| The flow of burning gas in nozzle is complex three dimension flow. It is a very important reason of thrust misalignment. At present, related theory and numerical value calculation are not perfect, so the design of micro side thrust nozzle lie on test, and restricted by condition, only simulate test can be done for the rocket' s engine of large thrust.At first, some little disturb theory is introduced in this paper, and explain the phenomenon of side thrust' s change in theory. Numerical value calculate also be done in this paper.In this paper, some simulate rule is obtain by the method of analysising Navier-stokes equation. And some work are done to find the status and to make sure the simulate rule that will be adopted.Finally, inside-trajectory is calculated to obtain the parameter of entry section of nozzle. Base on this, test is done to prove the theory. |
