Near-cylindrically deployable system

Abstract

The present disclosure relates to a spacecraft including a near-cylindrically deployable system (100) adapted to toggle between a stowed configuration and a deployed configuration. The deployable system includes a central body (102), a plurality of linkages (104), and a plurality of panels (106). The plurality of linkages (104) may be disposed around the central body (102). Each of the plurality of linkages (104) includes a first end connected to a periphery of the central body (102). The plurality of panels (106) may be disposed radially around the central body (102). Each of the plurality of panels (106) includes a first edge (106-1) and a second edge (106-2). The first edge (106-1) may be hinged to the first edge of an adjacent panel of the plurality of panels (106). The second edge (106-2) may be hinged to a second end of a linkage of the plurality of linkages (104).

Description

[0001] NEAR-CYLINDRICALLY DEPLOYABLE SYSTEM

[0002] TECHNICAL FIELD

[0003] The present disclosure relates to a deployable system and more particularly, the present disclosure relates to a near-cylindrically deployable system.

[0004] BACKGROUND

[0005] Existing solar panel configurations in a spacecraft are planar configurations and call for continuous sun -locking maneuvering of a holder object. Often, they are asymmetric and cause offsets in the Centre of Gravity (CG) of a stack either in stowed condition or upon deployment. In the case of a satellite or terminal stage of a rocket, such CG offsets demand either balancing mass or a control action for maintaining orientation.

[0006] US patent 3817481 explains a deployable solar array for a spin-stabilized spacecraft having thin flexible solar panels. The solar panels are spaced circumferentially about the spacecraft body, and deployment means are secured to the ends of each panel for effecting centrifugal deployment of the panels from a launch configuration. In the launch configuration, the panels are drawn firmly against the body to conform to the circumferential surface to a deployed configuration. Herein, the panels are disposed outwardly from the body, at least between the panel ends, to provide a solar array having an effective area substantially exceeding the circumferential surface area of the body.

[0007] The ends of the solar panels are wound on rotary drums from which the panels unwind during deployment in such a way that the deployed panels have a lobe-like, or a wing-like configurations and the three panels may be retracted to stowed configuration and deployed any number of times in the flight. Alternatively, the ends of the solar panels are attached to cables which are payed out from the spacecraft to deploy the panels. The panels of the latter embodiment may be joined end to end so as to deploy to an annular panel structure surrounding the body in an outwardly spaced relation to the body. Further, the cables are attached to drums on the spacecraft body on which both the cables and panels may wind to permit both deployment and retraction of the panels in flight.

[0008] The main limitation of this prior art is the dependence on the spinning of the spacecraft, as its deployed shape is achieved through the centrifugal force of the spin. It cannot employ rigid panels. It has a number of elements such as multiple cavities, drums, motors etc., which demand extra space inside the holding object.

[0009] Therefore, in view of the above-mentioned problems, it is desirable to provide a system that can inherently eliminate one or more of the above-mentioned problems associated with the existing art. SUMMARY

[0010] This summary is provided to introduce a selection of concepts, in a simplified format, that are further described in the detailed description of the invention. This summary is neither intended to identify key or essential inventive concepts of the invention nor intended to determine the scope of the invention.

[0011] In an embodiment, the present disclosure relates to a spacecraft including a deployable system adapted to toggle between a stowed configuration and a deployed configuration. The deployable system includes a central body and a plurality of linkages disposed around the central body. Each of the plurality of linkages comprises a first end connected to a periphery of the central body. The spacecraft also includes a plurality of panels disposed radially around the central body. Each of the plurality of panels includes a first edge hinged to a first edge of an adjacent panel of the plurality of panels and a second edge hinged to a second end of a linkage of the plurality of linkages. Further, the plurality of panels is adapted to form a star polygon shape in a stowed configuration, and the respective second edge of the plurality of panels is adapted to pivot relative to a movement of the plurality of linkages to form a near- cylindrical shape in the deployed configuration.

[0012] Another embodiment of the present disclosure relates to a deployable system adapted to toggle between a stowed configuration and a deployed configuration. The deployable system includes a central body and a plurality of linkages disposed around the central body. Each of the plurality of linkages comprises a first end connected to a periphery of the central body. The deployable system also includes a plurality of panels disposed radially around the central body. Each of the plurality of panels includes a first edge hinged to a first edge of an adjacent panel of the plurality of panels and a second edge hinged to a second end of a linkage of the plurality of linkages. Further, the plurality of panels is adapted to form a star polygon shape in a stowed configuration, and the respective second edge of the plurality of panels is adapted to pivot relative to a movement of the plurality of linkages to form a near-cylindrical shape in the deployed configuration.

