SYSTEMS AND METHODS FOR SPACECRAFT REPROVISIONING

Abstract

A reprovisionable spacecraft and reprovisioning subassemblies for mating with a reprovisionable spacecraft are both described. The reprovisionable spacecraft has one or more mechanical, thermal, data, and or electrical mating interfaces for attaching, powering, and communicating with a reprovisioning subassembly, which for one embodiment is a self-contained thruster unit. The self-contained thruster unit preferably comprises a fuel tank, control electronics, and a thruster assembly. Alternately, a reprovisioning subassembly can comprise a fuel tank and control electronics, a fuel tank, or a thruster. Also, a reprovisionable spacecraft may be carried into orbit without reprovisioning subassemblies attached, and then deployed after reprovisioning subassemblies have been attached to their respective mating interfaces. Reprovisioning utilizing a self-contained thruster unit or tank eliminates the large risk associated with refueling satellites in space. Reprovisioning also eliminates the need for a dedicated attached life extension vehicle.

Claims

1. A reprovisionable spacecraft, comprising: one or more mating interfaces, each of the one or more mating interfaces comprising: a mechanical interface and at least one of: an electrical interface, a data communication interface, and a thermal control interface; wherein the one or more mating interfaces are utilized in attaching respective reprovisioning subassemblies to the reprovisionable spacecraft, each of the respective reprovisioning subassemblies including at least one of: a fuel tank, an electronic subassembly, and a radio frequency subassembly; wherein, when at least one of the reprovisioning subassemblies includes a fuel tank, the one or more mating interfaces comprises an internal fuel flow interface whereby once attached to the reprovisionable spacecraft, an internal fuel flow may be activated; and wherein each of the one or more mating interfaces comprises a detachment mechanism such that the reprovisioning subassembly may be detached or robotically removed.

2. The reprovisionable spacecraft of claim 1, the one or more reprovisioning subassemblies includes the fuel tank, wherein the detachment mechanism provides for detaching or robotically removing the reprovisioning subassembly when a fuel supply in the fuel tank is exhausted.

3. The reprovisionable spacecraft of claim 1, wherein the detachment mechanism provides for detaching or robotically removing the reprovisioning subassembly when at least one of the mechanical interface, the electrical interface, the communication interface, and the thermal control interface needs to be replaced.

4. The reprovisionable spacecraft of claim 1, wherein each of the respective reprovisioning subassemblies comprises control electronics for controlling the fuel flow interface and for controlling the detachment mechanism.

5. The reprovisionable spacecraft of claim 4, wherein each of the respective reprovisioning subassemblies comprises a thruster unit, and the control electronics comprise control for activating and controlling the thruster unit.

6. The reprovisionable spacecraft of claim 1, wherein after a replacement of one or more of the respective reprovisioning subassemblies attached to the reprovisionable spacecraft, a center of mass of the complete reprovisionable spacecraft comprising all reprovisioning subassemblies, remains the same as when the reprovisionable spacecraft was initially deployed.

7. The reprovisionable spacecraft of claim 1, wherein the respective reprovisioning subassemblies are operable to be attached robotically to the reprovisionable spacecraft.

8. The reprovisionable spacecraft of claim 1, wherein the respective reprovisioning subassemblies are configured for robotic connection and manipulation.

9. A reprovisionable spacecraft, comprising: one or more mating interfaces, each of the one or more mating interfaces comprising at least one of: a mechanical interface, an electrical interface, a data communication interface, and a thermal control interface; wherein the one or more mating interfaces are utilized in attaching respective reprovisioning subassemblies to the reprovisionable spacecraft, each of the respective reprovisioning subassemblies including a fuel tank; wherein, the one or more mating interfaces comprises an internal fuel flow interface whereby once attached to the reprovisionable spacecraft, an internal fuel flow may be activated; and wherein each of the one or more mating interfaces comprises a detachment mechanism such that the reprovisioning subassembly may be detached or robotically removed.

10. The reprovisionable spacecraft of claim 9, the one or more reprovisioning subassemblies includes the fuel tank, wherein the detachment mechanism provides for detaching or robotically removing the reprovisioning subassembly when a fuel supply in the fuel tank is exhausted.

