Deployable annular solar array
阅读：228发布：2023-09-20
专利汇可以提供Deployable annular solar array专利检索，专利查询，专利分析的服务。并且A deployable spacecraft solar array having an annular thin-film solar panel circumferentially surrounding a spacecraft body and supported on the body by hinged frames which are swingable inwardly to retracted positions against the body to contract the panel to a launch configuration with an effective diameter approximating the body diameter and outwardly to radial extended positions to expand the panel to a deployed configuration with a diameter substantially greater than the body diameter and hence a surface area substantially exceeding the body surface area.，下面是Deployable annular solar array专利的具体信息内容。
1. A spacecraft comprising: a spacecraft body having a central axis; an annular flexible solar panel circumferentially surrounding said body and having essentially the same overall circumferential dimension in every plane normal to said axis and intersecting said panel whereby said panel intersects radial planes containing the longitudinal axis of said spacecraft body along lines of intersection substantially parallel to said axis; and relatively rigid panel mounting means on and spaced circumferentially about said body and secured to said panel along certain of said intersection lines spaced about said panel, said mounting means supporting said solar panel on said body for radial contraction of said panel to a launch configuration wherein the panel extends about said body in close conforming relation to the body and has an effective diameter approximating the diameter of said body and radial deployment of said panel to a deployed configuration wherein the panel is disposed in surrounding outwardly, radially spaced relation to said body and has an outer effective surface area exceeding substantially the surface area of said body.
2. A spacecraft according to claim 1 wherein: said mounting means comprise frames having inner ends hinged to the circumference of said body on pivot axes parallel to the central axis of and spaced circumferentially about said body for swinging between retracted positions against the outside of the body and extended positions in generally radial planes of the body, and means securing the outer frame ends to said solar panel for contraction of said panel to launch configuration by swinging of said frames to retracted positions and expansion of said panel to deployed configuration by swinging of said frames to extended positions.
3. A spacecraft according to claim 2 wherein: said solar panel has fold lines parallel to said body axiS about which the panel is folded in said stowage configuration.
4. A spacecraft according to claim 3 wherein: said panel is folded accordion-fashion in stowage configuration.
5. A spacecraft according to claim 3 wherein: said panel in stowage configuration is folded under said frames.
6. A spacecraft according to claim 1 wherein: said mounting means comprise frames having inner ends hinged to the circumference of said body on pivot axes parallel to the central axis of and spaced circumferentially about said body for swinging between retracted positions against the outside of said body and extended positions in generally radial planes containing said central body axis, and rotatable drums on the outer ends of said frames on which said solar panel is wound in stowage configuration and from which the panel unwinds during deployment of the panel by swinging of the frames to extended positions.
7. A spacecraft according to claim 6 wherein: said drums are spring biassed to wind said panel on the drums during swinging of said frames to retracted position.
8. A spacecraft according to claim 1 wherein: the mounting means comprise frames having inner ends hinged to tje circumference of said body on pivot axes parallel to the central axis of and spaced circumferentially about said body for swinging between retracted positions against the outside of the body and extended positions in generally radial planes of said body, and means securing the outer frame ends to said solar panel for contraction of said panel to launch configuration by swinging of said frames to retracted positions and expansion of said panel to deployed configuration by swinging of said frames to extended positions; and said solar panel in its launch configuration extends along the outside of each retracted frame from its inner end to its outer end, then under the outer end of the frame, and finally back on itself to the next frame to form a panel fold between the outer end of each frame and the spacecraft body.
9. A spacecraft according to claim 8 wherein: said solar panel mounts solar cells which are located on the confronting sides of each fold; and means within each panel fold to prevent contact of the confronting solar cells.
10. A spacecraft according to claim 1 wherein: said mounting means comprise frames having inner ends hinged to the circumference of said body on pivot axes parallel to the central axis of and spaced circumferentially about said body for swinging between retracted positions against the outside of the body and extended positions in generally radial planes of said body, and means securing the outer frame ends to said solar panel for contraction of said panel to launch configuration by swinging of said frames to retracted positions and expansion of said panel to deployed configuration by swinging of said frames to extended positions; and said solar panel in its launch configuration has a portion folded accordion-fashion within an opening at the inner end of each frame and extends from said opening along the outer side of the respective frame toward the outer frame end and then to the accordion folds in the opening of the next frame.
11. A spacecraft according to claim 10 including: wedge shaped formers extending across the opening in each frame within the accordion folds of the panel and fixed to the respective frame; and a pair of stiffeners between each pair of adjacent formers secured to upper and lower edges of the adjacent panel fold and extending between the respective frame and the spacecraft body, and means releasibly securing each stiffener to the respective frame and the body for deployment of the stiffeners with said solar panel.
12. A deployable solar array for a spacecraft having a body comprising: an annular flexible solar panel having a central axis encircled by the panel and having essentially the same overall circumferential dimension in every plane normal to said axis and iNtersecting said panel whereby said panel intersects radial planes containing said axis along lines of intersection substantially parallel to the axis; a number of panel mounting frames spaced circumferentially about the inside of said panel and having outer ends adjacent said panel and opposite inner ends; hinge means along said inner frame ends having hinge axes parallel to said central axis for pivotally mounting said frames about the circumference of said spacecraft body for swinging of said frames on axes parallel to said central axis between retracted positions wherein said frames extend generally circumferentially about said axis and extended positions wherein said frames are disposed in radial planes containing said axis; and means for securing said outer frame ends to said panel along certain of said intersection lines spaced circumferentially about said panel for radial contraction of the panel to a stowage configuration wherein the panel conforms generally to a cylindrical configuration of given diameter by swinging of said frames to retracted position and radial outward deployment of the panel to a deployed configuration wherein the panel conforms generally to a cylindrical configuration of a diameter exceeding substantially said given diameter by swinging of said frames to extended position.
13. A solar array according to claim 12 wherein: said solar panel in its launch configuration extends along the outside of each retracted frame from its inner end to its outer end, then under the outer end of the frame, and finally back on itself to the next frame to form a panel fold behind the outer end of each retracted frame.
14. A solar array according to claim 13 wherein: said solar panel mounts solar cells which are located on the confronting sides of each fold; and means within each panel fold to prevent contact of the confronting solar cells.
15. A solar array according to claim 14 wherein: said solar panel in its launch configuration has a portion folded accordion-fashion within an opening at the inner end of each frame and extends from said opening along the outer side of the respective frame toward the outer frame end and then to the accordion folds in the opening of the next frame.
16. A solar array according to claim 15 including: wedge-shaped formers extending across the opening in each frame within the accordion folds of the panel and fixed to the respective frame; and a pair of stiffeners between each pair of adjacent formers secured to upper and lower edges of the adjacent panel fold and means releasibly joining said stiffeners and frames.
17. A solar array according to claim 12 wherein: said securing means comprise rotatable drums on the outer ends of said frames on which said solar panel is wound in stowage configuration and from which the panel unwinds during deployment of the panel by swinging of the frames to extended positions.
18. A solar array according to claim 17 wherein: said drums are spring biassed to wind said panel on the drums during swinging of said frames to retracted position.
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