The Effect of a Complete Spin Turbine on the Exhaust Flow-Field for a Tube-Launched Rocket.

摘要

Unbalanced forces on tube launched rockets during launch caused by exhaust fluid flow in the launcher-rocket annular gap is a problem confronting tube-launched rocket system designers. One alternative considered to alleviate the adverse effects is to rotate the rocket about its center of gravity during the launch phase to average out small deviations in the flight path. The spin turbine is a possible alternative with which to increase the rocket's angular momentum. Previous work considered a single vane's effect on the exhaust flow, a complete spin turbine effect on the exhaust flow, and a rocket nozzle equipped with a complete spin turbine exhausting into a cylindrical launch tube. The current program demonstrates a significant difference in the flow around an isolated single vane from that around a single vane of a complete spin turbine. Three vane heights are considered. (Author)