11. The reprovisionable spacecraft of claim 9, wherein the reprovisioning subassemblies include at least one of: an electronic subassembly, and a radio frequency subassembly

12. The reprovisionable spacecraft of claim 11, wherein the detachment mechanism provides for detaching or robotically removing the reprovisioning subassembly when at least one of the mechanical interface, the electrical interface, the communication interface, and the thermal control interface needs to be replaced.

13. The reprovisionable spacecraft of claim 9, wherein each of the respective reprovisioning subassemblies comprises control electronics for controlling the fuel flow interface and for controlling the detachment mechanism.

14. The reprovisionable spacecraft of claim 13, wherein each of the respective reprovisioning subassemblies comprises a thruster unit, and the control electronics comprise control for activating and controlling the thruster unit.

15. The reprovisionable spacecraft of claim 9, wherein after a replacement of one or more of the respective reprovisioning subassemblies attached to the reprovisionable spacecraft, a center of mass of the complete reprovisionable spacecraft comprising all reprovisioning subassemblies, remains the same as when the reprovisionable spacecraft was initially deployed.

16. The reprovisionable spacecraft of claim 9, wherein the respective reprovisioning subassemblies are operable to be attached robotically to the reprovisionable spacecraft.

17. The reprovisionable spacecraft of claim 9, wherein the respective reprovisioning subassemblies are configured for robotic connection and manipulation.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0013] The aspects are illustrated by way of example and not by way of limitation in the figures of the accompanying drawings in which like references indicate similar elements. It should be noted that references to an or one aspect in this disclosure are not necessarily to the same aspect, and they mean at least one.

[0014] FIG. 1A shows a reprovisionable spacecraft with a reprovisioning subassembly attached.

[0015] FIG. 1B shows a reprovisionable spacecraft with a reprovisioining subassembly being removed or re-attached.

[0016] FIG. 2 shows an enlargement of an interface connection between a reprovisionable spacecraft and a reprovisioning subassembly.

[0017] FIG. 3 shows the components of a reprovisionable subassembly.

[0018] FIG. 4 shows an exemplary process for reprovisioning of a spacecraft using reprovisioning subassemblies.

[0019] FIG. 5 shows an exemplary process for initial assembly in space where reprovisioning subassemblies are attached for the first time to a spacecraft.

DETAILED DESCRIPTION

[0020] In this section we shall explain several preferred aspects of this invention with reference to the appended drawings. Whenever the shapes, relative positions and other aspects of the parts described in the aspects are not clearly defined, the scope of the invention is not limited only to the parts shown, which are meant merely for the purpose of illustration. Also, while numerous details are set forth, it is understood that some aspects of the invention may be practiced without these details. In other instances, well-known structures and techniques have not been shown in detail so as not to obscure the understanding of this description.

[0021] The terminology used herein is for the purpose of describing particular aspects only and is not intended to be limiting of the invention. Spatially relative terms, such as beneath, below, lower, above, upper, and the like may be used herein for ease of description to describe one element's or feature's relationship to another element(s) or feature(s) as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as below or beneath other elements or features would then be oriented above the other elements or features. Thus, the exemplary term below can encompass both an orientation of above and below. The device may be otherwise oriented (e.g., rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.

[0022] As used herein, the singular forms a, an, and the are intended to include the plural forms as well, unless the context indicates otherwise. It will be further understood that the terms comprises and/or comprising specify the presence of stated features, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, steps, operations, elements, components, and/or groups thereof.

[0023] The terms or and and/or as used herein are to be interpreted as inclusive or meaning any one or any combination. Therefore, A, B or C or A, B and/or C mean any of the following: A; B; C; A and B; A and C; B and C; A, B and C. An exception to this definition will occur only when a combination of elements, functions, steps or acts are in some way inherently mutually exclusive.

[0024] A reprovisionable spacecraft and reprovisioning subassemblies for mating with a reprovisionable spacecraft are both described. The reprovisionable spacecraft has one or more mechanical, thermal, data, and or electrical mating interfaces for attaching, powering, and communicating with a reprovisioning subassembly, which for one embodiment is a self-contained thruster unit. The self-contained thruster unit preferably comprises a fuel tank, control electronics, a thruster assembly, a structure, a thermal subsystem for controlling the thermal environment for the thruster and electronics), and robotic interfaces for attachment and/or detachment. Alternately, a reprovisioning subassembly can comprise a fuel tank and control electronics, or just a fuel tank, and robotic interfaces for attachment and/or detachment. Also, a reprovisionable spacecraft may be carried into orbit without reprovisioning subassemblies attached, and then deployed after reprovisioning subassemblies have been attached to their respective mating interfaces. Reprovisioning utilizing a self-contained thruster unit or tank eliminates the large risk associated with refueling satellites in space. Reprovisioning also eliminates the need for a dedicated attached life extension vehicle.

