Rocket engines are an essential component in delivering any payload such as satellites, rovers, and probes into space. One such kind of engine is the hybrid rocket engine. Classical hybrid rocket engines have first become popular in the early 1970s. These engines, while providing combined advantages of both solid rocket motors and liquid rocket engines, as well as being relatively cheap to manufacture when compared to liquid rocket engines, exhibit drawbacks in thrust throughout the burn of the engine caused by the oxidizer to fuel ratio shifts induced by fuel regression. Their loss in efficiency is what makes them undesirable in the construction of rockets and causes companies to use the more expensive liquid rocket engines which are higher in efficiency and overall thrust output. The negative side effects of the fuel regression can be reduced by eliminating the oxidizer to fuel ratio shifts during the operation of a hybrid rocket engine. In this paper, a new approach of controlled oxidizer flow is proposed to achieve a more favourable combustion. The differential equations of the fuel mass flow rate function are numerically solved in terms of oxidizer mass flow rate, the results of which are taken as a basis to define a control function. It was demonstrated that it is possible to eliminate the oxidizer-fuel ratio shifts for all fuel types.