises at least two photovoltaic cells or flexible canvas that can be folded and unfolded about the same axis.

[0037] Patents FR 2998876 and FR 3024227 disclose the use of said flexible photovoltaic cells or said flexible canvas, which as described in these patents can be rolled up or unrolled using a deployable structure or device as described in these patents.

[0038] No. 6,293,963 and U.S. Patent Application Publication No. 2005 / 013,906, both of which are incorporated herein in their entirety. As such, the deployable structures or apparatus and methods thereof may be related to current spacecraft, where applicable.

[0039] As used herein, the term "wound" refers to the stowed state and the term "unwound" refers to the deployed state.

[0040] According to one embodiment, a spacecraft includes a support structure for carrying payload, the support structure configured to be coupled to and decoupled from the first and second fuel canisters.

[0041] According to one embodiment, the solar electric energy generator comprises means for transmitting electrical energy by wire and / or by short range wave and / or by laser.

[0042] Optionally, a wired means of electrical energy transfer may be connected to the client vehicle using a robotic arm or manually by the astronaut.

[0043] According to one embodiment, the main structure comprises at least one third fuel canister for a chemical thruster to enable the spacecraft to return to orbit from the celestial body.

[0044] At least one third fuel container forms a fuel reserve that enables the spacecraft to take off again from the celestial body.

[0045] The third fuel canister may be attached to the main structure to ensure that the spacecraft is placed into orbit from the celestial body, and may be coupled to the spacecraft to fuel the chemical thrusters.

[0046] Of course, the fuel contained in this third fuel container is preferably monopropellant or polypropellant.

[0047] According to one embodiment, the main structure comprises mooring means configured to couple the spacecraft to a client vessel.

[0048] The mooring means allows the spacecraft to be stabilized on the client ship to facilitate the supply of electrical energy to the client ship located in orbit or in free space.

[0049] According to one embodiment, the main structure comprises landing means configured to enable the spacecraft to land on a celestial body.

[0050] According to one embodiment, the spacecraft is equipped with fuel transfer means to ensure refuelling of the spacecraft.

[0051] For example, plans can be made for refueling cargo ships to ensure refueling of spacecraft using fuel transfer means.

[0052] The refuelling means may be formed by a connector and a supply conduit.

[0053] The fuel transfer means may be provided for refuelling a spacecraft for chemical or electric propulsion.

[0054] Some embodiments may also relate to a method for supplying electrical energy to at least one client ship located at a point in free space, in orbit, or on a celestial body using the above-mentioned spacecraft, the method comprising passing the orbited spacecraft toward a client ship located in free space, in orbit, or on another celestial body using the electric thrusters and the solar electric energy generators deployed after the spacecraft is placed in orbit.

[0055] According to one embodiment, the method comprises the steps of mooring a spacecraft to a client ship located in free space or in orbit, and supplying the client ship with electrical energy generated by a solar electric energy generator.

[0056] According to one embodiment, the method comprises the steps of: placing the spacecraft into orbit around the celestial body; storing a solar electric energy generator; Separating the first fuel container from the main structure; coupling the main structure to a second fuel container; separating the first fuel container from the second fuel container; landing the spacecraft on the surface of the celestial body; deploying a solar electric energy generator; and supplying electrical energy generated by the solar electric energy generator to a client vessel on the celestial body.

[0057] According to one embodiment, the spacecraft comprises a support structure as defined above carrying onboard equipment, in which case the method comprises a step of offloading the main structure at the location of the client ship or providing refuelling to the client ship.

[0058] The support structure is advantageously located between the first and second fuel containers.

[0059] According to one embodiment, when continuing the electrical energy supply mission to another client ship, the method comprises the steps of storing the solar electric energy generator, filling a second fuel canister, or alternatively, coupling at least one third fuel canister to the main structure for supplying fuel to the chemical thrusters, and lifting off the spacecraft into orbit around the celestial body.

[0060] According to one embodiment, the method includes separating a third fuel container from the main structure, refueling on-orbit or in free space for the electric and chemical thrusters, and passing the spacecraft to the client vehicle.

[0061] The refueling step may consist of refueling the first fuel container and / or the second fuel container, or alternatively, equipping the spacecraft with another first fuel container and another second fuel container pre-filled with fuel.

