| 摘要 |
A single port rocket motor igniter nozzle features an adjustable throat or annulus that is formed by a tapered flange and an opening in an igniter body that contains a propellant charge, the position of the flange relative to the opening being adjustable to vary the throat area by a calibrated central shaft. The igniter allows rapid evaluation of propellant grain designs and nozzle throat areas, and as a result, enables the faster development and assembly of a less expensive igniter that is operative to produce at optimum pressure and burning rate, and to effectively propagate, the high temperature gases that are needed for rocket motor propellant ignition.
|
