摘要
为了满足航天有效载荷轻型化、高比强度、高比模量的要求,分析了航天有效载荷支撑结构常用工程材料的优缺点;阐述了碳/环氧复合材料在航天有效载荷承力支撑结构中应用的可行性;介绍了该材料在航天有效载荷中的实际工程应用及相关设计方法。用优化设计后的碳/环氧复合材料支撑机构支撑80kg重的有效载荷,在正弦振动和随机振动试验过程中碳纤支撑座没有发生破坏,而质量相对于铝合金结构降低了近30%。结果表明,碳/环氧复合材料应用于航天有效载荷支撑结构中是可行的。
In order to meet the requirements of light weights, high specific strength and high specific moduli for a space payload, the advantages and disadvantages of the engineering materials used in the supports of the space payload were analyzed, and the feasibility of the application of the carbon/epoxy composites to the support structures was explored. The design methods of the carbon/epoxy composites were introduced by the actual application in space fields. Finally, a carbon/epoxy composite structure was designed and fabricated to support a 80 kg weight payload and to undergo both sine and random vibration tests. Experimental results indi- cate that the structure can resist the acceleration of the random vibration tests in a structural basic frequency of 103.6 Hz successfully, while the mass has reduced almost 30% as compared with that of the structure made by A1 alloy materials. It is shown that the carbon,/epoxy composites can be used as the support structures of the space payloads.
出处
《中国光学与应用光学》
2009年第2期79-84,共6页
Chinese Optics and Applied Optics Abstracts
