초록 ▼

A thin membrane structure for stabilizing a spacecraft is provided. The spacecraft has a first end and a second end. The spacecraft has a center of pressure and a center of gravity. The thin membrane structure comprises a module secured to the spacecraft and a structure having a polygonal base and a

A thin membrane structure for stabilizing a spacecraft is provided. The spacecraft has a first end and a second end. The spacecraft has a center of pressure and a center of gravity. The thin membrane structure comprises a module secured to the spacecraft and a structure having a polygonal base and a plurality of triangular side panels meeting in a point opposite the base with the point secured to the module. Prior to deployment, the structure is entirely contained within the module. Subsequent to deployment, the structure expands to a pyramidal shape with the distance between the center of pressure and the center of gravity increasing to a length greater than approximately one-half the length of the spacecraft.

대표청구항 ▼

1. A thin membrane structure capable of being used to stabilize a spacecraft, the thin membrane structure comprising: a foldable structure having a plurality of triangular side panels, each triangular side panel having two side edges, a base edge, and first, second, and third corners;a deployment me

1. A thin membrane structure capable of being used to stabilize a spacecraft, the thin membrane structure comprising: a foldable structure having a plurality of triangular side panels, each triangular side panel having two side edges, a base edge, and first, second, and third corners;a deployment mechanism operatively attached to the foldable structure and for transitioning the foldable structure between an undeployed state in which each of the plurality of triangular side panels is folded and a deployed state in which each of the plurality of side panels is unfolded relative to the undeployed state; anda module for operatively engaging the remainder of a spacecraft, supporting the deployment mechanism, and supporting the foldable structure;wherein the first corner of each of the triangular side panels is operatively connected to the module and connected substantially adjacent to the first corner of each of the other triangular side panels so as to define an apex area;wherein the two side edges, between the second corner and the apex area and between the third corner and the apex area, of each of the triangular side panels being substantially unconnected from the two side edges of the other triangular side panels;wherein, when the deployment mechanism is used to place the foldable structure into a deployed state, (a) the first, second, and third corners of each of the plurality of side panels, when viewed from the same perspective, occur in a clockwise sequence beginning with the first corner, (b) the second corner of each of triangular side panels is located substantially adjacent to the third corner of one of the other triangular side panels so as to define a plurality of vertex areas, (c) the plurality of vertex areas and the base edges define a polygonal shape, (d) and each of the two side edges of each of the triangular side panels is disposed substantially adjacent to and substantially parallel to a side edge of another one of the triangular side panels to define a pyramid edge that extends between the apex and the polygonal shape, and (e) the plurality of vertex areas, the apex area, the base edges, and the pyramid edges define a pyramidal shape in which the apex area is spaced from a plane defined by the polygonal shape. 2. The thin membrane structure of claim 1 wherein the foldable structure has four triangular side panels. 3. The thin membrane structure of claim 2 and further comprising: a strengthening layer secured to each of the triangular side panels adjacent to the first corner. 4. The thin membrane structure of claim 3 wherein the strengthening layer secured to each of the triangular side panels is secured with a clamp bar and a plurality of fastening mechanisms. 5. The thin membrane structure of claim 1 wherein the deployment mechanism includes a plurality of pantographs, each of the pantographs having an attached end operatively attached to the module and a free end capable of being displaced relative to the attached end and operatively connected to a vertex area. 6. The thin membrane structure of claim 5 wherein the deployment mechanism includes: a pair of flanges extending from each of the second and third corners of each of the triangular side panels. 7. The thin membrane structure of claim 6 wherein each flange has a grommet secured therethrough, each flange secured to the free end of one of the plurality of pantographs with a pin extending through the grommets thereby securing the second corner of one of the triangular side panels adjacent to the third corner of an immediately adjacent triangular side panel. 8. A thin membrane structure capable of being used to stabilize a spacecraft, the thin membrane structure comprising; a foldable structure having a plurality of triangular side panels, each triangular side panel having two side edges, a base edge, and first, second, and third corners;a deployment mechanism operatively attached to the foldable structure and for transitioning the foldable structure between an undeployed state in which each of the plurality of triangular side panels is folded and a deployed state in which each of the plurality of side panels is unfolded relative to the undeployed state; anda module for operatively engaging the remainder of a spacecraft, supporting the deployment mechanism, and supporting the foldable structure;wherein the first corner of each of the triangular side panels is operatively connected to the module and connected substantially adjacent to the first corner of each