摘要
针对全C/SiC复合材料机身襟翼再入过程中受到强烈的气动载荷作用的受力状况,进行了静力试验考核。对静力试验方法进行了讨论与探索,通过验证性的试验,确定了传统的贴帆布带加载的静力试验方案。并通过有限元建模计算明晰了机身襟翼结构的静力试验的危险区域。静力试验中,襟翼试件在未达到试验设计载荷的情况下,出现了提前破坏。通过对试件的传力路线的分析以及损伤部位的观察和研究,找出了失效的原因是由于角盒工艺上的缺陷造成的,并提出了工艺上改进的方法。
All-C/SiC composites body flap is gas-loaded intensely when the return of the space vehicle into Earth＇ s atmosphere with high-supersonic. As to assess the strength of the body flap, we adopt the sticking canvas＇ method which is the traditional static test method, and do the validation test to prove the feasibility of the adoption. The risk area of body flap is perspicuity by finite element calculating. In static test, the body flap is failure in advance of getting to design load. Through the analysis for the transmission path and observation the failure part, the cause of failure of structure which is because of the fault of the technics has been found. At last, the improvement of the techniques has been brought forward.
出处
《飞机设计》
2008年第3期4-7,12,共5页
Aircraft Design
基金
航空基金(04B53012)
国家自然科学基金(10372081)资助项目
