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 supply of electrical energy by a spacecraft. It also relates to a method of supplying electrical energy using the above spacecraft.

Background Art

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

[0003] Depending on the mission requirements and the location of the client spacecraft to be powered, several distinct systems need to be implemented to bring a solar electric energy generator to the location of the client spacecraft and supply electrical energy to the client spacecraft. For the most complex missions, a launch system aimed at bringing a solar electric energy generator into space, a transfer and / or orbit circulation system in space to ensure the passage of the solar electric energy generator in space, and a descent system to ensure the descent of the solar electric energy generator onto the celestial body need to be provided.

[0004] For example, in the case of a mission dedicated to supplying electrical energy to a client spacecraft located in free space or in orbit, the solar electric energy generator is mounted on a spacecraft equipped with a transfer and / or orbit circulation system. A spacecraft previously placed in Earth orbit carries the solar electric energy generator to the client spacecraft. Then, the solar electric energy generator can be separated from the transfer and / or orbit circulation system so as to be connected to the client spacecraft to supply electrical energy until the end of the mission, even if it cannot be utilized for the purpose of a new mission.

[0005] In another example mission, a solar power generator, also positioned in Earth orbit, could be intended to supply electrical energy to a client spacecraft positioned on a celestial body. For this purpose, the solar power generator could be embedded as onboard equipment on a descent system that allows it to land on the celestial body. Once on Earth, the solar power generator would be removed from the landing system to connect to the client spacecraft and could supply electrical energy until the end of its mission, but it could not be operated for any new mission purpose.

[0006] In all cases of one-off missions, the solar electric energy generators used today are intended to perform missions that supply electrical energy to client ships located in free space, in orbit, and / or on celestial bodies, and cannot be used for other electrical energy supply missions. As a result, the operational area for supplying electrical energy in existing missions is limited.

[0007] Furthermore, such electrically powered missions, which do not require the use of high-mass equipment, become costly by using several separate systems, particularly launch systems, space transport and / or orbital circulation systems, and descent systems.

[0008] On the other hand, fuel containers planned for these missions, or onboard equipment brought onto or located on the same client vessel to supply electrical energy, may be launched into Earth orbit by a different launch system than the one planned to place the solar electric energy generator into Earth orbit. Therefore, the need for a launch system is increasing.

[0009] Furthermore, solar power generators have the disadvantage of supplying only a small amount of electrical energy (a few kW) to client ships that need to be powered. [Prior art documents] [Patent Documents]

[0010] [Patent Document 1] French Patent No. 2998876 [Patent Document 2] French Patent No. 3024227 Specification [Overview of the project] [Problems that the invention aims to solve]

[0011] It is desirable to solve at least one of the aforementioned shortcomings by providing a spacecraft that can carry out several electrical energy supply missions during its lifespan.

[0012] Furthermore, it may be desirable to carry out missions that supply high-power electrical energy.

[0013] Furthermore, it may be desirable to reduce the cost of the electric energy supply mission.

[0014] Furthermore, it may be desirable to reduce the need for launch systems in Earth orbit for the aforementioned missions.

[0015] Furthermore, it may be desirable to provide a spacecraft that can supply electrical energy to enable the carrying of onboard equipment. [Means for solving the problem]

[0016] For this purpose, embodiments of a spacecraft for supplying electrical energy to a client ship include a main structure comprising an electric thruster, a chemical thruster, and a solar electric energy generator having a variable geometric shape, and at least one first fuel container for the electric thruster and at least one second fuel container for the chemical thruster, wherein the main structure is detachably connected to the first fuel container to supply fuel to the electric thruster, or alternatively detachably connected to the second fuel container to supply fuel to the chemical thruster, and the first fuel container and the second fuel container We propose a modular spacecraft in which the energy containers are detachably connected to each other, and the solar electric energy generator is configured to supply electrical energy to a first client ship located at a first point in free space, in orbit, or on a first celestial body, and to deploy in order 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 carry out the mooring phase with the first or second client ship in free space or in orbit, the landing phase toward a third celestial body, and the takeoff phase from the third celestial body for return to orbit.

