3results about How to "Good space environment adaptability" patented technology

This invention discloses a space radiating plate based on a large vapor chamber and its manufacturing method, belonging to the field of spacecraft thermal control technology. The radiating plate includes a one-piece sealed metal cavity, the interior of which is a vacuum vapor chamber. The cavity has opposing first and second sidewalls; the outer surface of the first sidewall forms a radiating surface, and the inner side of the second sidewall integrates cooling channels. A micro-pillar array structure, directly formed integrally through micromachining, is disposed on the inner wall surface of the vacuum vapor chamber, and the cavity is filled with a phase change working fluid. This invention highly integrates the vapor chamber, channels, and radiating surface, utilizing phase change heat transfer to achieve ultra-high thermal conductivity and temperature uniformity, solving the problems of low heat dissipation efficiency, anisotropy, large weight, and poor adaptability to the space environment in existing technologies. It is suitable for thermal management of high-power spacecraft such as satellites, space stations, and space data centers.

The invention provides a modular satellite structure based on an open type grid framework and a final assembly method thereof, and belongs to the technical field of satellite structures. The problems that according to an existing method, the defects of blind operation and adhesive fixation are not fundamentally eliminated, the cable laying efficiency is low, and the weight of an outer plate is too large are solved. The thermal control protection structure comprises an open type main bearing grid framework and a plurality of thermal control protection outer plates, the open type main force bearing grid framework is a hexahedral cage-shaped framework formed by connecting six plate-shaped grid frameworks in a butt joint mode. The thermal control protection outer plates are arranged on at least one outer side face of the open type main force bearing grid framework. The plate-shaped grid frame is used for installing one side plane of the thermal control protection outer plate, and a force bearing structure of the plate-shaped grid frame is recessed inwards. The method is mainly used in the aerospace field.

The invention relates to the technical field of optical thin films, in particular to a low-phase-difference metal reflecting mirror suitable for a space environment and a preparation method and application of the low-phase-difference metal reflecting mirror. The bonding layer, the metal layer, the first protective layer, the first low-refractive-index layer, the high-refractive-index layer, the second low-refractive-index layer and the second protective layer are sequentially plated on the optical substrate; the optical substrate is made of silicon; the bonding layer is made of nickel-chromium; the metal layer is made of silver; the first protective layer and the second protective layer are made of aluminum oxide; the first low-refractive-index layer is made of silicon dioxide, and the second low-refractive-index layer is made of silicon dioxide; and the high refractive index layer is made of niobium pentoxide. High reflectivity in a broadband range is realized through the metal layer, phase difference regulation and control design is performed by using an asymmetric equivalent layer theory in an optical thin film design method, phase difference regulation and control of a communication waveband are realized, and adaptability and stability of an optical element under a space environment condition are improved by using the outermost protective layer.