Today developments of nano satellites, whose weight is less than 100 kg, become quite active. As nano satellites are used commercial, inexpensive components, the cost of nano satellites becomes cheap and also the size of subsystems of nano satellites becomes smaller and smaller. The latest nano satellite for single mission becomes very useful for commercial use. Above situations on nano satellites begin to request a low-cost launcher because a combination of low cost nano satellites and low cost launcher can develop nano satellite business market. For this request hybrid rocket is one of the most promising propulsion systems. However, some problems still remain in hybrid rocket such as low fuel regression rate, optimum scale rule and combustion oscillation. The present authors proposed a new method for increase of the fuel regression rate of hybrid rocket. The new method is to introduce swirling flow at multi-sections along the fuel. The new method has been applied for high density polyethylene fuels and paraffin fuels with gaseous oxygen. The results show the new method is quite useful for the increase of the fuel regression rate of hybrid rocket engines. For high density polyethylene fuels the fuel regression rate with multisection swirl injection method shows about 2 to 3 times higher than that of the conventional no-swirl injection method. For paraffin fuels the fuel regression rate with multi-section swirl injection method shows about 3 to 10 times higher than that of the conventional no-swirl injection method with paraffin fuels. The results show the new method of multi-section swirl injection is quite useful both for high density polyethylene fuels and paraffin fuels in order to increase the fuel regression rate of hybrid rocket engines.