首页> 外国专利> Traverse for docking of large-sized spacecraft from the launch vehicle fairing supply NADKALIBERNYM

Traverse for docking of large-sized spacecraft from the launch vehicle fairing supply NADKALIBERNYM

机译:用于从运载火箭整流罩供应NADKALIBERNYM对接大型航天器的导线架

摘要

1.travers, u0434u043bu00a0 docking of large spacecraft and carrier rocket, with the u043du0430u0434u043au0430u043bu0438u0431u0435u0440u043du044bu043c u043eu0431u0442u0435u043au0430u0442u0435u043bu0435u043c, u0441u043eu0434u0435u0440u0436u0430u0449u0430u00a0 carrier beam with p u0440u043eu0443u0448u0438u043du043eu0439 and u0445u0432u043eu0441u0442u043eu0432u0438u043au043eu043c, u0448u0430u0440u043du0438u0440u043du043e enshrined on the support beam and with u0441u0442u043eu043fu043eu0440u043eu043c stationed with the possibility of u0432u0437u0430u0438u043cu043eu0434u0435u0439u0441u0442u0432u0438u00a0 with fixing a nest, u0432u044bu043fu043eu043bu043du0435u043du043d ies on the support beam.the u0431u0430u043bu0430u043du0441u0438u0440u043eu0432u043eu0447u043du044bu0445 nests of the lines with u0442u0430u043au0435u043bu0430u0436u043du044bu043cu0438 nodes u043au0440u0435u043fu043bu0435u043du0438u00a0 large spacecraft, u043eu0442u043bu0438u0447u0430u044eu0449u0430u00a0u0441u00a0, such u043bu0430u0436u043du044bu0435 nodes u043au0440u0435u043fu043bu0435u043du0438u00a0 large spacecraft set to economies in the u0441u0432u00a0u0437u0430u043du043du043eu0439 with equipped with collapsible slider, and implemented in the form of front and rear u0440u0435u0433u0443u043bu0438 from brackets u0448u0430u0440u043du0438u0440u043du043e u0441u0432u00a0u0437u0430u043du043du044bu0445 in frame.with the adjustable brackets are placed by the docking of large spacecraft with the launch vehicle and installed with agriculture u043eu0436u043du043eu0441u0442u044cu044e fixing them to the u043fu043eu043bu043eu0436u0435u043du0438u00a0, with the lines are placed between the u0442u0430u043au0435u043bu0430u0436u043du044bu043cu0438 nodes u043au0440u0435u043fu043bu0435u043du0438u00a0 large spacecrafta rear adjustable brackets are placed between the horizontal axis of symmetry of large spacecraft, and an internal circuit u043du0430u0434u043au0430u043bu0438u0431u0435u0440u043du043eu0433u043e mr. u043eu043bu043eu0432u043du043eu0433u043e u043eu0431u0442u0435u043au0430u0442u0435u043bu00a0.;2. travers on 1, u043eu0442u043bu0438u0447u0430u044eu0449u0430u00a0u0441u00a0, as economies in the frame by the bearing beams are placed on the pins with balance weights and devices the latter, on the u0448u0442u044bu0440u00a0u0445 fixation.;3. travers on 1 or 2, u043eu0442u043bu0438u0447u0430u044eu0449u0430u00a0u0441u00a0, rear adjustable brackets are sectional, u0441u043eu0441u0442u043eu00a0u0449u0438u043cu0438 of consistently contained between a longitudinal pair ang.
机译:1,将 u043d u0430 u0434 u0434 u043a u0430 u043b u0438 u0431 u0435 u0440 u043d u043d u043d u043b u043c u043e u0431与大型航天器和运载火箭对接 u0442 u0435 u043a u0430 u0442 u0435 u043b u0435 u043c, u0441 u043e u0434 u0435 u0440 u0436 u0430 u0449 u0430 u00a0带p的承载梁 u0440 u043e u0443 u0448 u0438 u043d u043e u0439和 u0445 u0432 u043e u0441 u0442 u043e u0432 u0438 u043a u043e u043e u043c, u0448 u0430 u0430 u0440 u043d u0438 u0440 u043d u043d在 u0441 u0442 u043e u043f u043e u0440 u043e u043c的位置,并可能安装 u0432 u0437 u0430 u0438 u043c u043e u0434 u0435 u0435 u0439 u0441 u0442 u0432 u0438 u00a0并固定了一个嵌套 u0432 u044b u043f u043e u043b u043d u0435 u043d u043d在支撑梁上。 u0431 u0430 u043b u043b u0430 u043d u0441 u0438 u0440 u043e u0432 u043e u0447 u043d u044b u0445具有 u0442 u0430 u043a u0435 u043b u0430 u0436 u043d u044b u043b u043c u0438节点的行的嵌套 u043a u0440 u043 5 u043f u043b u0435 u043d u0438 u00a0大型航天器, u043e u0442 u043b u0438 u0447 u0430 u044e u0449 u0430 u00a0 u0441 u00a0,例如 u043b u0430 u0436 u u044b u0435节点 u043a u0440 u0435 u043f u043b u0435 u043d u0438 u00a0设置为 u0441 u0432 u00a0 u0437 u0430 u04d u043d u043d u043e u0439的大型航天器带有可折叠滑块,并通过括号 u0448 u0430 u0430 u0440 u043d u0438 u0440 u043d u043e u0431 u0431 u0433 u0443 u043b u0438 u0437 u0430 u043d u043d u044b u0445在框架中。可调节支架由大型航天器与运载火箭对接放置,并安装有农业用 u043e u0436 u043d u043e u0441 u0442 u044c u044e将它们固定到 u043f u043e u043b u043e u0436 u0435 u043d u0438 u00a0,并在 u0442 u0430 u043a u0435 u043b u0430 u0436 u043d u043b u043c u0438节点 u043a u0440 u0435 u043f u043b u0435 u043d u0438 u00a0 la rge spacecrafta后可调托架放置在大型航天器的水平对称轴和内部电路之间,该内部电路 u043d u0430 u0434 u043a u0430 u043b u0438 u0431 u0435 u0440 u043d u043e u0433 。 u043e u043b u043e u0432 u043d u043e u0433 u043e u043e u0431 u0442 u0435 u043a u0430 u0442 u0435 u043b u00a0。; 2。在1, u043e u0442 u043b u0438 u0447 u0430 u044e u0449 u0430 u00a0 u0441 u00a0上移动,因为框架中的经济性通过支承梁放置在带有平衡重的销上,而平衡重装置,在 u0448 u0442 u044b u0440 u00a0 u0445定位上; 3。在1或2上移动, u043e u0442 u043b u0438 u0447 u0430 u044e u0449 u0430 u00a0 u0441 u00a0,后部可调托架是分段的, u0441 u043e u0441 u0441 u0442 u043e u00a0 u0449 u0438 u043c u0438始终包含在纵向对ang之间。

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