ELECTRICAL DISTRIBUTION SPACECRAFT, AND ASSOCIATED METHOD

Abstract

A spacecraft for the distribution of electrical energy to client craft at points situated in free space, in orbit and/or on a celestial body includes a main structure equipped with an electric thruster, with a chemical thruster and with a solar generator, a first fuel container for fuel intended for the electric thruster, and a second fuel container for fuel intended for the chemical thruster. The spacecraft is able to be modulated such that the main structure can be coupled/decoupled alternatively to/from the first container or the second container, the first container and the second container are able to be coupled/decoupled to/from one another, and the solar generator can be deployed or retracted.

Claims

1. A spacecraft for distributing electrical energy to a client craft, the spacecraft comprising: a main structure equipped with an electric thruster, a chemical thruster, and a solar electrical energy generator with variable geometry; at least one first fuel container configured for use by the electric thruster; and at least one second fuel container configured for use by the chemical thruster, wherein the spacecraft is modular to removably couple the main structure alternately to the first container for supplying fuel to the electric thruster, or to the second container for supplying fuel to the chemical thruster, and to removably couple the first container and the second container to each other, and wherein the solar electrical energy generator is configured to be: deployed to distribute the electrical energy to a first client craft located at a first point in free space, in orbit or on a first celestial body, and to displace the spacecraft to a second craft client 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 landing phases towards a third celestial body and taking-off phases from the third celestial body for a return to orbit.

2. The spacecraft according to claim 1, wherein the solar electrical energy generator comprises flexible photovoltaic cells configured to be wound and unwound about an axis.

3. The spacecraft according to any claim 1, wherein the solar electrical energy generator is equipped with a system of transferring electrical energy by at least one of wire, short distance waves, and laser.

4. The spacecraft according to claim 1, comprising a supporting structure for carrying a payload, the supporting structure being configured to be coupled and decoupled from the first container and the second container.

5. The spacecraft according to claim 1, wherein the main structure comprises at least one third fuel container intended for the chemical thruster to facilitate the spacecraft to go back into orbit from a celestial body.

6. The spacecraft according to claim 1, wherein the main structure comprises docking systems configured to couple the spacecraft to a client craft.

7. The spacecraft according to claim 1, wherein the main structure comprises landing systems configured to facilitate the spacecraft to land on a celestial body.

8. The spacecraft according to claim 1, comprising fuel transfer systems to provide refueling of the spacecraft.

9. A method for distributing electrical energy to at least one client craft located at a point in free space, in orbit or on a celestial body, using the spacecraft of claim 1, the method comprising transiting the spacecraft placed in orbit, towards a client craft located in the free space, in orbit or on a celestial body, by using the electric thruster and the solar electrical energy generator deployed after the spacecraft is placed into orbit.

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

11. The method according to claim 9, the method further comprising: placing the spacecraft into orbit around a celestial body; retracting the solar electrical energy generator: decoupling a first container from a main structure of the spacecraft; coupling the main structure to a second container; decoupling the first container from the second container; landing the spacecraft on a ground of the celestial body; deploying the solar electrical energy generator; and distributing electrical energy generated by the solar electrical energy generator to the client craft on the celestial body.

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

13. The method according to claim 12, comprising steps of: decoupling the at least one third container from the main structure; refueling, in orbit or in the free space, the electric thruster and the chemical thruster; and transiting the spacecraft to the client craft.

Description

DRAWINGS

[0050] In order that the disclosure may be well understood, there will now be described various forms thereof, given by way of example, reference being made to the accompanying drawings, in which:

[0051] FIG. 1 represents a schematic view of a spacecraft, according to a form, equipped with a main structure, a first container, a supporting structure of a payload and a second container and mounted on a launcher for placing the spacecraft in Earth's orbit according to the present disclosure;

[0052] FIG. 2 shows a schematic view of the spacecraft placed in Earth's orbit according to the present disclosure;

[0053] FIG. 3 represents a schematic view of the spacecraft in a step of retracting the solar electrical energy generator of the spacecraft which the spacecraft carries for landing on a celestial body according to the present disclosure;

[0054] FIG. 4 represents a schematic view of the spacecraft in a step of decoupling the main structure from the first container and the main structure coupling to the second container for landing on the celestial body according to the present disclosure;

[0055] FIG. 5 represents a schematic view of a step of decoupling the first container from the payload for landing on the celestial body according to the present disclosure;

