共查询到13条相似文献,搜索用时 167 毫秒
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充气太阳能帆板展开动力学数值模拟预报 总被引:3,自引:0,他引:3
充气太阳能帆板是一种通过气体驱动支撑管展开的新型太阳能帆板。首先简要介绍其研究进展,然后针对充气展开支撑管,提出了分段式充气体积控制模型,基于LS—DYNA模拟了空间环境下Z型折叠充气太阳能帆板在支撑管无约束与有轴向约束控制时的展开过程,分析了支撑管每折叠段的气压变化,上横板的动力学特性以及基板的平面外振动,预报了展开过程中支撑管与基板的接触碰撞,并通过悬吊式展开试验验证了计算结果。结果表明,本文计算能够预报充气太阳能帆板在空间展开的动力学特性。 相似文献
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本文分别研究了Z形、卷曲形、嵌套形折叠充气管的有限元建模方法。折叠充气管在进行有限元建模时,由于折叠部位内外层蒙皮的长度不一致给模型带来几何误差。不同的折叠方式建模技巧各不相同,引入的误差量也各不相同,本文着重分析了Z形折叠和卷曲形折叠建模所产生的几何误差,并提出了相应的修正方法。针对三种典型折叠方式,建立了相应的有限元模型,并应用控制体积算法实现了充气管的展开仿真。仿真结果验证了修正方法的有效性。增加尼龙粘扣是实现长卷曲折叠管的有控制展开的有效手段之一,本文采用失效连接来模拟尼龙粘扣的作用,比较了有、无尼龙粘扣的卷曲管的展开过程。仿真结果表明采用尼龙粘扣既不会明显带来充气管额外质量和刚度的增加,又可保证展开次序和展开方向的可控性,改善了展开过程的稳定性。 相似文献
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为了掌握大型反射面从收拢状态到完全展开状态的动力学特性,采用气囊模型和控制体积(CV)法对反射面的充气展开过程进行研究。建立了包含中心轮毂、肋板、支撑杆、薄膜圆环和张拉绳的反射面有限元模型,提出逆解法获得折叠收拢状态下反射面的节点坐标,给出了充气展开动力学分析流程,获得了恒定充气速率下展开过程中圆环充气体积、环内压力等参数与展开时间的变化规律。结果表明,采用充气技术可进行大型反射面有序可控展开,反射面的充气展开过程分初始收拢状态、解锁释放、肋板展开、保压稳定四个阶段,地面充气展开试验结果验证了仿真分析的准确性。 相似文献
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新型充气展开遮光罩设计方案研究和仿真分析 总被引:2,自引:0,他引:2
设计一种充气展开遮光罩结构,实现径向和轴向依次展开.提出遮光罩的结构方案、折叠方式和结构中各组件合适的材料,使得结构展开状态和折叠状态分别能够达到一定的尺寸要求.文章还对充气展开遮光罩进行静力分析和展开过程仿真,仿真分析结果表明,遮光罩能够顺利展开,遮光罩壁保持理想的工作表面. 相似文献
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空间展开结构具有能构建大型结构、轻质而且成本低廉的特点。在航天器中呈折叠状的空间结构在空间充气展开后,要呈刚化,使其不因温度变化而引起变形并且不会因空间碎片或流星体的碰撞而被损坏。文中提出了展开前的折叠方法和包装效率评估方法。提出了两种刚化薄膜,在储存状态下易于折叠并能保持其所有的性能。一种采用单层薄膜浸渍长储存寿命树脂基的三轴编织纤维,另一种采用宽广温度范围长储存寿命的交互编织纤维刚性薄膜。 相似文献
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《固体火箭技术》2018,(6)
折叠方式对折叠翼的气动特性及展开特性有重要影响。对对称折叠、顺向折叠方式下折叠翼的气动特性及展开运动过程分别进行了数值模拟仿真和动力学仿真,比较了折叠方式对折叠翼气动特性、展开运动特性的影响,并分析其影响机制。计算结果表明,相对状态下,与对称折叠时相比,顺向折叠时,下折叠翼所受气动力减小,上折叠翼略有增大,导致负攻角情况下顺向折叠时,下折叠翼展开时间增加,展开同步性增强;正攻角情况下下折叠翼展开时间减小,展开同步性减弱。侧滑状态下,两种折叠方式下折叠翼展开时间基本相当,由于背风侧下折叠翼展开时间减小,导致顺向折叠时折叠翼展开的同步性有所减弱。同时,在小展开角度下,顺向折叠时全弹纵向静稳定性有所提高。 相似文献
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The deployment behaviour of inflatable booms with zigzag and modified zigzag folding patterns is experimentally and theoretically investigated in this paper with the aim to deploy the booms as the actuator for future deployable large-scale membrane structures. Regarding the experimental approach, the stable deployment of a modified zigzag folding pattern is demonstrated, and the relation between stable and unstable deployment behaviour is considered in relation to air pressure and flow rate. In terms of the theoretical approach, the folding process and deployment behaviour are simulated using commercially available software (PAM-CRACH and PAM-SAFE). To create folding lines from the zero stress condition in the case of analytical inflatable boom models, the stress distribution and the shapes of the folding lines are considered for the initial self-deployment behaviour and deployment behaviour using the uniform pressure method. From the folding experiments and the results of folding analyses and UPM, the deployment behaviour of inflatable boom models in zigzag and modified zigzag folding patterns is compared by using the finite point-set method. For the sequential deployment behaviour, which is difficult to replicate, the uniform pressure method is used for the calculations, and the relation between inlet air flow and stable deployment behaviour is discussed through comparison of the experimental and analytical results. 相似文献
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This paper summarizes the results of numerical experiments to determine the sensitivity of the final attitude of an inflatable solar sail with vanes after deployment to various parameters affecting the deployment process. These parameters are: in- and out-of-plane asymmetries during deployment, length inflation profile, and vane deployment failures. We show how robust the sail deployment is to geometric asymmetries before a 35° off-Sun angle is reached. Differential delays in the time to inflate the booms and a boom sweep-back angle affect the stability favorably. Adjacent vane failures to deploy affect the stability unfavorably, while the failure of opposing vanes is acceptable. Realistic boom length rate profiles obtained during ground tests are used in the simulation showing that failing adjacent vanes in conjunction with initial inflation delays in adjacent booms represent the worst case. We also demonstrate that by feeding back attitude and attitude rate measurements so that a corrective action is taken during the deployment, the final attitude can be maintained very close to the initial attitude, thus mitigating the attitude changes incurred during deployment. 相似文献