| 摘要 |
<p>The method involves positioning a circular body (5) inside a divergent section along the length of a correspondence axis from an axial position of the body so that a shock wave is incident on the section at an axial incidence position, during the starting phase of a rocket engine. The wave is induced by a disturbance of a combustion gas flow produced by the body. The section produces a jet separation, in the incidence position. An independent claim is also included for a device for reducing non stationary lateral forces acting on a pipe of a rocket engine, during the starting phase of the engine.</p> |