[0017] The term "electric thruster" refers to an electric propulsion unit that has one or more motors.

[0018] The term "chemical thruster" refers to a chemical propulsion unit that has one or more motors.

[0019] The phrase "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 within the same spacecraft. In this case, the functions are the launch of the spacecraft from a celestial body into space using chemical thrusters, the transfer and / or circulation of the spacecraft hull in space, and the supply of electrical energy to a client ship that brings it in, as well as the supply of electrical energy to a client ship using a solar electric energy generator.

[0021] The term "removably coupling" means, for example, a first element that is mechanically detached from a second element that is to be mechanically attached to a third element. The 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 and third elements.

[0022] By combining these functions, it becomes possible to supply electrical energy at any point to client ships located at different points in free space, in orbit, and / or on celestial bodies.

[0023] Therefore, such a spacecraft can be planned to continuously carry out several missions to autonomously supply electrical energy to client ships located in free space, in orbit, or on celestial bodies.

[0024] For example, such a spacecraft can carry out a first mission to supply electrical energy to a first client ship in free space or in orbit before carrying out a second mission to supply electrical energy on a celestial body to a second client ship. The present invention is of course not limited to this example of missions and can be used in any combination of missions available according to the present invention, for example, a first mission to supply electrical energy to a client ship located on a celestial body such as the moon, and then a second mission to supply electrical energy to another client ship located on another celestial body, etc.

[0025] The main structure, which includes an electric thruster, a chemical thruster, and a solar electric energy generator with a variable geometry, forms an integrated functional assembly.

[0026] Nevertheless, provisions can be made for the electric thruster to be separated from the main structure for replacement.

[0027] The client ship can be, for example, a residential infrastructure, a production infrastructure, a research infrastructure (microgravity), a computing center, and a means for re-assembly.

[0028] It will be understood that the chemical thruster enables the main structure to land on a celestial body other than the Earth or to place the main structure into orbit from the celestial body.

[0029] It will be understood that the electric thruster enables the main structure to pass through free space or in orbit.

[0030] A celestial body means a celestial body other than the Earth that has a ground, such as a planet, a moon, an asteroid, etc.

[0031] The chemical thruster can be a single-propellant or multi-propellant thruster.

[0032] The fuel contained in the first fuel container is preferably a single-propellant or multi-propellant.

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

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

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

[0036] According to one embodiment, a solar electric energy generator having a variable geometric shape comprises at least two photocells or a flexible canvas that can be folded and unfolded along the same axis.

[0037] Patent Document 1 (French Patent No. 2998876) and Patent Document 2 (French Patent No. 3024227) disclose the use of the above-mentioned flexible photocell or flexible canvas. As described in these patent documents, the above-mentioned flexible canvas can be rolled up or unrolled using a deployable structure or device as described in these patent documents.

[0038] These patent documents 1 and 2 are fully incorporated herein. Therefore, deployable structures or devices and methods thereof can be related to current spacecraft, where applicable.

[0039] In this specification, the term "wound" refers to a stored state, and the term "unwound" refers to an unfolded state.

[0040] According to one embodiment, the spacecraft is provided with a support structure for carrying onboard equipment, and the support structure is configured to be connected to and separated from the first fuel container and the second fuel container.

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

[0042] Optionally, a means of transferring wired electrical energy can also be connected to the client ship, either using a robotic arm or manually by an astronaut.

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

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

[0045] The third fuel container described above may be attached to the main structure to ensure that the spacecraft is placed into orbit from the celestial body, and may also be connected to the spacecraft to supply fuel to the chemical thrusters.

[0046] Naturally, the fuel contained in this third fuel container is preferably a single-engine propellant or a double-engine propellant.

[0047] According to one embodiment, the main structure includes mooring means configured to connect the spacecraft to the client ship.