[0062] It will be appreciated that when refueling the first fuel container and / or the second fuel container, these fuel containers have been previously collected.

[0063] According to another feature of this second embodiment, the method includes passing the spacecraft to another client vehicle located in free space, in orbit, or on a celestial body using at least electric thrusters and using solar electric energy generators that are deployed after being placed in orbit.

[0064] Some embodiments also provide a spacecraft for supplying electrical energy to a client ship at a location in free space, in orbit and / or at a location on a celestial body, the spacecraft comprising a main structure with an electric thruster, a chemical thruster and a solar electric energy generator having a variable geometry, at least one first fuel canister for the electric thruster and at least one second fuel canister for the chemical thruster, the spacecraft coupling the main structure to the first fuel canister for fueling the electric thruster or coupling the main structure to the second fuel canister for fueling the chemical thruster. A modular, variable-geometry solar electric energy generator alternatively connected to the second fuel container, the first fuel container and the second fuel container being capable of being connected to each other or separated from each other, may relate to a spacecraft intended to be deployed to power a client craft located at a point in free space, in orbit or on a first celestial body, to displace the spacecraft to another client craft located at another point in free space, in orbit or on a second celestial body, and to be stored to perform a landing phase towards the celestial body and a take-off phase from the celestial body for returning to orbit.

[0065] According to one embodiment, a solar electric energy generator having variable geometry comprises flexible photovoltaic cells that can be wound and unwound about the same axis.

[0066] According to one embodiment, the solar electric energy generator comprises means for transmitting electrical energy by wire and / or by short range wave and / or by laser.

[0067] According to one embodiment, the spacecraft comprises a support structure for carrying payload, the support structure being intended to be coupled to or separated from at least one first fuel canister and at least one second fuel canister.

[0068] According to one embodiment, the main structure comprises at least one third fuel canister for a chemical thruster to ensure the lift-off of the spacecraft from the celestial body into orbit.

[0069] According to one embodiment, the main structure comprises mooring means for connecting the spacecraft to a client vessel.

[0070] According to one embodiment, the main structure comprises landing means for landing the spacecraft on a celestial body.

[0071] According to one embodiment, the spacecraft comprises a fuel transfer means for refuelling the spacecraft.

[0072] Some embodiments may also relate to a method for supplying electrical energy to a client ship at a point in free space, on orbit and / or on a celestial body using a spacecraft as defined above previously placed in orbit, the method comprising passing the spacecraft towards the client ship in free space, on orbit or on a celestial body using at least electric thrusters and solar electric energy generators deployed after placement in orbit.

[0073] According to one embodiment, when the client vessel is in free space or in orbit, the method comprises a step of mooring a spacecraft to the client vessel and supplying the client vessel with electrical energy generated by a solar electric energy generator.

[0074] In one embodiment, when the client ship is on a celestial body, the method includes the steps of placing the spacecraft into orbit around the celestial body, storing a solar electric energy generator, separating a first fuel container from a main structure, coupling the main structure to a second fuel container, separating the first fuel container from the second fuel container, landing the spacecraft on a ground surface of the celestial body, deploying a solar electric energy generator, and supplying electrical energy generated by the solar electric energy generator.

[0075] According to one embodiment, if the mission continues to supply electrical energy to other client vessels, the method comprises the steps of storing the solar electric energy generator, filling a second fuel canister, or alternatively, coupling at least one third fuel canister to the main structure for fueling a chemical thruster, and taking off to place the spacecraft into orbit around the celestial body.

[0076] According to one embodiment, the method includes, if the spacecraft comprises at least one third fuel container, separating the at least one third fuel container from the main structure, refueling on-orbit or in free space for the spacecraft's electric and chemical thrusters, and passing the spacecraft to another client vessel.

