A feasibility study related to the scale-up of solid fuel with multiport was performed using the regression rate equation derived from a laboratory-scale hydrogen peroxide (${\mathrm{H}}_2{\mathrm{O}}_2$) hybrid rocket using a single-port solid fuel. First, a 250-N-class hybrid rocket using a single-port solid fuel was designed and experiments were conducted to derive the regression rate equation. Based on the derived equation and fuel design method for a 250-N-class hybrid rocket, a multiport solid fuel of a 2500-N-class hybrid rocket was designed. To evaluate the validity of the derived regression rate equation and the scale-up potential of solid fuel, not only experimental tests but also an analytical estimation was performed based on the derived equation. The design method using both experimental and analytical approaches was useful in determining the accuracy and effectiveness of the derived equation. It was useful in the scale-up design process of a rocket in a different scale and with a different type of feeding system. More than 90% of the design thrust was confirmed to be produced from the scale-up ${\mathrm{H}}_2{\mathrm{O}}_2/\mathrm{high}\text{-}\mathrm{density}$ polyethylene hybrid rocket during the blowdown mode operation. The maximum differences of the final port diameter and regression rate between the analytical estimation and experiments were found to be 2.6 and 8.4%, respectively. As a result, the design and estimation of multiport solid fuels in a different scale based on the regression rate equation derived from the ${\mathrm{H}}_2{\mathrm{O}}_2$ hybrid rocket with a single-port solid fuel were confirmed as sufficiently feasible.

使用实验室规模的过氧化氢得出的回归速率方程，进行了与多端口固体燃料放大相关的可行性研究（${\mathrm{H}}_2{\mathrm{Ø}}_2$）混合火箭使用单端口固体燃料。首先，设计了一种使用单端口固体燃料的250 N级混合动力火箭，并进行了实验以得出回归速率方程。基于推导的方程和250 N混合火箭的燃料设计方法，设计了2500 N混合火箭的多端口固体燃料。为了评估推导的回归率方程和固体燃料放大潜力的有效性，不仅进行了实验测试，还基于推导的方程进行了分析估计。使用实验和分析方法的设计方法对于确定导出方程的准确性和有效性很有用。它在不同比例和不同类型进给系统的火箭的放大设计过程中很有用。${\mathrm{H}}_2{\mathrm{Ø}}_2/高\text{--}\mathrm{密度}$排污模式操作中的聚乙烯混合动力火箭。分析估计和实验之间的最终端口直径和回归率的最大差异分别为2.6％和8.4％。结果，基于从模型得出的回归速率方程，设计和估算了不同规模的多端口固体燃料。${\mathrm{H}}_2{\mathrm{Ø}}_2$ 具有单端口固体燃料的混合火箭被证实是足够可行的。