CAJ | 학술논문

利用虚拟振动试验软件系统、多用途飞船返回舱的有限元模型和"神舟一号"返回舱的历史试验数据,对多用途飞船返回舱进行虚拟正弦和随机振动试验,考核了返回舱经受动力学环境的能力,研究发现设计方案在一阶共振区响应过大,存在较大的设计缺陷,经过多次迭代优化设计后的模型满足设计要求.研究结果为多用途飞船返回舱的设计和优化提供了依据.
이용허의진동시험연건계통、다용도비선반회창적유한원모형화"신주일호"반회창적역사시험수거,대다용도비선반회창진행허의정현화수궤진동시험,고핵료반회창경수동역학배경적능력,연구발현설계방안재일계공진구향응과대,존재교대적설계결함,경과다차질대우화설계후적모형만족설계요구.연구결과위다용도비선반회창적설계화우화제공료의거.
The vibrations of a re-entry spacecraft capsule are investigated by using the virtual vibration software. Combining the finite element model of the capsule and the history experimental data acquired from Shenzhou-1, the virtual sinusoidal/random vibration experiments are carried out to test the capsule's ability of surviving the vibration environment during the launch stage. This analysis provides reliable and significant data for the optimized design of the capsule since the real vibration tests will not be carried out in the design stage. The model 1, which is before optimization, is found to have defects and the resonant response of the nodes in the Dadi region is too large to satisfy the experimental requirements. After the iterative optimization, the mode finally satisfies the design requirements. To reduce the cost and save time, instead of the real vibration test, the virtual vibration tests are beneficial. This is the first spacecraft designed based only on the virtual vibration in China.