[0056] FIG. 6 represents a schematic view of a step of reorienting the spacecraft for landing on the celestial body according to the present disclosure;

[0057] FIG. 7 represents a schematic view of a step of descending the spacecraft for landing on the ground of the celestial body according to the present disclosure;

[0058] FIG. 8 represents a schematic view of steps of unloading the spacecraft and distributing the electrical energy supplied by the solar electrical energy generator to a client craft according to the present disclosure;

[0059] FIG. 9 represents a schematic view of steps of launching the spacecraft into orbit from the ground of the celestial body according to the present disclosure;

[0060] FIG. 10 represents a schematic view of steps of refueling the spacecraft before sending the spacecraft to another client craft according to the present disclosure;

[0061] FIG. 11 represents a schematic view of steps of refueling the spacecraft before sending the spacecraft to another client craft according to a variant of the present disclosure;

[0062] FIG. 12 is an enlarged isometric view of the main structure of the spacecraft comprising a solar electrical energy generator in the retracted position, according to a form of the present disclosure;

[0063] FIG. 13 is an enlarged side view of the main structure of the spacecraft representing the solar electrical energy generator in the deployed position, according to a form of the present disclosure;

[0064] FIG. 14 is a top view of the main structure of the spacecraft and the solar electrical energy generator in the deployed position, according to a form of the present disclosure;

[0065] FIG. 15 is an enlarged top view of the main structure of the spacecraft shown in FIG. 14 according to the present disclosure; and

[0066] FIG. 16 is an enlarged bottom view of the main structure of the spacecraft shown in FIG. 14 according to the present disclosure.

[0067] The drawings described herein are for illustration purposes only and are not intended to limit the scope of the present disclosure in any way.

DETAILED DESCRIPTION

[0068] The following description is merely exemplary in nature and is not intended to limit the present disclosure, application, or uses. It should be understood that throughout the drawings, corresponding reference numerals indicate like or corresponding parts and features.

[0069] In FIG. 1, a spacecraft 1 is shown for distributing electrical energy to a client craft 2 at points located in the free space, in orbit and/or on a celestial body.

[0070] The spacecraft 1 comprises a main structure 10, at least one first fuel container 11, a supporting structure 13 of a payload and at least one second fuel container 12 stacked and arranged in a single launcher 3. Thus, placing the spacecraft 1 into Earth's orbit may use a single launcher 3.

[0071] The main structure 10 is equipped with thrusters, namely an electric thruster 10A and a chemical thruster 10B. Moreover, the main structure 10 is equipped with a solar electrical energy generator 10C forming an integral part of the main structure 10.

[0072] The first container 11 forms a fuel tank intended for the electric propulsion. The fuel of the first container 11 can be an inert gas, such as Xenon, argon or Krypton. The second container 12 forms a fuel tank intended for the chemical propulsion. The fuel of the second container 12 can be a monopropellant or a bipropellant, liquid and/or solid.

[0073] The supporting structure 13 is intended for carrying a payload intended for the client craft 2 or the site of the client craft 2.

[0074] In one variation, the spacecraft 1 has a modular configuration so that the spacecraft 1 can be adapted to the needs of several consecutive missions. As such, the supporting structure 13, the first container 11 and the second container 12 form a logistic stack and can be coupled or decoupled from each other. The main structure 10 can alternatively be coupled/decoupled to/from the first container 11 or to/from the second container 12.

[0075] The arrangement of the supporting structure 13 arranged between the first container 11 and the second container 12 has the advantage of enabling the main structure 10 to be able to be supplied with fuel for the electric propulsion or for the chemical propulsion.

[0076] The main structure 10 is equipped with a control unit facilitating the transit of the spacecraft 1 and these maneuvers. When the main structure 10 is coupled to the first container 11, the supply of fuel to the electric thruster 10A is facilitated, Whereas when the main structure 10 is coupled to the second container 12, the supply of fuel to the chemical thruster 10B is facilitated. The control unit is configured to provide the coupling and decoupling of the main structure 10 to one of the containers 11, 12 depending on mission needs.

[0077] In an initial configuration planned for placing the spacecraft 1 into Earth's orbit, the main structure 10 is coupled to the first container 11 for powering the electric propulsion, to facilitate the transit of the spacecraft 1 in space once in Earth's orbit.

