The membrane structures are the potential solution for near term spacecraft systems due to its significant advantages such as lightweight, higher folding and packaging efficiency, ease of deployment, and low on-board volume requirement. For the membrane structures, maintaining the uniform state of stress conditions with a minimum mass penalty of a tensioning system is the most challenging task for space industries. The inflatable planar membrane reflector is attached to the satellite body, used for bidirectional communication between the satellite and earth stations. The aim of the study is to develop the methodology for designing the tensioning system for a planar membrane reflector antenna. The work presents a novel average diagonal stress distribution relation for rectangular membrane reflector. The loading analysis of membrane reflector and tensioning chord is carried out numerically and experimentally to achieve the design goals of the antenna structure. The outcome of the loading analysis is compared and found to be consistent with the method available in the literature. The inflatable torus diameter is calculated based on the tensioning force required at anchor points.

膜结构由于其显着的优点，例如重量轻，折叠和包装效率高，易于部署以及对机载体积的要求低，是短期航天器系统的潜在解决方案。对于膜结构而言，在张紧系统的最小质量损失下保持应力状态的均匀状态是航天工业最具挑战性的任务。充气式平面膜反射器安装在卫星主体上，用于卫星和地球站之间的双向通信。该研究的目的是开发一种用于设计平面膜反射器天线张紧系统的方法。这项工作为矩形膜反射器提出了一种新颖的平均对角应力分布关系。通过数值和实验对膜反射器和张紧弦进行了载荷分析，以达到天线结构的设计目标。比较负载分析的结果，发现与文献中可用的方法一致。充气圆环直径是根据锚点所需的拉力计算的。