Numerical Investigation of the Unsteady Behaviour of Side Jet Induced Control Concepts

In this study, the performance of side jet control for two different altitudes (10 km/30 km) was numerically investigated and compared with the effectiveness of secondary injection thrust vector control for a supersonic missile at M = 6.2 and 7.0. This comparison also considered the behavior of the transient force signal caused by the side jet thrust increasing with time, resulting in a time delay between reaching the maximum side jet thrust and reaching the maximum control force. It was shown that, in contrast to thrust vector control, the performance of side jet control decreases with increasing altitude as a result of a less effective shock wave boundary layer interaction. With respect to this interaction, it was found that the boundary layer state has a great influence on this interaction and affects the induced force to a certain extent.