[0025] Introducing the term Reprovisioning starts by examining the term Provisioning which is to provide (in the current context) fuel for a spacecraft for the reasons previously described. To Reprovision is to provide an appendage (a reprovisioning subassembly) including fuel and/or a fuel/thruster/controller combination which typically replaces the original subassembly with a self-contained fully fueled replacement, for some embodiments including a new thruster/controller. Note that embodiments of a reprovisioning subassembly require and include a structure that other components of the reprovisioning subassembly are mounted on or connected to. For one embodiment subsequently described in detail herein a subassembly, containing a cooperative robotic interface connection (which can comprise mechanical, electrical, data, and/or thermal interfaces) is connected to a like cooperative robotic interface connection. The reprovisioning subassembly involved can either be intrinsic (a modular part of the original spacecraft design) or extrinsic (not part of the original spacecraft design). The fuel/engine/controller appendage in another embodiment can also be fitted uncooperatively to a client spacecraft through a simple mechanical interface on the reprovisioning subassembly where it remains until replaced or exhausted. The reprovisioning subassembly is not an independent spacecraft. It is controlled by the client spacecraft after installation.

[0026] FIG. 1A shows a spacecraft 102 with a reprovisioning subassembly 106 attached through mating interface 104. Reprovisioning subassembly 106 may be detached from mating interface 104 during a reprovisioning operation whereby the detached reprovisioning subassembly is discarded and replaced with a new reprovisioning subassembly 106 which is complete with integral fuel supply. Also shown in FIG. 1A is payload 108 which may comprise for example but not limited to transponders, antennas, batteries, etc.

[0027] For further reference, FIG. 1B shows the spacecraft with payload units 108 that can be replaceable. For example, the payload 108 can be transponders, antennas, batteries, or any other suitable payload as recognized by a skilled artisan. Herein, the payload 108 can be another type of reprovisioning subassembly with one or more mating interfaces for attaching respective reprovisioning subassemblies to the reprovisionable spacecraft 102. Here, the payload element 108 can include a fuel tank and or other types of subassemblies, such as an electronic subassembly, a radio frequency subassembly or any other suitable type of subassembly. As part of the reprovisioning, each of the one or more mating interfaces comprises a detachment mechanism such that the reprovisioning subassembly may be detached or robotically removed. The detachment mechanism can provide for detaching or robotically removing the reprovisioning subassembly when at least one of the mechanical interface, the electrical interface, the communication interface, and the thermal control interface needs to be replaced.

[0028] FIG. 2 shows an enlargement of mating interface 104 which connects spacecraft 102 with reprovisioning assembly 106. Mating interface 104 comprises a first component 202 attached to spacecraft 102 and a second component 204 attached to reprovisioning assembly 106. First component 202 of mating interface 104 may comprise a number of connector types, optionally including a Langley-type connector. Also, a pointing mechanism 206 may be optionally included between spacecraft 102 and mating interface component 202 which may be controlled robotically to aid in the process of attaching a new reprovisioning subassembly 106 during reprovisioning operations.

[0029] FIG. 3 shows a reprovisioning subassembly 106 and some possible components. Typically, a reprovisioning subassembly will include a fuel tank 304 which prior to a reprovisioning operation contains a fuel supply. Reprovisioning subassembly 106 may also include control electronics 302 which can control or assist in controlling the reprovisioning process or a number of functions including for example docking operations. Control electronics 302 on reprovisioning subassembly 106 also communicates as required with spacecraft 102. This communication can be performed by either wired or wireless communication using methods known in the art.

[0030] A thruster mechanism 306 may be included and is typically controlled at least in part by control electronics 302. At the top of reprovisioning subassembly 106 in FIG. 3 is a component 204 of mating interface 104 that allows connection with a spacecraft. Fuel tank 304 may contain any of a variety of fuel types including but without limitation solid fuel, liquid fuel, and/or gas such as xenon which may be used to power a thruster using ion propulsion techniques.

