THRUST CHAMBER INTEGRATED WITH IGNITER OF ROCKET ENGINE USING CRYOGENIC FUEL AND LIQUID OXYGEN AND ROCKET INCLUDING THE SAME

Provided are an igniter-integrated thrust chamber for a rocket engine using a cryogenic fuel and liquid oxygen and a rocket including the thrust chamber. The thrust chamber includes a combustion chamber and a mixing head assembly, which is disposed at one side of the combustion chamber and is integrated with the combustion chamber.