[0048] The above mooring means allows the spacecraft to be stabilized in the client ship in order 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 includes 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 refueling of the spacecraft.

[0051] For example, a fuel transfer system could be used to plan for a refueling cargo ship to ensure the refueling of a spacecraft.

[0052] The above-mentioned fuel supply means can be formed by a connector and a supply conduit.

[0053] The above-mentioned fuel transfer means may be provided for refueling 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 in free space, in orbit, or on a celestial body using the spacecraft described above, wherein the method comprises the step of passing the orbiting spacecraft towards a client ship located in free space, in orbit, or on another celestial body, using the electric thrusters and solar electric energy generator deployed after the spacecraft has been 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 electrical energy generated by a solar electric energy generator to the client ship.

[0056] According to one embodiment, this method is The steps to place the spacecraft into orbit around a celestial body, The steps include storing the solar electric energy generator, A step of separating the first fuel container from the main structure, The steps include connecting the main structure to the second fuel container, The steps include separating the first fuel container from the second fuel container, The steps to land a spacecraft on the ground of a celestial body, Steps to deploy a solar electric energy generator, The system comprises the steps of supplying electrical energy generated by a solar electric energy generator to a client ship on a celestial body.

[0057] According to one embodiment, the spacecraft is equipped with a support structure as defined above for carrying onboard equipment, in which case the method comprises the steps of unloading the main structure at the client ship's location or providing refueling to the client ship.

[0058] The support structure is advantageously positioned between the first fuel container and the second fuel container.

[0059] According to one embodiment, when continuing an electrical energy supply mission to another client vessel, the method comprises the steps of: housing a solar electric energy generator; filling a second fuel container; or, alternatively, connecting at least one third fuel container to the main structure to supply fuel to a chemical thruster; and taking off to enter orbit around a celestial body.

[0060] According to one embodiment, the method comprises the steps of separating the third fuel container from the main structure, refueling the electric thrusters and chemical thrusters in orbit or in free space, and passing the spacecraft through to the client ship.

[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 that are pre-filled with fuel.

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

[0063] According to other features of this second embodiment, the method comprises the step of passing a spacecraft to another client spacecraft located in free space, in orbit, or on a celestial body, using at least electric thrusters and a solar electric energy generator that is deployed after being placed in orbit.

[0064] Some embodiments also relate to a spacecraft for supplying electrical energy to a client ship located in free space, in orbit and / or on a celestial body, wherein the spacecraft comprises a main structure comprising an electric thruster, a chemical thruster, and a solar electric energy generator having a variable geometric shape, and at least one first fuel container for the electric thruster and at least one second fuel container for the chemical thruster, wherein the spacecraft connects the main structure to the first fuel container to supply fuel to the electric thruster, or connects the main structure to the front to supply fuel to the chemical thruster. The solar electric energy generator, which is modular and has a variable geometric shape, can be connected to the second fuel container as an alternative, and the first and second fuel containers can be connected to or separated from each other, and is intended to power a client ship located in free space, in orbit, or on a first celestial body, to be deployed to displace the spacecraft to another client ship located in free space, in orbit, or on a second celestial body, and to be stored to carry out a landing phase toward the celestial body and a takeoff phase from the celestial body for return to orbit.

[0065] According to one embodiment, a solar electric energy generator having a variable geometric shape comprises a flexible photocell that can be wound and unwound around the same axis.

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

[0067] According to one embodiment, the spacecraft is provided with a support structure for carrying onboard equipment, the support structure is intended to be connected to or separated from at least one first fuel container and at least one second fuel container.

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

[0069] According to one embodiment, the main structure includes mooring means for connecting the spacecraft to the client ship.

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

[0071] According to one embodiment, the spacecraft is equipped with fuel transfer means for refueling the spacecraft.