[0078] The solar generator 10C has variable geometry. In other words, the solar generator 10C is intended to be deployed or retracted depending on mission needs. The solar generator 10C is intended to be deployed to provide the distribution of electrical energy to a client craft 2 located at a point in the free space, in orbit or on a celestial body, and retracted to allow the displacement of the spacecraft 1 towards another client craft 2 located at another point in the free space, in orbit or on another celestial body. The solar generator 10C may comprise flexible photovoltaic cells or a flexible canvas of photovoltaic cells that can be wound and unwound about the same axis, so that the unwound cells cover a large surface of solar radiation. Thus, such photovoltaic cells significantly increase the production and distribution capacity of electrical energy of the spacecraft 1.

[0079] Successive missions using the spacecraft 1, according to a form, facilitate the distribution of electrical energy to client crafts 2 at points in the free space, in orbit or on a celestial body. The configuration of FIG. 1 represents a spacecraft 1 placed in a launcher 3 to place the spacecraft 1 in Earth's orbit from a launch site.

[0080] 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 the placement phase of the spacecraft 1 in Earth's orbit.

[0081] FIG. 2 shows the spacecraft 1 in Earth's orbit where the spacecraft 1 was detached from the base 30 of the launcher 3 and separated from the launcher 3. Once placed in Earth's orbit, the solar generator 10C can be deployed. A step of transferring the spacecraft 1 to a client craft 2 can then be initiated using electric propulsion powered by the electrical energy supplied by the deployed solar generator 10C and by the fuel from the first container 11 to which the main structure 10 is coupled.

[0082] In a configuration of a first mission intended to distribute the electrical energy to a first client craft 2 (see FIG. 8) in the free space or in orbit, docking systems can be provided for coupling the spacecraft 1 to the client craft 2.

[0083] The solar generator 10C is equipped with a system of transferring electrical energy by wire and/or by short distance waves and/or by laser and can, once deployed, distribute the electrical energy to the client craft 2. During the docking phase the solar generator 10C will be retracted and deployed once the docking phase is completed. The spacecraft 1 can then carry out an electrical energy distribution mission successively to the one the spacecraft 1 has just accomplished. The spacecraft 1 can be directed towards a celestial body such as the Moon on which a second client craft 2 is placed on the ground. The spacecraft 1 is first placed into orbit around the celestial body comprising the second client craft 2. Then, as illustrated in FIG. 3, the solar electrical energy generator 10C is retracted to prepare the landing phase of the spacecraft 1 on the ground of the celestial body. The spacecraft 1 comprises landing systems configured to provide the landing phase. For example, the spacecraft 1 comprises a landing gear 16 (see FIG. 6).

[0084] As shown in FIG. 4, the main structure 10 is then decoupled from the first container 11 and the main structure 10 is controlled to facilitate the coupling of the main structure 10 to the second container 12. Then, the first container 11 can be decoupled from the second container 12 (FIG. 5). The spacecraft 1 thus configured comprises the supporting structure 13 of the payload coupled to the second container 12. The spacecraft 1 is suitable for carrying out a landing phase of the spacecraft 1 on the ground of the celestial body since the spacecraft 1 facilitates the use of the chemical propulsion.

[0085] FIG. 6 illustrates reorienting the spacecraft 1 in orbit to prepare the exit of the spacecraft 1 from orbit and the landing of the spacecraft 1 on the celestial body. FIG. 7 illustrates the landing phase of the spacecraft 1 on the celestial body. The spacecraft 1 illustrated in FIGS. 6 and 7 comprises the landing gear 16 in the open position.

[0086] As shown in FIG. 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. The solar electrical energy generator 10C can then be deployed for the distribution of electrical energy to the client craft 2. The spacecraft 1 can once again carry out an electrical energy distribution mission successively to the one the spacecraft 1 has just accomplished. For example, the spacecraft 1 can be directed towards another celestial body on which a third client craft 2 is placed on the ground. For directing the spacecraft 1 towards another celestial body, the solar generator 10C is previously retracted. At least one third container 14 is provided, which can be attached to the main structure 10 or be provided from the site on which the second client craft 2 is located.

[0087] FIG. 9 illustrates placing the spacecraft 1 in orbit from the ground of the celestial body comprising the second client craft 2. When the spacecraft 1 is placed into orbit, the landing gear 16 is closed 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 the chemical propulsion. The main structure 10 can then be supplied with fuel for the chemical propulsion to facilitate the take-off of the spacecraft 1 and the placement of the spacecraft 1 into orbit around the celestial body from which the spacecraft 1 takes off.

