To develop light, reliable, sanitary space station maneuverable orbital transfer thruster, the novel gas dynamic resonance ignition method was applied. By means of thruster combustor design combined with coaxial hydrogen/oxygen resonance igniter investigation, method of using fuel-rich resonance ignition torch to further combust with the rest main part of oxygen downwards was adopted for the thruster head scheme. Through investigation on schemes of the thruster head configuration, structural schemes of the main oxygen injector were studied and determined. With respect to the key technique of short ignition response for orbital transfer thruster’s quick starts, several solving approaches were proposed, including: optimization of the resonance device structure, optimization of matches between the resonance dominating parameters, improvement on materials and timing adjustment of the ignition propellants etc. By greatly increasing its heating speed and energy gathering efficiency of the resonance device, the starting delay of the thruster was restricted in 0.2?s.