[0072] Some embodiments may also relate to a method for supplying electrical energy to a client ship at a location in free space, in orbit and / or on a celestial body using the above-defined spacecraft which has been previously placed in orbit, wherein the method comprises the step of passing the spacecraft toward a client ship located in free space, in orbit or on a celestial body, using at least an electric thruster and a solar electrical energy generator which is deployed after being placed in orbit.

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

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

[0075] According to one embodiment, when continuing a mission to supply electrical energy to other client ships, the method comprises the steps of housing a solar electrical energy generator, filling a second fuel container, or alternatively, connecting at least one third fuel container to the main structure to supply fuel to chemical thrusters, and taking off to place the spacecraft into orbit around a celestial body.

[0076] According to one embodiment, the method comprises the steps of: separating at least one third fuel container from the main structure when the spacecraft is equipped with at least one third fuel container; refueling the electric and chemical thrusters of the spacecraft in orbit or in free space; and passing the spacecraft toward another client ship.

[0077] Other features and advantages will be understood by reading the following non-limiting description and the attached diagrams which schematically illustrate several embodiments. [Brief explanation of the drawing]

[0078] [Figure 1] Figure 1 shows a schematic diagram of a spacecraft according to an embodiment, comprising a main structure, a first fuel container, a support structure for onboard equipment, and a second fuel container mounted on a launch device intended to place the spacecraft into Earth orbit. [Figure 2] Figure 2 shows a spacecraft placed in Earth orbit. [Figure 3] Figure 3 shows a spacecraft carrying a solar energy generator in the step of housing the solar energy generator, with the aim of landing the spacecraft on a celestial body. [Figure 4] Figure 4 shows a spacecraft intended for landing on a celestial body, in the step of separating the main structure from the first fuel container and connecting it to the second fuel container. [Figure 5] Figure 5 shows a spacecraft intended to land on a celestial body during the step of separating the first fuel container from its onboard equipment. [Figure 6]Figure 6 illustrates the steps taken to change the orientation of the spacecraft in order to land it on a celestial body. [Figure 7] Figure 7 illustrates the steps involved in a spacecraft descending to land on the ground of a celestial body. [Figure 8] Figure 8 illustrates the steps of unloading the spacecraft and supplying electrical energy from the solar energy generator to the client vessel. [Figure 9] Figure 9 illustrates the steps involved in launching a spacecraft from the ground of a celestial body into orbit. [Figure 10] Figure 10 illustrates the step of refueling a spacecraft before sending it to another client ship. [Figure 11] Figure 11 illustrates a modified step of refueling a spacecraft before sending it to another client ship. [Figure 12] Figure 12 is an enlarged isometric view of the main structure of a spacecraft equipped with a solar electric energy generator in a storage location, according to one embodiment. [Figure 13] Figure 13 is an enlarged view of the main structure of a spacecraft, showing the solar electric energy generator in the deployed position, according to one embodiment. [Figure 14] Figure 14 shows the main structure of a spacecraft and a top view of the solar electric energy generator in its deployed position, according to one embodiment. [Figure 15] Figure 15 is an enlarged top view of the main structure of the spacecraft shown in Figure 14. [Figure 16] Figure 16 is an enlarged bottom view of the main structure of the spacecraft shown in Figure 14. [Modes for carrying out the invention]

[0079] Figure 1 shows a spacecraft 1 for supplying electrical energy to client ship 2 at a location 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 onboard equipment, and at least one second fuel container 12 stacked and arranged within a single launch device 3.

[0081] Therefore, a single launch device 3 may be required to place spacecraft 1 into Earth orbit.

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

[0083] Furthermore, the main structure 10 includes a solar electric energy generator 10C that forms an integrated part of the main structure 10.

[0084] The first fuel container 11 forms a fuel tank for electric propulsion. The fuel in the first fuel container 11 can 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 a single-engine propellant or a double-engine propellant, liquid and / or solid.

[0086] The support structure 13 is intended to support the client vessel 2 or the onboard equipment intended for the location of this client vessel 2.

[0087] In particular, spacecraft 1 has a modular structure to adapt to the needs of several consecutive missions.

