增阻球是实现低轨航天器寿命末期离轨的主要装置之一，薄膜球体在使用之前需要长期封装在狭小的空间中，因此如何实现高密度低损伤折叠以及平滑充气展开是该装置使用的关键。考虑到增阻球大多是由一定数量的单瓣粘接而成，因此首先提出考虑形状稳定性和经济性的最优瓣数构型设计方法。进一步针对单瓣结构提出对称并联式z型折叠方案，并给出了该方案的折叠体积和损伤量化方法。然后，为增大折展比，降低折痕损伤，给出了增阻球优化折叠方案，并对直径6 m增阻球进行了仿真验证。基于此方案，分析了瓣数构型、充气速度以及球体内部初始压力和温度等因素对增阻球平滑展开的影响。结果表明，该折叠方案能够实现增阻球的高密度低损伤折叠，此外，通过增加瓣数构型、减缓充气速度、避免过度抽真空以及减少太阳光直射等方法，可以有效减缓增阻球展开过程中的姿态振荡，加快其达到稳定状态。

The drag balloon is one of the primary devices for deorbiting of low Earth orbit spacecraft at the end of their life. Since the thin membrane sphere must be stored in a confined space for an extended period before use， achieving high-density and low-damage folding and smooth inflation and deployment is crucial for its operation. Considering the drag balloon is mostly composed of a certain number of bonded valves， an optimal valve configuration design method that considers shape stability and cost efficiency is firstly proposed. Furthermore， for the single petal structure， a symmetrical parallel z-type folding scheme is proposed， and methods for quantifying the folded volume and damage are provided. Then， to increase the folding-deployment ratio and reduce crease damage， an optimized folding scheme for the drag balloon is presented， and simulation of a sphere of 6-meter diameter is conducted. Based on this scheme， the effects of valve configuration， inflation speed， and initial internal pressure and temperature on the smooth deployment of the drag balloon are analyzed. The results show that the proposed folding scheme can achieve high-density and low-damage folding of the drag balloon. Additionally， by increasing the number of valves， slowing down the inflation speed， avoiding excessive vacuum， and reducing direct sunlight exposure， the attitude oscillation during the deployment process can be effectively mitigated， speeding up the attainment of a stable state.