[0031] FIG. 4 shows one exemplary process for reprovisioning of a spacecraft using reprovisioning subassemblies. In step 402, one or more first reprovisioning subassemblies are transported into orbit. In step 404, the first reprovisioning subassemblies are positioned in proximity to the spacecraft to be reprovisioned. In step 406, a mating interface on each of one or more second reprovisioning subassemblies currently attached to the spacecraft is activated to cause detachment of the second reprovisioning subassemblies from their respective mating interfaces on the spacecraft. The one or more second reprovisioning subassemblies, in one embodiment, can include an original subassembly. In step 408, each of the first reprovisioning subassemblies is attached to a respective mating interface on the spacecraft, wherein the respective mating interface was previously occupied by a second reprovisioning subassembly. In step 410, a fuel flow interface on each of the first reprovisioning subassemblies is activated to allow fuel to flow to the thruster as and when required. After replacement of the one or more second reprovisioning subassemblies with the one or more first reprovisioning subassemblies attached to the reprovisionable spacecraft, a center of mass of the complete reprovisionable spacecraft, including all reprovisioning subassemblies, remains the same as when the reprovisionable spacecraft was initially deployed.

[0032] FIG. 5 shows an exemplary process for initial assembly in space where reprovisioning subassemblies are attached for the first time to a spacecraft. In step 502, one or more first reprovisioning subassemblies are transported into orbit wherein each reprovisioning subassembly contains a fuel supply. In step 504, the spacecraft itself is transported into orbit, comprising either a set of unassembled components or having been completely assembled prior to launch, but with no reprovisioning subassemblies containing fuel attached to the spacecraft. In step 506 the one or more first reprovisioning subassemblies are attached to the spacecraft. In step 508, internal fuel flow is activated for each of the first reprovisioning subassemblies.

EXAMPLES

[0033] Example 1 is a reprovisioning subassembly for a reprovisionable spacecraft including at least one fuel tank; and a mating interface for attaching the reprovisioning subassembly to a reprovisionable spacecraft, wherein the mating interface includes an internal fuel flow interface whereby once attached to the reprovisionable spacecraft, fuel flow may be activated, and wherein the mating interface can detach the reprovisioning subassembly when its fuel supply has been exhausted.

[0034] In Example 2, the reprovisioning subassembly of Example 1 further includes control electronics for controlling the internal fuel flow interface; controlling a thermal environment within the reprovisioning subassembly; and controlling a detachment mechanism related to the mating interface.

[0035] In Example 3, the reprovisioning subassembly of Example 2 further includes a thruster unit, and the control electronics also include control for activating and controlling the thruster unit.

[0036] Example 4 is a method including positioning one or more reprovisioning subassemblies in proximity to a spacecraft to be reprovisioned; detaching a subassembly from a location on the spacecraft; and attaching one of the one or more reprovisioning subassemblies to the location on the spacecraft.

[0037] In Example 5, after replacement of reprovisioning subassemblies attached to the reprovisionable spacecraft, a center of mass of the complete reprovisionable spacecraft, including all reprovisioning subassemblies in the method of Example 4, remains the same as when the reprovisionable spacecraft was initially deployed.

[0038] In Example 6, the one of the one or more reprovisioning subassemblies in the method of Example 4 is attached robotically to the spacecraft.

[0039] In Example 7, the one of the one or more reprovisioning subassembly in the method of Example 4 is configured for robotic connection and manipulation.

[0040] Example 8 is a reprovisionable spacecraft, including one or more mating interfaces, each of the one or more mating interfaces including a mechanical interface; an electrical interface; a data communication interface; and a thermal control interface, wherein the one or more mating interfaces are utilized in attaching respective reprovisioning subassemblies thereto, each of the respective reprovisioning subassemblies including at least a fuel tank; wherein each of the one or more mating interfaces includes an internal fuel flow interface whereby once attached to the reprovisionable spacecraft, fuel flow may be activated; and wherein each of the one or more mating interfaces includes a detachment mechanism such that the reprovisioning subassembly may be detached or robotically removed when its fuel supply has been exhausted.

[0041] In Example 9, each of the respective reprovisioning subassemblies of the reprovisionable spacecraft of Example 8 includes control electronics for controlling the fuel flow interface and for controlling the detachment mechanism.

[0042] In Example 10, each of the respective reprovisioning subassemblies of the reprovisionable spacecraft of Example 9 includes a thruster unit, and the control electronics include control for activating and controlling the thruster unit.