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

[0089] The main structure 10 can, alternatively, be connected to or disconnected from the first fuel container 11, or from the second fuel container 12.

[0090] The arrangement of the support structure 13, which is positioned between the first fuel container 11 and the second fuel container 12, has the advantage of being able to supply fuel for electric or chemical propulsion to the main structure 10.

[0091] Naturally, the main structure 10 is equipped with a control unit that enables the passage of the spacecraft 1 and their operation.

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

[0093] The control unit is configured to ensure connection to and disconnection from one of the fuel containers 11 and 12 of the main structure 10, depending on the needs of the mission.

[0094] In the initial configuration planned to place spacecraft 1 into Earth orbit, the main structure 10 is connected to the first fuel vessel 11 to power the electric propulsion so that it can pass through space once it is in Earth orbit.

[0095] The solar electric energy generator 10C has a variable geometric shape. In other words, the solar electric energy generator 10C is intended to be deployed or retracted depending on the mission requirements.

[0096] In particular, the solar electric energy generator 10C is intended to be deployed to ensure the supply of electrical energy to a client ship 2 located in free space, in orbit, or on a celestial body, and to be retracted to allow the spacecraft 1 to be displaced toward another client ship 2 located in free space, in orbit, or on another celestial body.

[0097] The solar electric energy generator 10C may be equipped with a flexible photocell, or a flexible canvas of photocells that can be wound and unwound around the same axis, so that the unwound photocells cover a large surface area of ​​solar radiation. Thus, the photocells make it possible to significantly increase the electrical energy generation and supply capacity of the spacecraft 1.

[0098] Next, we describe an example of a series of missions that enable the supply of electrical energy to a client ship located in free space, in orbit, or on a celestial body using a spacecraft according to one embodiment.

[0099] The configuration in Figure 1 represents a spacecraft 1 positioned inside a launch device 3, intended to launch the spacecraft from the launch site into Earth orbit.

[0100] The spacecraft 1 described above forms 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 to ensure the stable maintenance of the spacecraft 1 during its deployment phase in Earth orbit.

[0101] Figure 2 shows spacecraft 1 in Earth orbit, which has detached from the base 30 of launch device 3 and separated from launch device 3.

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

[0103] Next, the step of transferring the spacecraft 1 to the client ship 2 can be initiated using electric propulsion powered by the electric energy supplied by the deployed solar electric energy generator 10C and by the 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 orbit, mooring means can 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 waves, and / or by laser, and once deployed, the solar electric energy generator 10C can supply electrical energy to the client ship 2.

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

[0107] Subsequently, Spacecraft 1 can carry out an electrical energy supply mission immediately following the recently completed electrical energy supply mission.

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

[0109] In this case, first, spacecraft 1 is placed into orbit around the celestial body containing the second client ship 2.

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

[0111] For this purpose, the spacecraft is equipped with landing means configured to ensure the landing phase. For example, the spacecraft is equipped with a landing gear 16 (see Figure 6).

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

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

[0114] The spacecraft 1, configured in this way, includes a support structure 13 for onboard equipment connected to the second fuel container 12. Since it is now capable of using chemical propulsion, it is suitable for the landing phase of spacecraft 1 on the ground of a celestial body.

[0115] Figure 6 illustrates the reorientation of spacecraft 1 in orbit in preparation for escaping orbit and landing on a celestial body, and Figure 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 a landing gear 16 in the open position.

[0117] As shown in Figure 8, once on the ground, spacecraft 1 can unload its cargo from the second fuel container 12 and the support structure 13 equipped with onboard equipment to the location where client ship 2 is located.

[0118] Next, the solar electric energy generator 10C can be deployed to supply electrical energy to client ship 2.

[0119] Spacecraft 1 can perform another electrical energy supply mission immediately following the one it just completed.

[0120] For example, spacecraft 1 can be directed towards another celestial body where the third client ship 2 is located on Earth.

[0121] For this reason, the solar electric energy generator 10C is stored in advance.

