A pulse detonation engine (Pulse Detonation Engine, PDE) generates a detonation wave intermittently, and obtains a thrust and work. In this research, the four cylinder pulse detonation rocket engine system “Todoroki II” was developed. The total weight of the flight test demonstrator is 32.5 kg. Moreover, the length is 1910 mm and the diameter of a combustion tube of a pipe in 800 mm is 37 mm. The launch and the recovery system for a flight test were also developed. The flight vehicle is recoveried without damage by winding system. It was proved that the flight test can be done repeatedly. In this flight test, the propellant mass flow estimated is mp=229 g/s. A time average thrust is Fave=254 N, the specific impulse of a propellant base is estimated to be Isp, PF =113 s, this specific impulse is 86 % of a ground test. The attitude of Todoroki incline to the positive direction of pitch up. The some factors of the inclination of Todoroki II are that the number of iginition different in each combustion tube and the attitude of Todoroki II launched is tilted. Considering these factors calculation results agree with experimental results in the attitude of Todoroki II.