[0013] According to the present disclosure, the linkages allow seamless toggling of the panel between the stowed configuration and the deployed configuration. Moreover, the panels in stowed configuration have 20% or more compaction in diameter compared to the deployed configuration. Moreover, the deployable system is a standalone unit, and can be mounted external to the central holding body and does not require any space inside the central body, such that the central body need not be dedicated exclusively for the holding purpose alone and the central body can be a propellant tank, a structure carrying payloads atop, or a vestibule between two modules of a space station, etc. Further, the central body can support the panels on its external surface, without affecting its own function.

[0014] To further clarify the advantages and features of the present disclosure, a more particular description of the invention will be rendered by reference to specific embodiments thereof, which are illustrated in the appended drawings. It is appreciated that these drawings depict only typical embodiments of the invention and are therefore not to be considered limiting of its scope. The invention will be described and explained with additional specificity and detail in the accompanying drawings.

[0015] BRIEF DESCRIPTION OF THE DRAWINGS

[0016] These and other features, aspects, and advantages of the present disclosure will become better understood when the following detailed description is read with reference to the accompanying drawings in which like characters represent like parts throughout the drawings, wherein:

[0017] Figure 1 illustrates a top view and a perspective view of a spacecraft including near- cylindrically deployable system in a stowed configuration, according to an embodiment of the present disclosure;

[0018] Figure 2 illustrates a top view and a perspective view of the spacecraft including near- cylindrically deployable system in a deployed configuration, according to an embodiment of the present disclosure;

[0019] Figure 3 illustrates different spacecrafts having different numbers of panels, according to an embodiment of the present disclosure; and

[0020] Figure 4 illustrates a scissor mechanism of a plurality of linkages of the spacecraft, according to an embodiment of the present disclosure.

[0021] Further, skilled artisans will appreciate that elements in the drawings are illustrated for simplicity and may not have necessarily been drawn to scale. For example, the flow charts illustrate the method in terms of the most prominent steps involved to help to improve understanding of aspects of the present invention. Furthermore, in terms of the construction of the device, one or more components of the device may have been represented in the drawings by conventional symbols, and the drawings may show only those specific details that are pertinent to understanding the embodiments of the present invention so as not to obscure the drawings with details that will be readily apparent to those of ordinary skill in the art having the benefit of the description herein. DETAILED DESCRIPTION OF FIGURES

[0022] For the purpose of promoting an understanding of the principles of the invention, reference will now be made to the embodiment illustrated in the drawings and specific language will be used to describe the same. It will nevertheless be understood that no limitation of the scope of the invention is thereby intended, such alterations and further modifications in the illustrated system, and such further applications of the principles of the invention as illustrated therein being contemplated as would normally occur to one skilled in the art to which the invention relates. Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skilled in the art to which this invention belongs. The system, methods, and examples provided herein are illustrative only and not intended to be limiting.

[0023] The term “some” as used herein is defined as “none, or one, or more than one, or all.” Accordingly, the terms “none,” “one,” “more than one,” “more than one, but not all” or “all” would all fall under the definition of “some.” The term “some embodiments” may refer to no embodiments or to one embodiment or to several embodiments or to all embodiments. Accordingly, the term “some embodiments” is defined as meaning “no embodiment, or one embodiment, or more than one embodiment, or all embodiments.”

[0024] The terminology and structure employed herein are for describing, teaching and illuminating some embodiments and their specific features and elements and do not limit, restrict or reduce the spirit and scope of the claims or their equivalents.

[0025] More specifically, any terms used herein such as but not limited to “includes,” “comprises,” “has,” “consists,” and grammatical variants thereof do NOT specify an exact limitation or restriction and certainly do NOT exclude the possible addition of one or more features or elements, unless otherwise stated, and furthermore must NOT be taken to exclude the possible removal of one or more of the listed features and elements, unless otherwise stated with the limiting language “MUST comprise” or “NEEDS TO include.”

[0026] Whether or not a certain feature or element was limited to being used only once, either way, it may still be referred to as “one or more features” “one or more elements” “at least one feature” or “at least one element.” Furthermore, the use of the terms “one or more” or “at least one” feature or element does NOT preclude there being none of that feature or element, unless otherwise specified by limiting language such as “there NEEDS to be one or more . . . ” or “one or more element is REQUIRED.” Unless otherwise defined, all terms, and especially any technical and / or scientific terms, used herein may be taken to have the same meaning as commonly understood by one having an ordinary skill in the art.