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

[0123] Figure 9 shows the point at which the spacecraft 1 is placed into orbit from the ground of a celestial body containing the second client ship 2. When the spacecraft is placed into orbit, the landing gear 16 is closed in its stowed position. The main structure 10, which has previously separated from the support structure 13 and the second fuel container 12, can then receive the third fuel container 14 containing fuel for chemical propulsion.

[0124] Next, fuel for chemical propulsion can be supplied to the main structure 10 to enable the spacecraft 1 to take off and to enter an orbit around the celestial body.

[0125] Figure 10 shows the preparations for continuing the electrical energy supply mission of spacecraft 1 toward a destination of the third client ship 2.

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

[0127] The new logistics stack may be similar to the initial configuration, namely, a first fuel container 11, a second fuel container 12, and a support structure 13 positioned between the first and second fuel containers 11 and 12. The newly formed spacecraft 1 can then be driven toward the third client ship 2 on the second celestial body according to the steps described above.

[0128] In the embodiment illustrated in Figure 11, the main structure 10 can be coupled to a separate first fuel container 11 for electric thrusters only, which will be provided for subsequent missions. The step of transporting the spacecraft 1 to the client ship 2 can then be initiated using electric propulsion powered by electric energy supplied by a deployed solar electric energy generator 10C and fuel from the first fuel container 11 to which the main structure 10 is coupled.

[0129] Figures 12 to 16 show the main structure 10 according to one embodiment.

[0130] Figure 12 shows a main structure 10 in orbit that houses a solar electric energy generator 10C having a variable geometric shape. In the embodiment shown in Figure 12, the solar electric energy generator 10C comprises two canvases, each formed from one or more flexible photocells, each wound around the same axis.

[0131] The main structure 10 includes an electric thruster or electric propulsion unit equipped with multiple electric motors 10A.

[0132] The main structure 10 includes an electric thruster or chemical propulsion unit having a plurality of chemical motors 10B.

[0133] The main structure 10 includes a mooring and fuel transfer system 18 configured to ensure connection or separation between the main structure 10 and fuel containers 11, 12, and 14 in order to ensure the transfer of fuel.

[0134] In the embodiment shown in Figure 12, the landing gear is stored in the stowed position (not visible).

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

[0136] In the embodiments shown in Figures 13 to 16, the solar electric energy generator 10C comprises two canvases of flexible photocells, each unfolded.

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

[0138] Figures 14 and 15 are plan views of the main structure 10, which includes a solar electric energy generator 10C having an unfolded variable geometric shape.

[0139] In the embodiments illustrated by Figures 12, 13, and 16, the main structure 10 comprises an electric thruster having several electric motors 10A that form an electric propulsion unit. The main structure 10 also comprises an electric thruster having a chemical motor 10B that forms a chemical propulsion unit.

[0140] As illustrated in Figure 15, the main structure 10 may include a rotational orientation device 20 for rotating the solar electric energy generator 10C around a vertical axis or longitudinal axis A. For example, the rotational orientation device 20 is configured to cause rotation of the photocell windings over 360° around the longitudinal axis or vertical axis A.

[0141] This rotational orientation device will allow us to track the sun's position and orient the photovoltaic cells towards it.

[0142] In the embodiments shown in Figures 12 to 16, the spacecraft is equipped with an optional energy dissipation device. For example, the energy dissipation device comprises two radiators 22', 22'' each extending over half of the surface of the main structure 10 so as to provide the maximum available surface area around the main structure 10.