of the other triangular side panels so as to define an apex area;wherein the two side edges of each of the triangular side panels being substantially free from direct attachment to either of the two side edges of the other triangular side panels;wherein, when the deployment mechanism is used to place the foldable structure into a deployed state, (a) the first, second, and third corners of each of the plurality of side panels, when viewed from the same perspective, occur in a clockwise sequence beginning with the first corner, (b) the second corner of each of triangular side panels is located substantially adjacent to the third corner of one of the other triangular side panels so as to define a plurality of vertex areas, (c) the plurality of vertex areas and the base edges define a polygonal shape, and (d) the plurality of vertex areas and the apex area define a pyramidal shape in which the apex area is spaced from a plane defined by the polygonal shape;wherein the deployment mechanism includes a plurality of pantographs, each of the pantographs having an attached end operatively attached to the module and a free end capable of being displaced relative to the attached end and operatively connected to a vertex area;a root sequencer mechanism operatively connected to the plurality of pantographs and capable of causing the free end of each of the plurality of pantographs to move away from the attached end of the related one of the plurality of pantographs. 9. A method capable of being used to stabilize a spacecraft, the method comprising: providing a module that is capable of being operatively connected to a spacecraft, the module being in a first state in which the module has an extent, the module supporting a foldable structure that is in a folded state and substantially located within the extent of the module, the foldable structure having an apex area operatively connected to the module and an outer edge that, if the foldable structure is unfolded on a planar surface, has a polygon shape having “x” number of edges;placing, following the step of providing, the module in a second state in which the foldable structure can be deployed from the module such that at least a portion of the foldable structure will extend beyond the extent of the module in the first state; andusing, following the step of placing, a deployment mechanism to transition the foldable structure from the folded state to an unfolded state with a pyramidal shape in which the outer edge of the foldable structure defines vertex areas of a base of a pyramidal shape and the apex area is spaced from the base, the pyramidal shape having (⅔)× edges due to pairs of edges that define the polygon shape being disposed substantially adjacent and substantially parallel to one another so as to constitute a single edge extending between the apex and the base of a pyramidal shape. 10. The method of claim 9 wherein the foldable structure has four triangular side panels, each side panel having first, second, and third corners, a first side extending between the first and second corners, a second side extending between the first and third corners, and a base side extending between the second and third corners, the first corner of each of the four triangular side panels operatively secured to the module to define a portion of the apex area. 11. The method of claim 10 and further comprising: a strengthening layer attached to each of the triangular side panels about the top point. 12. The method of claim 10, wherein the step of using a deployment mechanism comprises: providing a plurality of pantographs with each pantograph having a fixed end operatively attached to the module and a free end that is movable relative to the fixed end and operatively attached to the foldable structure; andextending each of a plurality of pantographs adjacent to one of a first and second sides of one of the triangular side panels and to one of the first and second sides of another one of the triangular side panels. 13. A method capable of being used to stabilize a spacecraft, the method comprising: providing a module that is capable of being operatively connected to a spacecraft, the module being in a first state in which the module has an extent, the module supporting a foldable structure that is in a folded state and substantially located within the extent of the module, the foldable structure having an apex area operatively connected to the module and an outer edge that, if the foldable structure is unfolded on a planar surface, has a polygon shape;placing, following the step of providing, the module in a second state in which the foldable structure can be deployed from the module such that at least a portion of the foldable structure will extend beyond the extent of the module in the first state; andusing, following the step of placing, a deployment mechanism to transition the foldable structure from the folded state to an unfolded state with a pyramidal shape in which the outer edge of the foldable structure defines vertex areas of a base of a pyramidal shape and the apex area is spaced from the base;wherein the foldable structure has four triangular side panels, each side panel having first, second, and third corners, a first side extending between the first and second corners, a second side extending between the first and third corners, and a base side extending between the second and third corners, the first corner of each of the four triangular side panels operatively secured to the module to define a portion of the apex area;wherein the step of using a deployment mechanism comprises: providing a plurality of pantographs with each pantograph having a fixed end operatively attached to the module and a free end that is movable relative to the fixed end and operatively attached to the foldable structure; andextending each of a plurality of pantographs adjacent to one of a first and second sides of one of the triangular side panels and to one of the first and second sides of another one of the triangular side panels;wherein the step of extending includes using a root sequencer mechanism that is operatively attached to the plurality of pantographs and adapted to apply an extending force to each of the plurality of pantographs to cause the free end of each of the plurality of pantographs to move away from the fixed end of the related one of the plurality of pantographs. 