[0027] Reference is made herein to some “embodiments.” It should be understood that an embodiment is an example of a possible implementation of any features and / or elements presented in the attached claims. Some embodiments have been described for the purpose of illuminating one or more of the potential ways in which the specific features and / or elements of the attached claims fulfil the requirements of uniqueness, utility, and non-obviousness.

[0028] Use of the phrases and / or terms such as but not limited to “a first embodiment,” “a further embodiment,” “an alternate embodiment,” “one embodiment,” “an embodiment,” “multiple embodiments,” “some embodiments,” “other embodiments,” “a further embodiment”, “furthermore embodiment”, “additional embodiment” or variants thereof do NOT necessarily refer to the same embodiments. Unless otherwise specified, one or more particular features and / or elements described in connection with one or more embodiments may be found in one embodiment or may be found in more than one embodiment, or may be found in all embodiments, or may be found in no embodiments. Although one or more features and / or elements may be described herein in the context of only a single embodiment, or alternatively in the context of more than one embodiment, or further alternatively in the context of all embodiments, the features and / or elements may instead be provided separately or in any appropriate combination or not at all. Conversely, any feature and / or element described in the context of separate embodiments may alternatively be realized as existing together in the context of a single embodiment.

[0029] Any particular and all details set forth herein are used in the context of some embodiments and therefore should NOT be necessarily taken as limiting factors to the attached claims. The attached claims and their legal equivalents can be realized in the context of embodiments other than the ones used as illustrative examples in the description below.

[0030] Embodiments of the present disclosure will be described below in detail with reference to the accompanying drawings.

[0031] Further, skilled artisans will appreciate those elements in the drawings are illustrated for simplicity and may not have necessarily been drawn to scale. For example, the flow charts illustrate the method in terms of the most prominent steps involved to help to improve understanding of aspects of the present disclosure. Furthermore, in terms of the construction of the device, one or more components of the device may have been represented in the drawings by conventional symbols, and the drawings may show only those specific details that are pertinent to understanding the embodiments of the present disclosure so as not to obscure the drawings with details that will be readily apparent to those of ordinary skill in the art having the benefit of the description herein.

[0032] Figure 1 illustrates a top view and a perspective view of a spacecraft including a near- cylindrically deployable system 100 in a stowed configuration, according to an embodiment of the present disclosure. Figure 2 illustrates a top view and a perspective view of the spacecraft in a near-cylindrically deployed configuration, according to an embodiment of the present disclosure. Referring to Figures 1 and 2, the spacecraft may include a deployable system 100 adapted to toggle between the stowed configuration and the deployed configuration. In an embodiment, the deployable system 100 may be coupled with the spacecraft such as a satellite, one or more spent terminal stages of a rocket in orbit, space stations, etc. In another embodiment, the deployable system 100 and the spacecraft may be an integral unit. Herein, the spacecraft and the deployable system 100 may have similar construction. Therefore, for the sake of readability, the constructional and functional details of the deployable system 100 are explained in subsequent paragraphs.

[0033] The deployable system 100 includes a central body 102, a plurality of linkages 104 disposed around the central body 102, and a plurality of panels 106. In an embodiment, the central body 102 may have a circular shape, without departing from the scope of the present disclosure. Herein, the central body 102 may be embodied as a holder object, without departing from the scope of the present disclosure.

[0034] The plurality of panels 106 may be disposed radially around the central body 102. Each of the plurality of panels 106 may include a first edge 106-1 and a second edge 106-2 opposite to the first edge 106-1. The first edge 106-1 may be hinged to a first edge of an adjacent panel of the plurality of panels 106. The second edge 106-2 of each of the panels 106 may be hinged to a second end of a linkage of the plurality of linkages 104.

[0035] Further, the plurality of panels 106 may be adapted to form a star polygon shape in the stowed configuration, and the respective second edge 106-2 of the plurality of panels 106 is adapted to pivot relative to a movement of the plurality of linkages 104 to form the near cylindrical shape in the deployed configuration. Thus, in the stowed configuration as shown in Figure 1, the plurality of panels 106 forms the star polygon shape. In the deployed configuration as shown in Figure 2, the plurality of panels 106 forms the near-cylindrical shape. Herein, the plurality of panels 106 moves radially relative to the periphery of the central body 102 to toggle between the stowed configuration and the deployed configuration. Each of the plurality of panels 106 may be embodied as a solar panel, without departing from the scope of the present disclosure. In a non-limiting embodiment, the plurality of panels 106 may have a rectangular shape. Herein, a diameter defined within the plurality of panels 106 in the deployed configuration is more by greater than 25 % of the diameter defined within the plurality of panels 106 in the stowed configuration. Thus, in the stowed configuration, the plurality of panels 106 has up to 20% less diameter than in the deployed configuration.