[0077] Other features and advantages will become apparent from reading the following non-limiting description and the attached figures which show, in schematic form, some embodiments. [Brief description of the drawings]

[0078] [Figure 1] FIG. 1 shows a schematic diagram of a spacecraft according to an embodiment, comprising a main structure, a first fuel container, a support structure for payloads, and a second fuel container mounted on a launcher intended for placement in Earth orbit. [Diagram 2] FIG. 2 shows a spacecraft in Earth orbit. [Diagram 3] FIG. 3 represents a spacecraft carrying a solar electric energy generator, intended for landing on a celestial body, during a step of storing the solar electric energy generator. [Figure 4] FIG. 4 represents a spacecraft intended for landing on a celestial body, during a step of separating the main structure from the first fuel canister and connecting it to the second fuel canister. [Diagram 5] FIG. 5 represents a spacecraft intended for landing on a celestial body, during a step of separating the first fuel canister from its payload. [Figure 6]FIG. 6 illustrates the steps of orienting a spacecraft for landing on a celestial body. [Figure 7] FIG. 7 illustrates the steps of descending a spacecraft in order for it to land on the surface of a celestial body. [Figure 8] FIG. 8 represents the steps of offloading the spacecraft and supplying the client vessel with electrical energy provided by a solar electric energy generator. [Figure 9] Figure 9 shows the steps involved in launching a spacecraft from the ground of a celestial body into orbit. [Figure 10] FIG. 10 illustrates the steps of refueling a spacecraft before sending it to another client vessel. [Figure 11] FIG. 11 represents, according to a variant, the step of refueling a spacecraft before sending it to another client ship. [Figure 12] FIG. 12 is an enlarged isometric view of the main structure of the spacecraft with the solar electric energy generator in a stowed position, according to one embodiment. [Figure 13] FIG. 13 is a close-up view of the main spacecraft structure showing the solar electric energy generators in a deployed position, according to one embodiment. [Figure 14] FIG. 14 illustrates a top view of the main spacecraft structure and solar electric energy generator in a deployed position, according to one embodiment. [Figure 15] FIG. 15 is an enlarged top view of the main structure of the spacecraft shown in FIG. [Figure 16] FIG. 16 is an enlarged bottom view of the main structure of the spacecraft shown in FIG. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0079] In FIG. 1 a spacecraft 1 is shown for supplying electrical energy to a client vessel 2 at a point located in free space, in orbit and / or on a celestial body.

[0080] The spacecraft 1 comprises a main structure 10, at least one first fuel container 11, a support structure 13 for payloads, and at least one second fuel container 12 arranged in a stack within a single launcher 3.

[0081] Thus, a single launcher 3 may be required to place a spacecraft 1 into Earth orbit.

[0082] The main structure 10 is equipped with thrusters, namely electric thruster 10A and chemical thruster 10B.

[0083] Additionally, the main structure 10 includes a solar electric energy generator 10C which forms an integral part of the main structure 10.

[0084] The first fuel container 11 forms a fuel tank for the electric propulsion. The fuel in the first fuel container 11 may preferably be an inert gas such as xenon, argon or krypton.

[0085] The second fuel container 12 forms a fuel tank for chemical propulsion. The fuel in the second fuel container 12 can be monopropellant or polypropellant, liquid and / or solid.

[0086] The support structure 13 is intended to carry the client ship 2 or the on-board equipment intended for the location of this client ship 2 .

[0087] In particular, the spacecraft 1 has a modular construction so that it can be adapted to the needs of several successive missions.

[0088] In this case, the support structure 13, the first fuel container 11 and the second fuel container 12 form a logistic stack and can be connected or disconnected from each other.

[0089] The main structure 10 may alternatively be coupled or detached to a first fuel container 11 or to a second fuel container 12 .

[0090] The arrangement of the support structure 13 arranged between the first fuel container 11 and the second fuel container 12 has the advantage that the main structure 10 can be supplied with fuel for electric or chemical propulsion.

[0091] Of course, the main structure 10 is equipped with the control units that allow the passage of the spacecraft 1 and the steering of these.

[0092] When the main structure 10 is coupled to a first fuel canister 11, fuel can be supplied to an electric thruster 10A, while when the main structure 10 is coupled to a second fuel canister 12, fuel can be supplied to a chemical thruster 10B.

[0093] The control unit is configured to ensure coupling and decoupling of the main structure 10 to one of the fuel canisters 11, 12 depending on the mission needs.

[0094] In an initial configuration planned for placing the spacecraft 1 in Earth orbit, the main structure 10 is coupled to a first fuel container 11 for powering electric propulsion to enable passage through space once in Earth orbit.

[0095] The solar electric energy generator 10C has a variable geometry, i.e., the solar electric energy generator 10C is intended to be deployed or retracted depending on the mission needs.