[0088] FIG. 10 illustrates the preparation of the spacecraft 1 for continuing the electrical energy distribution mission of the spacecraft 1 towards the destination of a third client craft 2. 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 logistic stack planned for the following mission or alternatively fuel transfer systems can provide the fuel supply of the first container 11 and the second container 12 previously recovered.

[0089] The new logistic stack can 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 can be driven towards the third client craft 2 on the second celestial body according to the steps previously described.

[0090] In a form illustrated by FIG. 11, the main structure 10 can be coupled to another first fuel container 11 intended for the electric thruster 10A, provided 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 supplied by the deployed solar generator 10C and by the fuel from the first container 11 to which the main structure 10 is coupled.

[0091] FIGS. 12 to 16 are views of the main structure 10 according to a form.

[0092] FIG. 12 represents the main structure 10 in orbit, in which the solar generator 10C of electrical energy with variable geometry is retracted. In the form illustrated in FIG. 12, the solar electrical energy generator 10C comprises two canvases each formed of one or more flexible photovoltaic cells, and which are each wound about the same axis.

[0093] The main structure 10 comprises the electric thruster 10A or electric propulsion unit comprising a plurality of electric motors.

[0094] The main structure 10 comprises the chemical thruster 10B or chemical propulsion unit including a plurality of chemical motors.

[0095] The main structure 10 comprises a mooring and fuel transfer system 18 configured to provide a coupling/decoupling between the main structure 10 and the fuel containers 11, 12, 14 to provide the transfer of fuel.

[0096] In the form illustrated in FIG. 12, the landing gear 16 is retracted into the retracted position (not visible).

[0097] FIG. 13 illustrates the main structure 10 on the ground, for example, placed on the ground of a celestial body in which the solar electrical energy generator 10C with variable geometry is deployed.

[0098] In the form illustrated by FIGS. 13 to 16, the solar electrical energy generator 10C comprises two canvases of flexible photovoltaic cells which are each unwound.

[0099] The landing gear 16 is deployed, in the open position, to provide the landing of the main structure 10 and maintenance of the main structures 10 on the ground of a celestial body (such as the Moon).

[0100] FIGS. 14 and 15 are top views of the main structure 10 with the solar electrical energy generator 10C with deployed variable geometry.

[0101] In the form illustrated by FIGS. 12, 13 and 16, the main structure 10 comprises an electric thruster 10A including several electric motors forming an electric propulsion unit. The main structure 10 comprises a chemical thruster 10B including the chemical motors forming a chemical propulsion unit.

[0102] As illustrated in FIG. 15, the main structure 10 may comprise a rotating orientation device 20 to drive the solar electrical energy generator 10C in rotation about a vertical or longitudinal axis A. For example, the rotating device 20 is configured to cause the rotation of the winding of photovoltaic cells over 360? about the longitudinal or vertical axis A. The rotating device facilitates the tracking of the position of the sun and orientation of the photovoltaic cells towards the sun.

[0103] In the forms illustrated by FIGS. 12 to 16, the spacecraft 1 comprises an optional energy dissipation device. For example, the energy dissipation device comprises two radiators 22, 22 which each extend over half of the surface of the main structure 10 to offer an increased available surface around the main structure 10.

[0104] 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. In one aspect, the different characteristics, shapes, variants, and forms can be associated with each other in various combinations to the extent that they are not incompatible or exclusive of each other. In one aspect, all the variants and forms described above can be combined with each other.

[0105] Unless otherwise expressly indicated herein, all numerical values indicating mechanical/thermal properties, compositional percentages, dimensions and/or tolerances, or other characteristics are to be understood as modified by the word about or approximately in describing the scope of the present disclosure. This modification is desired for various reasons including industrial practice, material, manufacturing, and assembly tolerances, and testing capability.

[0106] As used herein, the phrase at least one of A, B, and C should be construed to mean a logical (A OR B OR C), using a non-exclusive logical OR, and should not be construed to mean at least one of A, at least one of B, and at least one of C.

[0107] The description of the disclosure is merely exemplary in nature and, thus, variations that do not depart from the substance of the disclosure are intended to be within the scope of the disclosure. Such variations are not to be regarded as a departure from the spirit and scope of the disclosure.