[0043] In Example 11, after a replacement of one or more of the respective reprovisioning subassemblies attached to the reprovisionable spacecraft, a center of mass of the complete reprovisionable spacecraft including all reprovisioning subassemblies of the reprovisionable spacecraft of Example 8, remains the same as when the reprovisionable spacecraft was initially deployed.

[0044] In Example 12, the respective reprovisioning subassemblies of the reprovisionable spacecraft of Example 8 are operable to be attached robotically to the reprovisionable spacecraft.

[0045] In Example 13, the respective reprovisioning subassemblies of the reprovisionable spacecraft of Example 8 are configured for robotic connection and manipulation.

[0046] Example 14 is a method for reprovisioning a reprovisionable spacecraft, including transporting one or more first reprovisioning subassemblies into orbit; positioning the one or more first reprovisioning subassemblies in proximity with a reprovisionable spacecraft, wherein the reprovisionable spacecraft has one or more mating interfaces for attaching first or second reprovisioning subassemblies thereto, and wherein the first or second reprovisioning subassemblies each include at least a fuel tank initially containing a fuel supply; activating a mating interface on each of the one or more second reprovisioning subassemblies attached to the reprovisionable spacecraft, to detach each of the second reprovisioning subassemblies from their respective mating interface on the reprovisionable spacecraft; attaching each of the one or more first reprovisioning subassemblies to a respective mating interface on the reprovisionable spacecraft, the mating interface previously occupied by a second reprovisioning subassembly; and activating at least an internal fuel flow interface on each of the first reprovisioning subassemblies.

[0047] In Example 15, each of the first and second reprovisioning subassemblies of the method of Example 14 includes control electronics for controlling the internal fuel flow interface and for controlling the detachment mechanism.

[0048] In Example 16, each of the first and second reprovisioning subassemblies of the method of Example 15 includes a thruster unit, and the control electronics include control for activating and controlling the thruster unit.

[0049] In Example 17, after replacement of all second reprovisioning subassemblies initially attached to the reprovisionable spacecraft with first reprovisioning subassemblies, a center of mass of the complete reprovisionable spacecraft, including all reprovisioning subassemblies of the method of Example 14, remains the same with first reprovisioning subassemblies attached as it previously was when the second reprovisioning subassemblies were initially attached.

[0050] In Example 18, the first and second reprovisioning subassemblies of the method of Example 14 are attached robotically to the reprovisionable spacecraft.

[0051] In Example 19, the first and second reprovisioning subassemblies of the method of Example 14 are configured for robotic connection and manipulation.

[0052] Example 20 is a method for initially assembly in space of a reprovisionable spacecraft, including transporting one or more first reprovisioning subassemblies, each containing a fuel supply, into orbit; transporting a reprovisionable spacecraft into orbit, wherein when transported, there are no fuel-containing reprovisioning subassemblies attached to the reprovisionable spacecraft; attaching the one or more first reprovisioning subassemblies to the reprovisionable spacecraft.

[0053] In Example 21, each of the first reprovisioning subassemblies of the method of Example 20 includes control electronics for controlling the internal fuel flow interface and for controlling the detachment mechanism.

[0054] In Example 22, each of the first reprovisioning subassemblies of the method of Example 21 includes a thruster unit, and the control electronics also include control for activating and controlling the thruster unit.

[0055] In Example 23, after attachment of all first reprovisioning subassemblies to the reprovisionable spacecraft, a center of mass of the complete reprovisionable spacecraft, including all reprovisioning subassemblies of the method of Example 20, is an optimum center of mass per a stated design goal.

[0056] In Example 24, the first reprovisioning subassemblies of the method of Example 20 are attached robotically to the reprovisionable spacecraft.

[0057] In Example 25, the first reprovisioning subassemblies of the method of Example 20 are configured for robotic connection and manipulation.

[0058] In Example 26, the first reprovisioning subassemblies of the method of Example 20 are attached and activated robotically.

[0059] While certain aspects have been described and shown in the accompanying drawings, it is to be understood that such embodiments are merely illustrative of and not restrictive on the broad invention, and that the invention is not limited to the specific constructions and arrangements shown and described, since various other modifications may occur to those of ordinary skill in the art. The description is thus to be regarded as illustrative instead of limiting.