[0143] Clearly, this specification is not limited to the examples described herein, and numerous modifications can be made to these examples without departing from the scope of the appended claims. In particular, different features, shapes, variations and embodiments can be related to one another in various combinations, provided they are not incompatible or mutually exclusive. In particular, all of the above-described variations and embodiments can be combined with one another. Furthermore, this disclosure includes the following inventions. The first aspect is, In a spacecraft (1) for supplying electrical energy to a client ship (2), The aforementioned 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 geometric shape, At least one first fuel container (11) for the electric thruster (10A), The chemical thruster (10B) comprises at least one second fuel container (12), The spacecraft (1) is modular, wherein the main structure (10) is detachably connected to the first fuel container (11) to supply fuel to the electric thruster (10A), or the main structure (10) is detachably connected to the second fuel container (12) to supply fuel to the chemical thruster (10B), and the first fuel container (11) and the second fuel container (12) are detachably connected to each other. The aforementioned solar electric energy generator (10C) To supply electrical energy to a first client ship (2) located in free space, in orbit, or at a first point on a first celestial body, and to deploy the spacecraft (1) so as to displace it to a second client ship (2) located in free space, in orbit, or at a second point on a second celestial body, The spacecraft (1) is configured to be stored in order to perform the mooring phase with the first or second client ship in free space or in orbit, the landing phase toward the third celestial body, and the takeoff phase from the third celestial body to return to orbit. The second aspect is, The first embodiment of the spacecraft (1) comprises a solar electric energy generator (10C) equipped with a flexible photocell configured to be wound and unwound around the same axis. The third aspect is, The solar electric energy generator (10C) is a spacecraft (1) in a first or second embodiment, comprising means for transmitting electrical energy by wire, and / or by short-range waves, and / or by laser. The fourth aspect is, The spacecraft (1) is a spacecraft (1) in any one of the first to third embodiments, comprising a support structure (13) for carrying onboard equipment, wherein the support structure (13) is configured to be connected to and separated from the first fuel container (11) and the second fuel container (12). The fifth aspect is, The main structure (10) is a spacecraft (1) in any one of the first to fourth embodiments, comprising at least one third fuel container (14) for the chemical thruster (10B) to enable the spacecraft (1) to return from a celestial body to orbit. The sixth aspect is, The main structure (10) is a spacecraft (1) in any one of the first to fifth embodiments, wherein the main structure (10) is equipped with mooring means configured to connect the spacecraft (1) to the client ship (2). The seventh aspect is, The main structure (10) is a spacecraft (1) according to any one of the first to sixth embodiments, comprising landing means (16) configured to allow the spacecraft (1) to land on a celestial body. The eighth aspect is, The spacecraft (1) is provided with fuel transfer means for ensuring refueling of the spacecraft (1) according to any one of the first to seventh embodiments. The ninth aspect is, A method for supplying electrical energy to at least one client ship (2) at a point located in free space, in orbit, or on a celestial body, using a spacecraft (1) in any one of the first to eighth embodiments, The aforementioned method, The method includes the step of using the electric thrusters (10A) and solar electric energy generator (10C), which are deployed after the spacecraft is placed in orbit, to move the spacecraft (1) located in orbit towards a client ship (2) located in free space, in orbit, or on a celestial body. The tenth aspect is, The aforementioned method, The steps include: mooring the spacecraft (1) to a client ship (2) located in free space or in orbit; The method in the ninth embodiment comprises the step of supplying the electrical energy generated by the solar electric energy generator (10C) to the client ship (2). The eleventh aspect is, The aforementioned method, The steps include placing the aforementioned spacecraft (1) into an orbit around a celestial body, The steps include storing the solar electric energy generator (10C), The steps include separating the first fuel container (11) from the main structure (10), The steps include connecting the main structure (10) to the second fuel container (12), The steps include separating the first fuel container (11) from the second fuel container (12), The steps include: landing the spacecraft (1) on the ground of the celestial body, The steps include deploying the solar electric energy generator (10C), The method according to the ninth or tenth embodiment, comprising the step of supplying electrical energy generated by the solar electric energy generator (10C) to the client ship (2) on the celestial body. The twelfth aspect is, In the case of continuing a mission to supply electrical energy to other client vessels, the method described above is: The steps include storing the solar electric energy generator (10C), A step of filling the second fuel container (12), or alternatively, a step of connecting at least one third fuel container (14) to the main structure (10) to supply fuel to the chemical thruster (10B), A method according to any one of the 9th to 11th embodiments, comprising the step of taking off the spacecraft (1) so that it enters an orbit around the celestial body. The 13th aspect is, The aforementioned method, The steps include separating the third fuel container (14) from the main structure (10), A step of refueling the electric thruster (10A) and the chemical thruster (10B) in orbit or in free space, The method is one of any 9th to 12th embodiments, comprising the step of passing the spacecraft (1) to the client ship (2).

