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该研究在日本系首次将复合材料用于机体结构,没有可以利用的数据,只知道这是应该研究的技术课题,在这种状况下起步,主受力结构的难度太大,所以CFRP化的对象选择了次受力结构部位。在为时二年的基础研究中,研究了解析方法、加工方法、环境影响、质量保障方法,之后于1976年进行细部设计,制作静强度试验用试验件,确认了静强度。1978年,实施了耐久性试验和环境试验,确认可以满足在考虑了气动加热的温、湿度范围下的强度要求。此外,将CFRP部件实际装机进行了计测飞行试验,目的是对飞行中发生载荷及颤振的安全裕量加以研究,计测了高度、加速度、应变分布、表面温度等。还调查过从飞行员的操纵感觉也证明换装CFRP后没有异常。在这些严格检验之后,对各试验件进行了二年至
The study in Japan for the first time the composite material used in the body structure, there is no available data, only know that this is a technical issue that should be studied, in this situation, the main force structure is too difficult, so CFRP The object selected the second force structure parts. During the two years of basic research, analytical methods, processing methods, environmental impacts and quality assurance methods were studied. Detailed designs were carried out in 1976, and test pieces for static strength tests were made to confirm the static strength. In 1978, a durability test and an environmental test were carried out to confirm that the strength requirement under the temperature and humidity ranges considering pneumatic heating was satisfied. In addition, CFRP components were actually installed for the purpose of flight test, the purpose of which is to study the safety margin of load and flutter in flight, and to measure the height, acceleration, strain distribution and surface temperature. It was also investigated that the pilot’s handling felt that there was no abnormality after the CFRP dressup. After these rigorous tests, the test pieces were carried out for two years