System driven technology selection for future European launch systems

Investigation of the effect of ring-cavity on secondary-combustion and interior ballistic stabilization with low-temperature solid propellant in gas ejection

“…The secondary-combustion high-temperature zone is reversed from the rail cover and forms a moustache-shaped high-temperature zone at t = 80 ms which is stage (3). Once the hightemperature zone reaches the rail cover, the high-temperature zone suddenly changes expansion direction due to the restriction of area.…”

“…Low-temperature solid propellant gas ejection has attracted tremendous attention in the past two decades because of its outstanding features, which include the advantages of compacted powers, high density, small volume, more flexibility, lower cost and providing large volumes of gas in milliseconds [1,2]. Many applications of this technique can be found such as carrier-based aircraft take-off, aircraft seat ejection and other weapon launch fields [3][4][5][6]. The research on low-temperature solid propellant, whose binder is hydroxyl terminated polybutadiene (HTPB) and oxidizer is ammonium perchlorate (AP) can be traced back to the 1970s.…”