Pulse type liquid rocket engine for electrolytic ignition of hydroxylamine nitrate propellant

The invention discloses a pulse type liquid rocket engine for electrolytic ignition of a nitric acid hydroxylamine propellant, and belongs to the field of engines. Comprising a pressure gas tank, a propellant storage tank, an electromagnetic valve, an electrode section, a combustion chamber and an exhaust nozzle, and a propellant stored in the propellant storage tank is a nitric acid hydroxylamine propellant; the first electromagnetic valve is used for controlling filling of a propellant, the electrode section and the combustion chamber are used for electrolytic ignition of fuel, and the second electromagnetic valve is used for controlling emission of high-temperature and high-pressure gas to generate thrust. Under the control of the first electromagnetic valve, a nitric acid hydroxylamine propellant is sprayed into the electrode section and the combustion chamber through the injection port and is in contact with the cathode and the anode of the electrode to form a loop, electrolytic ignition is completed at