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为研究气压对平流层飞艇变形性能的影响,基于铁木辛柯梁分析理论,将低阻尼流线形飞艇假设为分段等截面充气梁,采用叠加法推导了考虑气压效应的柔性飞艇总体挠度计算式。同时,将柔性飞艇作为预应力薄膜结构,应用ANSYS软件,采用小杨氏模量法进行充气预应力找形,并基于找形结果进行载荷下非线性变形分析。在此基础上计算了飞艇外气囊在不同头部荷载与气压下的总体挠度并比较了两种方法的计算值,发现两者变化趋势一致。最后,建立了25 m验证飞艇的计算模型,得到了控制点应力和总体变形;给出了飞艇下腹线在不同气压下的位形,将其与测量值进行比较表明:计算值和测量值基本相等,误差小于5%。本文对大型柔性飞艇设计分析具有一定的参考价值。
In order to study the effect of air pressure on the deformation performance of stratospheric airship, based on the theory of Timoshenko beam, a low-damping streamlined airship is assumed to be a sectionally sectioned inflatable beam. The total deflection Formula. At the same time, using the flexible airship as the prestressed thin-film structure, the ANSYS software was used to conduct the pre-stressing and shape-finding by the Young’s modulus method. The nonlinear deformation analysis under load was carried out based on the result of the shape-finding. On this basis, the total deflections of the airship outer bag under different head loads and pressures are calculated and the calculated values of the two methods are compared. The trend of the two is consistent. Finally, the calculation model of a 25-m airship is established and the stress and overall deformation of the control point are obtained. The shape of the lower abdomen of the airship at different pressures is given. Comparing this with the measured value shows that the calculated value and the measured value are basically Equal, the error is less than 5%. This paper has some reference value for the design and analysis of large-scale flexible airship.