14. A thin membrane structure capable of being used to stabilize a spacecraft, the thin membrane structure comprising: a foldable structure having at least three triangular side panels, each triangular side panel having two side edges, a base edge, and first, second, and third corners;a plurality of pantographs, each of the plurality of pantographs having an attached end operatively connected to the module and a free end capable of being displaced relative to the attached end, the free end having a first location operatively secured to the second corner of one of the triangular side panels and a second location that is separated from the first location operatively secured to the third corner of a different one of the triangular side panels, the first and second locations moving closer to a center line defined by the center pivots of the pantograph as the free end of the pantograph is displaced away from the attached end; anda module for operatively engaging the remainder of a spacecraft, supporting the plurality of pantographs, and supporting the foldable structure, wherein the module is operatively connected to the attached end of each of the plurality of pantographs;wherein the first corner of each of the triangular side panels is operatively connected to the module and connected substantially adjacent to the first corner of each of the other triangular side panels so as to define an apex area;wherein, prior to deployment, the foldable structure and the plurality of pantographs are entirely contained within the module;wherein, when the deployment mechanism is used to place the foldable structure into a deployed state, (a) the first, second, and third corners of each of the at least three triangular side panels, when viewed from the same perspective, occur in a clockwise sequence beginning with the first corner, (b) the second corner of each of the at least three triangular side panels is disposed substantially adjacent to the third corner of a different one of the at least three triangular side panels due to the displacement of the free end away from the attached end of one of the plurality of pantographs, thereby defining a plurality of vertex areas, (c) the vertex areas and the base edges define a polygonal shape, and (d) the plurality of vertex areas and the apex area defining a pyramidal shape in which the apex area is spaced from the a plane defined by the polygonal shape. 15. The thin membrane structure of claim 14 and further comprising: a strengthening layer secured to each of the triangular side panels about the first corner; anda pair of flanges extending from each of the second corner and the third corner of each of the triangular side panels;wherein each flange has a grommet secured therethrough, each flange secured to the free end of one of the pantographs with a pin extending through the grommets thereby securing the second corner of one of the triangular side panels adjacent to the third corner of an adjacent triangular side panel such that as the pantographs expand, the triangular side panels expand creating the pyramidal shape with each of the triangular side panels forming one side of the pyramidal shape. 16. A thin membrane structure capable of being used to stabilize a spacecraft, the thin membrane structure comprising: a foldable structure having at least three triangular side panels, each triangular side panel having two side edges, a base edge, and first, second, and third corners;a plurality of pantographs, each of the plurality of pantographs having an attached end operatively connected to the module and a free end capable of being displaced relative to the attached end and secured to the second corner of one of the triangular side panels and the third corner of a different one of the triangular side panels; anda module for operatively engaging the remainder of a spacecraft, supporting the plurality of pantographs, and supporting the foldable structure, wherein the module is operatively connected to the attached end of each of the plurality of pantographs;wherein the first corner of each of the triangular side panels is operatively connected to the module and connected substantially adjacent to the first corner of each of the other triangular side panels so as to define an apex area;wherein, prior to deployment, the foldable structure and the plurality of pantographs are entirely contained within the module;wherein, when the deployment mechanism is used to place the foldable structure into a deployed state, (a) the first, second, and third corners of each of the plurality of side panels, when viewed from the same perspective, occur in a clockwise sequence beginning with the first corner, (b) the second and third corners of the at least three triangular side panels define a plurality of vertex areas, (c) the vertex areas and the base edges define a polygonal shape, and (d) the plurality of vertex areas and the apex area defining a pyramidal shape in which the apex area is spaced from the a plane defined by the polygonal shape;a root sequencer mechanism operatively connected to the plurality of pantographs and capable of causing the free end of each of the plurality of pantographs to move away from the attached end of the related one of the plurality of pantographs.