The invention discloses an equivalent calculation method for a
rocket engine
combustion chamber and a
nozzle strong dynamic load test device, which directly converts an energetic medium into a high-temperature and high-pressure
air mass according to the energy released in the reaction process of the energetic medium in the initial state of the flow field of the strong dynamic load test device; the
mass and mole number of the high-temperature and high-pressure
air mass are calculated according to the initial
mass of the energetic medium and the product form, and the
thermodynamic state of the high-temperature and high-pressure
air mass is determined according to the initial
mass and calorific value of the energetic medium, and the temperature and air pressure of the high-temperature and high-pressure air mass are equivalently calculated; the high-temperature and high-pressure air mass with equivalently calculated mass, mole number,
temperature and pressure is taken as an analysis object, the high-temperature and high-pressure air mass is equivalently placed at a designated position of the initial state of the flow field of the strong dynamic load test device, and a numerical
simulation calculation is performed on the strong dynamic load process generated by the high-temperature and high-pressure air mass; the invention reduces the difficulty of boundary condition
processing, improves the calculation efficiency of
simulation, and can obtain
simulation results in a shorter time.