Claims

1. In a spacecraft (1) for supplying electrical energy to a client ship (2), The aforementioned 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 geometric shape, At least one first fuel container (11) for the electric thruster (10A), The chemical thruster (10B) comprises at least one second fuel container (12), The spacecraft (1) is modular, wherein the main structure (10) is detachably connected to the first fuel container (11) to supply fuel to the electric thruster (10A), or the main structure (10) is detachably connected to the second fuel container (12) to supply fuel to the chemical thruster (10B), and the first fuel container (11) and the second fuel container (12) are detachably connected to each other. The aforementioned solar electric energy generator (10C) To supply electrical energy to a first client ship (2) located in free space, in orbit, or at a first point on a first celestial body, and to deploy the spacecraft (1) so as to displace it to a second client ship (2) located in free space, in orbit, or at a second point on a second celestial body, A spacecraft (1) configured to be stored in order to perform a mooring phase with the first or second client ship in free space or in orbit, a landing phase toward the third celestial body, and a takeoff phase from the third celestial body for returning to orbit.

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

3. The spacecraft (1) according to claim 1, wherein the solar electric energy generator (10C) is equipped with means for transmitting electrical energy by wire and / or by short-range waves and / or by laser.

4. The spacecraft (1) according to claim 1, comprising a support structure (13) for carrying onboard equipment, wherein the support structure (13) is configured to be connected to and separated from the first fuel container (11) and the second fuel container (12).

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

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

7. The spacecraft (1) according to claim 1, 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 claim 1, further comprising fuel transfer means for ensuring refueling of the spacecraft (1).

9. A method for supplying electrical energy to at least one client ship (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, The aforementioned method, A method comprising the step of using the electric thrusters (10A) and the solar electric energy generator (10C), which are deployed after the spacecraft is positioned in orbit, to move the spacecraft (1) positioned in orbit toward a client ship (2) located in free space, in orbit, or on a celestial body.

10. The aforementioned method, The steps include: mooring the spacecraft (1) to a client ship (2) located in free space or in orbit; The method according to claim 9, further comprising the step of supplying the electrical energy generated by the solar electric energy generator (10C) to the client ship (2).

11. The aforementioned method, The steps include: placing the aforementioned spacecraft (1) into an orbit around a celestial body; The steps include storing the solar electric energy generator (10C), The steps include separating the first fuel container (11) from the main structure (10), The steps include connecting the main structure (10) to the second fuel container (12), The steps include separating the first fuel container (11) from the second fuel container (12), The steps include: landing the spacecraft (1) on the ground of the celestial body, The steps include deploying the solar electric energy generator (10C), The method according to claim 9, further comprising the step of supplying electrical energy generated by the solar electric energy generator (10C) to the client ship (2) on the celestial body.

12. In the case of continuing a mission to supply electrical energy to other client vessels, the method described above is: The steps include storing the solar electric energy generator (10C), A step of filling the second fuel container (12), or alternatively, a step of connecting at least one third fuel container (14) to the main structure (10) to supply fuel to the chemical thruster (10B), The method according to claim 9, further comprising the step of taking off the spacecraft (1) so as to enter an orbit around the celestial body.

13. The aforementioned method, The steps include separating the third fuel container (14) from the main structure (10), The steps include refueling the electric thruster (10A) and the chemical thruster (10B) in orbit or in free space, The method according to claim 9, further comprising the step of passing the spacecraft (1) to the client ship (2).

Images