[0036] Due to such compaction of diameter, the deployable system 100 has a lesser load eccentricity compared to a system with a permanent cylindrical panel of deployed diameter. Thus, the deployable system 100 may withstand the structural loads with optimal support design during a launch phase due to lesser load eccentricity. Further, the panels 106 in the stowed configuration may be easily accommodated within an allowable envelope of the rocket. Further, the height of the deploy able system 100 may be reduced by using a greater number of petals of panels.

[0037] The deployable system 100 includes a tether and a device. The tether may be connected to the second edge 106-2 of each of the plurality of panels 106 to maintain the star polygon shape in the stowed configuration. The device may be adapted to disengage the tether from the plurality of panels 106 to allow the plurality of panels 106 to toggle from the stowed configuration to the deployed configuration.

[0038] Figure 3 illustrates different spacecrafts having different numbers of panels 106, according to an embodiment of the present disclosure. The deployable systems 100 of the different spacecrafts may have a different number of panels 106. As depicted in (a) of Figure 3, the deployable system 100 may include twelve panels 106. In another embodiment, as shown in (b) of Figure 3, the deployable system 100 may include sixteen panels. In yet another embodiment, as shown in (c) of Figure 3, the deployable system 100 may include twenty panels 106.

[0039] Figure 4 illustrates a scissor mechanism of a plurality of linkages 104, according to an embodiment of the present disclosure. Each of the plurality of linkages 104 may include a first end connected to a periphery of the central body 102. The plurality of linkages 104 may be configured in the scissor mechanism, as shown in Figure 4. Herein, a first supporting member 402 may be coupled with the central body 102 and a second supporting member 404 may be coupled through a hinge with two adjacent panels from among the plurality of panels The first supporting member 402 includes a first slot 402-1 and a first hole 402-2. The first hole 402-2 may be adapted to support an end of a first linkage 104-1 from among the plurality of linkages 104, and the first slot 402-1 may be adapted to support an end of a second linkage 104-2 from among the plurality of linkages 104. The second supporting member 404 includes a second slot 404-1 and a second hole 404-2. The second hole 404-2 may be adapted to support another end of the second linkage 104-2 from among the plurality of linkages 104, and the second slot 404-1 may be adapted to support another end of the first linkage 104-1 from among the plurality of linkages 104.

[0040] The scissor mechanism of the plurality of linkages 104 may be formed between the first supporting member 402 and the second supporting member 404. Herein, the scissor mechanism may facilitate the collapsing of the plurality of panels 106 to form the star polygon shape in the stowed configuration. Further, the scissor mechanism may facilitate the extension of the plurality of panels 106 to form the near-cylindrical shape in the deployed configuration.

[0041] In the present disclosure, the implementation of the deployable system 100 includes panels 106 with an almost-cylindrical deployed area which avoids sun locking manoeuvres. In the deployed configuration, the plurality of panels 106 may provide near-zero centre of gravity (CG) offset in the plane of deployment. The plurality of panels 106 may be fitted or removed from the central body 102 as a single functional unit. Being a closed structure, the plurality of panels 106 in the deployed condition offers lesser oscillations compared to a free- ended panel. The scissor mechanism may provide adequate forces for deployment and thereby, the deployable system 100 may be independent of any externally derived forces. The plurality of panels 106 may include rigid type solar panels, flexible type solar panels or a combination of both. The flexible solar panels may be used with end-stiffeners for interfacing with the linkage members. In an embodiment, the deployable system 100 may be used to create a near-cylindrically deployed array of light reflectors, thermal barriers, sensors, antennas, and combinations of such components including the solar panels, that needs to be kept coaxially away from the central body 102 on account of various possible considerations like unobstructed field of view of cameras, electromagnetic interference etc.

[0042] According to the present disclosure, the linkages 104 allow seamless toggling of the panel 106 between the stowed configuration and the deployed configuration. Further, the panels 106 in the stowed configuration have up to 20% less diameter than in the deployed configuration. This makes the deployable system 100 compact. Moreover, the deployable system 100 is a standalone unit, and the plurality of panels 106 can be mounted external to the central body 102, such that no space is required inside the central body 102. Thus, the central body 102 is not required to be dedicated for holding purpose alone and the central body 102 may also be a propellant tank, a structure carrying a payload atop, or a vestibule between two modules of a space station, etc. Herein, the plurality of panels 106 may be mounted on an external surface of the central body 102 without affecting the functionality of the central body 102.