[0096] In particular, the solar electric energy generator 10C is intended to be deployed to ensure the supply of electric energy to a client ship 2 located at a point in free space, in orbit or on a celestial body, and to be stored to enable the displacement of the spacecraft 1 towards another client ship 2 located at another point in free space, in orbit or on another celestial body.

[0097] The solar electric energy generator 10C may comprise flexible photovoltaic cells or a flexible canvas of photovoltaic cells that can be wound and unwound around the same axis, so that the unwound photovoltaic cells cover a large surface of the solar radiation, thus making it possible to significantly increase the electric energy generation and supply capacity of the spacecraft 1.

[0098] Next, examples of successive missions are described that allow the supply of electrical energy to client ships in free space, in orbit, or at points on celestial bodies using a spacecraft according to one embodiment.

[0099] The configuration in FIG. 1 represents a spacecraft 1 arranged in a launcher 3 intended to be placed into Earth orbit from a launch site.

[0100] Spacecraft 1 as described above form a stack that fits into a single launcher 3. The second fuel container 12 of the spacecraft 1 is connected to the base 30 of the launcher 3 for keeping the spacecraft 1 stable during its deployment phase in Earth orbit.

[0101] In FIG. 2, a spacecraft 1 is shown in Earth orbit, here detached from the base 30 of a launcher 3 and separated therefrom.

[0102] Once in Earth orbit, the solar electric energy generator 10C can be deployed.

[0103] The step of transferring the spacecraft 1 to the client vessel 2 can then begin using electric propulsion powered by electric energy supplied by the deployed solar electric energy generators 10C and by fuel from the first fuel container 11 to which the main structure 10 is connected.

[0104] In a first mission configuration intended to supply electrical energy to a first client ship 2 (see Figure 8) in free space or in orbit, mooring means may be provided for connecting the spacecraft 1 to the client ship 2.

[0105] The solar electric energy generator 10C is equipped with means for transmitting electrical energy by wire and / or by short range wave and / or by laser, and once deployed, the solar electric energy generator 10C is able to supply electrical energy to the client vessel 2.

[0106] During the mooring phase, the solar electric energy generator 10C is stowed and is expected to be deployed once this mooring phase is completed.

[0107] Spacecraft 1 can then perform an electrical energy supply mission consecutive to the electrical energy supply mission just completed.

[0108] In this case, the spacecraft 1 can be pointed towards a celestial body, such as the Moon, on whose ground a second client ship 2 is located.

[0109] In this case, first the spacecraft 1 is put into orbit around a celestial body which also comprises the second client ship 2 .

[0110] Then, as shown in FIG. 3, the solar electric energy generator 10C is retracted, preparing the landing phase of the spacecraft 1 on the ground of said celestial body.

[0111] For this purpose, the spacecraft comprises landing means arranged to ensure a landing phase, for example the spacecraft comprises a landing gear 16 (see FIG. 6).

[0112] As shown in FIG. 4, the main structure 10 is then controlled to be separated from the first fuel container 11 and to allow connection to a second fuel container 12.

[0113] Then, the first fuel container 11 and the second fuel container 12 can be separated (FIG. 5).

[0114] The spacecraft 1 thus constructed comprises a support structure 13 for the onboard equipment connected to a second fuel container 12. It now allows the use of chemical propulsion and is therefore suitable for carrying out a landing phase of the spacecraft 1 on the ground of a celestial body.

[0115] FIG. 6 illustrates the in-orbit reorientation of spacecraft 1 to prepare for escape from orbit and landing on a celestial body, and FIG. 7 illustrates the landing phase of spacecraft 1 on a celestial body.

[0116] The spacecraft 1 shown in Figures 6 and 7 is equipped with the landing gear 16 in the open position.

[0117] As shown in FIG. 8, once on the ground, the spacecraft 1 can be offloaded from the second fuel canister 12 and from the support structure 13 with its onboard equipment to where the client vessel 2 is located.

[0118] The solar electric energy generator 10C can then be deployed to supply electrical energy to the client vessel 2.

[0119] Spacecraft 1 can again perform an electrical energy supply mission following the one just completed.

[0120] For example, spacecraft 1 may be pointed at another celestial body on which a third client ship 2 is located on the ground.

[0121] For this purpose, the solar electric energy generator 10C is pre-stored.