[0043] While specific language has been used to describe the present subject matter, any limitations arising on account thereto, are not intended. As would be apparent to a person in the art, various working modifications may be made to the method in order to implement the inventive concept as taught herein. The drawings and the foregoing description give examples of embodiments. Those skilled in the art will appreciate that one or more of the described elements may well be combined into a single functional element. Alternatively, certain elements may be split into multiple functional elements. Elements from one embodiment may be added to another embodiment.

Claims

We Claim:

1. A spacecraft comprising: a near-cylindrically deployable system (100) adapted to toggle between a stowed configuration and a deployed configuration, comprising: a central body (102); a plurality of linkages (104) disposed around the central body (102), each of the plurality of linkages (104) comprises a first end connected to a periphery of the central body (102); and a plurality of panels (106) disposed radially around the central body (102), wherein each of the plurality of panels (106) comprising: a first edge (106-1) hinged to a first edge of an adjacent panel of the plurality of panels (106) and a second edge (106-2) hinged to a second end of a linkage of the plurality of linkages (104), wherein the plurality of panels (106) is adapted to form a star polygon shape in a stowed configuration, and the respective second edge (106-2) of the plurality of panels (106) is adapted to pivot relative to a movement of the plurality of linkages (104) to form a near-cylindrical shape in the deployed configuration.

2. The spacecraft as claimed in claim 1, wherein the plurality of panels (106) moves radially relative to the periphery of the central body (102) to toggle between the stowed configuration and the deployed configuration.

3. The spacecraft as claimed in claim 1, wherein the plurality of linkages (104) is configured in a scissor mechanism.

4. The spacecraft as claimed in claim 1, wherein a diameter defined within the plurality of panels (106) in the deployed configuration is more by 25% percent of a diameter defined within the plurality of panels (106) in the stowed configuration.

5. The spacecraft as claimed in claim 1, comprising: a tether connected to the hinge of a second edge (106-2) of each of the plurality of panels (106) to maintain the star polygon shape in the stowed configuration; and a device adapted to disengage the tether from the plurality of panels (106) to allow the plurality of panels (106) to toggle from the stowed configuration to the deployed configuration.

6. The spacecraft as claimed in claim 1, wherein each in the plurality of panels (106) has a rectangular shape.

7. The spacecraft as claimed in claim 1, wherein the plurality of panels (106) is a solar panel.

8. The spacecraft as claimed in claim 1, wherein the plurality of panels (106) is configured to form the star polygon shape in the stowed configuration and the near-cylindrical shape in the deployed configuration.

9. A near-cylindrically deployable system (100) adapted to toggle between a stowed configuration and a deployed configuration, comprising: a central body (102); a plurality of linkages (104) disposed around the central body (102), each of the plurality of linkages (104) comprise a first end connected to a periphery of the central body (102); and a plurality of panels (106) disposed radially around the central body (102), wherein each of the plurality of panels (106) comprising: a first edge (106-1) hinged to a first edge of an adjacent panel of the plurality of panels (106) and a second edge (106-2) hinged to a second end of a linkage of the plurality of linkages (104), wherein the plurality of panels (106) is adapted to form a star polygon shape in the stowed configuration, and the respective second edge (106-2) of the plurality of panels (106) is adapted to pivot relative to a movement of the plurality of linkages (104) to form a near-cylindrical shape in the deployed configuration.

10. The near-cylindrically deployable system (100) as claimed in claim 9, wherein the plurality of panels (106) moves radially relative to the periphery of the central body (102) to toggle between the stowed configuration and the deployed configuration.

11. The near-cylindrically deployable system (100) as claimed in claim 9, wherein the plurality of linkages (104) is configured in a scissor mechanism.

12. The near-cylindrically deployable system (100) as claimed in claim 9, wherein the central body (102) is at least a portion of a satellite, a spacecraft, or a space station.

13. The near-cylindrically deployable system (100) as claimed in claim 9, comprising: a tether connected to the second edge (106-2) of each of the plurality of panels (106) to maintain the star polygon shape in the stowed configuration; and a device adapted to disengage the tether from the plurality of panels (106) to allow the plurality of panels (106) to toggle from the stowed configuration to the deployed configuration.

14. The near-cylindrically deployable system (100) as claimed in claim 9, wherein the plurality of panels (106) has a rectangular profile.

15. The near-cylindrically deployable system (100) as claimed in claim 9, wherein the plurality of panels (106) is a solar panel.

16. The near-cylindrically deployable system (100) as claimed in claim 9, wherein the plurality of panels (106) is configured to form the star polygon shape in the stowed configuration and the near-cylindrical shape in the deployed configuration.

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