[0122] At least one third fuel container 14 is provided which may be attached to the main structure 10 or may be provided from where the second client vessel 2 is located.

[0123] 9 shows the launching of the spacecraft 1 into orbit from the ground of a celestial body with a second client ship 2. When the spacecraft is launched into orbit, the landing gear 16 is closed in a stowed position. The main structure 10, previously separated from the support structure 13 and the second fuel canister 12, can then receive a third fuel canister 14 with fuel for chemical propulsion.

[0124] The main structure 10 can then be supplied with fuel for chemical propulsion to enable the spacecraft 1 to take off and be placed into orbit around the celestial body.

[0125] FIG. 10 shows the preparation of spacecraft 1 for continuing its electrical energy supply mission to a destination on a third client ship 2.

[0126] Once in orbit as described above, the third fuel canister 14 is separated from the main structure 10. The solar electric energy generator 10C is then deployed. Finally, the main structure 10 can be coupled to another first fuel canister 11 of a new logistics stack planned for a subsequent mission, or alternatively, a fuel transfer means can ensure the fuel supply of the previously retrieved first and second fuel canisters 11, 12.

[0127] The new logistics stack may be similar to the initial configuration, i.e., a first fuel canister 11, a second fuel canister 12, and a support structure 13 disposed between the first fuel canister 11 and the second fuel canister 12. The newly formed spacecraft 1 may then be driven towards the third client vessel 2 on the second celestial body, following the steps previously described.

[0128] In the embodiment illustrated by Figure 11, the main structure 10 can be coupled to a separate first fuel canister 11 for electric thrusters only, provided for a subsequent mission. The step of transferring the spacecraft 1 to the client vehicle 2 can then commence using electric propulsion powered by electric energy provided by the deployed solar electric energy generators 10C and by fuel from the first fuel canister 11 to which the main structure 10 is coupled.

[0129] 12-16 are diagrams of a main structure 10 according to one embodiment.

[0130] Figure 12 shows the main structure 10 in orbit housing a solar electric energy generator 10C of electrical energy having a variable geometry. In the embodiment shown in Figure 12, the solar electric energy generator 10C comprises two canvases, each formed from one or more flexible photovoltaic cells, each wrapped around the same axis.

[0131] The main structure 10 comprises an electric thruster or propulsion unit comprising a number of electric motors 10A.

[0132] The main structure 10 is equipped with an electric thruster or chemical propulsion unit having a number of chemical motors 10B.

[0133] The main structure 10 is provided with a mooring and fuel transfer system 18 configured to ensure connection or disconnection between the main structure 10 and the fuel containers 11, 12, 14 to ensure fuel transfer.

[0134] In the embodiment illustrated in FIG. 12, the landing gear is stowed in a stowed position (not visible).

[0135] FIG. 13 shows a main structure 10 placed on the ground of a celestial body, for example, on which a solar electric energy generator 10C having a variable geometry is deployed.

[0136] In the embodiment shown in Figures 13-16, a solar electric energy generator 1OC comprises two canvases of flexible photovoltaic cells, each unwrapped.

[0137] The landing gear 16 is deployed to ensure the landing of the main structure 10 and its maintenance on the ground of a celestial body (such as the Moon), i.e. in an open position.

[0138] 14 and 15 are plan views of the main structure 10 with the solar electric energy generator 10C having an expanded variable geometry configuration.

[0139] In the embodiment illustrated by Figures 12, 13 and 16, the main structure 10 is equipped with an electric thruster having several electric motors 10A forming an electric propulsion unit, and the main structure 10 is equipped with an electric thruster having a chemical motor 10B forming a chemical propulsion unit.

[0140] 15, the main structure 10 may include a rotational orientation device 20 for driving the solar electric energy generator 10C in rotation about a vertical or longitudinal axis A. For example, the rotational orientation device 20 is configured to cause rotation of the photovoltaic cell windings through 360° about the longitudinal or vertical axis A.

[0141] This rotational orientation device allows the position of the sun to be tracked and the photovoltaic cells to be oriented towards the sun.

[0142] In the embodiment illustrated by Figures 12-16, the spacecraft comprises an optional energy dissipation device. For example, the energy dissipation device comprises two radiators 22', 22", each extending across half of the surface of the main structure 10 so as to provide the maximum available surface around the main structure 10.

[0143] Obviously, the present specification is not limited to the merely described examples, which can be modified in numerous ways without departing from the scope of the appended claims. In particular, different features, forms, modifications and embodiments can be associated with each other in various combinations, unless they are incompatible or mutually exclusive. In particular, all modifications and embodiments described above can be combined with each other.

Claims

1. A spacecraft (1) for supplying electrical energy to a client vessel (2), The spacecraft (1) A main structure (10) comprising an electric thruster (10A), a chemical thruster (10B), and a solar electric energy generator (10C) having a variable geometry; At least one first fuel container (11) for said electric thruster (10A); at least one second fuel container (12) for said chemical thruster (10B); the spacecraft (1) is modular in that the main structure (10) is removably connected to the first fuel canister (11) for fueling the electric thrusters (10A) or alternatively the main structure (10) is removably connected to the second fuel canister (12) for fueling the chemical thrusters (10B), and the first fuel canister (11) and the second fuel canister (12) are removably connected to each other; The solar electric energy generator (10C) comprises: to be deployed to supply electrical energy to a first client vehicle (2) located at a first point in free space, in orbit or on a first celestial body, and to displace said spacecraft (1) to a second client vehicle (2) located at a second point in free space, in orbit or on a second celestial body; A spacecraft (1) configured to be stored for carrying out a mooring phase with the first client ship or the second client ship in the free space or in the orbit, as well as a landing phase toward a third celestial body, and a takeoff phase from the third celestial body for returning to orbit.

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

3. 2. A spacecraft (1) according to claim 1, characterized in that the solar electric energy generator (10C) comprises means for transmitting electric energy by wire and / or by short range wave and / or by laser.

4. 2. The spacecraft (1) of claim 1, comprising a support structure (13) for carrying on-board equipment, the support structure (13) being configured to be connected to and disconnected from the first fuel container (11) and the second fuel container (12).

5. 2. The spacecraft (1) according to claim 1, wherein the main structure (10) comprises at least one third fuel canister (14) for the chemical thruster (10B) so as to enable the spacecraft (1) to return to orbit from a celestial body.

6. 2. The spacecraft (1) according to claim 1, wherein the main structure (10) comprises mooring means configured to couple the spacecraft (1) to a client vessel (2).

7. 2. The spacecraft (1) according to claim 1, wherein the main structure (10) comprises landing means (16) configured to enable the spacecraft (1) to land on a celestial body.

8. 2. A spacecraft (1) according to claim 1, comprising fuel transfer means for ensuring refuelling of the spacecraft (1).

9. A method for supplying electrical energy to at least one client vehicle (2) at a point located in free space, in orbit or on a celestial body using a spacecraft (1) according to any one of claims 1 to 8, comprising: The method comprises: The method comprises a step of passing the spacecraft (1) placed in orbit towards a client ship (2) located in free space, in orbit or on a celestial body using the electric thrusters (10A) and the solar electric energy generators (10C) deployed after the spacecraft is placed in orbit.

10. The method comprises: - berthing said spacecraft (1) to a client vessel (2) located in said free space or in orbit; and supplying the client vessel (2) with electrical energy generated by the solar electric energy generator (10C).

11. The method comprises: placing the spacecraft (1) into orbit around a celestial body; storing said solar electric energy generator (10C); Separating the first fuel container (11) from the main structure (10); connecting said main structure (10) to said second fuel container (12); Separating the first fuel container (11) from the second fuel container (12); Landing the spacecraft (1) on the ground of the celestial body; deploying said solar electric energy generator (10C); and supplying the electrical energy generated by said solar electrical energy generator (10C) to a client vessel (2) on said celestial body.

12. In the case of a continuation of the mission of supplying electrical energy to other client vessels, the method further comprises: storing said solar electric energy generator (10C); filling the second fuel container (12) or, alternatively, coupling at least one third fuel container (14) to the main structure (10) for supplying fuel to a chemical thruster (10B); and launching said spacecraft (1) into orbit around said celestial body.

13. The method comprises: Separating a third fuel container (14) from the main structure (10); on-orbit or in-free space refueling for the electric thrusters (10A) and the chemical thrusters (10B); and passing the spacecraft (1) to a client vessel (2).

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